SCIENCE OF AERONAUTICSAND

ENGINEERING EDUCATIONAL TECHNICS

Journey of MangalyaanIndia's First (MOM) Mars Orbiter Mission

CH. PURUSHOTHAMAERONAUTICAL ENGG.

DEPARTMENT OF AERONAUTICAL ENGINEERING

CHAPTERS1. MARS INTRODUCTION

1.1 ATMOSPHERE 1.2 TEMPERATURE AND PRESSURE

2. MARS SPECIFICATION2.1 EARTH/MARS COMPARISON

2.2 INSIDE PLANET MARS

3. WHY THIS JOURNEY ?4. MISSION PLAN 5. MISSION OBJECTIVES

5.1 TECHNOLOGICAL OBJECTIVES5.2 SCIENTIFIC OBJECTIVES5.3 THE DEUTERIUM/HYDROGEN (D/H) RATIO 

6. POLAR SATELLITE LAUNCH VEHICLE 6.1 PSLV-XL (Operational)6.2 PSLV C256.3 TECHNICAL SPECIFICATIONS6.4 DIFFERENT STAGES OF PSLV

7. SPACECRAFT 8. PAYLOADS

8.1 LYMAN ALPHA PHOTOMETER (LAP)8.2 METHANE SENSER FOR MARS (MSM)8.3 MARS EXOSPHERIC NEUTRAL

COMPOSITIONANALYSER (MENCA)8.4 THERMAL INFRARED IMAGING SPECTROMETER

(TIS)8.5 MARS COLOR CAMERA (MCC)

9. MISSION PHASES or TRAJECTORY9.1 GEOCENTRIC PHASES9.2 HELIOCENTRIC PHASES9.3 MARTIAN PHASES

9(a) EARTH PARKING ORBIT

10. TRACKING AND COMMAND11. COST COMPARE WITH OTHERE MISSION12. 14 BRAINS BEHIND THE SUCCESS13. CONALUSION14. REFERENCE

ABSTRACT

India made history by becoming the first country in the world to enter the Martian orbit in its maiden attempt. The Indian Space Research Organisation (ISRO) successfully inserted the Mars Orbiter Mission (MOM) into mars orbit. MOM is the first interplanetary mission of India launched by Indian Polar Satellite Launch Vehicle (PSLV-XL), it is the fifth in world travel journey toward Mars or Red Planet. Interplanetary missions are susceptible to gravitational and non-gravitational perturbing forces at every trajectory phase. These forces are mainly due to planetary and solar-forcing-induced perturbations during geocentric, heliocentric and Martian trajectories, and before orbit insertion. Mission Goal and Objectives is to develop the technologies required for design, planning, management and operations of an interplanetary mission.

The spacecraft carries five science payloads, namely: Methane Sensor for Mars (MSM), Mars Colour Camera (MCC), Lyman Alpha Photometer (LAP), Mars Exospheric Neutral Composition Analyzer (MENCA), TIR Imaging Spectrometer (TIS).

The knowledge is important for mission planning, design, implementation and situational awareness. 14 brains behind Mangalyaan success. This paper will present the details of the why this journey? Study the Martian atmosphere, instruments, observation plan, and expected science.

1. Mars Introduction

Mars is the fourth planet from the Sun and is commonly referred to as the Red Planet. The rocks, soil and sky have a red or pink hue. The distinct red color was observed by stargazers throughout history. It was given its name by the Romans in honor of their god of war. Other civilizations have had similar names. The ancient Egyptians named the planet Her Descher meaning the red one.

Before space exploration, Mars was considered the best candidate for harboring extraterrestrial life. Astronomers thought they saw straight lines crisscrossing its surface. This led to the popular belief that irrigation canals on the planet had been constructed by intelligent beings. In 1938, when Orson Welles broadcasted a radio drama based on the science fiction classic War of the Worlds by H.G. Wells, enough people believed in the tale of invading Martians to cause a near panic.

Fig 1: Solar system

Another reason for scientists to expect life on Mars had to do with the apparent seasonal color changes on the planet's surface. This phenomenon led to speculation that conditions might support a bloom of Martian vegetation during the warmer months and cause plant life to become dormant during colder periods.

In July of 1965, Mariner 4, transmitted 22 close-up pictures of Mars. All that was revealed was a surface containing many craters and naturally occurring channels but no evidence of artificial canals or flowing water. Finally, in July and September 1976, Viking Landers 1 and 2 touched down on the surface of Mars. The three biology experiments aboard the landers discovered unexpected and enigmatic chemical activity in the Martian soil, but provided no clear evidence for the presence of living microorganisms in the soil near the landing sites. According to mission biologists, Mars is self-sterilizing. They believe the combination of solar ultraviolet radiation that saturates the surface, the extreme dryness of the soil and the

oxidizing nature of the soil chemistry prevent the formation of living organisms in the Martian soil. The question of life on Mars at some time in the distant past remains open.

Other instruments found no sign of organic chemistry at either landing site, but they did provide a precise and definitive analysis of the composition of the Martian atmosphere and found previously undetected trace elements.

1.1Atmosphere

The atmosphere of Mars is quite different from that of Earth. It is composed primarily of carbon dioxide with small amounts of other gases. The six most common components of the atmosphere are:

Carbon Dioxide (CO2): 95.32% Nitrogen (N2): 2.7% Argon (Ar): 1.6% Oxygen (O2): 0.13% Water (H2O): 0.03% Neon (Ne): 0.00025 %

Martian air contains only about 1/1,000 as much water as our air, but even this small amount can condense out, forming clouds that ride high in the atmosphere or swirl around the slopes of towering volcanoes. Local patches of early morning fog can form in valleys. At the Viking Lander 2 site, a thin layer of water frost covered the ground each winter.

There is evidence that in the past a denser martian atmosphere may have allowed water to flow on the planet. Physical features closely resembling shorelines, gorges, riverbeds and islands suggest that great rivers once marked the planet.

1.2 Temperature and Pressure

The average recorded temperature on Mars is -63° C (-81° F) with a maximum temperature of 20° C (68° F) and a minimum of -140° C (-220° F).

Barometric pressure varies at each landing site on a semiannual basis. Carbon dioxide, the major constituent of the atmosphere, freezes out to form an immense polar cap, alternately at each pole. The carbon dioxide forms a great cover of snow and then evaporates again with the coming of spring in each hemisphere. When the southern cap was largest, the mean daily pressure observed by Viking Lander 1 was as low as 6.8 millibars; at other times of the year it was as high as 9.0 millibars. The pressures at the Viking Lander 2 site were 7.3 and 10.8 millibars. In comparison, the average pressure of the Earth is 1000 millibars.

2. Mars Specification:• Mars is the fourth planet from the sun.• Mars is the seventh largest planet in our solar system.• Mars is referred to as the Red Planet, due to its red soil made up of iron oxide, more

commonly known as rust.• Mars is named after the Roman god of war.• The equatorial Diameter of Mars is 6,805 km.• The polar diameter of Mars is 6,755 km.• The Diameter of Mars is 6,794 km• Martian day = 24 hours 34 minutes and 22 seconds.• Martian year = 687 Earth days.• The mass of Mars is 641,850,000,000,000,000,000,000 kg.• Surface temperature on Mars can range from the maximum of 310 K to a minimum

of 150 K.• Atmospheric components on Mars consists of 95.32% carbon dioxide, 2.7%

nitrogen, 1.6% argon, 0.13% oxygen.• Average Surface Temperature:218K (-53º C)• Average Distance from Sun:2.279 x 108 km• Average Density:3934 kg/m3 • Moons of Mars = 2

Phobos – Diameter 22 km, orbit 5981 km from the surface of Mars.Deimos - Diameter 12 km, orbit 20,062 km from the surface of Mars.

• Mars atmospheric pressure at surface = 6.35 mbar; < 100th Earth’s atmosphericpressure

Fig 2: Moons of Mars

Mars StatisticsMass (kg) 6.421e+23Mass (Earth = 1) 1.0745e-01Equatorial radius (km) 3,397.2Equatorial radius (Earth = 1) 5.3264e-01Mean density (gm/cm^3) 3.94Mean distance from the Sun (km) 227,940,000Mean distance from the Sun (Earth = 1) 1.5237

Rotational period (hours) 24.6229Rotational period (days) 1.025957Orbital period (days) 686.98Mean orbital velocity (km/sec) 24.13Orbital eccentricity 0.0934Tilt of axis (degrees) 25.19Orbital inclination (degrees) 1.850Equatorial surface gravity (m/sec^2) 3.72Equatorial escape velocity (km/sec) 5.02Visual geometric albedo 0.15Magnitude (Vo) -2.01Minimum surface temperature -140°CMean surface temperature -63°CMaximum surface temperature 20°CAtmospheric pressure (bars) 0.007Atmospheric compositionCarbon Dioxide (C02)Nitrogen (N2)Argon (Ar) Oxygen (O2)Carbon Monoxide (CO)Water (H2O)Neon (Ne) Krypton (Kr)Xenon (Xe)Ozone (O3)

95.32%2.7%1.6%

0.13%0.07%0.03%

0.00025%0.00003%

0.000008%0.000003%

Table 1: Mars Statistics

2.1 Earth/Mars Comparison

Mars Earth

In solar system 4th planet 3rd planetDistance from sun 227,936,637 km 149,597,891 kmDiameter 6,794 km 12,742 kmEquatorial Radius 3,397 km 6,378 kmMass 6.418 x 10^23 kg 5.972 × 10^24 kgLength of Day 24 hours, 37 minutes and

22 seconds23 hours 56 minute and 4.1 sec

Length of Year 687 Earth days 365 daysLargest Volcano Olympus Mons

26 km high602 km in diameter

Mauna Loa(Hawaii)10.1 km high121 km in diameter

Gravity 0.375 that of Earth 2.66 times that of MarsTilt of Axis 25° 23.45°Atmosphere(Composition)

Carbon dioxide (95.32%)Nitrogen (2.7%)Argon (1.6%)

Oxygen (0.13%)Water vapour (0.03%)Nitric oxide (0.01%)

Carbon dioxide (0.038%)Nitrogen (77%)

Argon (1%)Oxygen (21%)

Water vapour (1%)

Atmosphere(Pressure)

7.5 millibars (average)

1,013 millibars (at sea level)

Temperature 218 K(-63º C) 287 K (14°C)Temperature Range -127°C to 17°C -88°C to 58°CNumber of Moons 2

(Phobos and Deimos)1(Moon)

Polar Caps Covered with a mixture of carbon dioxide ice and water ice

Permanently covered with water ice

Average density 3.93 g/cm³ 5.51 g/cm³

Table 2: Earth/Mars Comparison

Fig 2.2: Inside Planet MARS

3. Why this Journey?In an interview, with The Hindu, Radhakrishnan to a question on what’s the most interesting on Mars, he replies saying Life. So, we talk about Methane...which is of biological origin or geological origin. So, we have a methane sensor plus a thermal infrared spectrometer. These two together should be able to give some information.

He went on to say that “We want to look at environment of Mars   for various elements like Deuterium-Hydrogen ratio. We also want to look at other constituents — neutral constituent

After the Earth Its soil contains water to extract It isn’t too cold or too hot There is enough sunlight to use solar panels Gravity 1/3 or 38% our Earth's, be sufficient for the human body to adapt Human speculation The day/night a Mars day is 24 hours, 39 minutes and 35 seconds 687 Days year Planet similar to earth extraterrestrial life scientists to expect life on Mars

4. Mission Plan

The Launch Vehicle - PSLV-C25 will inject the Spacecraft into an Elliptical Parking Orbit with a perigee of 250 km and an apogee of 23,500 km. With six Liquid Engine firing, the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earth’s Sphere of Influence (SOI) and arrives at the Mars Sphere of Influence. When spacecraft reaches nearest point of Mars (Peri-apsis), it is maneuvered in to an elliptical orbit around Mars by firing the Liquid Engine. The spacecraft then moves around the Mars in an orbit with Peri-apsis of 366 km and Apo-apsis of about 80000 km.

Fig 4: Mission Plan

5. Mission Objectives

ISRO website stated that, one of the main objectives of the first Indian mission to Mars is to develop the technologies required for design, planning, management and operations of an interplanetary mission. 5.1. Technological Objectives:

1. Design and realisation of a Mars orbiter   with a capability to survive and perform Earth bound manoeuvres, cruise phase of 300 days, Mars orbit insertion / capture, and on-orbit phase around Mars.

2. Deep space communication, navigation, mission planning and management and incorporate autonomous features to handle contingency situations.

  5.2. Scientific Objectives: 1. Exploration of Mars surface features, 2. morphology,3. mineralogy 4. and Martian atmosphere by indigenous scientific instruments.5. Existence of life

5.3 The deuterium/hydrogen ratio 

One measurement of particular interest is the ratio of deuterium to hydrogen (D/H ratio) in cometary water. 

Fig 5.3(a): Hydrogen atom. Fig 3.5 (b): Deuterium atom.

Hydrogen is the simplest atom, with one electron in orbit around a nucleus of one proton. Deuterium is an isotope of hydrogen, in which the nucleus also has one neutron. Chemical

compounds that contain hydrogen also come in versions made with deuterium. 

Water that contains deuterium is known as "heavy water." Earth's oceans contain a characteristic percentage of heavy water. So do comets, which are mostly water, and some of the other planets and moons. 

Knowing the D/H ratio of water and other substances is useful to scientists for two basic reasons. 

First, it acts as a fingerprint. By comparing the D/H ratios in Earth's water with that in cometary water, for example, scientists can determine whether our planet's water could have come from comets. The same determination can be made for other planets and moons in the solar system. 

Second, the D/H ratio in comets provides a clue to conditions at the beginning of the Universe! 

Scientists think the D/H ratio of pristine comets represents that of our original nebula, which in turn is typical of the rest of the Universe. And all of the hydrogen and deuterium in the Universe is thought to have formed during the first three minutes after the Big Bang (the nuclei, that is - stable atoms didn't develop for another 300,000 years or so), so the D/H ratio of the Universe was fixed in place at that time. 

Knowing that ultimate D/H ratio would help scientists determine the conditions that could have generated hydrogen and deuterium in that particular ratio, and therefore help them deduce the nature of the Universe in its earliest stages. 

Mars 

Understanding the atmospheric chemistry of Mars is important both for an understanding of Mars' history - including the possibility that it was more like Earth in its earlier days - and as a tool for comparing how atmospheres differ on different planets. Such studies may provide insights into the workings and possible future of our own atmosphere here on Earth. 

Herschel has explored the Martian atmosphere in the 200-670 micron range for the first time, enabling scientists to

Fig: Mars.

determine the vertical profiles of water vapor and oxygen molecules. Monitoring water at various times during the Martian year has revealed seasonal changes. 

Herschel has also measured deuterium and carbon monoxide, and may detect other compounds, such as hydrogen peroxide, that are predicted by models of Martian photochemistry. 

Finally, Herschel has obtained information about the composition and emissivity of minerals covering Mars' surface.

6. Polar Satellite Launch Vehicle

The Polar Satellite Launch Vehicle (Hindi: ध्रुवीय उपग्रह प्रके्षपण यान), commonly known by its abbreviation PSLV, is an expendable launch system developed and operated by the Indian Space Research Organisation (ISRO). It was developed to allow India to launch its Indian Remote Sensing (IRS) satellites into Sun synchronous orbits(SSO), a service that was, until the advent of the PSLV, commercially available only from Russia. PSLV can also launch small size satellites into geostationary transfer orbit (GTO).

PSLV – The Polar Satellite Launch Vehicle is an Indian expendable launch system developed and operated by the Indian Space Research Organisation. The launch vehicle is a medium lift launcher that can reach a variety of orbits including Low Earth Orbit, Polar Sun Synchronous Orbit and Geosynchronous Transfer Orbit. PSLV is operated from the Satish Dhawan Space Center located in Sriharikota on India’s East coast.PSLV is a four-stage rocket that uses a combination of liquid fueled and solid fueled rocket stages. The vehicle can fly in three different configurations to adjust for mission requirements.

The Polar Satellite Launch Vehicle features six Strap-on Solid Rocket Boosters clustered around its first stage which itself is also solid-fueled. The second stage is liquid fueled while the third stage is a solid rocket motor. The Upper Stage of the PSLV uses liquid Propellant. The launcher stands 44.4 meters tall and has a diameter of 2.8 meters. Depending on the launcher’s configuration, PSLV weighs 229,000, 296,000 or 320,000 Kilograms.In addition to the ‘regular’ PSLV version, it can fly in its Core Alone configuration, without the six Solid Rocket Boosters and less propellant in the tanks of its upper stage – a configuration used for missions that feature small payloads.PSLV can also fly in a XL Version that launches with additional propellant in its Solid Rocket Boosters to increase payload capability.

Type PSLVVersions Regular, Core Alone, XLHeight 44.5mDiameter 2.8mLaunch Mass

229,000kg (CA) to 320,000kg (XL)

Mass to LEO 3,250kgMass to GTO 1,410kgMass to SSO 1,600kg – XL: 1,800kg – CA: 1,100kg

In the year 2015 alone India successfully launched 17 foreign satellites belonging to Canada, Indonesia, Singapore, the UK and the United States. Some notable payloads launched by PSLV include India's first lunar probe Chandrayaan-1, India's first interplanetary mission Mangalyaan (Mars orbiter) and India's first space observatory Astrosat.

6.1 PSLV-XL (Operational)

PSLV-XL is the up rated version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful, stretched strap-on boosters. Weighing 320 tonnes at lift-off, the vehicle uses larger strap-on motors (PSOM-XL) to achieve higher payload capability. PSOM-XL uses larger 1-metre diameter, 13.5m length motors, and carries 12 tonnes of solid propellants instead of 9 tonnes used in the earlier configuration of PSLV. On 29 December 2005, ISRO successfully tested the improved version of strap-on booster for the PSLV. The first version of PSLV-XL was the launch of Chandrayaan-1 by PSLV-C11. The payload capability for this variant is 1800 kg compared to 1600 kg for the other variants. Other launches include the RISAT Radar Imaging Satellite andGSAT-12

6.2 PSLV-C25PSLV-C25, twenty fifth flight of PSLV will launch Mars Orbiter Mission Spacecraft from the First Launch Pad at Satish Dhawan Space Centre SHAR, Sriharikota.

Fig 6.2: PSLV XL C25 Launch clip

The challenging PSLV-C25 mission is optimised for the launch of Mars Orbiter Mission spacecraft into a highly elliptical Earth orbit with a perigee (nearest point to Earth) of 250 km and an apogee (farthest point to Earth) of 23,500 km with an inclination of 19.2 degree with respect to the equator.

PSLV- C25 Stages at a Glance

Propellant STAGE-1 PSOM-XL STAGE-2 STAGE-3 STAGE-4Solid(HTPBBased)

Solid(HTPBBased)

Liquid(UH25 + N2O4)

Solid(HTPB Based)

Liquid(MMH + MON-3)

Propellant Mass (Tonne) 138 12.2 42 7.6 2.5Peak Thrust (kN) 4800 718 799 247 7.3 X 2Burn Time (sec) 103 50 148 112 525Diameter (m) 2.8 1 2.8 2.0 2.8Length  (m) 20 12 12.8 3.6 2.7

Table 6: PSLV-C25 Stages at a Glance

POLAR SATELLITE LAUNCH VEHICLE

About the Launch Vehicle

The PSLV is one of world's most reliable launch vehicles. It has been in service for over twenty years and has launched various satellites for historic missions like Chandrayaan-1, Mars Orbiter Mission,

Space Capsule Recovery Experiment, Indian Regional Navigation Satellite System (IRNSS) etc. PSLV remains a favourite among various organisations as a launch service provider and has launched over 40 satellites for 19 countries. In 2008 it created a record for most number of satellites placed in orbit in one launch by launching 10 satellites into various Low Earth Orbits.

Vehicle Specifications

Height : 44 mDiameter : 2.8 mNumber of Stages : 4Lift Off Mass : 320 tonnes (XL)Variants : 3 (PSLV-G, PSLV - CA, PSLV - XL)First Flight : September 20, 19936.3 TECHNICAL SPECIFICATIONS

Payload to SSPO: 1,750 kg

PSLV earned its title 'the Workhorse of ISRO' through consistently delivering various satellites to Low Earth Orbits, particularly the IRS series of satellites. It can take up to 1,750 kg of payload to Sun-Synchronous Polar Orbits of 600 km altitude.

Payload to Sub GTO: 1,425 kg

Due to its unmatched reliability, PSLV has also been used to launch various satellites into Geosynchronous and Geostationary orbits, like satellites from the IRNSS constellation.

Fourth Stage: PS4

The PS4 is the uppermost stage of PSLV, comprising of two Earth storable liquid engines.

Engine : 2 x PS-4Fuel : MMH + MONMax. Thrust : 7.6 x 2 kN

Third Stage: PS3

The third stage of PSLV is a solid rocket motor that provides the upper stages high thrust after the atmospheric phase of the launch.

Fuel : HTPBMax. Thrust : 240 kN

Second Stage: PS2

PSLV uses an Earth storable liquid rocket engine for its second stage, know as the Vikas engine, developed by Liquid Propulsion Systems Centre.

Engine : VikasFuel : UDMH + N2O4Max. Thrust : 799 kN

First Stage: PS1

PSLV uses the S139 solid rocket motor that is augmented by 6 solid strap-on boosters.

Engine : S139Fuel : HTPBMax. Thrust : 4800 kN

Strap-on Motors

PSLV uses 6 solid rocket strap-on motors to augment the thrust provided by the first stage in its PSLV-G and PSLV-XL variants. However, strap-ons are not used in the core alone version (PSLV-CA).

Fuel : HTPBMax. Thrust : 719 kN

6.4 DIFFERENT STAGES OF PSLVThe first stage uses a 2.8 meter diameter, 20 meter long, 472 ton thrust solid motor that burns 138 tons of propellant for 107 seconds. The first stage is augmented by six solid strap-on boosters that produce 67.5 tons of thrust each for 45 seconds. Four of the strap-on boosters ignite at liftoff. The two air-start strap-ons ignite 25 seconds after liftoff. The strap-on boosters are jettisoned after burn-out. More powerful "XL" boosters carrying 12 tones of propellant and producing up to 73.4 tones of thrust debuted in 2008. PSLV's 12.5 x 2.8 m PS-2 second stage is powered by a 73.9 ton-thrust Viking 4 engine that burns unsymmetrical dimethyl hydrazine fuel and nitrogen tetroxide ((N2O4) oxidizer for 162 seconds. Viking 4,called "Vikas" by ISRO, was originally built by Europe's SEP for the Ariane 1 launch vehicle. The third stage is another 2.8 meter diameter solid motor. It burns 7.6 tons of propellant for 109 seconds, producing 33.5 tons of thrust. The fourth and final stage is a twin-engine liquid propulsion system that is housed within the payload fairing below the satellite. It burns 2.5 tons of mono-methyl hydrazine fuel and nitrogen tetroxide (N2O4) oxidizer. The 1.43 ton thrust stage can burn for up to 420 seconds

Fig 6.4: Important elements of PSLV

7. SPACECRAFTMars Orbiter Mission is India's first interplanetary mission to planet Mars with an orbiter craft designed to orbit Mars in an elliptical orbit. The Mission is primarily technological mission considering the critical mission operations and stringent requirements on propulsion and other bus systems of spacecraft. It has been configured to carry out observation of physical features of mars and carry out limited study of Martian atmosphere with following five payloads:

Mars Colour Camera (MCC) Thermal Infrared Imaging Spectrometer (TIS) Methane Sensor for Mars (MSM) Mars Exospheric Neutral Composition Analyser (MENCA) Lyman Alpha Photometer (LAP)

Mass: The lift-off mass was 1,350 kg , including 852 kg of propellant mass.Dimensions: Cuboid in shape of approximately 1.5 m .Power: Electric power is generated by three solar array panels of 1.8 × 1.4 m each. Electricity is stored in a 36 Ah Li-ion battery.

Propulsion: Liquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit, and 8 numbers of 22 N thrusters are used for attitude control.

Communications: Two 230 W TWTAs and two coherent transponders. The antenna array consists of a low-gain antenna, a medium-gain antenna and a high-gain antenna.

Fig 7: SpacecraftLift-off Mass 1337 kgStructures Aluminum and Composite Fiber Reinforced Plastic (CFRP)

sandwich construction-modified I-1 K BusMechanism Solar Panel Drive Mechanism (SPDM), Reflector & Solar panel

deploymentPropulsion Bi propellant system (MMH + N2O4) with additional safety and

redundancy features for MOI. Proplellant mass:852 kgThermal System Passive thermal control systemPower System Single Solar Array-1.8m X 1.4 m - 3 panels - 840 W Generation (in

Martian orbit), Battery:36AH Li-ionAttitude and Orbit Control System

AOCE (Attitude and Orbit Control Electronics): with MAR31750 Processor

Sensors: Star sensor (2Nos), Solar Panel Sun Sensor (1No), Coarse Analogue Sun Sensor

Actuators: Reaction Wheels (4Nos), Thrusters (8Nos), 440N Liquid

EngineAntennae: Low Gain Antenna (LGA), Mid Gain Antenna (MGA) and High

Gain Antenna (HGA)Launch Date Nov 05, 2013Launch Site SDSC SHAR Centre, Sriharikota, IndiaLaunch Vehicle PSLV - C25

Table 7: Spacecraft

8. PayloadsThe Mars Orbiter Mission carries five payloads to accomplish its scientific objectives. Three electro-optical payloads operating in the visible and thermal infra-red spectral ranges and a photometer to sense the Mars atmosphere & surface. One additional backup payload is planned in case of non-availability of the identified payloads. 

Atmospheric studies• Lyman-Alpha Photometer (LAP)• Methane Sensor For Mars (MSM)

Particle environment studies• Mars Exospheric Neutral Composition Analyser(MENCA)

Surface imaging studies• Thermal Infrared Imaging Spectrometer (TIS)• Mars Color Camera (MCC)

The 15 kg (33 lb) scientific payload consists of five instruments

LAP Lyman-Alpha Photometer 1.97 kg MSM Methane Sensor For Mars 2.94 kg MENCA Mars Exospheric Neutral Composition Analyser 3.56 kgTIS Thermal Infrared Imaging Spectrometer 3.20 kgMCC Mars Colour Camera 1.27 kg

Fig 8: MOM Spacecraft Payload location

8.1 Lyman Alpha Photometer (LAP)Lyman Alpha Photometer (LAP) is an absorption cell photometer. It measures the relative abundance of deuterium and hydrogen from Lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase). Measurement of D/H (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet.

The objectives of this instrument are as follows:Estimation of D/H ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles Fig 8.1: LAPSpecific areas of interest:

1. Atmospheric escape process addressing especially water loss mechanisms in Martian exosphere.

2. Algorithm realization, code development and construction of a Far Ultra-violet wavelength model of radiative transfer for the Mars exosphere from 250 km onwards.

3. Models addressing isotopic fractionation and enrichment of deuterium.4. Assessment of Martian atmospheric escape process, especially water escape rate using

the measured Hydrogen, deuterium fluxes and estimated D/H ratio.5. Combined analysis of LAP and MENCA data to assess the hydrogen atomic density

and distribution in Martian exosphere.6. Integrated studies of LAP payload data with other international

Mars missions.

8.2 Methane Sensor for Mars (MSM) MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources. Data is acquired only over illuminated scene as the sensor measures reflected solar radiation. Methane concentration in the Martian atmosphere undergoes spatial and temporal variations. Hence global data is collected during every orbit.

Specific areas of interest: Fig 8.2: MSM

1. Algorithm development for Methane detection in atmosphere of Mars 2. Mars reflectance changes due to dynamic atmosphere

using MSM3. Radiative transfer modeling in VNIR part of EM

spectrum 

8.3 Mars Exospheric Neutral Composition Analyser (MENCA)MENCA is a quadruple mass spectrometer capable of analysing the neutral composition in the range of 1 to 300 amu with unit mass resolution. The heritage of this payload is from Chandra’s Altitudinal Composition Explorer (CHANCE) payload aboard the Moon Impact Probe (MIP) in Chandrayan-1 mission.

Specific areas of interest: Fig 8.3: MENCA

1. Exopsheric composition of Mars2. Atmospheric escape from Mars.

8.4 Thermal Infrared Imaging Spectrometer (TIS)TIS measure the thermal emission and can be operated during both day and night. Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement. Many minerals and soil types have characteristic spectra in TIR region. TIS can map surface composition and mineralogy of Mars.

Specific areas of interest:Fig 8.4: TIS

1. Algorithm development for analysis of TIS data

2. Inversion of surface temperature of Mars using TIS data

8.5 Mars Color Camera (MCC)This tri-color Mars Color camera gives images & information about the surface features and composition of Martian surface. They are useful to monitor the dynamic events and weather of Mars. MCC will also be used for probing the two satellites of Mars – Phobos & Deimos. It also provides the context information for other science payloads.

Specific areas of interest:

1. Geomorphology and morphometric analysis of martian volcanoes 2. Geomorphology and morphometric analysis of fluvial landforms3. Aeolian processes on Mars4. Dust storms5. Dust devils6. Wind streaks

a. Study of genesis and direction of wind streaks on Marsb. Dark streaksc. Bright streaksd. Other streaks

7. Dunesa. Dune movementb. Modeling Wind speeds and directions

8. Combined analysis of MCC and MSM data to study dust storms, dust devils, cloud heights etc.

9. Understanding the process geomorphology of canyons, gullies and outflow channels present on Mars

10. Photometric correction of MCC11. Crater Size Frequency Distribution (CSFD) for surface age detection and geological

mapping12. Surface change detection by comparative analysis of MCC data with international

datasets13. International sensor data comparison and data merging for geomorphological and

mineralogical studies14. Study of geomorphology of Mars with terrestrial analogues 

9. Mission Phases or Trajectory

Mars is to develop the technologies required for design, planning, management and operations of an interplanetary mission

9.1 Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy

Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers. At the end of this phase the spacecraft is escaped from Earth Sphere Of

Influence(SOI). Earth SOI is 918347.

9.2 Heliocentric Phases

Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth, Mars and Sun Such relative arrangement recur periodically at interval of about 780 days.

9.3 Martian Phases

The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface of Mars]

At the time of spacecraft reaches the closest approach to Mars, It is captured into planed orbit around Mars

9(a) Earth Parking Orbit

It would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body, like the ISS, the Moon, or Mars. It might even be impossible for particular launch locations to do that.So, instead, a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth, in that orbit, until the timing and geometry are right to fire its engine again, initiating a trajectory to its target.  That temporary orbit is called a parking orbit.

Perform checks of the following systems:

Biomedical & safety equipment Environmental control system Comm & instrumentation system Electrical power system (EPS) Stabilization and control system (SCS) Crew equipment system SM propulsion system (SPS) SM reaction control system (RCS) Command Module Computer optics Entry monitoring system (EMS)

In order to achieve the velocity required to escape the earth’s gravity(escape velocity), 6 orbit

raising manoeuvers were performed on 6th, 7th, 8th, 10th, 11th and 15th November.

Fig 9.1: Geocentric Phases PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower

Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are

called EPOs ( Earth Parking Orbits ) LEO Perigee : 240 Km LEO Apogee : 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee : 193000 Km Corresponding Speed Of Satellite : ~ 11 Km/sec

On 30th November 2013, the engines of MOM were fired for 23 minutes.

The earth’s escape velocity was achieved by MOM and the spacecraft left the earth’s orbit.

Fig 9.2: Heliocentric Phases

With six Liquid Engine firing, the spacecraft is gradually

maneuvered into a hyperbolic trajectory with which it escapes

from the Earth’s Sphere of Influence (SOI) and arrives at the

Mars Sphere of Influence.

The spacecraft then embarked on its 10-month, 670 million

kms long journey towards Mars

Fig 9.2.1 : six engine firing at the end of heliocentric phases

Fig 9.2.2: Mangalyaan Trajectrory

• launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit,

then six engine firings will raise that orbit to one with an apogee of 215,000 km and a

perigee of 600 km, where it will remain for about 25 days.

• A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory.

• Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft

to enter a highly elliptical orbit of 422 km x 77,000 km around Mars

• The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and

apoapsis ~80000 km, inclination 151 degree, and orbital period 3.15 sols. The

spacecraft mass is 1350 kg, with dry mass of 500 kg and science payload mass of 14

kg

Fig 9.2.3: overall three phases

10. TRACKING AND COMMANDThe Indian Space Research Organisation Telemetry, Tracking and Command

Network(ISTTCN) performed navigation and tracking operations for the launch with ground

stations at Sriharikota, Port Blair, Brunei and Biak in Indonesia, and after the spacecraft's

apogee becomes more than 100,000 km, two large 18-metre and 32-metre diameter antennas

of the Indian Deep Space Network will be utilised. NASA's Deep Space Network will

provide position data through its three stations located in Canberra, Madrid and Goldstone on

the U.S. West Coast during the non-visible period of ISRO's network.

ISRO Telemetry Tracking and Command Network (ISTRAC) will be providing support of

the TTC ground stations, communications network between ground stations and control

center, Control center including computers, storage, data network and control room facilities,

and the support of Indian Space Science Data Center (ISSDC) for the mission. The ground

segment systems form an integrated system supporting both launch phase, and orbital phase

of the mission

The South African National Space Agency's (SANSA) Hartebeesthoek (HBK) ground station

is also providing satellite tracking, telemetry and command services. Additional monitoring is

provided by technicians on board two leased ships from the Shipping Corporation of India,

SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific.

Fig 10.1: Shipping Corporation Fig 10.2: Indian Deep Space networking

The radio waves (to be more precise, in the case microwaves) travelling at the

speed of light(300,000km/s) take 10minutes to travel from Earth to a spacecraft

orbiting Mars.

11. MISSION COSTThe government of India approved the project on 3 august 2012, after the Indian Space Research Organization completed 125 crore of required studies for the orbiter. The total project cost may be up to 454 crore . The satellite costs 153 crore  and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects.

Fig 11: Mission Cost

12. 14 Brains behind the success

We bring you the 14 brains behind Mangalyaan who helped put India in the elite club.

1. K Radhakrishnan: He is the chairman of ISRO and secretary, department of space. The 65-year-old avionic engineer graduated in engineering from Kerala University in 1970. Radhakrishnan also has an MBA degree from IIM-Bangalore and he also got a doctorate from IIT-Kharagpur. Besides being a top space scientist, Radhakrishnan is an enthusiast of Kerala's classical art form Kathakali and a keen music lover. He received a Padma Bhushan in 2014.

 2. M Annadurai: He is the programme director of Mars Orbiter Mission. Mylswamy Annadurai joined Isro in 1982 and was the project director for Chandrayaan I, Chandrayaan II,

ASTROSTAT, Aditya -I and the Mars Obiter Mission. Annadurai and his works are mentioned in the 10th standard Science Text Book of Tamil Nadu. Born in Kodhawady near Pollachi in Coimbatore district of Tamil Nadu, Annadurai has been leading many Remote Sensing and Science missions at ISRO.

3. S Ramakrishnan: Director of Vikram Sarabhai Space Centre and Member Launch Authorisation Board. A senior Isro scientist has more than four decades of experience in rocketry in the Indian space programme. Joined ISRO in the August of 1972, Ramakrishnan played a key role in the development of PSLV which carried the Mangalyaan into the space. He had said, "From here to go to Mars we are going to use only a fraction of what we did in getting to the (Earth) orbit." The challenge for him was the launch of the rocket. He said the launch window was only five minutes. Ramakrishnan is a mechanical engineer from the College of Engineering, Guindy, Chennai. He received his M.Tech in Aerospace from IIT-Madras with the first rank.

4. SK Shivakumar: Director of ISRO Satellite Centre, Shivakumar joined ISRO in 1976. He was part of the team that developed the telemetry system for Chandrayaan-I, India's first lunar exploration mission.  He also developed satellite technology and implemented satellite systems for scientific, technological and application missions. He said, "Our baby is up in the space. It was almost like a caesarean."

5. V Adimurthy: Born in Andhra Pradesh and educated at IIT-Kanpur, Adimurthy joined ISRO in 1973 and was the Mission Concept Designer of Mars Orbiter Mission. He was also awarded the Padma Shri in 2012.

6. P Kunhikrishnan: He is the Mission Director for

the launcher. From the Vikram Sarabhai Space Centre

in Thiruvananthapuram, Kunhikrishnan has seven

successful PSLV launches under his belt since 2009. He

was appointed the mission director for the ninth

time. He was responsible for seeing the rocket

completes its mission successfully and that the satellite

is correctly injected in the designated orbit. The

challenge for him was that the orbital characteristic of the Mars Mission is different from

regular PSLV missions.

7. Chandradathan: Took over as the Director of the Liquid Propulsion Systems Centre in 2013. He joined ISRO in 1972. Initially, he worked for the SLV-3 project during its design phase and later was involved in the development of solid propellant formulations for SLV-3. Over three decades, Chandradathan made contribution to the realisation of solid motors for sounding rockets, SLV-3, ASLV and PSLV.

8. AS Kiran Kumar: Joined ISRO in 1975, Kumar is the Director of Satellite Application Centre. He was responsible for designing and building three of the orbiter payloads - the Mars Colour Camera, Methane Sensor and Thermal Infrared Imaging Spectrometer. The challenge before him was miniaturising the components as the satellite does not provide much space.

9. MYS Prasad: He is the director of Satish Dhawan Space Centre and chairman of the Launch Authorisation Board. From 1975 to 1994, he worked in the launch vehicle development programmes of Isro. He was part of the project Ttam of SLV-3, the first

indigenously developed launch vehicle of India. As the launch was during northeast monsoon season the challenge was to enhance weather forecasting capability to 10 days and simultaneously carrying out preparatory work for Mars Mission while dismantling the GSLV rocket after the mission was aborted earlier this year.

10. S Arunan: He is the project director of

Mangalyaan. Arunan was responsible for leading

a team to build the spacecraft. The challenge for

him was to build a new communication system,

which would largely be autonomous so that it

could take decision and 'wake up' the orbiter

engine after 300 days.

11. B Jayakumar: The associate project director

of PSLV project,  Jayakumar was responsible for the rocket systems, testing till the final lift-

off.

12. MS Pannirselvam: The chief general manager of range operation director at Sriharikota

Rocket port, Pannirselvam was responsible for maintaining launch schedules without any

slippages.

13. V Kesava Raju: He is the mission director of Mangalyaan. Raju and his team will track

the journey of the MOM in the outer space.

14. V Koteswara Rao: He is the Isro scientific secretary.

13. CONCLUSION

India set for maiden Mars mission!!!!India is inching closer to its maiden mission to Mars with just a day to go before the historic launch.During the countdown, the Polar Satellite Launch Vehicle (PSLV), the Indian Space Research Organisations's workhorse launch vehicle that will carry Mangalyaan, will be fuelled and its health checked. The giant 45-metre rocket will blast off from Sriharikota, which is about 80 kilometres from Chennai.

The launch of Mangalyaan, which was scheduled for October 28 initially, was postponed due to bad weather in the Pacific Ocean. Two Indian ships, SCI Yamuna and Nalanda, which will monitor the health of the rocket and the satellite as it sails over the ocean after the launch, had been delayed due to bad weather.The launch window will remain open till November 19.It is of critical importance for Mangalyaan to begin its over 200-million-kilometre journey on its trans-Martian orbit by November 30; further delay could prove disastrous for the mission.This will be the first-ever launch that ISRO will conduct in November at India's space port, which is usually dogged by recurring cyclones at this time of the year.The Mangalyaan mission will cost Rs 450 crores and will study the Martian atmosphere.

The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology.

The primary objective of the Mars Orbiter Mission is to showcase India's rocket launch systems, spacecraft-building and operations capabilities.

Taken using the Mars Colour Camera from an altitude of 8449 km

Phobos, one of the two natural satellites of Mars silhouetted against the Martian surface

Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC

REFERENCES

1. isrohq.vssc.gov.in/isr0dem0v5a/index2. http://en.wikipedia.org/wiki/polar_satellite_launch_vehicle3. http://www.antrix.gov.in/pslv.html4. www.isro.org/pslv-c25/Imagegallery5. http://www.isro.gov.in

K. RadhakrishanChairman, ISRO

M. AnnaduraiProgr Director, MOM

S Ramakrishnan

Director,VSSC

S. K. ShivkumarOrbiting payload

Director, ISAC

V Adimurthy

Mission Concept

Designer(MOM)

P. Kunhikrish

nanLaunch Mission

Director,PSLV-XL

Madhavan ChandradathanDirector, Propulsion Systems

VSSC

A.S. Kiran KumarDirector, SAC

S. Arunan Project Director,

MOM