revolutionary entry, descent, and deployment concept for...

Revolutionary Entry, Descent, and Deployment Concept

for the Mars Balloon Scout Mission

(Searching for Organics with a Long Duration Balloon)

University of Michigan Mars Balloon Scout Mission Team

Christopher Daywalt

Nathan Falstad

Danielle Layher

Tian Lian

Shintaro Taniguchi

Ryan Zhao

Faculty Advisor Dr. Nilton Renno

RASC-AL Forum 2006

May 21-25, 2006

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Abstract NASA has established the future of space exploration by launching projects that will ultimately lead to human missions to the Moon and eventually to Mars. As a result, the Martian environment must be understood to minimize the risk of placing humans on its surface. Although Mars rovers and orbiting satellites are able to gather a significant amount of planetary data, neither form of exploration has provided adequate data for accessing the full risks to human exploration, nor have they provided a good balance between mobility and precise in-situ measurements. However, these requirements can be fulfilled with a super-pressure balloon system. This idea has driven the University of Michigan team to launch the Mars Balloon Scout (MBS) mission. The objectives of the Mars Balloon Scout mission includes the detection of organic compounds and toxic elements in the atmosphere, measurement of ambient weather patterns and detailed exploration of the local Mars geology. Thus, we have designed a balloon and gondola system to carry the scientific payload along with its associated power and communication equipment. In order to support the proposed payload, we will need a thirty meter diameter spherical super-pressure gas cell. The gas cell is composed of a high strength Kevlar and Mylar composite material previously conceived by JPL. With this design, the MBS mission can successfully meet its objectives while surviving the harsh environment of the Mars atmosphere. Our confidence in the super-pressure balloon system results from its simple technology, its ability to survey both the atmosphere and the surface, and its long mission life span. The riskiest part of a Mars balloon mission is the entry, descent, and deployment (EDD) phase. Typical EDD phases of previous missions lasted approximately six minutes from entry to touchdown. In the Mars Balloon Scout, the EDD phase is the time period ranging from the spacecraft entry on the Martian atmosphere to the full inflation of the balloon. In order to increase the balloon inflation time, we propose to replace the subsonic parachute by a revolutionary drogue envelope. The drogue envelope not only serves as a subsonic parachute but also creates a protective “shell” around the superpressure balloon as it inflates. The successful implementation of this design will allow for a low-risk mission that capable of advancing NASA’s goal of sending humans to Mars. 1 Experimental Objectives and Obstacles Entry, descent, and deployment present a unique systems engineering challenge. Many aspects of EDD are poorly understood due to the hostile environment and short time in which it occurs, in addition to its inherently complex physics. The entry, descent, and landing (EDL) of a Mars mission is often referred to as the "six minutes of terror" and the EDD phase of the MBS Mission presents an even larger challenge. Atmospheric entry dissipates 99% of the kinetic energy of the spacecraft entering the atmosphere, slowing it from 5400 m/s to about 430 m/s. After atmospheric entry, the remaining kinetic energy must be dissipated in less than six minutes in order to slow the spacecraft from 430 m/s to about 10 m/s and allow full inflation of the balloon before impact. A balloon mission has not yet been selected for Mars, mainly due to failures of most previous deployment tests. These failures have included tangling of tethers, lack of full inflation of the balloon, rupture of the balloon, lack of stability after inflation, and impact of the balloon into the

Mars Balloon Scout Mission Revolutionary Entry, Descent, and Deployment Concept

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ground before inflation. All previous tests used a supersonic parachute during entry, followed by the use of a subsonic parachute during descent and balloon deployment. Because previous failures have all been due to deployment problems, we believe that the redesign of the subsonic parachute is necessary to solve this problem and decrease the risks to EDD. We have developed a revolutionary drogue envelope concept to be used in lieu of a subsonic parachute. The drogue envelope can be thought of as a hybrid between a subsonic parachute and a zero-pressure natural shape balloon. 2 Design of the Entry, Descent, and Deployment System 2.1 Aeroshell The aeroshell consists of two parts, the heat shield and the backshell. The aeroshell of the MBS Mission is based on the Mars Exploration Rover (MER), Pathfinder, and Viking systems. The aeroshell is the first “brake” for the spacecraft upon Mars atmospheric entry. During entry, the heat shield provides protection and dissipates over 99% of the entry energy through aerothermodynamic heating and drag. Peak temperatures reach 1447 °C while slowing the system from 5400 m/s to 430 m/s. The proposed heat shield is made of an aluminum honeycomb structure inserted between graphite-epoxy sheets. The outside of the aeroshell is coated with a layer of phenolic honeycomb. The phenolic honeycomb is then filled with an ablator: a blend of wood, binder, and tiny silica glass spheres. The backshell is made of similar materials, but has a much thinner layer of ablater than the heat shield. The backshell is covered with a thin layer of aluminized Mylar to protect it from the low temperatures encountered in deep space. The packing of the MBS Mission systems is shown in Figure 2-1. In addition to the MBS Mission systems, electronics and batteries that fire various EDD devices such as separation nuts and the parachute mortar are stored in the aeroshell. Finally, a Litton LN-200 Inertial Measurement Unit that monitors and reports the orientation of the heat shield throughout the entire EDD phase is stored in the aeroshell.

Figure 2-1 – Aeroshell Packing Scheme

2.2 Supersonic Parachute The supersonic disk-gap-band parachute is similar to that used in the MER Missions, and is a scaled version of the Pathfinder parachute. Our parachute is a scaled version of these parachutes and will be based on the loads calculated by NASA’s Mars parachute development system. This parachute establishes a stable vertical trajectory for deployment while decelerating the vehicle from supersonic flight to about 200 m/s through aerodynamic drag. The supersonic parachute deploys from a mortar that is interfaced with the backshell structure. The mortar is able to accelerate the parachute to beyond the recirculating wake for controlled and reliable inflation. The disk-gap-band parachute is the only parachute that is qualified for supersonic planetary entry deployment. The disk-gap-band provides more stability than a traditional parachute at the higher velocities and loads encountered during entry and descent. The parachute itself is made of polyester and nylon, which are durable and lightweight fabrics. A triple bridle made of Kevlar constitutes the tethers which are connected to the backshell. When backshell jettisons, the


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supersonic disk-gap-band parachute provides the lift to carry the backshell away from the entry vehicle. 2.3 Drogue Envelope The innovative drogue envelope is composed of 24 half-gores made of a polyethylene film with silicon coating. They are sewn together to form the same natural-shape of a hot-air balloon. The

drogue envelope deploys at an altitude of about 10 km and act as a subsonic parachute by taking in ram-air through scoops on each of its gores. The drogue will therefore create both separation drag and ram drag as it provides a protective envelope for the gas cell during inflation. The design of the drogue envelope is illustrated in Figure 22. The shape of the envelope was determined using a toolkit developed by Cameron Balloons. The toolkit takes as input basic information about the envelope, such as desired volume and number of gores, and then uses the J.H. Smalley natural shape balloon equations to output points along the curvature of one half-gore. Smalley’s set of equations defining the natural-shape is based on his studies of the equilibrium balance of forces acting on the balloon film. This study was performed in the 1930s and is the current accepted method for determining the ideal shape of hot-air balloons.

-

olyethylene by s

late the

er the

At full inflation, the drogue balloon envelope has a

diameter of 32 m at the equator (the largest envelope diameter). To create the ram-air scoops, the upper gores are designed with a diameter of 35.84 m, 12% larger than the bottom gores' diameter of 35 m. Upon inflation of the gas cell, the drogue envelope will be jettisoned with the inflation equipment.

Figure 2-2 – Drogue Envelope Diagrams

2.4 Gas Cell The gas cell is a spherical superpressure balloon, 30 m in diameter, made of a composite of Mylar and pwith Kevlar scrims. This composite film was developedJPL and is illustrated in Figure 2-3. The gas cell inflatewithin the protected environment of the drogue envelope. Hydrogen tanks located in the gondola are used to infgas cell. Full inflation could take nearly a minute. Aftjettison of the drogue envelope and inflation equipment, gas cell will float at altitudes between 5and 15 km. The gas cell has about 56 kg with 49 kg of fabric material and7 kg of hydrogen lifting gas.

Figure 2-3 – Composite Film Material


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2.5 Gondola Instrumentation will be contained within a thin shell made of composite material and surrounded by solar panels. The solar panels provide all power necessary to operate the instrumentation, computers, and communications equipment. Also, the solar panels charge the batteries throughout the day in preparation for nighttime operations. Altogether, the gondola and its payload weigh about 20 kg. 3 Entry, Descent, and Deployment Operational Sequence The interplanetary trajectory was chosen to minimize delta V and time. Thus, a Type-I ballistic trajectory was chosen in lieu of a free-return trajectory. An Atlas V rocket will propel the MBS Mission to its interplanetary trajectory. The first and second stages of launch will place the spacecraft into LEO. Following a short coast period, third-stage burnout will inject the craft into interplanetary cruise via Hohmann transfer. Figure 3-1 below provides the overall view of the operational sequence for EDD once the MBS Mission reaches Mars.

Figure 3-1 – Operational Sequence for EDD of MBS Mission

1) A direct ballistic entry from hyperbolic approach is taken. At entry minus-15 min, the cruise stage is separated from the aeroshell as the aeroshell prepares for entry. 2) Atmospheric entry begins at about 125 km above the Martian surface with a top entry speed of 5400 m/s. 3) The supersonic parachute deploys at about 240 s after entry and at speeds near 430 m/s. 4) The aeroshell continues to slow to around 200 m/s and develop a stable mission deployment trajectory. The supersonic disk-gap-band parachute and backshell are jettisoned. The backshell


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pull out the folded drogue envelope and gas cell from the aeroshell. 5) Inflation of the drogue

envelope occurs shortly after it deploys. The drogue provides significant amounts of drag and

continues to slow the system down. 6) As the drogue envelope is deployed, the gas cell is

stretched vertically within the envelope. The inflation system engages immediately and the gas

cell inflation begins. The lift generated by the inflating gas cell provides additional time for

inflation. 7) When inflation is complete, the drogue envelope cuts away from the aeroshell heat

shield and rip stitches within the gores allow it to float away from the gas cell. The heat shield

and inflation system are jettisoned. 8) Finally, less then 6 minutes after entry, the gas cell and

gondola float to operation altitude and the MBS Mission begins its operational phase.

4 Prototyping 4.1 Overview Prototyping was done in two phases. An Į-prototype was

designed to provide qualitative information on the

feasibility and performance of the drogue deployment

system and a ȕ-prototype was designed to provide

quantitative tests of the entire inflation system at high

altitudes. A flow diagram of the prototyping plan is s

in Figure 4-1.

Į- Prototyping

hown

4.2 Į-Prototype Test-Phase 4.2.1 Criteria for Success The main focus of the initial deployment test was to

qualitatively assess the reliability of the drogue envelope

system. This was done using a 2 feet diameter scaled drogue envelope. We have established

criteria for success for the two main phases of deployment: inflation, and post-inflation.

These are outlined in Table 4-1.

4.2.2 Scaling Proper scaling is an important consideration in the development of prototypes capable of

reproducing the behavior of full-scale systems.

In the case of the drogue envelope, Table 4-2 presents the important physical parameters that

must be matched for the deployment on Earth to behave similarly to that on Mars.

Deployment Phase Criteria for Success Inflation How well do the gores take in the incoming air?

Is inflation even?

How long does it take?

Post-Inflation How much does the drogue oscillate or respond to

changes in airflow?

Table 4-1 – Prototype Testing Criteria

Beta Prototyping

(Entire Inflation System)

Free Fall Testing

With Cameron Balloons

Beta Prototyping

(Re-Design Drogue)

Wind Tunnel Testing

(UM - 5x7)

Qualitative Testing

Wind Tunnel Testing

(UM - 5x7)

Success Fail

Figure 4-1 – Prototyping Plan

Mars Balloon Scout Mission

Revolutionary Entry, Descent, and Deployment Concept 5

atmospheric pressure > @ 2smkg

patm � diameter of drogue > @ mdd

atmospheric density > @ 3mkg

atm U length of drogue > @ mld

kinematic viscosity > @s

m2

X thickness of drogue > @ mt

gravitational acceleration > @ 2sm

g diameter of spill hole > @ mdh

mean-free path > @ m O length of tether > @ mlt

free-stream velocity > @sm

U f area of gore opening > @ 2mAg

Table 4-2 – Important Physical Parameters Table 4-2 shows that there are 12 important physical parameters containing 3 primary quantities. Thus, it follows from the Buckingham S–theorem that 9 non-dimensional numbers must be matched for the prototype to properly simulate the behavior of the full-scale system. The similarity conditions can be separated into the three categories described below.

Geometric Similarity The following geometric ratios, as well as the Knudsen number, must be matched between our drogue prototype and the full-scale model

h

d

dd

, dd

h , lh

, g

d

Ad ,

ddKn

O

Dynamical Similarity The important aerodynamic considerations are the two ratios of inertial forces to viscous forces and inertial forces to gravitational forces (Reynolds and Froude Number), as well as pressure drag

Xf�

UddRe ,

ddgU

Fr�

f2

, 2f�

U

pD

atm

atmp U

Because of the blunt shape and high velocity of the body though, Reynold's effects become negligible. In matching the Froude Number, we use

27.3sm

gmars mdmarsd 30

sm

Umars

85 f 28.9sm

gearth mdearthd 61.0

This gives sm

Uearth

73.19 f for proper dynamical behavior.

In matching pressure drag, we use


6

2300mN

pmarsatm 30062.0

mkg

marsatm U

sm

Umars

85 f 251001.1

mN

pearthatm 323.1

mkg

earthatm U .

This gives sm

Uearth

73.110 f

Due to the high testing velocity required, we were unable to match pressure drag during the D-prototype phase. The Froude number however, was well within our range of testing velocities.

Deployment Similarity In order to understand the deployment of the drogue on Mars, we need to properly scale its inflation time. We do this first by matching the time of deployment, , with a non-dimensional

parameter,

dt

fUdd , to get

f

Ud

t

d

dW .

3

234

nAU

d

tgatm

datm

d ��

¸¹·¨

©§�

fU

SU

nAd

g

d

��

6

2SW

This shows that to match the deployment time, assuming we specify a scaled diameter and keep the number of gores the same as the full-scale system, we need only to correctly choose the size of the gore opening. In our case, we use

mdmarsd 30 22mA

marsg 12 earthmars nn

This gives . We allowed for this in the design of each half-gore by correctly choosing the right difference in height between the top and bottom gores.

241027.8 mAearthg

�

4.2.3 Design and Fabrication Drogue Gores The drogue envelope is composed of 24 top and bottom half gores, sewn with minimal clearance into a natural-shape envelope. The line of curvature of each gore was determined using Smalley's natural-shape equations applied to our 2 ft. scale model. With the help of Cameron Balloons US, we were able to cut the individual gores using a CAD compatible fabric cutting machine. The parameters used in the fabrication of the prototype are displayed in Figure 4-2.


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Bottom Gore

Top Gore

Scoop Entrance

Gore Overlap

Figure 4-2 – Gore Design Parmeters and Representation

Aeroshell Design and Fabrication Since the bottom half of the aeroshell is still part of the system during drogue deployment, we fabricated a similarly scaled model of the aeroshell to accurately model the flow around it during drogue inflation. Currently, we propose to use the MER aeroshell in our mission; however, volume constraints may require the use of the larger MSL aeroshell. The Atlas V has a fairing that can fit either of these two aeroshells. Using stereolithography, we fabricated both models, as shown in Figure 4-3.

Figure 4-3 – Scaled Aeroshells for Į-Prototype (MER right, MSL left)

4.2.4 Initial Test As show in section 4.2.2, high flow velocities were needed to test the drogue inflation. This was accomplished by constructing a test structure in the back of a pickup truck. The Į-prototype was mounted on a beam that extended above the truck high enough to ensure free stream flow. The drogue was then released by hand when the truck achieved the desired velocity. A total of seven tests were conducted at speeds ranging from 25 mph to 65 mph. Six of the seven tests resulted in successful inflation. During the first test the drogue ties became wrapped around the envelope before deployment and resulted in inflation failure. The scoops successfully allowed the air to rapidly enter the drogue envelope. The drogue inflated almost instantaneously at each test. Once inflated, the drogue envelope maintained full inflation; however, it oscillated after inflation. At high speeds the drogue envelope oscillated erratically. These oscillations were much less severe at lower velocities.


8

4.2.5 Design Modifications and Secondary Test In order to check the stability problem, secondary tests were conducted at the University of Michigan High Speed Wind Tunnel, where we could be sure we were testing under steady flow. The wind tunnel tests confirmed the stability problem. In an attempt to solve the problem, we modified the drogue envelop by adding a spill-hole on its top. Two configurations were tested: spill-hole with diameters of 1.5 and 2 inches. However, the stability problems were not resolved by this method, thus further studies must be conducted to mitigate the oscillations.

versity of Michigan

Į-prototype drogue envelope, we are ȕ-prototype is to test the

ent of the drogue envelope from the ȕ-prototype will consist of a 2 m.

htly smaller gas cell. An inflation flate a superpressure gas cell while the balloon

lates the drogue envelope will be

t of a gas storage tank, two regulators, two ȕ-prototype, carbon

dioxide (CO em reaches r the deployment of the

u olenoid valve on the low-pressure feed line. wn.

the

If the

ol

feed line. The remain cell in a little over 5 s.

Free Stream Velocity Drogue Envelope Į-prototype

Sting Balance

Figure 4-4 – Wind Tunnel Test at Uni

4.3 ȕ-Prototype Test-Phase Following the successful inflation of the proof-of-concept currently developing a larger scale ȕ-prototype. The purpose of the

inflation system and the detachmballoon system at high altitudes. The diameter drogue envelope with a sligsystem will be used to insystem falls. Once the gas cell infjettisoned. The inflation system will consissolenoid valves, and tubing. For the purposes of the

2) gas will be used to fill the gas cell. When the systthe desired velocity, a timing circuit will triggedrog e envelope and open the sThe drogue envelope will inflate quickly, slowing the falling system doThe gas cell will inflate by means of the low-pressure feed line for about 5s. This will allow the gas cell material to move away from the inlet ofhigh-pressure feed line before the high-pressure feed line is opened. gas cell material is too close to the high-pressure feed line when it is pened, the force of the entering gas could tear the gas cell. After filling the

ow- pressure feed line by 5 s, the timer switch will open the high-pressureing gas in the gas storage tank should fill the gas

Figure 4-5 – Beta Design gas cell through the


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Then the drogue envelope will be cut away and rise over the gas cell. Because the gas cell will

)

he feasibility of our EDD concept using a drogue envelope will be developed and evaluated in

s

prove

results from this stage

ill be used to evaluate the feasibility of the design. The tests conducted during this stage

ic deployment, static inflation, and wind tunnel tests. The goal

e that the fabric will

aintain functionality after the 8-month interplanetary cruise. This stage will determine the

system (TRL 6).

t

only be filled with CO2, it will continue to fall, but the main focus of the ȕ-Prototype is to test

the inflation of the gas cell and the detachment of the drogue envelope.

5 Drogue and MBS Mission Development Plan (Years 2006 – 2011 and BeyondThe new drogue envelope concept must undergo extensive tests to achieve the Technical

Readiness Level (TRL) required for a Mars mission. Based on previous NASA efforts to

develop a Mars Balloon, the tests required for development include: wind tunnel tests, inflation

tests, free drop tests, static pull tests, static deployment tests, dynamic deployment tests, vacuum

chamber tests, storage tests, and tests for deployment induced defects. The feasibility of the

ill be analyzed and demonstrated through a systems engineering approach (Phase A –

Phase D). Please use Figure 6-1 as a reference for schedule estimates.

Phase A (Feasibility Analysis)

design w

T

thi phase. Preliminary tests will be done to explore this configuration option on a small scale in

the laboratory, wind tunnel, vacuum chamber, and in free drops. The goal for Phase A is to

develop the basic principles, formulate the technology concepts and their applications, and

the concepts through analytical and experimental results (TRL 1 – TRL 3).

Phase B (Feasibility Demonstration) Stage 1 In this stage, ground and flight tests of the sub-scale and full-scale drogue and parachute system

will be conducted in hangars, vacuum chambers, and wind tunnels. The

w

include static deployment, dynam

of Stage 1 is to validate the concept in the laboratory and field environment (TRL 4 – TRL 5).

Stage 2 In this stage, a full-scale system will be tested by means of pull tests and free drop test at

tropospheric altitudes. Furthermore, storage tests will be conducted to ensur

m

feasibility of the design at the full-scale

Phase C/D (Flight System Development/Production) In this phase, the feasibility of the design will be studied and validated at stratospheric altitudes

using a full-scale system. This phase is the most critical and challenging of the developmen

program. The goal of this phase is to demonstrate the performance of the full-scale prototype in

a space-like environment and to flight-qualify the proposed system (TRL 7 – 8).

Mars Balloon Scout Mission

Revolutionary Entry, Descent, and Deployment Concept 10

Table 5-1 – Drogue and MBS Development and Validation Plan

6 MBS Mission Overall Cost Analysis With a $400 million cost cap, the Mars Balloon Scout Mission concept falls into the Medium Mission category. The cost model for the MBS Mission was developed using statistics of

issions. 3 will be kept as serves; this is a NASA standard. The reserves will decrease as the mission progresses. The llo onable estimate of the mission budget breakdown.

previous mre

0% of the total mission cost (approximately $120 million)

fo wing cost model in Table 7-1 gives a reas

Mars Balloon Scout Mission Millions of Dollars Percent Phase A $2.0 0.5% Phase B $4.0 1.0% Phase C/D Total $100.0 25.0% Project management $12.0 3.0%

eam $r Mission Operation $

ic Outreach V 501

$

opment Cost $ 10

Project System Engineering ission Assurance

$14.0 $12.0

3.5 %3.0%M

Science T 16.0 4.0% Prepare fo 12.0 3.0% Education and Publ $8.0

$2.0%

2Launch Vehicle Atlas 100.0 5.0% Reserves (NASA Standard) 120.0 30.0%

evel

Total Mission D 400.0 0.0% Table 6-1 – MBS Mission Cost Ta

ble


11

7 Education and Public Outreach (EPO) The MBS Mission y o ion and Public

utreach activities and have dev MBS team has made gnificant contributions to further the interest of students of various age groups in space science nd engineering.

g in ‘Real’ NASA EPO Activities)

nd

ion. Team members participated of EPO activities were at Dicken and Martin uther King Elementary Schools, in Ann Arbor, the Hands On Science Museum in Ann Arbor

4th grade udents during their class time which included a PowerPoint presentation and a ‘Mars Match

s

Match Game at Dicken Elementary School

l tests to middle school students during their an. The team interacted with these students

answ e

tate of the art facility at University of ichigan.

team members have been participating of aeloped plans for future EPO. The

variet f EducatOsia 7.1 Outreach to Elementary Schools (Participatin The University of Michigan Mars Balloon Team participated in a real NASA Education aPublic Outreach activities. Our team was trained on NASA’s EPO activities by the 2007 Phoenix Mars missLand the Detroit Science Museum. We participated of various activities with 3rd and stGame’, in which students match images of the Martian surface with that of similar features onEarth. The opportunity of our team to participate in a real NASA mission EPO activity wahighly beneficial as allowed us to be trained by an EPO specialist. Our team acquired knowledge about the NASA efforts toward education in science and engineering.

Figure 7-1 – Mars Balloon Team Participating in Mars

7.2 Outreach Efforts to Local Middle School Students The mars balloon team demonstrated wind tunnescience class field trip to University of Michig

ered many questions regardingp rototype design. The team also answered general sciencand engineering questions. The activities were successful because the young students were exposed to a real engineering problem and observed a sM


12

dle School Students. Introduction to Wind Tunnel tration in the wind tunnel.

ber 2005 and April 2006. The outreach al PowerPoint presentation. These

cating our ideas to the college community. Many cal community members were interested in our

entary video to advertise our project an inspire Modern IT technology allow the public to easily

engineering. Furthermore, we conducted an interested in our project and the overall Mars

A

r revolutionary EDD concept. ployment concept.

ssists highly motivated students who wish to pursue a career in space systems engineering by ichigan. The society is also interested in

troducing the concept of systems engineering to the general public. The society representatives il s e

stud t

Figure 7-2 – Wind Tunnel Test Demonstration to Midfollowed by prototype demons

7.3 Outreach Efforts to High School and College Community We presented our design at the Design Expo in Decemwas done in Poster Presentation format as well as an informposter sessions were very effective in communistudents, staff, faculty members, as well as loproject. We also developed a website and documfuture generations of scientists and engineers. access to our project and learn about science and EPO survey at the Design Expo to assess the public Scout Balloon mission.

total of 26 people participated in the EPO survey.

x 96% of the survey participants expressed interest in oux This was a 24% increase from the regular parachute dex 67% of the participants were interested in the space missions using balloons. x 88% expressed interest in NASA space missions. x University of Michigan

o 65% of the students have heard about Systems Engineering. o 40% of students have heard the term ‘Education and Public Outreach’.

Furthermore, the Mars Balloon Team founded the Michigan Engineering Society of Space Mission Analysis and Design (MESSMAD), a student organization to support systems engineering education and to improve student awareness of NASA’s EPO efforts. The society aconnecting them with professors at the University of Minw l al o visit students in elementary, middle, and high school to present projects and expose th

en s to space sciences and engineering through various EPO activities.


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Figure 7-3 – Poster Presentation to General Public

7.4 Outreach Efforts to Local Community One of the strength of our EPO program is that we have a very close relationship with our local community in Ann Arbor, Michigan. We have a strong partnership and me

pany, Cameron Balloons US. All of parts for our prwere purchased within our community, supporting small businesses around the University of

ntorship program with a local balloon com ototype in this phase

Michigan.

Figure 7-4 – Mars Balloon Team Collaborated with Local Balloon Company through Mentorship Program

7.5 Outreach Efforts to International Balloon Community The Mars Balloon Team will also display posters at the Anderson – Abruzzo Albuquerque International Balloon Museum during their 1st Annual Balloon Museum Air, Wind & Wheels Fair. A team member will also be available at this event to answer questions in the display. Presentation of the Mars Balloon concept to the museum docents will be also delivered by our team member.


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References D. Crisp. In-Situ Environmental Measurements for Mars Long Lived Network, February 16, 2003 D. Crisp. Netlander ATMIS Wind and Temperature Requirements; April 2003. Steven A. Benner, Keven G. Devine, Lidia N. Matveeva, and David H. Powell. The Missing Organic Molecules on Mars; December 13, 1999 D.M. Murphy, D.S. Thomson, M.J. Mahoney. In-Situ Measurements of Organics, Meteorite Material, Mercury, and the Elements in Aerosols at 5 to 19 Kilometers; November 27 1998

Steve Smith, Jr., Joel M. Simpson, Steven M. Raque, Magdi A. Said, Henry M. Cathey. AIAA Document A97-31332. “The Mars 2001 Balloon Design.” 1997. http://www.grc.nasa.gov/WWW/K-12/airplane/atmosmrm.html Kerry T. Nock, J. Balaram & Matthew K Heun, I. Steve Smith, Terry Gamber. AIAA Document A97-31331. “Mars 2001 Aerobot/Balloon System Overview.” 1997. Salvador M. Aceves, Development and Demonstration of Insulated Pressure Vessels for Vehicular Hydrogen Storage http://www.ovonic-hydrogen.com Steve Matolvsek, Kim Leschly, Bob Geshman, and John Rener. Mars Micromissions; August 23-26, 1999 Dr. Alexey Pankine. Sailing the Planets: Science with Directed Aerial Robot Explorers (DARE) Wiley J. Larson and James R. Wertz. Space Mission Analysis and Design; 2005 V.V Kerzhanovich, etal. Cospar Balloon Technology Conference 2002. "Breakthrough in Mars Balloon Technology." 2002.

V.V. Kerzhanovich, etal. AIAA Balloon Technology Conference 1999. "Mars Aerobot Validation Program" 1999. Allen Witkowsky. AIAA Document A99-1701. "Mars Pathfinder Parachute System Performence" 1999. Elie Allouis, Alex Ellery, Chris Welch. "Parachutes and Inflatable Structures: Parametric Comparison of EDL Systems for the Proposed Vanguard Mars Mission." J.R. Cruz , M. Kand , and A. Witkowski. AIAA

Schofield and Michael E. Lisano. AIAA the

Allen Witkowski. AIAA Document 99-1701. "Mars Pathfinder Parachute System Performance" 1999. J.R. Cruz, R.E. Mineck, D.F. Keller, and M.V. Bobskill. AIAA Document 2003-2129. "Wind-Tunnel Testing of Various Disc-Gap-Band Parachutes" 2003. The Mars Society Germany. "The Mars Balloon Probe Final Report on Preliminary Flight System Analysis" 2002. David L. Keese. AIAA Document 78-314 "Zero-Pressure Balloon Design" 1978

Sal

ushil K. Atreya, Ah-San Wong, Nilton O. Renno, et Document 2003-2131 "Operning Loads Analysis for Various Disc-Gap-Band Parachutes" 2003.

. Oxidant Enhancement in Martian Dust Devils and Storms: Implication for Life and Habitability

John T.

An Analysis of the Precursor Measurements of Mars Needed to Reduce the Risk of the First Human Missions to Mars; June 2, 2005 Mars Balloon Sizer Tool

Document 2003-2126. "Flight Reconstructin ofMars Pathfinder Disc-Gap-Band Parachute Drag Coefficient" 2003. MER Parachute Decelerator System, PDR. 2001.

is


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