I A · ! I PSLV PROJECT

INoIA·!aiPSLV PROJECT4INDIAN SPACE RESEARCH ORGANISATION

PSlV-C22IRNSS-lA MIssionFirst RegionalNavigation SatellitePSlV-C19RISAT-l MissionHeaviest Satelliteever launched by PSlVPSlV-C17GSAT-12 MissionDedicatedCommunication SatellitePSlV-CllCHANDRAYAAN-l Mission I.PSlV-C11Chandrayaan-11380 kg255 km x 22860 km22-10-2008PSlV-C17GSAT-121410 kg284 km x 21000 km15-07-2011PSlV-C19RISAT-11858 kg480 km (SSPO)26-04-2012PSlV-C22IRNSS-lA1426 kg284 km x 20650 km01-07-2013

9?SggJ-C2s/S\\.arsOrbiter ssio"PSLV-C25, the 25th mission ofPSLV and 5th in the XL conRguration, will carry the MarsOrbiter Satellite (1337 kg) into a 250 km x 23500 km elliptical orbit. The Satellite willbe further navigated to a hyperbolic departure trajectory and thereafter it traverses aninterplanetary cruise trajectory before reaching the intended orbit around the Mars.Challenges.The major technical challenges for the Launch Vehicle in accomplishing this Mission arisefrom the larger Argument of Perigee (AOP) requirement ranging from 276.40 to 288.60compared to 1780 in earlier Missions. This AOP minimises the energy required in transferringthe satellite from the Earth to the Mars. In this regard, the Launch Vehicle Right regimeis extended to 2657s (against 1200s for regular PSLV Missions) with a long coasting(1580-1800s) before the ignition of the PS4 stage. The long coasting necessitated specificmodification and validation of the coast phase guidance algorithm, on-board batterycapacity augmentation, assessment on the performance of inertial systems for extendedRight duration and deployment of two Ship-borne Terminals to capture the critical telemetrydata during Right in the non-visibility zone.Additional provisions are made for the thermal management of Vehicle Equipment Bay, PS4stage and also the Spacecraft elements considering the longer exposure to extreme coldspace.Another unique task associated with management of this Mission is the generation andConfiguration Control of multiple Initialization Filesforthe on-board computers correspondingto the different launch dates.Lift off Mass320 tPropulsion StagesFirst Stage6PSOM-XL S139Second StagePL40Third StageHPS3L2.5Fourth Stage3.2 m diaPayload FairingMission SpecificationsApogee23500 :t675 kmPerigee250 5 kmArgument of Perigee282.55 :t 0.20Inclination19.2Payload Mass1337 kg 0.20 I(For launchon 5'" November.2013)III

9?ofar Sateffite %uncft COefticfeThe Polar Satellite Launch Vehicle (PSLV) caters to the requirements of launchingsatellites into Sun-Synchronous and Low Earth Orbits. PSLV is a Four stage vehicle withalternate Solid and Liquid propulsion stages. The booster stage along with the strap-onmotors and the third stage are solid motors while the second and Fourth stages useliquid engines.PSLV has the capability to launch 1750 kg class satellites into 600 km Sun-SynchronousPolar Orbit (SSPO) and 1425 kg satellites into Sub-Geosynchronous TransFer Orbit (SubGTO) oF284 km X 21000 km. The vehicle has provision to launch multiple satellites.PSLV has successfully accomplished 2 developmental and 21 operational Missions ina row. It has established itselF as a work horse operational launcher of ISRO and has ademonstrated reliability oFO.96. Currently two variants oFPSLV are operational, namelyPSLV-XL (with six extended strap-on motors attached to the First stage) and PSLV-CoreAlone (without strap-on motors). PSLV-C25/Mars Orbiter Mission employs the PSLV-XLversion which has already been used in Four earlier Missions.Length (rn)Diameter (rn)PropellantSolidSoild(HTPB based)(HTPB based)13812.2Propellant Mass (t)Peak Thrust (kN)4800Burn Time (s)PSLV-C25 VehicleConfiguration103fLiquid(UH25 NzO.)427197995014BtSolid(HTPB based)Liquid(MMH MON3)2.5762477.3x211252523 Successive Successful Missions AccomplishedPSLV VariantsLaunchedSuccessfulMissions - Orbit types63 C6C7ellC10Rellablll1:yC9C11 C12AchievedC14C1S C16C:1.7C18C19C21C20C22

ldofIof PS4PSLV - C25 Flight Events for Launch on 5th Nov. 2013 ofPS3SeLocalAltitude(km)Time(s)Eventss.,. ofPSlRCT Ignition-3.00PSI 51.89Iof PoytoadfWi PSOM XL 1,2 (GLl Ignition0.46PSOM XL 3.4 (GL) Ignition0.66PSOM XL 5, 6 (AL) I .80IpIltion of PSI S.".rJdon of PSi 69.94PSOM XL 3.4 (GL) Separation70.1423.6181436.54PSOM XL 5,6 (AL) Separation92.0439.7042024.36112.7557.6782387.67- --l1PSI Separation.,tIonoflsu.pons. .·lIt2 95.PS2 Ignition117.95CLG Initiation ·fPSOM XL 1,2 (GL) Separation23.4895epaqdon of.Groun6-UtStrapons57.84661.955Payload fairing 265.94132.531i5PS3 Ignition.u. 1dofI1 . . su.ponslenitionof' Gn und-lIt583.60PS3 Separation I2100.50PS4 Ignitionlenotlonof ayload AdaptorPS4 StageView from y- PSlV\I'Iew from p. PSlVPayload Accommodationin PSLV-C25-5378.94271.317PS4 Cut-offMars Orbiter SatelliteI194.869Mars Orbiter SeparationI.---2415.46PS2 SeparationAI,,-.'"2387.16t--I9833.499804.01

0'\ars 0rbitcrMars Orbiter Mission is ISRO's First Interplanetary Mission withan Orbiter craft designed to orbit Mars in an elliptical orbit of366 km x 80000 km. The technological objective of the Mission isto design and realize a spacecraFt with a capability to perForm EarthBound Manoeuvre, Martian TransFer Trajectory (MTT) and Mars OrbitInsertion (MOl) phases.TechnologicalMars OrbiterObjectivesTo develop the technologies required Fordesign, planning, management, deep space communicationand operations of an Interplanetary Mission.To design and realize Mars Orbiter with a capability to survive and perForm Earth boundManoeuvres, cruise phase oF300 days, Mars orbit insertion E captu re, and on-orbit phase aroundMars.Incorporate autonomous Features to handle contingency situations.PayloadsLyman Alpha Photometer (LAP)Methane Sensor For Mars (MSM)Martian Exospheric Neutral Composition Explorer (MENCA) Mars Colour Camera (MCC)VemalEquinoxTIR Imaging Spectrometer (TIS)The scientific objectives of these payloads are exploration ofMars surFace Features, morphology, mineralogy and Martianatmosphere.Reaching Mars.Man orbitInMrdon(MOI)24-1)'1·14Trajectory DesignThe Earth-Mars transition comprises the Following three phasesEarth-centeredphaseHeliocentric phaseMartian phaseThe SpacecraFt is injected into an elliptical parking orbit by the launcher. AFter injection of the MarsOrbiter into the orbit, Fiveorbit raising burns using Liquid Engine are planned. After these burns, theOrbiter will be given a Trans-Mars Injection (TMI) manoeuvre at perigee which will put the Spacecraftin the Mars TransFerTrajectory. AFter the end oFthe TMI, the Orbiter travels in a hyperbolic departuretrajectory with which it escapes From the Earth's Sphere OF InAuence (501). AFter crossing theEarth's 501, the Spacecraft is in an elliptical interplanetary cruise trajectory around the sun For theplanned transFer time after which it has its rendezvous with Mars. The spacecraFt arrives at the Mars501 in a hyperbolic trajectory. When the Orbiter reaches Periapsis, closest to Mars, it is manoeuvredFor Mars Orbit Insertion (MOl), which will insert the Orbiter into an elliptical Martian orbit of366 km x 80000 km .

Payloads Lyman Alpha Photometer (LAP) Methane Sensor ForMars (MSM) Martian Exospheric Neutral Composition Explorer (MENCA) Mars Colour Camera (MCC) TIR Imaging Spectrometer (TIS) The scientific objectives of these payloads are exploration of Mars surFace Features, morphology, mineralogy and Martian atmosphere. Vemal Equinox Man orbit InMrdon .