agni - iii test fired on 12 april 2007 · dr. a.p.j. abdul kalam, the president of india, who will...
TRANSCRIPT
AGNI - III Test Fired on 12 April 2007
SOUVENIR
International Conferenceon
HIGH SPEEDHIGH SPEEDHIGH SPEEDHIGH SPEEDHIGH SPEED
TRANSATRANSATRANSATRANSATRANSATMOSPHERIC AIRTMOSPHERIC AIRTMOSPHERIC AIRTMOSPHERIC AIRTMOSPHERIC AIR
&&&&&
SPSPSPSPSPACE TRANSPORACE TRANSPORACE TRANSPORACE TRANSPORACE TRANSPORTTTTTAAAAATIONTIONTIONTIONTION
29 - 30 June 2007
The Aeronautical & Astronautical Societies of India
SOUVENIR
Hyderabad | Bangalore | Thiruvananthapuram
PREFACE
This exclusive Souvenir is brought out specially to mark the occassion of
the first International Seminar on “High Speed Transatmospheric Air
and Space Transportation” organised by the Aeronautical & Astronautical
Societies of India on June 29-30, 2007.
Chairman and the Organising Committee, AeSI and ASI places on
record their deep sense of sincere thanks and gratitude towards all the
guests, members, sponsors, organisations and Industries who have
contributed through their Advertisements, Exhibits & valuable
Participation. We are very thankful to all the learned speakers on this
occasion.
We are deeply indebted to the message received from dignatories on this
occasion. We are also thankful for the support by one and all and the
tasks rendered by various committees towards organising this event by
Hyderabad chapter.
Souvenir Committee&
Organising Committee
MESSAGE
I am happy to know that the Aeronautical Society of India and the Astronautical Society of
India are organizing an International Conference on ‘High Speed Transatmospheric Air
and Space transportation’ on June 29-30 at Hyderabad.
The Conference is of global importance as this area of research will lead to new
technology applications. The conference could be an opportunity to provide a platform for
the participants to exchange views, ideas, experiences and dreams for expediting progress
and drawing a road-map for future work in this area of advanced transportation.
I extend my greetings and felicitations to the organizers and the participants and wish
the Conference all success.
(Dr. A.P.J. ABDUL KALAM)New DelhiJune 22, 2007
It is very heartening to note that an International conference-cum exhibition is beingjointly organized by Aeronautical Society of India and Astronautical Society of Indiaon “High Speed Transatmospheric Air and Space Transportation” on 29-30 June2007 at Hyderabad.
The forum like this provides most ideal environment for exchange of innovativeideas and advances in the aerospace research and opportunities of establishmentof collaborative programme for research and manufacturing. This will definitelybenefit the scientific community and industry participants to overcome technologicalchallenges towards space transportation.
I convey my good wishes for success of the conference.
MESSAGE
(Dr. Rameshwar Thakur)
RAJ BHAVANHYDERABAD - 500 041
HyderabadJune 21, 2007
MESSAGE
I am pleased to learn that an Exhibition-cum-International Conference on “High SpeedTransatmospheric Air & Space Transportation” is being organized and a Souvenir is beingbrought out on the occasion.
In today’s world, aerospace systems assume critical importance for the developmentof warfare technology. The design of these systems has to be robust and reliable to deliverthe kill mechanism on the targets. Technology in this area of aerospace weapons is gettingupgraded day-by-day in terms of accuracy of impact, destruction potential andminiaturization.
I hope this international conference will take stock state-of-the-art technology andsuggest a roadmap to focus on the thrust areas.
I have no doubt that our scientists, researchers, technologists,entrepreneurs andengineers will benefit immensely from the technical content as well as exchange of ideasthrough this platform.
I wish the Conference all success.
MINISTER OF DEFENCEINDIA
(AK ANTONY)New DelhiJune 18, 2007
I am glad to note that the Hyderabad, Bangalore and Tiruvananthapuram branches ofAeronautical Society of India in collaboration with the Astronautical Society of India areorganizing an Exhibition-cum-International Conference on “ High Speed Trans-atmosphericAir & Space Transportation” at Hyderabad on 29th & 30th June 2007, and bringing out asouvenir to mark the occasion.
It is heartening to note that the International event is being inaugurated by His Excellency,Dr. A.P.J. Abdul Kalam, the President of India, who will further enthuse the participantsfrom scientific community and industry, to overcome the technological challenges relatedto aerospace.
I have always wished that Andhra Pradesh, particulary Hyderabad, to be hub fortechnological and industrial development and play a great role in the world forum.
I take this opportunity to wish all the organizers and members of Aeronautical Societyof India and the Astronautical Society of India all success in their endeavours.
(Dr. Y.S. RAJASEKHARA REDDY)
MESSAGE
HyderabadJune 17, 2007
It gives me immense pleasure to know that the Hyderabad, Bangalore and Trivansrumbranches of AeronauticalSociety of India have come together and teamed up with the Astronautical Society ofIndia to organize an International Conference -cum-Exhibition on "High SpeedTransatmospheric Air and Space Transportation"on 29-30 June at Hyderabad.
The ideas on the development of advanced aerospace systems and technologieswould prove to be highly beneficial for achieving excellence in aerospace endeavours.
I wish the efforts of the society a sucess and look forward to more such events.
MINISTER OF STATE FORDEFENCE
(M.M. Pallam Raju)
New DelhiJune 18, 2007
Government of India108-B, South Block
New Delhi - 110 011
MESSAGE
MINISTER OF STATE FORCIVIL AVIATION
It has been the dream of mankind to reach any point on earth or the universe in the shortest
possible time. This would indeed help in resolving several issues as well as in alleviating
the sufferings of human beings by reaching assistance and relief supplies speedily.
The Exhibition-cum-International Conference on ‘High Speed Trans atmospheric Air &
Space Transportation ‘ being organized by the Aeronautical Society of India and
Astronautical Society of India on 29th –30th June,2007 at Hyderabad will provide ample
opportunity to scientific, technological and industry participants to interact in the endeavour
that would pave way in the direction of achieving and realization of the dream.
On this occasion, I convey my good wishes to the organizers and participants of this
Exhibition-cum-International Conference and wish the event a great success.
Government of IndiaRajiv Gandhi BhawanNew Delhi - 110 003
MESSAGEI am happy to note that the Aeronautical Society of India and Astronautical Society of India is
jointly organizing an International Seminar on "High Speed Trans-atmospheric Air and Space
Transportation" in Hyderabad.
Air transportation for passengers, cargo and other services has become an integral part of day-
to-day life. With the advent of bigger and high speed aircrafts, the time taken to fly to different
parts of the world has really shrunk. In the long run, if such systems have to work safely and
efficiently, there is a bigger challenge to design the systems that are robust enough to perform
under severe and sustained flight environment. Successful and safe air transportation will de-
pend on cohesive working of all such elements whether airborne or ground systems, procedures
and the software associated with it.
Everywhere there is a thrust to save on time and energy. Hence the high speed supersonic flying
machines will be of great importance for the future. Lot of R&D efforts in propulsion, aerodynam-
ics and structures are required to achieve this goal.
An international seminar of this kind with participation from some of the leading specialists
will provide the right platform for deliberating on some of the most complex and multidisciplinary
topics related to aviation and aerospace technologies like high speed computational techniques,
aerodynamics etc. This would pave the way towards enhancing the role of R&D activity in the
field of aeronautics and space.
I extend my warm greetings to all delegates, participants and organizors of the seminar and wish
the event a great success.
Indian Space Research OrganisationDepartment of SpaceGovernment of IndiaAntariksh BhavanNew BEL Road, angalore - 560094, India
G. Madhavan NairChairman &President, ASI
(Dr. G. Madhavan Nair)
PRESIDENT
The Aeronautical Society Of India13-B, Indraprastha Estate
New-Delhi - 110002
I am greatly pleased to note that the Hyderabad, Bangalore and Trivandrum branchesof the Aeronautical Society of India and Astronautical Society of India have joined handscofor organizing an International Conference-cum-Exhibition on “High SpeedTransatmospheric Air and Space Transportation” on 29-30 June 2007 at Hyderabad. Inaddition to this they are also releasing a Souvenir to mark the occasion.
The ideas presented in the conference in the Design and Development of advancedaerospace systems and technologies would be of tremendous importance for theaerospace activities in the country.
The conference promises immense potential for the future and collaborations with intraand international organisations for further advancement in the development of aerospacesystems.
I wish the teshnical sessions of the conference great success and hope the societieswould keep up the good work.
MESSAGE
(THULASIDAS)
General JJ SinghPVSM, AVSM, ADCChief of the Army Staff
18 Jun 07
I am happy to know that the Aeronautical Society of India is conducting an Exhibitioncum International Conference on “ High Speed Transatmospheric Air and SpaceTransportation” on 29-30 Jun 07.
The recent past has witnessed a proliferation of technology and opportunity in thedomain of Air and Space Transportation. This subject is of interest to civil as well asmilitary practitioners besides scientists who will undoubtedly spearhead our efforts inthis direction. The country’s emergence as a technological power house mustimportantly include research in this vital field of strategic significance.
I am certain that the forthcoming Seminar will provide an ideal opportunity forexchange of ideas and a platform for sharing knowledge and experience.
I wish the organizers and participants of the Seminar the very best for theirdeliberations.
MESSAGE
(JJ Singh)General
MESSAGE
I am pleased to learn that the Aeronautical Society of India is organizing an internationalSeminar on “High Speed Transatmospheric Air & Space Transportation” on 29 and30 Jun 2007 at Hyderabad.
The last century has witnessed dreams being converted to reality wherein thehuman race has taken to the skies. Technology has further enabled us to break thesound barrier. With the advent of ‘super - cruise’ we are moving further in our questfor speed.
The issue of hypersonic flight is, therefore, germane at this juncture. I am confidentthat the seminar would provide an oppurtunity to the Aerospace fraternity to focus ontransatmospheric transportation and I do look forward to reading the proceedings.
As a proud fellow of this august Society, I take this oppurtunity to wish theAeronautical Society of India all success in its endeavours.
Admiral Sureesh MehtaPVSM, AVSM, ADCChief of the Naval StaffFAeSI
June 15, 2007
Integrated HeadquartersMinistry of Defence (Navy)
New Delhi - 110011
(SUREESH MEHTA)
Air Chief Marshal F H MajorPVSM, AVSM, SCVM, ADC
Air HeadquartersNew Delhi - 110011
MESSAGE
1. I am happy to know that the Aeronautical Society of India and the Astronautical Societyof India, Hyderabad – two premiere agencies – are jointly organising an InternationalConference on ‘High Speed trans-atmospheric Air and Space Transportation’, from 29to 30 Jun 07 at Hyderabad.
2. Communications and reaching out beyond ones borders – a characteristic feature ofthe 20th Century – have received a huge impetus through aerospace technologies. Thereis yet considerable scope for improvements and advancements in this field, with spaceapplication becoming increasingly common. The ‘Space Club’ has few members andIndia is one of the handful that can boast of spacecraft design and launch capabilities.These technologies have military utility as well. We need to attract young scientists,professionals and technocrats to this fascinating and promising field of technology.Organising more such events will help. It will also serve to educate those already in thefield.
3. I look forward to learning of your conclusions and convey my best wishes to theorganizers and participants of the Conference
Jai Hind!
15 Jun 07
(Air Chief Marshal)Chief of the Air Staff
MESSAGE
I am happy to know that Aeronautical Society of India and Astronautical Societyof India is organizing international conference on HIGH SPEEDTRANSATMOSPHERIC AIR & SPACE TRANSPORTATION on 29 - 30 June 2007.
2. This Conference is of special significance in today’s world. The demand forefficient transportation is there forever. Concern for environmental factors andpassenger’s expectations are driving factors on new technologies, ideas, methodsand oppurtunities. I am sure that this conference would pave way for to buildcollaborative intra-and international linkages for exchange of information and sharingof experience. India as an emerging giant in the Aerospace related applications would play a significantrole in world travel.
3. I wish all members and participants a great success during this conference.
M NATARAJANScientific Advisor to Defence MinisterSECRETARY & DG R&D (DRDO)
(M NATARAJAN)
June 13, 2007
Government of India
Ministry of Defence
Deptt. of Defence Research & Development
DRDO Bhawan
New Delhi - 110011
MESSAGE
I am very pleased to note that the Aeronautical Society of India and AstronauticalSociety of India are jointly organizing an International Conference-cum-Exhibitionon “High Speed Transatmospheric Air and Space Transportation” on 29th and 30th
June 2007 at Hyderabad. This is a definite step towards establishing collaborativeresearch programmes and exchange of ideas and advances that will greatly benefitthe entire scientific community.
In the age of technological development and setting up of space stations, thespace travel is an exorbitantly costly affair beyond the realm of the common man.However, I trust that it can be made efficient and feasible if the scientists and industriesacross the globe come forward and team up to take up technological challengesrelated to space explorations and transportation. I strongly believe that this synergywill work successfully.
On this occasion, I wish all the members of the Society, organizers and theparticipants a great success.
K.V.S.S. Prasad RaoChairman, NTRO & Ex-officioSECRETARY TO THE GOVT. OF INDIA
(K.V.S.S. Prasad Rao)
June 13, 2007
Government of India
National Technical Research Organisation
J-16, Hauz Khas, Sri Aurobindo Marg
New Delhi - 110016
I am delighted to note that the International Conference on High SpeedTransatmospheric Air & Space Transportation is being jointly organized by the Hyderabad,Bangalore and Thiruvananthapuram Chapters of the Aeronautical Society of India and theAstronautical Society of India.
This Conference is conducted at the time when DRDO and ISRO have embarked onhypersonic Technologies for their technology demonstrator programmes. It is noteworthyto see that the areas, viz., Scramjet Engine Devlopment, High - Temperature materials,Hypersonic Aerothermodynamic Design using state-of-the-art CFD techniques and testingare scheduled to be deliberated by the experts from India and abroad.
I hope the Panel discussions by the experts will come out with action plan for thehypersonic technology road map of our country. I wish fruitful deliberations and discussionsin the Conference leading to strengthening the technology base of our nation.
I wish the Conference all success.
MESSAGE
(Dr. V.K. Saraswat)
Dr. V. K. SaraswatFNAE, FAeSI, FIECC R&D (MSS) &Programme Director ‘AD’
Government of India
Ministry of Defence
Defence Res & Dev Organisation
PROGRAMME ‘AD’
Hyderabad - 500 058.
OFFICE OF THE RECTOR AND VICE-CHANCELLOR
MESSAGE OF OFFICIAL SUPPORT
The University of the Western Cape in South Africa sends its strong support to your important Trans-
Atmospheric Vehicle research conference, and Dr to Dr V.K. Saraswatís earlier call for international
cooperation and partnerships in this exciting research programme. We consider that both the vision and
the challenges of the TAV project could build the research and development capacities, and ultimately
manufacturing capacities, in both our countries.
South Africa is now setting up its national space agency, and is fascinated with the thought of
starting the twenty-first century with cooperation on RLVs with India, instead of the financial cul-de-sac
of reinventing the wheel of ELVs. This has been the vision of one Department of UWC for quite a long
time.
UWC is eminently qualified to be a hub for intellectual exchanges by India with South Africa in
advanced areas, because it has: the stature of being one of South Africaís leading Universities; strong
linkages with South Africaís science and technology establishments in government, industry and with
other academic institutions; as well as much experience in handling international conferences and
coordinating international research projects.
The University of the Western Cape offers to convene a follow-up conference to facilitate introductions
and contacts with all our potential key South African participants in universities, institutes, and our
space infrastructure facilities. Together we can take this TAV project forward to the next stage.
Yours sincerely
Prof Brian OíConnell
Rector and Vice-ChancellorA Place of Quality, A Place to Grow
University of the Western CapePrivate Bag X 17 Bellville South Africa Telegraph: UnibellTelephone: +27 21 959 2101 Fax: +27 21 959 2973
MESSAGE
The first International Conference on “High Speed Transatmospheric Air & SpaceTransportation” is a significant step towards our technological and commercial stake in
space related activities. Globally speaking, there has been exponential growth in space
applications and activities. Seamless intercontinental communication for design and
development activities distributed across many countries is a reality. Space Tourism is a
reality. Study of celestial bodies with advanced transport vehicles and probes has given a
new dimension to the understanding of Space.
DRDO, ISRO and Indian Industry have been ardently working on many advanced
technologies to realize Indian dreams in Space applications. Recently many successes
have been reported in re-entry Missions like ABM Defence, AGNI-III and Space Capsule
Recovery Experiment. This Conference is aptly timed and is covering large spectrum of
topics directly related to advancement of Space related Technologies. Efforts of
Aeronautical Society of India and Astronautical Society of India with industry alliance brings
in important stakeholders under one umbrella are commendable.
I wish the participants, in-depth deliberations and fruitful outcome in the form of
identification of thrust areas for future research. I wish the Conference Organizers all
Success.
Avinash Chander, F.N.A.E.Distinguished ScientistDirector
HYDERABADJune 22, 2007
(AVINASH CHANDER)
GOVERNMENT OF INDIA
MINISTRY OF DEFENCE
DEFENCE R & D ORGANISATION
ADVANCED SYSTEMS LABORATORY
Hyderabad - 500 058
“The fastest thing in Sky” is no more a dream but becoming a reality. Westerncountries research on Scramjet engines is showing promise of realization ofhypersonic vehicles and missiles.
Defence scientists are planning to replace nuclear payload by a conventionalpayload to strike the target at hypersonic speed with zero miss distance. A boon toreduce usage of nuclear warheads.
Air defence system finds difficult to recognize, track and hit on hypersonicmaneuvering vehicles, putting a nation at even more strategic advantage.
It is heartening to note that AeSI is conducting a seminar on “High Speed TransAtmospheric Air ans Space Transportation” at Hyderabad which will lead to matureindia in the field of science, technology and development of hypersonic vehicles.
I wish a grand success of the seminar with a suitable work plan to develop lowcost, long duration hypersonic vehicles.
Place: HyderabadDate: 20th June 2007
(S.K. RAY)
S. K. RayOutstanding Scientist & Director
RESEARCH CENTRE IMARATMinistry of DefenceP O Vignyana Kancha, Hyderabad - 069.
MESSAGE
I am happy that the Aeronautical Society of India and the Astronautical Society ofIndia of Hyderabad are jointly organizing an International conference on “High SpeedTransatmospheric Air and Space Transportation” on 29-30 June 2007 at Hyderabad.
These societies have always been the apex bodies of professionals in the field ofaviation and aerospace sciences in the country for last five decades and I am proud to beassociated with it during all these years. It is indeed due the contributions of these societiesthat Hyderabad and Bangalore have emerged as the technology hubs in the field ofaerospace technologies.
Now, when India has emerged as a global player in the field of aerospacetechnology, challenges have also increased and I see greater role of the societies in thecoming years. We need to attract young scientists, professionals and technocrats to thisfascinating and promising field of technology by organizing more and more such eventsthat can give a wide exposure to opportunities in this field. I convey my heartiestcongratulations and best wishes to the organizers and participants of the conference andwish that the conference turns out to be a great success.
MESSAGE
GOVERNMENT OF INDIA
MINISTRY OF DEFENCE
DEFENCE R & D ORGANISATION
Hyderabad - 500 058
P VenugopalanOutstanding ScientistDirector, DRDL
(DIRECTOR)
PPPPPAAAAATRONSTRONSTRONSTRONSTRONS
Dr G. Madhavan Nair
Chairman, ISRO & President, Astronautical Society of India
Shri M. Natarajan
Scientific Advisor to Raksha Mantri
Shri V. Thulasidas
CMD, Air India & President Aeronautical Society of India
ADADADADADVISORVISORVISORVISORVISORY COMMITTEEY COMMITTEEY COMMITTEEY COMMITTEEY COMMITTEE
Dr V.K. Saraswat, CC R&D(DRDO) & Chairman, AeSI, Hyderabad Branch
Dr B.N. Suresh, Director, VSSC
Mr Avinash Chander, Director, ASL
Mr S.K. Ray, Director, RCI
Mr P Venugopalan, Director, DRDL
Dr A.R. Upadhya, Director, NAL
Air Cmd (Retd.) R Gopalaswamy, Former CMD, BDL
Dr S. Panneerselvam, Associate Director, DRDL
Dr R Balasubrahmanium, Editor, JAeST
Dr Satish Kumar, Director, TBRL
Wg Cdr(Retd.) A.E. Patrawala, Chairman, AeSI, Bangalore
Mr N. Narayanamoorthy, Chairman, AeSI, Thiruvananthapuram
Mr C.U. Hari, Director of Aeronautics
Organising Committee
Mr P. Venugopalan, Director, DRDL Chairman
Dr S. Panneerselvam, Associate Director, DRDL
Mr Madan Lal, VSSC
Mr Balaram Gupta, Former Reg. Dir., RCMA
Capt. S. N. Reddy, Secy., AP Flying Academy
Dr M Nagarathinam, DRDL
Dr V.G. Sekaran, ASL
Dr J. J. Isac, NAL
Dr Sajeer Ahmed, NAL
Mr B. Vasudevan, IISc
Mr Vijay Kumar, IA
Dr V. Ramanujachari, DRDL
Dr R.K. Sharma, DRDL
Mr P. Ranga Rao, IA
Mr R. Shiva Kumar, Zetatek
Mr S. Varaprasad Rao, ASL
Mr Rajeev Gupta, RCMA
Col. T. Kashi
Mr K. Ram Sharma, RCI
Mr B. Madan Mohan Rao, DRDL
Wg Cdr U Raja Babu Organizing Secretary
Reception, Transport,Accommodation & Security
Lt. Col T Kasi (Retd.) ChairmanCol Rajeev NegiY Sreenivasa RaoS M BhatiaLt Col DeshpandeLt Col Venkat ReddyLt Col PhilipLt Col Harsha Vardhan
Registration, Kits & Memento
R S Hastak ChairmanJ RammohanN IssacK V P SaradhiAvnish KumarMs Usha VermaA PadmajaA KamaleshRajendar
Venue & Event Management
K Rama Sharma ChairmanK JagadisanCol R GanesanYogesh VermaSandhya NairRajendarK Ram Prasad
Technical Session Management
Dr V Ramanujachari ChairmanDr R K SharmaCh Surya KiranMs Sandhya NairMs Anjani
Catering
Vijay Kumar ChairmanRajeev GuptaLt. Col Venkat ReddyLt. Col T Kasi (Retd.)R Siva Kumar
Website
Dr.R.K. Sharma Chairman
ORGANIZING SUB-COMMITTEES
Information Control Management
Y Sreenivasa Rao ChairmanR A SrivardhanA KamaleshK V S N BabuM ManjulaSurya Bhagwan
Exhibition & Souvenir
R Siva Kumar ChairmanLt. Col T Kasi (Retd.)S M BhatiaAdalat AliA Linga Murthy
Media Coverage
G Satheesh Reddy ChairmanDivyananda, Zonal PRORaju, PRO DRDOK Rohin, GID
Resource Generation/Finance
D S Reddy ChairmanR S HastakR Siva KumarS Varaprasada RaoP Ranga Rao
Publication Committee
Dr R K Sharma ChairmanJVS MoorthyCH. Surya KiranAvnish KumarSumit Sharma
ORGANIZING SUB-COMMITTEES
INAUGURAL PROGRAMME
29 June 2007
Time09:15 Hrs Arrival of Chief Guest
Ushering Guests on to Dais
Presentation of Flower Bouqets
Lighting of the Lamp
Invocation
09:25 Hrs Welcome Address by Dr. VK Saraswat,
Chairman, AeSI, Hyderabad
09:30 Hrs Address by Shri V Thulasidas,
President, AeSI
09:35 Hrs Address by Shri M Natarajan,
SA to RM
09:40 Hrs Address by Shri KVSS Prasada Rao,
Chairman, NTRO
09:45 Hrs Address by Mr. Itzhak Nissan,
President & CEO, IAI, Israel
09:50 Hrs Release of Souvenir / Newsletter / Proceedings
10:00 Hrs Inaugural Address by Chief GuestHis Excellency Dr. A.P.J. Abdul KalamHonourable President of India
10:30 Hrs Felicitation & Presentation of Mementos
10:40 Hrs Vote of Thanks by Shri Vijay kumar,Hon. Secy., AeSI, Hyderabad.
10:45 - 11:00 Hrs Inauguration of Exhibition
11:00 - 11:30 Hrs Interaction with delegates
11:30 Hrs High Tea
Plenary SessionsDAY - 1 ( 29 June 2007 )Venue : Grand Ballroom
Plenary Session - I Time : 1200 - 1330 Hrs
Chairman : Dr. Kota HarinarayanaCo-Chairman: Dr. V. Ramanujachari
Title of paper Speaker
Advanced Space Transportation Systems: Dr B N SureshNeeded Technologies & Facilities Director, VSSC,
ThiruvanathapuramFrom Earth to Orbit in Transatmospheric Air Air Cmde R. GopalaswamiBreathing Vehicles (Retd.), Former CMD, BDL,
Hyderabad
IBSA in Space: Strategy for Global Prof Keith GotschalkCooperative Advantage UWC, South Africa
Plenary Session- II Time : 1430 -1600 Hrs
Chairman : Dr. Prahlada, CC R&D (SI)Co-Chairman: Mr. A.S. Narayana
Title of paper Speaker
Progress on the Design and Development Dr S Panneerselvam,of Hydrocarbon Fuelled SCRAMJET Engine DRDL, HyderabadIntegrated Vehicle towards DemonstratingHypersonic Autonomous Flight
Hypersonic Vehicles Powered by Scramjet Engine – Y. Ramati, IAI, IsraelTechnical & Future Prospects
Materials for Hypersonic Aerospace Vehicles Dr Y. R. Mahajan, ARCI,Hyderabad
Lunch : 1330-1430 Hrs
Plenary SessionsDAY - 1 ( 29 June 2007 )
Venue : Grand Ballroom
Plenary session - III Time : 1600 - 1730 Hrs
Chairman: Shri. Avinash ChanderCo-Chairman: Dr. R.K. Sharma
Title of paper Speaker
A Multi-Role Flight Technology Demonstrator Dr Satish Kumar, TBRL,for Advanced Air & Space Transportation ChandigarhSystems Development
Hydrogen Fueled Scramjet Development J. D. A. Subramanyam,and Test Facilities in ISRO VSSC, Thiruvanathapuram
The programme of wind tunnel tests and A. N. Polikarpov, TsAGI,features of models design for aerodynamicinvestigations of Indian HSTDV Vehicles
Panel Discussion :
Theme : Approach Towards an International Joint Venture for Safe,Affordable Air & Space Transportation
Chairman : Dr. B.N. Suresh
Facilitator : Air Cmde(Retd.) R. Gopalaswamy
Russia
Time : 1730 - 1830 Hrs
Cultural Programme Followed by Dinner : 1930 Hrs
DAY - II (30 June 2007)Invited Papers Session - I (0900-1100)
Venue : Grand Ballroom
Chairman : Mr Y RamatiCo-Chairman : Dr BSS Chandran
Title of paper Speaker
Space Capsule Recovery Mission Dr GeorgeThomas,VSSCThiruvananthapuram
Evaluation of Aerodynamic Testing in a Blow Down Dr Moshe Zilberman, IAI,Hypersonic Wind Tunnel Israel
Study on Integration of Inlets and Scramjets in System of Dr Y. P. Goonko, ITAM,Hypersonic aircraft Russia
Supersonic Combustion Experiments Dr David J. Mee,in the T4 Shock Tunnel University of
Queensland, Australia
Aeromedical Challenges of Hypersonic Flight Wg Cdr Rajat Baijal, IAM,Bangalore
Invited Papers Session - II (1115-1315)
Chairman : Mr Thomas YoungCo-Chairman : Dr. Debasis Chakraborthy
Title of paper Speaker
Current Status of Research on Hypersonic Combustion & Dr Hideyuki Tanno,High Enthalpy Aerodynamics in the Free Piston Shock Tunnel Kakuda Space Centre,
Japan
Wind Tunnel Tests of HSTDV Models Dr Anatoly Gubanov,TsAGI, Russia
CFD Analysis of Energy & Phase Separation in a Dr S S Bandopadhyay,Cryogenic Vortex Tube IIT, Kharagpur
Vortex Tube Technology for LOX Separation Dr S Jacob, IISc,Bangalore
Hypersonic Missile Defence Systems Alan Merbaum,Lockheed Martin
Lunch : 1315-1400 Hrs
CONTRIBUTED PAPERSSession – I ( 30 June 2007)
Session CA- 1 AerodynamicsChairman : Prof. K P J Reddy Time : 1400 -1545Co-Chairman : Mr P Theerthamalai Venue : Hall-1Title of paper Speaker
1 Methodology for Aerodynamic Characterisation of P. Balaram, G D Rao, MM Patil,
TSTO Winged Body Vehicle S Swaminathan and Madan Lal
2 Blunt Body Drag Reduction using Aerospike R. Kalimuthuand Aerodisk at Mach 6
3 Longitudinal and Lateral Aerodynamic Characteristics T.K. Ganesh Anavaradham andof a Hypersonic Air Breathing Vehicle Configuration S. Panneerselvam
4 Flow Numerical Study of Shock-Boundary Layer Kiran kumar and Manoj T. NairInteraction in Hypersonic Flow
5 Effect of Fore Body Fence on the Aerodynamics T. K. Ganesh Anavaradham,and SCRAMJET Intake Performance of a S. Panneerselvam andHypersonic Vehicle V. Thiagarajan
6 Aerodynamic Performance of a R. Gopalaswami and M.Hypersonic Flight Test Vehicle Thirumoorthy
Session CA- 2 ScramjetChairman : Shri Subhananda Rao Time : 1400 -1545Co-Chairman : Dr BVN Charyulu Venue : Hall-2
Title of paper Speaker1 Evaluation of a Ramp Cavity Based Concept A. Rajasekaran and V. Babu
Supersonic Combustor for the HSTDV Part I2 Evaluation of A Ramp Cavity Based Concept A. Rajasekaran and V. Babu
Supersonic Combustor for the HSTDV Part23 Numerical Optimization Study of Scramjet P. Manna
Combustor Performance4 Experimental Investigations on the Performance C.Chandrasekhar,D.K.Tripathi,
of Strut Based Supersonic Combustor V.Ramanujachari andS.Panneerselvam
5 Fuel Injection and Flame Stabilization in a D. P. Mishra and K.V.SridharSupersonic Combustor
6 Tip to End Simulation for Predicting the B.RajinikanthV.RamanujachariPerformance of SCRAMJET Powered and S.PanneerselvamFlight Vehicle.
Session CA- 3 Thermo Structural DesignChairman : Dr R Balasubramaniam Time : 1400 -1545Co-Chairman : Mr. V.K. Agarwal Venue : Hall-3Title of paper Speaker
1 Design Optimization of Axi-Symmetric Nose M.Ramesh Babu,Tip for Hypersonic Vehicles Prangyadeepta choudhury
and R.K.Gupta2 Thermal Design Methodology for Scramjet Engine G.Vijayakumar and A.K. Kachroo
and Control Surfaces of Hypersonic Flight Vehicle3 Thermo-Structural Design and Analysis of HSTDV PC Jain,VKAgarwal,
Scramjet Engine Casing G.Vijayakumar and A.K. Kachroo4 Conceptual Design and Analysis of the Nose K Madhusudhan Naidu,
Cap of A Wing Body Re-Entry Vehicle G V Rajesh Kumar and TSivamurugan5 Nonlinear Thermal Analysis of Laminated P.Patrick Joseph Kennedy
Composite Shells - A Novel Approach6 Aerospace Mechanisms based on Electro S Vara Prasad Rao and
Explosive Devices CH.Surya Kiran
Session CA- 4 System Concepts & In-Flight Air Collection and Oxygen LiquefactionChairman : K Sekhar Time : 1400 -1545Co-Chairman : Mr S VaraPrasada Rao Venue : Hall- 4
Title of paper Speaker1 Systems Preliminary Design of an In-Flight Air R. Gopalaswami and Liquefaction and Oxygen Separation System K. Srinivasan
forA Hypersonic Flight Test Vehicle2 Air Liquefier Design Considerations for In-Flight G. Venkatarathnam
Air Collection & Oxygen Liquefaction at Hypersonic Speeds
3 Novel Technologies for Liquid Oxygen Collection D. P. Rao, A. Bhowal S. Pandey,during the Flight of a Hypersonic Air-Breathing R. Gopalaswami,Satish Kumar,vehicle P.Manna and S. S. Panwar
4 Numerical Simulation Techniques for Group Satyanarayana Yedidi, R.SrilakshmiConcurrent Design of Hypersonic and and R. GopalswamiTrans atmospheric Vehicles
5 Aerodynamic Challenges of a manned Wg. Cdr. Vipin Sharma space flight
CONTRIBUTED PAPERSSession – I ( 30 June 07)
CONTRIBUTED PAPERSSession – II ( 30 June 07)
Session CB- 1 Stage Separation Studies
Chairman : Dr V G Sekharan Time : 1545 - 1715Co-Chairman : Dr G. Balu Venue : Hall- 1Title of paper Speaker
1 Nose Panel Opening Study of A Hypersonic Rohit R. More, S. Srinivasa Raju,Launch Vehicle K.Anandhanarayanan and
R. Krishnamurthy
2 Prediction of Aerodynamic Characterstics for Sanjay Kumar, T. K. GaneshStage Separation Studies of Hypersonic Anavaradham, J.J. Geetha,Technology Demonstrator Vehicle S Panneerselvam and G.R. Shevare
3 Stage Separation Studies of HSTDV Shivarama Reddy.K, Srikanthat Mach 6.5 Padbidri, Shiva Shankar
4 Preliminary Stage Separation Analysis of J. J. Geetha,T.K. GaneshHypersonic Technology Demonstrator Vehicle Anavaradham* and S. Panneerselvam
5 Heat Flux Evaluation on the Nose Cone of Launch T.K. Ganesh Anavaradham andVehicle at Hypersonic Mach Numbers S. Panneerselvam
6 CFD Studies for Heat Flux Estimation on a Sourabh Jain, B.Rajinikanth andHypersonic Air Breathing Vehicle G.R. Shevare.
Session CB- 2 Intakes & Nozzles
Chairman : Prof. G R Shevare Time : 1545 - 1715Co-Chairman : Dr R Krishnamurthy Venue : Hall- 2
Title of paper Speaker1 Experimental Studies on HSTDV Intake Sajeer Ahmed, N.B.Mathur,
Configuration in the Mach Number Range of S Panneerselvam and V Thiagarajan3.0 to 4.0
2 Experimental Studies on Base Flow Simulation of N.B Mathur, S.PanneerselvamHSTDV After Body-Nozzle Configuration and V.Thiagarajan
3 Hypersonic Intake Optimization Pratik Donde, Anil Marathe andK. Sudhakar
4 Effect of Nozzle Cowl Position on the V. Thiagarajan and S. PanneerselvamPerformance of Single Expansion Ramp Nozzle
5 Estimation of Heat Flux on a Launch Vehicle Abhishek Jain, T.K. Ganesh and Fin at Hypersonic Mach Numbers G.R. Shevare
Valedictory Function : 1715 Hrs
Session CB- 3 Facilities & Mechanisms
Chairman : Surendra Kumar Time : 1545 - 1715Co-Chairman : Mr C. Chandrasekar Venue : Hall- 3
Title of paper Speaker
1 Design of a High Performance Hypersonic T.K.Chandra, R. K. Sharma,Wind Tunnel V. Shanmugam, D.K. Yadav, A. S Krishnan
and A.S. Narayana
2 Commissioning of 1 Meter Diameter Shock T.K. Chandra, V. Shanmugam,Tunnel at DRDL Ravi J Prasad, P. JanardhanaRao,
Treena SenGupta,S. Prakash and A.S. Narayana
3 Experimental Study of Transverse Sonic G. Dhananjaya Rao, S.Swaminathan,Jet Injection Over A Cone at Free stream K. Srinivasan and E.RathakrishnanMach Number 2
4 Design of Glide Slope Control System for K.Senthil Kumar, C.Sudhir Reddy andLanding Phase of Large Unmanned J.ShanmugamAerial Vehicle
5 Design of Ejector System for Scramjet Rolex Ranjith, Nayan DubeyCombustor Test Facility, V.Ramanujachari
and S. Panneerselvam
CONTRIBUTED PAPERSSession – II ( 30 June 2007)
Valedictory Function : 1715 Hrs
Venue : Grand Ballroom
BRIEF HISTORY
The Aeronautical Society of India a professional body, devoted to advancement ofaeronautical sciences and engineering in India, was founded in the year 1948. PanditJawaharlal Nehru, the great visionary of India was the first Patron-in-Chief of the Society.Currently Honorary Prime Minister Shri Atal Behari Vajpayee is the Patron-in-Chief of theSociety.
The Society has its strength of more than 5000 members drawn from all major aeronauticalestablishments such as Defence Research & Development Establishments, HindustanAeronautics Limited, DGCA, Academic Institutions, Aeronautical Development Agency,Indian Air Force, Indian Space Research Organization, Vikram Sarabhai Space Centre,National Airports Authority of India, Air India, Indian Airlines, Jet Airways, Pawn Hans andprivate airlines. Most of the organizations / industries in this field in this country and abroadare Corporate Members of the Society.
OBJECTIVES
The objectives of the Society are to promote the advancement and diffusion of theknowledge of aeronautical sciences and aircraft engineering and the elevation of theaeronautical profession.
The Aeronautical Society of India is the only forum in the country that provides intenseinteraction between professionals from all facets of civil and military aviation as well asthe manufacturing/training/maintenance agencies. Over the years, the Aeronautical Societyof India has generated large pool of aviation manpower through non-formal educationand training programmes.
ORGANIZATION AND MANAGEMENT
The Society is managed by a Council consisting of a President, President-Elect, SevenVice Presidents, the Honorary Secretary General, Honorary Treasurer and fifteenMembers, twelve of whom are elected and the other three nominated to represent specialinterests
Aeronautical Society of India
ACTIVITIES
The Society’s activities include fraternization amongst professionals, promotion ofaeronautical activities and policy and increased awareness of indigenous / internationalinformation/events through lectures, workshops and seminars on subject of topical interest.
The Society also conducts examinations in aeronautical engineering twice a year. A passin this examination has been recognized by the Central Government in the Ministry ofeducation as being equivalent to a degree in Aeronautical Engineering from an IndianUniversity. Approximately 50 candidates graduate every year. The Society is thusrendering a yeoman’s service by giving an opportunity to the young to acquire a degree inAeronautical Engineering without straining the educational system and providing flexibilityto students to undertake this on a part time basis. It also provides a centralized libraryfacility to its members and students.
The Society publishes a quarterly journal containing Research and Technical papers onvarious facets of aeronautical sciences and a Quarterly Newsletter. The journal is of avery high standard and is rated world class.
The Society conducts and Annual Essay competition to recognize and encourage talentamong young students, engineers and scientist, and awards prizes to winners.
The Society also confers a number of prestigious awards for outstanding contributions infundamental / applied research in the field of aeronautics and space, every year.
Address
The Aeronautical Society of India13-B, Indraprastha EstateNew Delhi – 110 002, India
Tel : ++91 11 23370516Fax : ++ 91 11 23370768e-mail : [email protected]
Patron-in ChiefJawaharlal Nehru
PresidentN.C. Ghosh
Vice PresidentsV.M. Ghatage
H.M. Wadia
Hon. SecretaryP. Nilakantan
Hon. TreasurerS.C. Sen
Members
FIRST COUNCILOF
THE AERONAUTICAL SOCIETY OF INDIA(Year 1948)
B.C Carter Capt. L.M ManilalGP. Capt. Harjinder Singh D. NarayanamurtiR.N. Kathju K.K. RayR.R. Krishna Rao M.B Sarwate
PAST PRESIDENTSOF
THE AERONAUTICAL SOCIETY OF INDIAShri N.C. Ghosh … 1948-1951Air Marshal S. Mukerjee … 1952-1957Shri K.K. Roy … 1958Dr. V.M. Ghatage … 1959Shri K.M. Raha … 1960Dr. P. Nilakantan … 1961Air Marshal A.M. Engineer … 1962-1963Shri R.N. Kathju … 1964-1965Air marshal M.S. Chaturvedi … 1966-1967Dr. S. Dhawan … 1968Air Chief Marshal P.C. Lal … 1969-1972Air Chief Marshal O.P. Mehra … 1973-1975Shri S. Ramamritham … 1976Dr. S. R. Valluri … 1977Shri K.G. Appusamy … 1978-1980Shri A.H. Mehta … 1980-1982Air Chief Marshal Dilbagh Singh … 1982-1984Dr. V.S. Arunachalam … 1984-1986Air Marshal M.S.D Wollen … 1986-1988Wg. Cdr. I.M. Chopra … 1988-1990Dr. A.K. Rao … 1990-1992Dr. A.P.J. Abdul Kalam … 1992-1994Dr. C.G. Krishnada Nair … 1994-1997Lt. Gen. (Dr) V.J. Sundram … 1997-1998Shri H.S. Khola … 1998-1999Air Marshal P. Rajkumar (Retd.) PVSM, AVSM,VM … 1999-2001Kota Harinarayana … 2001-2002N R Mohanty … 2002-2003Air Chief Marshal (Retd) S.Krishnaswamy … 2003-2005Dr. G. Madhavan Nair … 2005-2007Shri V. Thulasidas … 2007
THE AERONAUTICAL SOCIETY OF INDIAGOVERNING COUNCIL FOR THE YEAR 2007
Patron-in-Chief :Dr. Manmohan Singh
President :Shri V.Thulasidas
President-Elect :Shri Ashok K. Baweja
Vice Presidents :Shri B.P. Baliga Dr. V. K. saraswat Shri Babu PeterAVMN.V.Tyagi Capt. G.R. Gopinath Major H.S. SandhuProf. N.G.R. Iyengar
Members :
Dr. V. Adimurthy Shri Ravi Menon Shri P.S. ChopraDr. Satish Chandra Ms Harpreet A De Singh Shri Sanjay BahadurProf. Job Kurian Shri S.K. saraswati Gp.Capt. (Retd)Niteen M.GuptaShri K. Tamilmani Wg.Cdr.(Retd) A.E. Patrawalla Ms. Yatindra Kumar
Honorary Secretary General : Honorary Treasurer :Shri Ashok Bhushan Shri Lalit Gupta
Past Presidents :Air Chief Marshal (Retd) S.Krishnaswamy
Dr. G. Madhavan Nair
Editor, Journal of the Ae SI :Dr. P. Balasubramaniam
The Aeronautical Society of IndiaHyderabad
OFFICE BEARERS & EXECUTIVE COMMITTEE
ChairmanDr. V. K. Saraswat
CC R&D (MSS) & Prog. Dir., AD
Vice – ChairmanShri Balram GuptaCapt S N ReddyDr R K Sharma
Wg Cdr Raja BabuShri K S Subba Rao
Hon. SecretaryShri Vijay Kumar
Hon. TreasurerShri P. Ranga Rao
EC MembersShri S. Vara Prasada Rao
Shri S.M. BhatiaShri G. Ramesh
Shri Rajeev GuptaShri U.S. Paul Russel
Shri R N GhaiShri R Siva Kumar
Lt Col T KasiShri Madhujit Roy
Shri Y V Raju
Astronautical Society of India
The Astronautical Society of India (ASI) was set up in 1990 to foster the development
of astronautics in the country. ASI is engaged in the dissemination of technical and other
information related to astronautics by conducting technical meetings, bringing out technical
publications and organising exhibitions. The society is also playing an active role to promote
the interests of other developing countries in the field of astronautics through the
International Astronautical Federation, Paris, in which the ASI is a voting
member.
ASI has, on its roll, eminent personalities in the field of astronautics as Honorary Fellows/
Fellows. A Programme Council consisting of elected Honorary Fellows/Fellows with
Chairman, Space Commission, as its Ex-officio Chairman, overseas the functioning of
the Society. An Executive Council consisting of 9 members including the President and
Vice President, Executive Secretary and Treasurer, elected by the General Body, looks
after the day-to-day administration of the society.
The Aryabhata Award and the four ASI awards, instituted by ASI are aimed at
recognising the talented Indian individuals who have made significant contributions in
fostering astronautics in India.
Objectives
1. To promote and foster the development of Astronautics for advancement
of scientific knowledge for peaceful purpose.
2. To encourage wide spread dissemination of technical and other information
relating to Astronautics through various means such as seminars,
publications, audio visual presentations, collaborative research, etc.
3. To stimulate public interest in and support for the multifaceted development
and applications of Astronautics through any appropriate media.
4. To stimulate and encourage participation in research and applications related
to Astronautics by national Institutions, Universities, Commercial and
Industrial Organizations and Individual specialists.
5. To encourage and support, among members, activities related to growth in
their professional knowledge on Astronautics.
6. To participate in and to foster co-operation with international institutions
and associates with similar purpose and to represent internationally, the
scientific and technological work of India in the field of Astronautics and to
advise, as called for by appropriate government or non government
organizations, on professional aspects related to the development and
application of Astronautics.
7. To create and foster subsidiary associations and institutions dedicated to
promote the development and peaceful applications of Astronautics.
8. To organize and arrange for meetings of the Congresses, Committees and
Conferences in pursuance of its activities.
9. To secure and administer funds, grants and endowments for the furtherance
of research in Astronautics and to institute awards, prizes or research grants
to individuals or institutions for furtherance of advancement of knowledge
in Astronautics.
10.To utilize the income of property of the Society towards the promotion and
fulfillment of the objects set-forth in this memorandum. No portion of the
income and property of the Society shall be paid or transferred directly or
indirectly by way of dividend or otherwise howsoever by way of profit to
any persons including the members of the Society.
Astronautical Society of India
Programme Council
Name Designation held in the Society
Shri G. Madhavan NairChairman, Space Commission
Ex-Officio Chairman
Dr K Kasturirangan, Fellow Member
Dr V K Aathre, Fellow Member
Dr C G Krishnadas Nair, Fellow Member
Sri N Pant, Fellow Member
Dr P S Goel, Fellow Member
Sri R K RajangamExecutive Secretary, ASI
Non-Member Secretary
Executive Council
Shri G. Madhavan Nair President
Shri. K.V.S.S. Prasada Rao Vice President
Shri R.K.Rajangam Exe.Secretary
Shri. V. Sundararamaiah Treasurer
Dr. Prahlada Member
Dr. K. Ramamurthi Member
Shri S. Sankara Subramanian Member
Dr. K. Badari Narayana Member
Shri. S.C. Bawa Member
ADVANCED SPACE TRANSPORTATION SYSTEMS:NEEDED TECHNOLOGIES & FACILITIES
Dr. BN Suresh, Director, VSSC
ABSTRACT
The theme for advanced space transportation is low cost access to space and could be achieved through
use of atmospheric air for propulsion and by reuse of launch vehicle hardware. Advancement in the areas
of hypersonic aerodynamics/thermodynamics and high-speed propulsion are key to this and Indian Space
Research Organization (ISRO) is putting concerted efforts in these enabling technologies. In addition to
developing a strong theoretical base and necessary computational tools, establishing major test facilities
and well thought of flight test programs are in focus.
ISRO has successfully proven the reentry capability through SRE (Space capsule Recovery Experiment).
Severe heat fluxes of 250W/ cm2 and above encountered during atmospheric flight has been withstood.
1MW Plasma Jet Facility was established and the SRE Thermal Protection System (TPS) was extensively
tested at the specimen level for integrated heat load & shear simulation. Based on the success,
establishment of 6MW Plasma Wind Tunnel is being taken up. This would enable sub system level
testing for gas enthalpies of 32MJ/kg with heat flux ranging up to 500W/cm2. Further flight tests of SRE
are planned (with advanced TPS materials) for enhanced database on reentry/recovery technology.
Air Breathing Propulsion can drastically bring down the size of the launch vehicle as about 75% of the
propellant is consumed within 50km altitude and oxidizer constitutes about 60% of the take off mass.
ISRO has made success in demonstrating stable supersonic combustion through a series of ground
tests for equivalent flight Mach number of six to seven. Following this success in supersonic combustion,
DMRJ-FTD (Dual Mode Ram Jet-Flight Technology Demonstrator) flight tests are planned on a novel
economical platform using sounding rocket. The mission is specially designed to provide required dwell
time for scramjet evaluation within the “Mach number-dynamic pressure” window of interest. A major
Scramjet Propulsion Test Facility capable of 20kg/s airflow rates is being established and this facility
can test & evaluate scramjet combustors up to flight Mach number of eight.
Atmospheric descent & landing for reuse calls for high lift configurations suitable for ‘hypersonic-
supersonic-subsonic’ flight. Major effort is being put to realize a 1m diameter Hypersonic Wind Tunnel
expected to be commissioned shortly. It will be capable of testing aerodynamic models at Mach 6 to 12
simulating Reynolds number up to 80 million per meter and temperatures up to 1750K. RLV-TD (Reusable
Launch Vehicle-Technology Demonstrator) program is envisaged to master hypersonic aerodynamics
and the double delta wing demonstrator vehicle would be boosted using a solid rocket motor and evaluated
during descent flight. Progressively, RLV-TD flights would evaluate high temperature material/thermal
protection systems, powered cruise flight/autonomous landing and vehicle integrated air-breathing
propulsion in real flight conditions.
Technology demonstration flight programs of SRE, DMRJ-FTD and RLV-TD along with major test
facilities of Hypersonic Wind Tunnel, Plasma Wind Tunnel and Scramjet Propulsion Test Facility will
provide necessary technology inputs for design and realization of advanced space transportation systems.
Going from where we are today with operational launch vehicles PSLV & GSLV and GSLV MKIII launch
vehicle for which the maiden flight is planned shortly, the near term technologies aim for a Two Stage To
Orbit (TSTO) vehicle by 2020 & the road map leading to fully reusable Single Stage To Orbit (SSTO)
vehicle by 2030.
FROM EARTH TO ORBIT IN TRANSATMOSPHERIC AIRBREATHING VEHICLESV.K.Saraswat*, P.Venugopalan**, Satish Kumar#, R.Gopalaswami$
email:[email protected]* Chief Controller R&D (MSS), DRDO.
** Director, Defence Research & Development Laboratory, Hyderabad.
# Director, Terminal Ballistic Research Laboratory, Chandigarh.
$ Former Chairman &Managing Director,BDL,Hyderabad.
ABSTRACT
Transatmospheric vehicles (TAV), flying like an aircraft, from runway take-off directly to near earth orbit,have many revenue earning societal missions, that include small satellite launching and recovery, solarenergy from space, and space tourism. TAV technologies have much in common with hypersonictransportation for civil aviation.
The system and technology design choices of over 20 TAV system design concepts made in 1980’s and1990’s are brought out. These design choices had resulted in very large vehicles with low payload-to-structure ratios. Without adequate ground and flight testing, hypersonic vehicles weighing hundreds oftonnes at take-off are highly risky to develop and operate. Hence, even though some of the requiredcritical airbreathing propulsion and materials technologies were ground tested on small scales, a functional,full-scale airbreathing TAV for safe, affordable access to space is yet to be realized by any nation.
Critical design factors affecting TAV design are identified and their effect on safety and affordability of thevehicle are discussed. Four fundamental design criteria for an aircraft to ascend directly from runwaytake-off to near earth orbit are brought out. These criteria are fuel weight fraction at take-off, missionaverage specific impulse, thrust-to-drag ratio and propulsive efficiency. It is shown that for direct ascentto orbit of an aircraft, like a single stage rocket vehicle, a minimum 56% hydrogen fuel fraction is requiredat take-off. This is feasible only if oxidizer tanks are empty on take-off, and liquid oxygen is collected inflight.
A high-speed flight regime for in-flight liquid oxygen collection and storage has been determined. Numericalsimulation tools, to optimize 26 interactive vehicle system design variables, were used to maximizevehicle payload performance. Airbreathing ram-scramjet engines are used in the air collection and oxygenliquefaction regime, a concept that is called ‘aerobic’ flight. It is seen that using air-breathing engines within-flight oxygen liquefaction and storage, results in low mission-average fuel consumption, low propellantfraction and high payload fraction. These attributes in turn enables geometrically down-scalableconfigurations and hence design and development of small size orbital vehicles is economically viable.
Extensive studies for aerobic vehicles up to 275-tonnes take-off weight reveals that an aerobic TAVweight as low as 25-tonnes is the minimum weight for direct ascent like an aircraft into earth orbit withpositive payload fraction. However, many system and technology design premises
and attributes need experimental verification by ground test and in flight. A reliable design-engineeringdatabase needs to be built up before full-scale investments are made risk-free for development of full-scale, operational, revenue-earning aerobic TAV’s. For this purpose, a small, 3.5 tonnes weight at take-off, unmanned, non-orbital aerobic hypersonic transportation technology demonstrator has been designedand over 75,000 man-hours of detailed concept and preliminary studies have been completed on thisaerobic TAV flight demonstrator [called HTV].Unlike any other flight test vehicle designed for a similarpurpose anywhere in the world , the flight time of the hypersonic air and space transportation flightdemonstrator is more than half an hour.
After the ongoing comprehensive design review is completed, a design and development programme forthe HTV is to be initiated in two stages. In the first stage, HTV with kerosene fuel can be flight tested upto Mach 5 for its future applications as a high speed air transportation system [Hypersonic Executive Jet],while ground tests are concurrently carried out using hydrogen fuel on critical technologies like the aerobicsystem. In the second stage, the flight envelope of HTV can be extended to Mach 7/8 using hydrogenfuel, with air collection and oxygen liquefaction in high-speed flight.
International cooperation is advocated for this advanced aerospace project. This will lay a strong foundationfor large risk-free flow of foreign direct investments (FDI) in India on full-scale systems and technologydevelopment of high speed transatmospheric air and space transportation of the 21st Century
IBSA IN SPACE:STRATEGY FOR GLOBAL COOPERATIVE ADVANTAGE
Keith Gottschalkemail:[email protected]
Head, Political Studies Department, University of the Western Cape, South Africa.
ABSTRACTStartling possibilities on the supply-side of access to space could cause exponential growth on thedemand-side of the space market.
India has, for over one decade, advocated a global cooperative design, development and deploymentprogramme for air-breathing, single-stage-to-orbit vehicles that carry no liquid oxygen on board at take-off, but harvest lox in high-speed flight while ascending, called “aerobic” flight to orbit. This transatmosphericvehicle design (TAV) is conceptually three generations ahead of any existing systems concept andprogramme. Its air transportation version would operate as an airliner traveling at Mach 5, over twice thespeed of Concorde (e.g. Cape Town - Mumbai in around two hours). The space transportation version willorbit around the world in 92 minutes, providing access to space - at 1% of the costs that customerscurrently have to pay. This will grow the space market exponentially.
This Trans-Atmospheric Vehicle (TAV) project with applications for low cost aerospace transportationwith complementary applications in high-speed air transportation
• exactly matches the three Governments’ aims of organically growing and strengthening the IBSAtripartite alliance (India-Brazil-South Africa) from an inter-governmental alliance, to also includingthe research and business sectors;
• exactly matches the three Department of Science & Technology’s (DST) aims of increasing ourR&D capacity, and our DTI’s aims of increasing our innovation of hi-tech industrial capacity andexports;
• exactly matches the three countries aerospace industry strategy of becoming part of the value-addition chain of international product development and manufacturing consortia, in addition tomarketing complete systems.
The TAV programme, if configured as an IBSA project, would brilliantly play to the strengths ofeach of the three countries:
� Brazil’s aircraft industry with its half-century of experience in running assembly lines for airliners,and its brand reputation in the market, would be a natural lead corporate partner at various stagesof the new aerospace product value addition chain; especially at the final, manufacturing stage ofcomplementary product integration arising from the basic TAV project.
� India’s R&D resources, including infrastructure and expertise for design, technology developmentand production of supersonic aircraft, space vehicles, cryogenic rocket engines, and its on-goingdevelopment of supersonic combustion ramjet engines and hypersonic flight technologydemonstrators, make it the lead partner for TAV systems and technologies. The size of its corporatesector would make it a leader in providing capital for the marketization stage.
� South Africa has niche leads in advanced composite materials, avionics, computing, design engineering,
software, and above all, its national test- flight facility with the coastal runways that the other nations lack.
METHODOLOGY FOR AERODYNAMIC CHARACTERIZATION OF TSTO WINGEDBODY VEHICLE
Balram Panjwani, G. Dhananjaya Rao, MM Patil, S Swaminathan and Madan LalEmail: [email protected]
ABSTRACT
A winged body vehicle (WBV) is conceived to fly from low subsonic to hypersonic Mach numbers fordemonstrating various technologies for a future Two-Stage-to-Orbit (TSTO) vehicle. A winged body vehiclewith double delta wing is configured to give maximum L/D in low subsonic Mach numbers considering acruise back option. Methodology for aerodynamic characterization of the TSTO winged body vehicle isdiscussed. And aerodynamic characteristics of the vehicle are estimated from subsonic to hypersonicMach numbers using engineering methods and CFD codes. Validation of the codes with the availablewind tunnel data and uncertainty of computed data are discussed. The vehicle has maximum L/D of 2.1in hypersonic flight regime and 5.4 in subsonic flight regime.
PROGRESS ON THE DESIGN AND DEVELOPMENT OF HYDROCARBONFUELED SCRAMJET ENGINE INTEGRATED VEHICLE TOWARDS
DEMONSTRATING HYPERSONIC AUTONOMOUS FLIGHTS. PANNEERSELVAM*
e-mail: [email protected]*Project Director, HSTDV
ABSTRACT
A flight demonstration mission has been evolved for the autonomous flight of the hypersonic air-breathingvehicle powered by a supersonic combustion ramjet engine and launched by a well proven AGNI A1booster. As the launch vehicle encounters high temperatures, extensive heat flux estimation on the bodyand fin has been carried out using CFD. Hypersonic vehicle configuration has been designed by consideringthe aerodynamics and propulsion intensive interactions. A non-circular octagonal shape of the aerodynamicconfiguration has been evolved in pitch yaw roll mode satisfactory stability and control characteristics inaddition to positive thrust margin. Aerodynamic characteristics of the hypersonic cruise vehicle havebeen estimated through wind tunnel tests. Extensive CFD analysis has been carried out for the vehicleviz., tip to end simulation considering simultaneously the external and internal flows with heat release inthe combustor and heat flux evaluation on the body and the engine. The computed results are in agreementwith the wind tunnel data. Strut based combustor testing has been carried out in connect-pipe mode toascertain its performance and suitability for the vehicles. High temperature materials have been identifiedand characterized for the realization of airframe, engine and mechanisms. Separation of the hypersonicair breathing cruise vehicle from the launch vehicle has been a critical event in the flight programme.Extensive simulation of stage separation has been carried out through CFD, considering the relativepositions between the launch vehicle and the cruise vehicle. Extensive ground testing is being progressedin India and abroad to update the aero-propulsion characteristics of the vehicle. The activities are identifiedat the micro level and are being addressed for the successful autonomous flight of the air-breathinghypersonic vehicle.
MULTIROLE FLIGHT TECHNOLOGY DEMONSTRATORFOR ADVANCED AIR & SPACE TRANSPORTATION SYSTEMSV.K.Saraswat*, P.Venugopalan**, Satish Kumar#, R.Gopalaswami$
email:[email protected]* Chief Controller R&D (MSS), DRDO.
** Director, Defence Research & Development Laboratory, Hyderabad.# Director, Terminal Ballistic Research Laboratory, Chandigarh.
$ Former Chairman &Managing Director, Bharat Dynamics Limited, Hyderabad.
ABSTRACT
Extensive studies have been done in India on “aerobic” aerospacevehicles that generate and store liquidoxygen on board while in high-speed flight. Airbreathing engines with in-flight oxygen liquefaction andstorage (Flox) results in high mission-average fuel specific impulse, low propellant fraction and highpayload fraction. These attributes in turn enable geometrical down-scalable configurations and hencedesign of small size orbital vehicles is feasible. The system design attribute of ‘scalability’ is also usefulto concurrently start a high-speed passenger air transportation programme at least technical risk andcost.
It was seen that for aerobic transatmospheric Vehicles [TAV’s], a take-off weight of 25-tonnes is theminimum weight for direct ascent like an aircraft into earth orbit with 4% payload fraction. Higher takeoffweights result in higher payload fractions. However, many critical system and technology design premisesneed experimental verification on ground and in flight. A reliable design-engineering database built upbefore full-scale investments are feasible on reusable spaceplane or high-speed passenger aircraftengineering design and development.
For this purpose, a small (3.5 tonnes take-off weight), unmanned, non-orbital aerobic hypersonictransportation system and technology demonstrator (HTV) has been designed. Over 75,000 man-hoursof detailed concept design and preliminary studies have been completed on this atmospheric hypersonicaerobic demonstrator in multiple academic and research institutions and teams, over a 4-year period,from year 2000 to 2003. The hypersonic flight time of the HTV is more than half and hour, unlike anyother spaceplane test vehicle designed for a similar purpose anywhere in the world. The HTV useslightweight, dual-fuel (kerosene-hydrogen) turbojet engines for take-off and powered landing, and forascent to 30 kms altitude where hydrogen fuelled ram/scramjet engine can take over in long range, halfhour cruise flight. Advanced lightweight composites are used for the airframe. It descends by aerodynamicbraking, and finally loiters and lands under its own turbojet engine power.
The commonality of flight regimes in atmospheric flight and similarity of fuels used, propulsion technology,aerodynamic configuration design, and airframe structure materials in high-speed flight regimes for airand space transportation are discussed in detail. An integrated system engineering design and continuedconceptual design studies are suggested. This programme may consist of comprehensive review andpreliminary engineering design of the HTV [Hypersonic, or, Hyperplane Test Vehicle], concurrently with aconcept design study on a 25-tonne aerobic spaceplane to deliver 1-tonne in orbit as well as a 6/8 seaterHypersonic Executive Jet, cruise speed Mach 4/5.
DESIGN OF GLIDE SLOPE CONTROL SYSTEM FOR LANDING PHASE OFLARGE UNMANNED AERIAL VEHICLE
K.Senthil Kumar, C.Sudhir Reddy and Dr.J.Shanmugame-mail : [email protected]
ABSTRACT
This paper analyzes classical control theory, specifically focusing on closed-loop control systems orfeedback control systems used for the design of glide slope control system for landing phase of largeunmanned aerial vehicle. Using the software program MATLAB Simulink, a Windows based programfrom Math Works Inc., short period approximation equations for a typical UAV were used to design andanalyze a model of a control system, which flies an aircraft towards or on a glide path. In the process,multiple feedback loops are used to represent the aircraft being flown on the glide path. In addition,compensators are used to combine the aircraft to the glide slope. As a measure of robustness, theresultant typical UAV autopilot control system is applied to a Boeing 747 commercial plane. The resultantdata showed that using specific gains for the rate gyro Kr and amplitude Ka in the closed loop transferfunction provided the best response without overshoot. The best values were found by taking theresponse of five systems to a step input and choosing the best ones to build the autopilot. Once theautopilot is established, the compensator and a gain for the glide slope are determined. Based on theroot locus and bode plots that it rendered, compensator #1 was determined to be the primary compensatorto use on the design of the system. The system proved to be robust since even when placed in a 747,the coupler is capable of at minimum controlling the vehicle. The results for compensator #1 provedthat it is a good compensator for a typical UAV with good noise attenuation capabilities, quick risereasonable, decent bandwidth, and performance, which increases when gain is allowed to vary.
STAGE SEPARATION STUDIES OF HSTDV AT MACH 6.5
Shivarama Reddy. K, Srikanth Padbidri, Shiva Shankar & B.Vasudevanemail:[email protected]
ABSTRACT
Hypersonic Technology Demonstration Vehicle development is an Indian program that is slated to bringto fruition the various technologies that have been associated with hypersonic flight. The vehicle isreasonably large and gets released from a Booster system at hypersonic speeds. The Booster-HSTDVseparation is a crucial event that requires careful studies in a hypersonic wind tunnel. Since the tunnel issmall (300mm dia), 1:25 scaled model and truncated boosters were used for experimental simulation.
NUMERICAL SIMULATION TECHNIQUES FOR GROUP CONCURRENT DESIGNOF HTOHL - HYPERSONIC TRANSATMOSPHERIC VEHICLES
Satyanarayana Yedidi, R. Srilakshmi and R. Gopalaswami
e-mail: [email protected]
ABSTRACT
1.0m hypersonic shock tunnel has been established at DRDL in order to meet the testing requirementsof hypersonic vehicles being developed by DRDL. Operating range includes Mach number from 6 to 10,stagnation pressure upto 100 bar and stagnation temperature upto 4000K. Variety of possible testsinclude studies on pressure distribution, scramjet engine intake characterization, flow field visualization,heat transfer studies etc. The tunnel circuit has been designed and fabricated as per ASME code andvetted by third party.
AERO THERMO KINEMATIC OPTIMIZATION TO MINIMIZE FUEL CONSUMPTIONIN HYPERSONIC AEROBIC FLIGHT
R.Gopalaswami *e-mail : [email protected]
*Formerly Chairman & Managing Director, Bharat Dynamics Ltd., Hyderabad, India
ABSTRACT
In-flight air collection and oxygen liquefaction system, called “flox system” is essential to maximize thepayload fraction delivered to low earth orbit by a single-stage-to-orbit aerospacevehicle. This vehiclesystem concept is also described as “aerobic” system. A systems approach to design of the flox systemis described.
Thermodynamic and kinematic analysis of a hypersonic flight vehicle with flox system suggest thatthere is an optimum “cruise” acceleration profile, which minimizes hydrogen fuel consumption duringliquid oxygen collection regime in hypersonic flight. This profile also depends on the aerodynamiccharacteristics of the aerobic vehicle.
Payload maximization of an ideal overall aerobic vehicle requires lox to be collected in atmosphericflight as late and as high a mass flow rate as technically feasible. However, the phenomenon of liquefactiondrag appears to limit the upper speed beyond which some loss of overall vehicle system fuel efficiency isentailed. Thermodynamic analysis suggests some fuel will be consumed to minimize liquefaction drag.
To minimize this extra fuel consumption, the kinematic and thermodynamic analysis indicates thatlower acceleration is needed at lower collection speeds and higher acceleration at higher collection speedswith upper sped limited to Mach 7 from material and thermodynamic conditions. The aerodynamic analysiscarried out substantiates that this upper collection speed will be around Mach 7. Approaches to extendthe upper speed of lox collection to Mach 8 are suggested.
STUDY ON INTEGRATION OF INLETS AND SCRAMJETSIN SYSTEM OF HYPERSONIC AIRCRAFT
Y.P. Goonkoemail :[email protected]
Khristianovich Institute of Theoretical and Applied Mechanics (ITAM),
Siberian Branch of Russian Academy of Sciences, Novosibirsk City
ABSTRACT
Results of theoretical and experimental investigations of certain aero-propulsive problems of scramjet-powered aircraft are reviewed. The comparative estimates of flight efficiency of scramjet-powered aircraftwith different layout of the scramjet flowpaths were studied with determination of their resultant aero-propulsive forces in the Mach number range M = 4-15. The considered aircraft configurations includedbox-like scramjet nacelles with two-dimensional (2D) inlets. The approach to determination of aerodynamiccharacteristics was based on consideration of so called polyhedral configurations which presented eitherschematically designed configurations or configurations approximating predetermined aircraft. Approximateanalytical methods of aerodynamic calculation as applied to the polyhedral configurations were developed;two-dimensional approximations of high supersonic flows over wings and three-dimensional lifting bodieswere used. Aerodynamic design of inlets, waveriders and lifting bodies, as well as complete aircraftconfigurations was performed with basing on the principle of convergent compression of supersonicflows, which provides streamlines converging in a space. Theoretical and experimental Investigationswere carried out which demonstrate the main properties of flows around these configurations and theiraerodynamic characteristics.
AERODYNAMIC PERFORMANCE OF A HYPERSONICFLIGHT TEST VEHICLE
R.Gopalaswami + and M.Thirumoorthy *
+ Formerly CMD, BDL, Hyderabad.* Scientist, ASL, Hyderabad.
ABSTRACT
A mathematical code for aerodynamic performance is developed for use in HTV Preliminary ConceptualDesign. The equations of lift and drag for subsonic, transonic, supersonic and hypersonic conditions arederived. The component of drag considered include skin friction drag, wave drag (fore body, wings & tails),Intake drag (turbojet, scramjet & Flox), and induced drag due to lift and super velocity drag. The wave dragfor an elliptical cone body is a major component of drag in high-speed flight. This is estimated using ananalytical model of a 3-D flow field, for which a “form factor” is derived using Experimental NASA windtunnel results for elliptical cone bodies. The aerodynamic coefficients of HTV using the above mathemati-cal code are in reasonable agreement with the CFD study. The HTV Aerodynamic code was further vali-dated when it was applied to the NASA Reference Configuration for which experimental wind tunnel resultshad been reported.
NOSE PANEL OPENING STUDY OF A HYPERSONIC LAUNCH VEHICLE
Rohit R. More*, S. Srinivasa Raju*, K. Anandhanarayanan* andR. Krishnamurthy*
email : [email protected]
* Scientists, CFD Division, DOCD, DRDL, Hyderabad
ABSTRACT
Nose panels of a hypersonic launch vehicle are separated to facilitate the injection of a hypersonic cruisevehicle that is kept inside the nose portion of the launch vehicle. A CFD study has been conducted toestimate the loads on the nose panels at various opening angles before it is released. Overset gridapproach, which facilitates tackling of multi-body configuration, is used to distribute points within thecomputational domain. A preprocessor has been used to generate connectivity that required for a grid-free solver. The grid-free Euler solver has been applied to predict aerodynamic loads on the panels. Theforces and moments are obtained to study the panel motion before release and the possible panelrelease angle is also suggested based on the results.
CONCEPTUAL DESIGN AND ANALYSIS OF THE NOSE CAP OF A WING BODYRE-ENTRY VEHICLE
K Madhusudhan Naidu, G V Rajesh Kumar, T Sivamurugan,S Swaminathan , Madan Lal
email: [email protected]
ABSTRACT
This paper describes the methodology followed for designing the nose cap of a wing-body re-entry vehiclefor a sub-orbital trajectory. Carbon-carbon is considered as the thermal protection system material fornose cap. Aerodynamic heating rates on nose cap are estimated using engineering methods. Carbon-carbon shell thickness is arrived at based on one-dimensional transient thermal analysis and preliminarystructural analysis. Fastening mechanism to integrate nose cap with vehicle fuselage front-end ring isconfigured. Design adequacy is checked by carrying out thermal response analysis and thermo structuralanalysis using finite element software. Maximum temperature at the stagnation region is 1430 K and allthe materials are within the design temperature and stress limits.
BLUNT BODY DRAG REDUCTION USING AEROSPIKE AND AERODISKAT MACH 6
R. Kalimuthu*, R.C. Mehta , E. RathakrishnanEmail: [email protected]
*Scientist/Engineer, Aerothermal Test Facilities Division, VSSC/ISRO, Trivandrum.
ABSTRACT
Experiments were carried on a blunt body drag reduction using different type of aerospikes and aerodiskfor L/D = 0.5 and 1.0 at Mach 6 in hypersonic wind tunnel. Drag reduction varies from 3.5% to 65% for thetested configurations. Hemisphere Aerodisk gives better drag reduction than other spikes. Drag reductionincreases as the length of the spike increases. Increasing in pitching moment to be considered while fordesigning the re-entry type of vehicles. As the angle of attack increase pitching moment also increasestherefore it requires for control of the vehicle.
EXPERIMENTAL STUDY OF TRANSVERSE SONIC JET INJECTION OVER ACONE AT FREESTREAM MACH NUMBER 2
G. Dhananjaya Rao, S. Swaminathan, K. Srinivasan and E. Rathakrishnanemail:[email protected]
ABSTRACT
Investigation of transverse jet injection into a supersonic flow at Mach 2 over a sharp cone was carried outusing experiments for different jet to freestream momentum flux ratios. The test model is a sharp conewith an included angle of 20° and a transverse jet nozzle of convergent angle of 10 deg with throatdiameter of 2.5 mm is mounted flush with cone surface. Nitrogen gas was used as fluid for transverse jetinjection and the pressures are varied to achieve momentum flux ratios from 1.69 to 6.9. Schlierenpictures of flow around jet injection were taken to visualize the flow field. Surface pressure measurementswere carried out on the cone surface around jet injection. The location of primary separation, shock standoff distance and reattachment point in the suction zone are measured from Schlieren. Jet penetrationheight is measured and it is seen that penetration height is proportional to the jet to freestream momentumflux ratio to the power of 0.56. Effective back pressure is computed and it is dependent on jet to freestreammomentum flux ratios.
DESIGN OPTIMIZATION OF AXI-SYMMETRIC NOSETIP FOR HYPERSONICVEHICLES
M.Ramesh Babu, Prangyadeepta Choudhury, R.K.Guptae-mail : [email protected]
Scientists, ASL, Hyderabad-500058.
ABSTRACT
The objective of this paper is to optimize the design of Axi-symmetric nosetip for hypersonic vehicles. Optimizationis done using a MACRO written in ANSYS. The MACRO is used for thermal analysis, which will convert cold wall heatflux to hot wall heat flux and simultaneously predicts temperature distribution throughout the domain. The MACROalso includes the modeling of re-radiation from the surface of the body. The analysis has been carried out for bothwith and without re-radiation cases. The MACRO has been validated with 1-D transient heat conduction code withtime varying boundary conditions. The MACRO developed is not limited to Axi-symmetric case, but can be used forany complex 3-D geometry. From the thermal analysis, thermal loads (heat fluxes) are given as input for structuralanalysis. In Structural analysis, nosetip is subjected to thermal loads due to kinetic heating and structural loads dueto aerodynamic forces. Stress distribution over the nosetip is obtained from the structural analysis. Carbon-phenolicmaterial is used for analysis purpose.3D orthotropic material properties are assigned.
LONGITUDINAL AND LATERAL AERODYNAMIC CHARACTERISTICS OF AHYPERSONIC AIR BREATHING VEHICLE CONFIGURATION
A scramjet engine integrated aerodynamic configuration has been designed to provide required aerodynamicforce, stability and control at its flight Mach number 6.5. It has been also designed to provide requiredcompression/expansion for scramjet engine so that the airframe engine integrated vehicle flies in thecruise mode efficiently. CFD studies of the complete vehicle involving simultaneous simulation of internal-external flow have been carried out using a Navier Stokes solver with standard k-e turbulence model. Thesimulations have been performed for different angles of attack, different sideslip angles, tail surfacedeflection in pitch mode and nozzle cowl deflection. This paper describes the longitudinal / lateralaerodynamic characteristics of the scramjet integrated air breathing vehicle at Mach number 6.5, consideringengine flow through condition.
T.K. Ganesh Anavaradham*, S. Panneerselvam+
email:[email protected]*Scientist, Proj. HSTDV,DRDL, Hyderabad
+Project Director,Proj. HSTDV,DRDL,Hyderabad
ABSTRACT
EXPERIMENTAL STUDIES ON HSTDV INTAKE CONFIGURATION IN THE MACHNUMBER RANGE OF 3.0 TO 4.0
Sajeer Ahmed, N B Mathur, S Panneerselvam and V Thiagarajane-mail : [email protected]
ABSTRACT
An experimental study was carried out on a 1: 8.5 scale model of HSTDV intake configuration at freestream Mach numbers of 2.91, 3.44 and 3.87 and corresponding unit Reynolds numbers of 33, 41 and 47million per meter respectively. The purpose of this study was to ascertain the starting of intake at highercontraction ratio using the concept of variable geometry and also to evaluate the performance of theintake in terms of back pressure limit, total pressure recovery and Mach number of the flow entering thediffuser/ combustion chamber. The starting characteristic of the intake was ascertained throughmeasurements of surface static pressures along the centreline of inner wall surfaces of the duct. Totalpressure recovery and Mach number of the flow entering the diffuser were computed using the totalpressures measured at the exit of isolator. Results show starting of intake flow can be achieved upto flapangle of 7.8°, 11.9° and 11.9° with corresponding range of back pressure of about 12, 17 and 17 times thefreestream static pressure for free stream Mach numbers of 2.91, 3.44 and 3.87 respectively. Analysisof rake pressures show average pressure recovery of about 0.64 and average Mach number of about 2.2at the entry of diffuser for freestream Mach number of 3.87 and at flap angle of 11.9°.
HEAT FLUX EVALUATION ON THE NOSE CONE OF LAUNCH VEHICLE ATHYPERSONIC MACH NUMBERS
T.K. Ganesh Anavaradham*, S. Panneerselvam+
e-mail : [email protected]*Scientist, Proj. HSTDV,DRDL, Hyderabad
+Project Director,Proj. HSTDV,DRDL,Hyderabad
ABSTRACT
An axi-symmetric Navier Stokes code with Spalart-Allmaras turbulence model is used to evaluate theheat flux on the HSTDV launch vehicle for different isothermal wall conditions. The heat flux has beenestimated for different flight conditions, namely, Mach number ranging from 1.5 to 8.0 and altitude rangingfrom 11 km to 32 km. This heat flux data base for different isothermal wall temperature conditions (300K to 1500 K) is used for solving the energy balance equation involving convection, conduction andradiation along the flight trajectory, thereby estimating the temperature experienced by the wall for a givenmaterial. This paper discusses the heat flux computation for different isothermal wall temperature atdifferent flight Mach numbers.
EXPERIMENTAL STUDIES ON BASE FLOW SIMULATION OF HSTDVAFTERBODY-NOZZLE CONFIGURATION
N.B Mathur, S. Panneerselvam, V.Thiagarajane-mail : [email protected]
ABSTRACT
An experimental study has been carried out on a 1:10 scaled model of HSTDV afterbody-nozzleconfiguration system in NAL 0.3m trisonic wind tunnel at freestream Mach numbers of 3.5 and 4.0 andthe corresponding unit Reynolds numbers of 38x106 and 47x106 per meter respectively. The purpose ofthese studies was to study the effects of: (i) jet nozzle Mach numbers (Mj = 1.6, 1.8 & 2.0), (ii) nozzlecowl extensions (0, 0.5h & 1.0h) and (iii) fencing (parallel and divergent) on expansion ramp surfacepressures to evaluate overall performance of the afterbody-nozzle system of this HSTDV configuration.Test results show that underexpanded jet-freestream interactions caused significant effect on expansionramp surface pressure distributions in the presence of cowl extensions (0.5h & 1.0h) and in the presenceof parallel fences. Also, jet nozzles of 1.6 and 1.8 with the cowl extensions of 0.5h & 1.0h with parallelfences caused maximum increase in static pressures on the ramp surface, indicating the optimumoperating condition of the nozzle for this afterbody-nozzle configuration.
NUMERICAL STUDY OF SHOCK-BOUNDARY LAYER INTERACTION INHYPERSONIC FLOW
Kiran Kumar1 and Manoj T. Nair2
1 Research Assistant, CTFD Div., NAL, Bangalore2 Scientist, CTFD Div., NAL, Bangalore
ABSTRACT
The aim of the present work is to access the ability of the three-dimensional RANS code MB-EURANIUMis predicting shock wave boundary-layer interaction. Results are presented for two cases in this paper. Thefirst is the turbulent boundary-layer shock interaction on a two-dimensional ramp. The second case is thatof laminar boundary-layer shock interaction over a blunted cone-flare.
PREDICTION OF AERODYNAMIC CHARACTERISTICS FOR STAGESEPARATION STUDIES OF HYPERSONIC TECHNOLOGY DEMONSTRATOR
VEHICLESanjay Kumar, T. K. Ganesh Anavaradham, J.J. Geetha , S Panneerselvam,
G.R. Shevare
ABSTRACT
CFD based simulation have been carried out to evaluate the aerodynamic interference between CruiseVehicle (CV) and booster portion of Launch Vehicle (LV) at various horizontal separations at zero angleof attack. Simulations are pseudo un-steady in the sense that relative velocity of CV with respect to LVbooster portion is not modelled as it is very small compared to hypersonic free stream velocity. To gainconfidence in the simulation, validation studies have been carried out on configuration available in literature.The paper discusses the validation and the simulations carried out to predict overall loads on CV and LVbooster portion.
PRELIMINARY STAGE SEPARATION ANALYSIS OF HYPERSONICTECHNOLOGY DEMONSTRATOR VEHICLE
J. Justina Geetha*, T.K. Ganesh Anavaradham* and S. Panneerselvam+* Scientist, Project HSTDV, DRDL, Hyderabad
+ Project Director, HSTDV, DRDL, Hyderabad
ABSTRACT
CFD Euler simulations have been carried out on the cruise vehicle and the booster configuration fordifferent axial separation distances between them. The mutual interference aerodynamic characteristicson the cruise vehicle and the booster configurations for different axial separation distances are computed.These are used in the 3 degrees of freedom trajectory study to evaluate the trajectory of the separatedcruise vehicle and the separated booster. It is seen that active separation is needed for separating thecruise vehicle from the launch vehicle. Pyro pusher has been chosen for active separation and therequired impulse level for the pyros has been evaluated. A part of separation sequencing viz. pyroinitiation, intake cowl opening and scramjet ignition are decided based on this study.
EFFECT OF FORE BODY FENCE ON THE AERODYNAMICS AND SCRAMJETINTAKE PERFORMANCE OF A HYPERSONIC CRUISE VEHICLE
T.K. Ganesh Anavaradham*, V. Thiagarajan* and S. Panneerselvam+e-mail : [email protected]
*Scientists, Proj. HSTDV,DRDL, Hyderabad+Project Director,Proj. HSTDV,DRDL,Hyderabad
ABSTRACT
An engine integrated vehicle has been designed with the objective being demonstration of sustainedhypersonic flight at Mach number 6.5. The vehicle has an octagonal cross section body with the scramjetengine mounted below the mid body. The fore body of the vehicle provides the external compression ofair and it is further internally compressed in the intake portion of the scramjet engine. A major amount ofnormal force, axial force and pitching moment is generated due to fore body. Fore body fences areprovided to improve the performance of the vehicle. This paper describes the effect of fore body fence onthe aerodynamics and fore body compression of the air breathing hypersonic cruise vehicle.
CFD STUDIES FOR HEAT FLUX ESTIMATION ON A HYPERSONIC AIRBREATHING VEHICLE
Sourabh Jain , B. Rajinikanth , G.R. Shevare
ABSTRACT
Calculation of heat fluxes on hypersonic vehicle geometry is very crucial. This is a difficult task aspresence of intake, wings and tail with control surfaces makes these aerospace geometries very complex.It is known that structured multi-block solvers are very effective for CFD simulations. However, creatingthese mashes is extremely taxing and difficult. Many times this may not be possible at all. The presentpaper describes attempts made to calculate heat flux on a hypersonic vehicle using structured meshesusing non-abutting one-to-one (i.e. meshes with C0 discontinuity) multi-block structured meshes. Use ofnon-abutting meshes has been reported in literature [1], but their use for heat flux calculations is achallenge. In our work, the existing solver has been modified to accept the C0 meshes so that heat fluxevaluation for hypersonic vehicles is possible.
The air breathing propulsion has the advantage of enhancing the performance and operability of a ReusableLaunch Vehicle (RLV) and it is possible to use this propulsion for ascend and descend atmosphericflight phases of an advanced RLV.
For obtaining maximum benefit from the air breathing propulsion, it is necessary to “air-breathe” upto high flight Mach numbers (say Mach 10). Supersonic combustion ramjet (Scramjet) is the only propulsionsystem which can operate at such high flight Mach numbers, and liquid Hydrogen with its extraordinaryhigh cooling capability and high specific impulse is its choice fuel.
The flight Mach number range of Scramjet is between 6 and 10+. In one of the options, a combinationof Rocket and Subsonic combustion ramjet (Ramjet) propels the RLV from take off to Mach number 6.
ISRO identified the development of supersonic combustion technology as the most crucial andchallenging. This has several technological challenges in terms of efficient mixing of very high speed air(in excess of a Km/s) with fuel, achieving the ignition, holding the flame and combusting the fuel efficientlywithin a practical length of a combustor (less than a meter).
ISRO worked on an integrated development program for the Scramjet propulsion technology. It comprisedof design of a test combustor (of 2.5 Kg/s air flow), in depth analysis of high speed mixing and combustion,extensive CFD simulations to understand complex flows within the combustor and large number of groundtests simulating the combustor entry conditions. The tests conducted covered wide range of fuel equivalenceratios, and also tests with off-nominal pressure and temperature conditions. In all the tests, stablesupersonic combustion was demonstrated for wide equivalence ratios up to 0.9. Detailed CFD simulationshave also been carried out to predict the performance. Subsequently, scale-up of the combustor wascarried out with 5Kg/s air flow and several ground tests were successfully conducted.
These detailed tests of the combustors, CFD simulations, analysis and results obtained havedemonstrated ISRO’s capability of development of scramjet combustors.
ISRO has now embarked on a low cost flight demonstration program of a total scramjet engineconsisting of appropriate supersonic air intake and nozzle systems in addition to the combustor. Theplanned flight test program employs a two stage (RH 560+RH 560) sounding rocket vehicle. Twoidentical scramjet engine modules, mounted on rear of the second stage of the vehicle. The trajectory ofthe vehicle is deigned to take the scramjet engines for their testing in the required Mach number &dynamic pressure envelope.
Presently, the design and development activities for the scramjet engine flight units are progressing atVSSC,ISRO. Detailed tests are planned for the air intakes using the wind tunnel test facilities at NAL andVSSC. Flight combustor will be tested and qualified in the High Speed Combustor Test Facility beingjointly set up at NAL.
HYDROGEN FUELLED SCRAMJET DEVELOPMENT AND TEST FACILITIES INISRO
J.D.A.Subramanyam Visiting Scientist, VSSC & Former Project Director, Air Breathing Propulsion Project, VSSC, ISRO
ABSTRACT
The present invited paper covers an account of supersonic combustor design and development wokscarried out by ISRO and its presently planned scramjet engine flight demonstration program using asounding rocket vehicle. It also gives brief details of the High Speed Combustor Test Facility shortlybeing commissioned at NAL as part of the VSSC-NAL joint project.
SUPERSONIC COMBUSTION EXPERIMENTS IN THE T4 SHOCK TUNNEL
David J. [email protected]
Center of Hypersonics, Mechanical Engineering,The University of Queensland, Brisbane, Australia
ABSTRACT
This paper presents an overview of experiments performed on supersonic combustion in the T4 ShockTunnel at The University of Queensland. This facility has been used to obtain fundamental data fromsupersonic combustion experiments over a period of 20 years. Results show that useful measurementscan be made for supersonic combustion phenomena in the short-duration test flows produced in Stalkertubes. The establishment of steady supersonic combustion is demonstrated using experimental resultsfrom the facility. Force measurement instrumentation developed for use in short-duration impulse hypersonicfacilities is discussed and sample results for supersonic combustion experiments are presented.
EVALUATION OF A RAMP CAVITY BASED CONCEPT SUPERSONICCOMBUSTOR FOR THE HSTDV – Part I
A. Rajasekaran and V. Babuemail:[email protected]
Department of Mechanical EngineeringIndian Institute of Technology, Madras, INDIA 600 036.
ABSTRACT
In this paper, numerical simulations of a full scale concept supersonic combustor using kerosene fuelare presented. The numerical procedure used in this work has been validated extensively with experimentaldata available in the literature for model combustors. The level of agreement between the predictionsand the experiments gives the confidence required to attempt numerical simulations for full scalecombustor designs. Results are reported first for a baseline model. These results are then used foridentifying the shortcomings in this model, which allows improvements to be made. Results for theimproved model are presented next. Shortcomings in the preliminary model are addressed in this design.In particular, the spacing between the ramps is widened so that the heat addition is not confined to ashort region and is distributed over a larger volume. Also the design of fuel supply lines has beenreworked so that they do not obstruct the supersonic flow. Details of the flow field inside the combustorsuch as contours of static pressure, static temperature, species mass fraction, reaction rate and Machnumber are discussed. Wall static pressure distribution along the top wall of the combustor is presented.Intricate details of the flow field such as separation zones, shocks and expansion fans and their interactionare also brought out. Finally, thrust developed by the combustor is calculated using two different methods.
EVALUATION OF A RAMP CAVITY BASED CONCEPT SUPERSONICCOMBUSTOR FOR THE HSTDV – Part II
A. Rajasekaran and V. Babuemail:[email protected]
Department of Mechanical EngineeringIndian Institute of Technology, Madras, INDIA 600 036.
ABSTRACT
In this paper, numerical simulations of a full scale concept supersonic combustor using kerosene fuelare presented. The numerical procedure used in this work has been validated extensively with experimentaldata available in the literature for model combustors. The level of agreement between the predictionsand the experiments gives the confidence required to attempt numerical simulations for full scalecombustor designs. Results are reported first for a baseline model. These results are then used foridentifying the shortcomings in this model, which allows improvements to be made. Results for theimproved model are presented next. Shortcomings in the preliminary model are addressed in this design.In particular, the spacing between the ramps is widened so that the heat addition is not confined to ashort region and is distributed over a larger volume. Also the design of fuel supply lines has beenreworked so that they do not obstruct the supersonic flow. Details of the flow field inside the combustorsuch as contours of static pressure, static temperature, species mass fraction, reaction rate and Machnumber are discussed. Wall static pressure distribution along the top wall of the combustor is presented.Intricate details of the flow field such as separation zones, shocks and expansion fans and their interactionare also brought out. Finally, thrust developed by the combustor is calculated using two different methods.
NUMERICAL OPTIMIZATION STUDY OF SCRAMJET COMBUSTORPERFORMANCE
P. Manna, Malsur Dharavath , Debasis Chakrabortyemail:[email protected]
ABSTRACT
Full scale nine strut based scramjet combustor of a hypersonic air-breathing vehicle is numericallyexplored for the different fuel injection systems. A commercial software CFX-TASCflow has been usedfor the reacting flow computation within the combustor. Three dimensional Navier-Stokes equations aresolved along with k-e turbulence model to analyse the flow field. Eddy Dissipation Model (EDM) with fastrate chemical kinetics is used for combustion modeling. Lagrangian Particle Tracking Method (LPTM)has been used to simulate the trajectory of the kerosene droplets. Kerosene is injected from the struts.The reacting flow simulations have been carried out for the fuel equivalence ratio of 1.0. The overall flowcharacteristics in the combustor are presented through the distribution of various thermochemicalparameters at different cross sections. Kerosene which is injected in liquid phase completely vaporizeswithin the combustor in the reacting flow. Considerable improvement in the performance in terms of thrustand combustion efficiency could be observed with the modified fuel injection system.
EXPERIMENTAL INVESTIGATIONS ON THE PERFORMANCE OF STRUTBASED SUPERSONIC COMBUSTOR
C.Chandrasekhar, D.K.Tripathi, V.Ramanujachari, S.Panneerselvamemail:[email protected]
Scientists, Scramjet Engine Division, DRDL, Hyderabad – 500 058
ABSTRACT
Experimental studies have been carried out to study the effect of mixing on ignition and combustion of airbarbotaged kerosene in Mach 2.0 vitiated air flow. Two tests have been carried out on a seven-strutbased scramjet combustor in the connect-pipe mode for Hypersonic Technology Demonstrator Vehicle.In the first test, the effect of stage-II struts without fuel injection and in the second test the absence ofstage-II struts were studied in the supersonic vitiated air flow for a duration of 5 s in each test. The wallstatic pressures, gas temperatures near the bottom wall of the combustor, external top wall skintemperatures and the mass flow rates are measured during the test. The barbotaged kerosene is injectedperpendicular to the supersonic vitiated air flow from the five fuel injection struts in both the tests. Theamount of fuel injected into the supersonic vitiated air stream in the combustor in terms of overall fuelequivalence ratio is 0.8. Although ignition and sustained supersonic combustion of kerosene fuel havebeen achieved with vitiated air in both the tests, non-uniform flame signature is observed at the exitplume indicating inefficient mixing of fuel/air. Non-uniform flame signature is found to be more in thesecond test possibly due to less flow disturbance in the absence of stage-II struts. The performance ofthe combustor in the first test is found to be better in terms of rise in pressure, uniform rise in gastemperature and computed thrust. It is concluded from these investigations that the stage-II struts withmetered fuel injection is essential to obtain the desired performance of the combustor for the missionrequirement.
FUEL INJECTION AND FLAME STABILIZATION IN A SUPERSONICCOMBUSTOR
D. P. Mishra and K.V.Sridharemail: [email protected] of Aerospace Engineering
Indian Institute of Technology Kanpur-208 016
ABSTRACT
The supersonic combustion ramjet (scramjet) engine is considered to be viable propulsive system forhypersonic vehicle. However, the mixing of fuel and air in the combustor is one of the main hurdles inachieving efficient combustion in supersonic flow condition which remains to be understood that mayaugur new methods of enhancing mixing and flame stability. Considerable efforts both in national andinternational level have been made by various groups to enhance understanding of fuel-air mixing insupersonic combustor. In this article, an attempt has been made to review fuel injection into supersoniccombustor. Various fuel injection methods such as normal injection, ramp injector, and cavity basedinjectors have been proposed by several researchers. It has been shown that the maximum mixingefficiency and its large upstream recirculation region has a good flame holding capability. In recent times,the cavity has been used as flame holder as the recirculation flow in cavity would provide a stable flameholding while enhancing the rate of mixing or combustion. The cavity effect is discussed from a viewpointof total pressure loss and combustion efficiency. The effect of various geometric variables on theperformance has also been investigated. Both fuel injector location and injection scheme play veryimportant role in determining the effectiveness of fuel-air mixing and combustion.
SYSTEMS PRELIMINARY DESIGN OF AN IN-FLIGHT AIR LIQUEFACTION ANDOXYGEN SEPARATION SYSTEM FOR A HYPERSONIC FLIGHT TEST VEHICLE
(HTV)
R. Gopalaswami and K. Srinivasan
ABSTRACT
This paper addresses an approach to systems preliminary design of an in-flight air liquefaction andoxygen separation system for a 3.5 tonne Hypersonic Test Vehicle (HTV) that can be ground tested overits entire hypersonic flight regime. A steady–state process simulation for the FLOX system process flowsheet comprising of set of cryogenic heat exchangers, oxygen separators, pumps, compressors andturbines has been carried out. The air liquefaction ratios obtained in the present study are comparablewith the reported values. Preliminary weight estimates of the FLOX system are also made and comparedwith the published literature.
AIR LIQUEFIER DESIGN CONSIDERATIONS FOR IN-FLIGHT AIR COLLECTION &OXYGEN LIQUEFACTION AT HYPERSONIC SPEEDS
G. VenkatarathnamDepartment of Mechanical EngineeringIndian Institute of Technology Madras
ABSTRACT
The launch weight of space vehicles can be decreased markedly by collecting and liquefying air duringhigh speed flight, using liquid hydrogen stored on board. Liquid oxygen is then separated from the liquefiedair to the extent of about 90% and the rest along with nitrogen (known as depleted air or DA) is returnedto atmosphere through the ascent engine afterburner. The Air Liquefier consists of a set of compact,light weight cryogenic heat exchangers. Both the depleted air and liquid hydrogen are used to cool andliquefy the air in a series of heat exchangers. Design considerations for the Air Liquefier to maximize theair liquefaction ratio, such as single/multi-stream heat exchangers, temperature profiles and “pinch” inthe set of heat exchangers are presented. Designing the air liquefier to operate at speeds beyond Mach6/7 and up to Mach 8 would need special provisions that are discussed.
CFD ANALYSIS OF ENERGY AND PHASE SEPARATION IN A CRYOGENICVORTEX TUBE
T. Dutta, P. Sandilya, S. S. Bandyopadhyay*email: [email protected]
* Corresponding author,Cryogenic Engineering Centre IIT Kharagpur,Kharagpur – 721302, India
ABSTRACT
In this work theoretical analyses of the energy separation and phase separation phenomena in a vortextube have been investigated at cryogenic temperatures with single-phase as well as two-phase air as theworking fluid. CFD software package FLUENT 6.3.26 has been used to generate the profiles of pressure,velocity, temperature and liquid volume fraction (in case of two-phase flow) inside the vortex tube. Theseprofiles have been analyzed to get an insight into the processes of energy separation and phase separation.The analysis is a prelude to the phenomenon of mass separation, i.e. separation of oxygen and nitrogenfrom air.
NOVEL TECHNOLOGIES FOR LIQUID OXYGEN COLLECTION DURING THEFLIGHT OF A HYPERSONIC AIR-BREATHING VEHICLE
D. P. Rao, A. Bhowal and S. Pandey * R. Gopalaswami ,Satish Kumar, P. Manna andS. S. Panwar
email :[email protected]* Department of Chemical Engineering, IIT Kanpur, Kanpur India 208016
ABSTRACT
This paper presents high-gravity cryogenic distillation and an ion-electronic conducting membrane oxygenseparator for In-flight oxygen collection system of a hypersonic air-breathing vehicle. The former operatesat about -90 ºC whereas the latter operates at high temperature of about 1100 ºC. Preliminary evaluationindicates they have the potential to meet the stringent weight and volume constraints of the air-breathingvehicle.
VORTEX TUBE TECHNOLOGY FOR LOX SEPARATIONS. Jacob, P.J. Paul, S. Kasthurirengan, R. Karunanithi and Upendra Behera
email:[email protected], Centre for Cryogenic Technology, IISc, Bangalore - 560 012.
ABSTRACT
In-flight collection of air, pre-cooling, liquefaction and separation of liquid oxygen (LOX) are key technologiesfor futuristic launch vehicles. Vortex tube technology is a potential technology for this application. Extensivestudies have been carried out on straight and conical vortex tubes towards the development of the vortextube technology for high purity LOX separation. The geometrical parameters such as the inlet nozzleprofile and number of nozzles, cold end orifice diameter (dc), length to diameter ratio (L/D), hot gasfraction, etc. have been optimized through CFD studies and validated through experiments. The influenceof the operating parameters like the inlet pressure, inlet temperature, etc. on LOX separation has beenalso studied. LOX purity of H”96% with ~14% separation efficiency has been achieved with conical vortextube of 12mm diameter and L/D = 10. Studies show that vortex tube can be optimized suitably for highLOX purity and low separation efficiency or low purity and high separation efficiency by adjusting the hotend mass fraction accordingly. It is not possible to obtain both high LOX purity and high separationefficiency simultaneously in a single vortex tube. However, it is possible to achieve both high LOX purityand separation efficiency by staging of vortex tubes. In staging of vortex tubes the enriched air streamfrom the first stage of the vortex tubes is introduced to the inlet of the second stage of vortex tubes. LOXpurity of 96% and separation efficiency of 73.5% has been achieved for second stage vortex tube suppliedwith pre-cooled air having 60% oxygen purity.
ABSTRACT
The current work has been directed towards combining low-fidelity models with CFD for parametric
optimization of a hypersonic intake. After identifying the performance parameters, design variables and
constraints, samples were picked through stratified sampling for CFD analysis. Results from this analysis
were used for developing low-fidelity models, which were used for modifying the design space. Samples
from the new design space were analyzed using CFD and the configuration leading to the highest gain in
performance parameters was considered the optimal geometry.
HYPERSONIC INTAKE OPTIMIZATION USING CFD WITH LOW-FIDELITY MODELS
P. P. Donde*, A.G. Marathe and K. Sudhakare-mail : [email protected]
* Research Assistant, Department of aerospace Engineering, IIT Bombay
EFFECT OF NOZZLE COWL POSITION ON THE PERFORMANCE OF SINGLEEXPANSION RAMP NOZZLE
V. Thiagarajan and S. Panneerselvamemail:[email protected]
ABSTRACT
Single Expansion Ramp Nozzle (SERN) has been adopted for a Hypersonic Technology DemonstratorVehicle. As a part of vehicle design, computational analysis of SERN nozzle has been carried out. Inthe present study, the effect of combustor cowl deflection on the performance of SERN has been evaluatedcomputationally. PARAS-3D, computational fluid dynamic software is used to predict the nozzle flow.The pressure distribution on the on the cowl and on the ramp has been computed for intake closedcondition and intake open condition for the cowl deflection of 25o. Also computed the nozzle forcecharacteristics for different cowl deflection angles with the increased nozzle entry pressure correspond tothe power-on condition. The results show that the normal force produced by the cowl with deflection of25o at intake is closed condition and with deflection of 25o at power-on condition help in achieving thestability margin to the required extent so that the vehicle can be controlled with the existing tail surfaces.
TIP-TO-END SIMULATION FOR PREDICTING THE PERFORMANCE OFSCRAMJET POWERED FLIGHT VEHICLE
B.Rajinikanth, V.Ramanujachari , S.Panneerselvamemail: [email protected]
Scientists, DRDL, Hyderabad-58.
ABSTRACT
This paper discusses the Tip-To-End Reacting flow simulation of Scramjet integrated Hypersonic TechnologyDemonstrator Vehicle (HSTDV). External and external flows over HSTDV are solved simultaneouslyconsidering kerosene as fuel. Multi-block structured grid is generated over the vehicle. Density basedsolver is used. The calculations are made with five species and laminar single step kerosene chemistry.Fuel injection is modeled as droplets using Discrete Phase Modeling (DPM). Non reactive simulations arecarried out to generate initial conditions for reactive simulation. The flow field parameters such as staticpressure, static temperature and Mach number are compared between non-reactive and reactivesimulations. The simulation predicts mass averaged Mach number as supersonic throughout, for thereactive simulation. The reactive simulation predicts a positive thrust margin, indicating the cruisabilityand possible acceleration capability of HSTDV.
THERMO-STRUCTURAL DESIGN AND ANALYSIS OFHSTDV SCRAMJET ENGINE CASING
P.C.Jain, G.Vijayakumar, V.K.Aggarwal, A.K. Kachroo
email:[email protected]
ABSTRACT
This paper deals with a design methodology and case study for scramjet engine casing. The scramjet isregarded as the propulsion system suitable for hypersonic flight. The scramjet engines are subjected tohigh pressure and high heat transfer rate due to high temperature and high speed combustion productsflowing through the engine. Double wall construction of HSTDV Scramjet engine casing is proposed towithstand the thermal as well as pressure loads. High temperature materials, viz. C-103 Niobium basedalloy , C-263 Nimonic alloy are being considered for the double wall construction of the engine. Theengine casing is designed based on the strength and stiffness requirements at elevated temperaturewith the objective of minimum weight of the engine. An optimum design has been evolved throughsuccessive iterations.
MATERIALS FOR HYPERSONIC AEROSPACEVEHICLES – A REVIEW AND INDIAN STATUS
Y.R. Mahajan, Ananya Ghosal, K.R. Ananth, A.G. Sarwade, S.S. Panwar,C.S. Raju, C. Chandrasekhare-mail : [email protected]
ABSTRACT
Hypersonic vehicles with airbreathing engines have to fly at ultra-high speeds and moderate dynamic pressuresfor long time resulting in vehicle and engine flight environments with extreme temperatures and heating rates,large aerodynamic forces and acoustic loads. A major constraint to the construction of hypersonic vehicles isrelated to the choice of available structural materials for airframe and engine applications that will fulfill thestringent requirements of hypersonic flight. This paper gives a brief review of the intense worldwide efforts todevelop these vehicles and the materials and processes used for this purpose. It also briefly describes thecurrent Indian scenario in which a number of R&D institutions, universities and organizations are activelyengaged in the development of advanced materials and processing technologies that are relevant to hypersonicvehicle programme.
NONLINEAR THERMAL ANALYSIS OF LAMINATEDCOMPOSITE SHELLS - A NOVEL APPROACH
P.Patrick Joseph Kennedy ,R.Palaninathan*
email:[email protected]
*Professor, Applied Mechanics Department,Indian Institute of Technology, Madras-36.
ABSTRACT
This paper presents a completely hierarchical p-version finite element formulation for a curved shell element
for nonlinear conduction in laminated composites, where the element temperature approximation in the shell
thickness direction can be of any arbitrary polynomial order p. A typical numerical integration scheme (NI
model) would require 3x3 integration in the tangential ( ξ η ) plane of each layer and (p+1)th order integration in
the thickness direction of each layer for the pth order temperature approximation. Such a scheme is however
inefficient since it results in an enormous number of sampling points for the computation of various element
matrices as the number of layers in the composite construction increases.
In view of the above, an efficient integration scheme, without sacrificing numerical accuracy and at the
same time reducing computer time is considered necessary. In reality the geometric parameters of the composite
shell are such that the radius-to thickness ratio are high. Taking advantage of this, simplifying assumptions
namely the elements of the Jacobian inverse and the determinant of the Jacobian are constant (EICJ model)
through the thickness, which will make the exact through thickness integration possible.
Because of temperature dependence of thermal conductivities, internal heat generation, film coefficients
and radiation boundaries, the resulting discretised equations of equilibrium are nonlinear. These equations
are solved using residual method. Numerical examples are presented to demonstrate the accuracy, efficiency
and overall superiority of the present formulation. Comparisons are made with available results in the literature.
LIGHT WEIGHT CRYOGENIC FUEL TANK STRUCTURES
R.Srinivasane-mail : [email protected]
General Manager, Aerospace Division, Hindustan Aeronautics Limited, Bangalore
ABSTRACT
The paper describes the materials, structures and the welding technology pertaining to the light weightcryogenic fuel tanks. The main focus of this paper is the development of the welding technology for thecryogenic tankages made of AA2219 alloy. The paper discusses factors governing the choice of fillerwire, physical metallurgy, welding metallurgy, major welding defects and the weld efficiency. The paperdwells at length on the selection of the welding process, design of the welding trials, parametric study ofthe welding trials and the results of the welding trials leading to the optimized and recommended parametersfor consistent weld quality.
CURRENT STATUS OF RESEARCH ON HYPERSONIC COMBUSTION ANDHIGH-ENTHALPY AERODYNAMICS IN THE FREE-PISTON SHOCK TUNNEL
HIEST
Hideyuki Tanno, Masahiro Takahashi, Tomoyuki Komuro, Kazuo Sato,Masatoshi Kodera, and Katsuhiro Itoh
e-mail : [email protected] Space Center, Institute of Aerospace Technology, Japan Aerospace Exploration Agency
1 Koganesawa, Kimigaya, Kakuda, Miyagi 981-1525, JAPAN.
ABSTRACT
This paper mainly describes the current status of research on hypersonic combustion in the high-enthalpyfree-piston shock tunnel HIEST. A new scramjet engine model M12-03 was developed to investigate theperformance characteristics of scramjet engines under hypervelocity conditions over Mach 10 flight. Inthe design of the new engine, the pressure at the combustor entrance was set to be twice that of theprevious engine M12-02 and the combustor length reduced while maintaining the gas temperature at thecombustor entrance at an adequately low level. A further attempt was also made to apply a combustorwith a diverging section to the present engine with the aim of further reduction of the net heat release lossby gradually expanding the combusting gas flow. These modifications successfully improved the combustorperformance at stagnation enthalpy of 7MJ/kg or higher. This paper also mentions the latest results of aforce measurement technique newly applied in the HIEST for hypervelocity aerodynamics.
THERMAL DESIGN METHODOLOGY FOR SCRAMJET ENGINE AND CONTROLSURFACES OF HYPERSONIC FLIGHT VEHICLE
G.Vijayakumar1 and A.K. Kachroo2
e-mail : [email protected],[email protected] Scientist, Heat Transfer Division, Directorate of Propulsion, DRDL, Hyderabad
2 Head, Heat Transfer Division, Directorate of Propulsion, DRDL, Hyderabad
ABSTRACT
Hypersonic vehicles fly at Mach number of 6-8 at around 30-35km altitude and Scramjet is regarded asthe propulsion system suitable for hypersonic flight regime. The scramjet engine experiences high heattransfer rates due to high temperature combustion products flowing with high speed in the combustionchamber of the engine. Also, the engine as well as vehicle airframe including control surfaces are subjectedto kinetic heating arising out of high speed areodynamic flow which also contributes to the rise in the walltemperature. Theoretical prediction of the thermal response of engine wall and control surfaces becomesnecessary before going for a flight test of this kind. Double wall construction of Scramjet engine casingis being proposed to ensure that it withstands both thermal as well as pressure loads with minimumdeflection. Heat transfer analysis for the vehicle becomes imperative for material selection and estimationof safe duration during which the engine should operate considering the severe thermal environment. Thethermal design methodology in respect of scramjet engine and control surfaces of the vehicle is presentedin this paper. Heat transfer analysis carried out for the engine considers passive cooling technique,treating its walls as heat sink for a short duration flight of 20 seconds. Control surfaces, viz., wing andtail, experience heat flux that mainly arises out of kinetic heating and, therefore, undergo substantialheating that can produce large thermal gradients in the body. Heat fluxes have been estimated for boththe stagnation as well as off-stagnation regions using suitable empirical correlations. Heat dissipationdue to radiation from control surface skin at higher temperatures is also considered in the analysis.Transient three dimensional conduction analysis based on FEM, considering convective and radiativeloads, has been carried out and the wall temperature profiles for the engine and control surfaces predictedfor the specified flight duration. High temperature materials like Niobium based alloy, Nimonic alloy,Titanium alloy and high temperature alloy steel which retain their strengths to the desired levels at elevatedtemperatures have been considered in the analysis. The estimated wall temperatures are found to be wellwithin the allowable limits and as a result, the proposed configurations of the engine and control surfacesare being pursued for fabrication and testing.
EVALUATION OF AERODYNAMIC TESTING IN A BLOW DOWN HYPERSONICWIND TUNNEL
Dr. M. Zilberman, Dr. S. Seror, J. HefetzIsrael Aerospace Industries, CAG, Engineering Division, Israel
Dr. S. Panneerselvam, Dr. T.K. Ganesh AnavaradhamDefence Research & Development Laboratory, India
email : [email protected]
ABSTRACT
The development of hypersonic trans-atmospheric air vehicles requires a big variety of testing facilities.There is no single facility that can simultaneously duplicate all the flight conditions. It is our objectivein the present paper to demonstrate the basic building block of hypersonic design by presenting theaccumulated practices and applications of the hypersonic blow down wind tunnel at IAI. The paperpresents a short description of the IAI hypersonic wind tunnel (HYWT). The Mach distribution atseveral sections downstream the exit nozzle is presented for Mach numbers 6.2 and 8. Flow qualityand blockage effect in the test section are evaluated by using an AGARD standard calibration body(HB2) of several sizes. The flow Mach number at the test section is validated by static pressuremeasurements on a cone. One of the major objectives of the hypersonic wind tunnel is the validationand calibration of CFD codes. The performance of the prescribed wind tunnel in our paper is comparedwith Navier- Stokes CFD code. Experimental measurements are compared with the CFD calculationsfor the Mach number distribution at mach 6.2 nozzle exit, for the static pressure distribution on acone and for the aerodynamic coefficients of the HB2 model and the LORA (LOng Range Artillery)configuration. The paper is demonstrating some of the techniques that are less sensitive to the “coldflow” nature of the wind tunnel. An inlet cowl mechanism is introduced as part of flow throughaerodynamic measurement on a Hypersonic Test Vehicle. The “run” and “start” positions were calculatedprior to the final design of the cowl mechanism. The “heavy” free drop simulation technique is suggestedfor the validation of a safe ejection of the HSTDV covering panels from the booster, prior to separationof the test vehicle. Static measurements of aerodynamic loads at different position during theseparation phase are used as a data base for 6-DOF trajectory calculations for the separation stage.
THE PROGRAM OF WIND-TUNEL TESTS AND FEATURES OF MODELSDESIGN FOR AERODYNAMIC INVESTIGATIONS OF INDIAN HSTDV VEHICLE
A.N. Polikarpov, A.F. Chevagin, A.A. Gubanov, S.A. TakovitskyTsAGI, Zhukovsky Moscow region, Russia
T.K. Ganesh Anavaradham, V. Thiagarajan, J. Justina Geethaand S. Panneerselvam
Defence Research and Development Laboratory, Hyderabad - 58, India
email:[email protected]
ABSTRACT
This paper deals with experimental investigations on aerodynamics and intake characteristics for IndianHSTDV test vehicle in TsAGI high-speed wind tunnels. The set of the models is being described, aimedto determine the features of the flow past vehicle and its intake, intake starting conditions, pressuredistributions, intake throttling characteristics, and aerodynamic forces and moments acting on the vehicle.
DESIGN OF A HIGH PERFORMANCE HYPERSONIC WIND TUNNEL
Chandra T.K.*, Sharma R.K. $, Shanmugam V. *, Yadav D.K. *,Krishnan A. S. * and Narayana A.S#
e-mail:[email protected]* Scientists, Aerodynamics, DRDL, Hyderabad
$ Deputy Project Director, ASTRA, DRDL, Hyderabad# IDST Consultant, DRDL, Hyderabad
ABSTRACT
DRDL has proposed to establish a high performance hypersonic wind tunnel to cater for its growingtesting requirements. This paper briefly describes various design features of the tunnel. Specifications ofmajor international wind tunnels are provided.
Broad specifications of the wind tunnel and of its various subsystems including high pressurecompressed air supply ,vacuum systems, pebble bed heaters ,settling chamber, nozzle ,model motioncontroller , diffuser and after cooler are discussed .Nozzle contours are generated using method ofcharacteristics. CFD analysis of flow field in nozzle are also discussed. Nozzle throat heat transfer andwater cooling of throat are briefly discussed.
Highlights of tunnel performance capabilities are brought out. This paper brings out the major andnovel features of the design work.
COMMISSIONING OF 1 METER DIAMETER SHOCK TUNNEL AT DRDL
Chandra T.K.*, Shanmugam V.*,Janardhana Rao P.*, Ravi J Prasad*,Treena Sen Gupta*, Prakash S.*, Narayana A.S#.
email:[email protected]* Scientist DRDL, Hyderabad
# IDST Consultant, DRDL, Hyderabad
ABSTRACT
1.0m hypersonic shock tunnel has been established at DRDL in order to meet the testing requirementsof hypersonic vehicles being developed by DRDL. Operating range includes Mach number from 6 to 10,stagnation pressure upto 100 bar and stagnation temperature upto 4000K. Variety of possible testsinclude studies on pressure distribution, scramjet engine intake characterization, flow field visualization,heat transfer studies etc. The tunnel circuit has been designed and fabricated as per ASME code andvetted by third party.
DESIGN OF EJECTOR SYSTEM FOR SCRAMJET COMBUSTOR TEST FACILITY
A. Rolex Ranjith*, Nayan Dubey*, V. Ramanujachari# and S. Panneerselvam$
e-mail: [email protected]* Scientist,Scramjet Engine Division,DRDL Hyderabad# Head, Scramjet Engine Division,DRDL Hyderabad
$ Project Director, HSTDV, DRDL Hyderabad
ABSTRACT
Several connect pipe tests have been conducted on Scramjet combustor at the Scramjet Test Facility,DRDL. In order to fully characterize the Scramjet combustor, a fair estimate of the thrust generated bythe combustor under full supersonic flow conditions is needed. An ejector system has been designed forthe Scramjet combustor so that full supersonic flow can be achieved in the Scramjet combustor. One-dimensional studies and detailed CFD simulations are made to understand the phenomena associatedwith the Ejector. A parametric study is made to obtain an optimized design for the Ejector.
ABSTRACT
CAPABILITIES OF TSAGI WIND TUNNELS FOR AEROTHERMODYNAMICINVESTIGATIONS OF HIGH SPEED VEHICLES
A.N. Polikarpov1, A.F. Chevagin2, A.A. Gubanov3, V.I. Plyashechnik4, A.V. Vaganov5
1 Deputy Director, TsAGI, Zhukovsky Moscow region
e-mail : [email protected] Head of Propulsion Division, TsAGI, Zhukovsky Moscow region
e-mail : [email protected] Deputy Head of Aerodynamics Division, TsAGI, Zhukovsky Moscow region
e-mail : [email protected] Deputy Head of Aerothermodynamics Division, TsAGI, Zhukovsky Moscow region
e-mail : [email protected] Deputy Head of Aerothermodynamics Division, TsAGI, Zhukovsky Moscow region
e-mail : [email protected]
The paper presents general description of TsAGI expermental facilities which are used for aerodynamicand aerothermodynamic investigations of high-speed vehicles. Consideration is given to main parametersof the facilities and the main types of tests which could be carried out. The range of facilities includeswind tunnels for general applications and special experimental facilities allowing to investigatecharacteristics of propulsion system components: air intakes, combustion chambers, and engine nozzles.
AEROSPACE MECHANISMS BASED ONELECTRO EXPLOSIVE DEVICES
S Vara Prasad Rao*, CH.Surya Kiran*e-mail : [email protected]
*Scientists, Directorate of Aerospace Mechanisms,Advanced Systems Laboratory, Hyderabad.
ABSTRACT
Design, development, qualification testing and deployment of Aerospace and related mechanisms is achallenging activity in the area of satellite launch vehicles, missiles, weaponry, satellites, aircrafts androbotics. Over the years the country has made rapid strides and achieved commendable successes inthe field of aerospace mechanisms. Our country has wide spectrum of engineers and scientists wellexperienced in design, development, testing, assembly and integration of such mission criticalmechanisms. Present paper deals with various mechanisms which were designed, qualified and deployedwith the expertise gained over a period of time in the field of Aerospace Mechanisms and gives an insightin to the futuristic challenges.
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With Best Complements From
301-302 ELDORADO ESTATE, 3-6-526,HIMAYAT NAGAR, HYDERABAD-500 029PH. 040-27632763FAX : 040-27636935URL : WWW.STSOLS.COM
E-MAIL : [email protected]
ISO 9001 Certified Regf. No. 34-39646
KALAPURNA STEEL & ENGINEERING Co.
Engineers & Manufaturer's Representative
R.K. Bldg. No. 3, Office No. 1,
Gr. Floor, 8th khetwadi Lane,
Post Box No. 3726
Mumbai - 400 004, (India)
Tel: 00-91-22-23895056 / 5683 / 0740
Fax: 00-91-22-23820628
E-mail: [email protected]
ELCOME TECHNOLOGIES Pvt. Ltd.
7, Arjun Nagar, Bhisma Pitamah Marg
Kotla Mubarakpur, New Delhi 110003 (India)
Tel: (o) 24652178, 24652787-88, 24636809
Fax: 24652789
E-mail: [email protected]
With Best Complements From
With Best Complements From
ELECTRO CIRCUIT SYSTEMS, HYDERABAD
VENTURA ENGINEERS INDIA Pvt.Ltd., CHENNAI
With Best Complements From
With Best Complements From
With Best Compliments From
HYDRO PNEUMATIC ENGINEERS (HYD) PVT. LTD.,HYDRO PNEUMATIC ENGINEERS (HYD) PVT. LTD.,HYDRO PNEUMATIC ENGINEERS (HYD) PVT. LTD.,HYDRO PNEUMATIC ENGINEERS (HYD) PVT. LTD.,HYDRO PNEUMATIC ENGINEERS (HYD) PVT. LTD.,AN ISO 9001:2000 CERTIFIED COMPANY
MECHANICAL & ELECTRICAL ENGINEERS & CONTRACTORS
1-3-183/40/46, Plot No. 36, Sai Nagar, New Bakaram, Hyderabad - 500 080
Phones: 040-27535123 / 27530224, Fax: 040-27537742,
Email: [email protected]
TURNKEY PROJECTS FOR ALL KINDS OF PIPING SYSTEMS, FACILITY
MANAGEMENT SERVICES AND ANNUAL MAINTENANCE CONTRACTORS
FOR
PRODUCTION OF AEROSPACE COMPONENTS MEETING
HIGH QUALITY STANDARDS AS PER ISO SPECIFICATIONS
AMIT AERO MODELSFlat No-304, Building No.A8, Kunal Icon Pimple Saudagar.
Pune:- 411-027, Ph No:- (020) 27260898, 27201015Email:- [email protected]
..............................................................................................APPROVED MODEL MAKER FOR DRDO & SERVICE GROUPS
Specialised Fields :-
� High-tech working Models of various Systems.
� Missile Models & Training Aids.
� Flying R/C Aero Models & Target Aero Models.
� Engineering Project Models & Display.
� Microprocessor Based Working Models.
8/9th Milestone, G.T. Road, Sahibabad,Ghaziabad - 201 007
Delhi :Tel : 95 - 120 - 2634661 95 - 120 - 2638400 95 - 120 - 2638500
Fax : 95 - 120 - 2634660 91 - 11 - 23010128
Chennai :Res : 044 - 24962174Off : 044 - 24962488
[email protected]@hotmail.com
DASS HITACHI LIMITED
With Best Complements From
J-237/1, MIDC, BHOSARI,PUNE - 411 026 [MS], INDIAPhone : 020 2747 4032 & 3096 3454Fax : 020 2747 9690e-mail: [email protected]
PatangeIndustries Pvt. Ltd.
With Best Complements From
Mashvill Industries Products6-3-1219/1/1/1, Umanagar, Begumpet,
Hyderabad - 500 016, A.P.Tel : 040-3412633, 6625673,
e-mail : [email protected]
With Best Complements From
With Best Complements From
Mechanical & Electrical Engineers & Contractors1-3-183/40/46, Plot No. 36, Sai Nagar, New Bakaram,
Hyderabad - 500 080 Phones : 040-27535123 / 27530224,Fax : 040-27537742, e-mail : [email protected]
HYDRO PNEUMATIC ENGINEERS(HYD) PVT. LTD.,
An ISO 9001 : 2000 Certified Company
Stahl Tecniks Private Ltd.C-2/2449 Vasant Kunj, New Delhi 110 070Tel : 011-26123382 Fax : 011-26136931email : stahl@[email protected]
With Best Complements From
Plus Inc.Concepts & Solutions
Tel : 011-47013744, 23867646e-mail : [email protected]
With Best Complements From
Regd. Office : # 47, 36th Main Road, BTM 1st Stage, Dollar Scheme, Bangalore - 560068Tel. Ph: 080 2668 3860. Fax: 080 2668 39335.Email: [email protected]
Factory : 14/2, Raghuvanahalli, 14th
KM, Kanakapura Road, Bangalore - 560062.Tel. Ph: 080 2842 5477. Fax : 080 2843 5207.Email : [email protected], [email protected]
Offices : USA. Tel: 001 8479690630, Fax: 0018479690631.Email: [email protected]
Avasarala Technologies Ltd.Avasarala Technologies Ltd.Avasarala Technologies Ltd.Avasarala Technologies Ltd.Avasarala Technologies Ltd.
Apart from the standard Fasteners we develop and supply itemsas per customer specifications like AISI 4137, 51B37, 15-5PH,A286, EN24 ESR grade, Titanium, etc. We have our Lab accreditedby A2LA, USA for chemical and mechanical testing. Thus mostof the testing is done in-house with complete lot traceabilityrecords. We have in-house plating facility like Zinc, Cadmium,Dacromet, Delta Tone, HDG, etc.
CALTECH ENGINEERING COMPANY (P) LTD
DESIGNERS AND MANUFACTURERS OF
� Complete set of components for Cold Gas Reaction Control System for missiles.
� Pilot Operated Solenoid valves (Pneumatic as well as Electro - Mechanical Pilot)
� High Pressure Valves - up to 400 BAR
� High Speed Solenoid Valves - On / Off 30 Milli Seconds
� Pressure Regulators - 0 to 400 BAR (up to 25mm Orifice)
� Fill Port Guns
� Vent Port Guns
� Control Valves
� Venturi Meter with Differential Pressure Transducer
� Quick Disconnect Coupling of various sizes and pressure rating - 5 KSC to 250KSC
� 25 Micron High Flow Filters / Strainers
� Hydraulic Proportional Flow COntrol Valves in pressure ranges from 5 KSC to400 KSc for Submarine controls
Factory & Office: 137, Prashanthinagar, IDA, Kukatpally, Hyderabad - 500 072Phone: 040-23075914; Fax: 040-23720019E-mail ID: [email protected]
With best Compliments from
Serving the needs of Sectors of National Importance likeAtomic Energy, Defence, Space, Security, Power, Telecommunications,
Oil/Gas, Steel, Process, Education and E-Governance towards achievingSelf-Reliance
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Offers: Control & Automation, Computers, Communication Systems,Antenna Systems, Strategic Electronics, Telecommunication Products,Encryption Systems, Instrumentation Systems, Integrated SecuritySolutions, Electronic Voting Machines and more.
The only multi- technology company that providesTotal Systems Solutions
Electronics Corporation of India LimitedCorporate Business Development Group
PO ECIL, Hyderabad - 500 062, IndiaE-mail: [email protected] web: www.ecil.co.in
ENERTECH GROUP OF INDUSTRIESENERTECH ENGINEERING PVT. LTD.
PRODUCTS� Nuclear Hardened & NBC protected EMP/
EMI Shielded Mobile Integrated Shelters.
� Mobile Communication EMI ShieldedShelters.
� Intergraded Hybrid Wind/Solar System forAlternative Power Generation.
� NBC Protection Ventilation Systems in jointventure with SP Defense, France.
� NBC Collective and Survival ProtectionShelter in joint venture with SP Defense,France.
� Fully Ruggedized, MIL Grade Air Conditioner.
� Roof–Top/Ground TelecommunicationShelters.
� DG Shelter cum Acoustic Enclosures.
� Outriggers, Screw Jacks and ElectricalDistribution Systems.
� Integrated Shelter with Tower–SHELT(OW)ER
PRODUCTS� Mobile VSAT Antenna Systems for Disaster
Management, OB & DSNG applications
� VSAT Antennas
� Earth Station Antenna Systems
� Antenna Tracking Systems like
• Antenna Control Units
• Motor Control Units
• Beacon Tracking Receivers
• Down Converters
• Auto Up-Link Power Controllers
• Low Cost Antenna Controllers
OUR SERVICES� Installation, Integration & Commissioning of Antenna
Systems
� NOCC Testing
� Electro Mechanical Integration of CommunicationSystems for Static & Mobile applications
AMC Support for all kinds of Antenna Systems
