7/27/2015 LAUNCH VEHICLE SYSTEMS MARS ORBITER MISSION. ROCKETS Vs LAUNCH VEHICLE THE JOURNEY INTO SPACE. V cr

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1 MARS ORBITER MISSION INDIAN FORAY INTO PLANETARY EXPLORATION & GLOBAL PERSPECTIVE S. Ramakrishnan ISRO VIKRAM SARABHAI PROFESSOR ( Formerly DIRECTOR, VSSC ) TAMHANKAR MEMORIAL LECTURE 29 th JULY 2015 DMRL Hyderabad THE JOURNEY INTO SPACE ROCKETS Vs LAUNCH VEHICLE FROM SOUNDING ROCKETS TO..LAUNCH VEHICLES X O =at + b cr LAUNCHING A SATELLITE AROUND EARTH V cr V cr, cr Required characteristics of movement at the end of active leg. V cr - Velocity value cr - Angle of velocity inclination to local horizon - Pitch angle t - Flight time a, b - Constants insuring required V cr and cr LAUNCH VEHICLE SYSTEMS VEHICLE STRUCTURES PROPULSION SYSTEMS CONTROL /STEERING SYSTEMS NAVIGATION & GUIDANCE (INERTIAL) SYSTEMS STAGE AUXILIARY SYSTEMS STAGING DESTRUCT LAUNCH PAD INTERFACES / UMBILICALS VEHICLE AVIONICS SEQUENCING / PYRO /CONTROL TELEMETRY TELECOMMAND TRACKING 1

2 PSLV: Vehicle Configuration FOURTH STAGE 2.5 T LIQUID PROPELLANT 420 s BURN TIME WITH TWIN ENGINE VEHICLE EQUIPMENT BAY CONTAINS VEHICLE ELECTRONICS POWER SYSTEMS, SEQUENCER INERTIAL SYSTEM & ON-BOARD PROCESSOR SECOND STAGE 40 T LIQUID PROPELLANT 160 s BURN TIME THIRD STAGE LARGEST UPPER SOLID STAGE 7.6 T SOLID PROPELLANT 80 s BURN TIME TYPICAL PSLV FLIGHT SEQUENCE FOR SSPO MISSION 6 STRAP-0N MOTORS SAME AS SLV-3 & ASLV 10 /13T SOLID PROP. 44 s BURN TIME FIRST STAGE 139 T SOLID PROPELLANT 110 s BURN TIME USED AS IS FOR GSLV 1 st -STG IMPACT km UPPER STG MASS - 66 T 3 rd -STG IMPACT km UPPER STG MASS - 4 T 2 nd -STG IMPACT km UPPER STG MASS - 12 T Launch Azimuth corridor for different missions from SHAR Range SHAR Trivandrum Mauritius SSO Launch Az P.Blair Brunei GTO Launch Az - 18 Incn. Biak LEO Launch Az Inclination PSLV Operational Flights PSLV-C IRS-1D 1207 kg PSLV-C IRS-P4 KITSAT-3 TUBSAT kg PSLV-C TES PROBA BIRD kg PSLV-C KALPANA kg PSLV-C IRS- P kg PSLV-C CARTOSAT-2, PSLV-C6 SRE, LAPANSAT, 2005 PEHUENSAT IRS- P kg HAMSAT kg PSLV-C RISAT-2, ANUSAT kg PSLV-C CHANDRAYAAN kg PSLV-C CARTOSAT-2,A IMS 1 NANOSATS 8nos 850 kg PSLV-C POLARIS 300 kg PSLV-C AGILE AAM kg PSLV C25 / MARS ORBITER MISSION MARS ORBITER 1340 kg GUIDANCE MARGIN PS2 : 461 kg RSS : 543 kg PS4 : 59 kg RSS : 36.5 kg VEHICLE CONFIGURATION PSLV-XL 6PSOM-XL+S139+PL40+HPS3 +L2.5 # 36 kg extra propellant loading ORBIT SPECIFICATIONS Apogee Perigee : km : 250 km Inclination : 19.2 Launch Pad : FLP Launch Azimuth : 104 Argument of Perigee : DISPERSION Apogee Perigee LAUNCH 5 th November 14:38:26 hrs (IST) : ±675km : ±5km Inclination : ±0.2 Argument of Perigee : ±0.2 BUILDING OF PSLV AT MOBILE SERVICE TOWER MOBILE SERVICE TOWER- WEIGHS 3000 TON, DESIGNED FOR CYCLONIC WIND CONDITIONS CLEAN ROOM FOR SATELLITE INTEGRATION SERVICE INTERFACES FOR PSLV & GSLV 2

3 INTEGRATION OF PSLV THIRD & FOURTH STAGE (PS3/PS4) STACK MOM SPACECRAFT MATED TO PSLV C25 VEHICLE AT LAUNCHPAD PAYLOAD FAIRINGS CLOSURE INSIDE CLEAN ROOM VEHICLE INTERFACES WITH LAUNCH PAD ELECTRICAL UMBILICALS PNEUMATIC UMBILICALS PROPELLANT SERVICING INTERFACES PSLV-C25/Mars Orbiter Mission MST STARTED MOVING MST MOVED TO PARKING SLOT India s First Interplanetary Mission Initiative MISSION CONTROL CENTRE LAUNCH CONTROL CENTRE Lift Off 5 th Nov 2013 at 14:38:26 hrs PSLV-C25/Mars Orbiter Mission 3

4 Orbit : x km, deg, deg (AOP) [ , , ] [ , , ] [ , , ] From 1180 s onwards vehicle will be in Earth shadow [582.76, , ] SPD (S) [263.00, , ] YAMUNA [201.14, , ] SHAR PORTBLAIR NALANDA [112.14, , ] BRUNEI SPD (P) BIAK MOM SEP PS4 SH [92.00, , ] PS4 IGN [70.00, , ] [25.00, 2.709, ] PS2 IGN PS3 BO PS3 IGN [0.00, 0.023, ] Flight Sequence for PSLV-C25/MARS ORBITER MISSION Time Launch windows The minimum-energy launch windows for a Martian expedition occur at intervals of approximately two years and two months, i.e. 780 days (the planet's synodic period with respect to Earth). Opportunities Year Launch 2013 Nov 2013 Jan Jan 2016 Apr Apr 2018 May Jul 2020 Sep 2020 Mars Orbit is slightly tilted with respect to the sun-earth plane (Inclination with respect to Ecliptic is 1.85 deg). Planets appear close to the path of the sun in the sky, the ecliptic Profile o Six EBNs take the spacecraft gradually into a departure hyperbolic trajectory. S/C escapes from the Earth s Sphere Of Influence (SOI) with Earth s orbital velocity + ΔV boost. o Spacecraft leaves Earth in a direction tangential to Earth s orbit around sun. Encounters Mars tangentially to its orbit around sun. The flight path is roughly one half of an ellipse around sun. o The spacecraft arrives at Mar s SOI in a hyperbolic trajectory. When the spacecraft reaches Mars Periapsis, it is captured into the planned orbit around Mars by imparting ΔV retro. Minimum-energy launch windows for Martian expedition occurs at intervals 780 days 4

5 Mars at Departure Departure Satellite Earth Bound Manoeuvers and Escape EBNs Sun Earth at MOI Mars Orbit Insertion (MOI) Constraints from Spacecraft (MOM) on launcher : Optimal & (To have optimal direction for velocity vector at perigee for departure ) (Argument of perigee) : Large values of AOP ( deg) requires long coast to inject the spacecraft in southern latitude (RAAN) : Demands lift-off at 2.38 PM (Vehicle enters into Earth shadow after PS3 burnout and issues related to deep space cooling effects) Orbit Capture at Mars MARS DISC AS SEEN BY MOM DURING FIRST ORBIT CAPTURE MANOUVRE 370 x km On entering into MARS Sphere of Influence, retarding velocity of 1.11 km/s to be imparted. Orbital velocity wrt MARS is 4.6 km/s As the Spacecraft approaches MARS,it is at 222 million km (1.51 Au) away from Earth Commands from ground take 12.1 minutes to reach MARS ORBITER MISSION PROPULSION SYSTEM PRESSURANT TANK PG 1 Active, Bipropellant(MON-3, MMH) FVG Type system Regulated mode for Apogee NCG1 NCG2 NCG3 System operating maneuvers at 16.5 bar (Nominal) pressure Blow down mode for AOCS thrusters TPG1 from 16.5 bar at BOL to 11.5 bar at FV2 FV1 EOL PR1 LAM 440 N X 1 Engine PGR Thruster rating 22 N X 8 Thrusters PR 2 MEOP of TPG4 250 bar of GHe Pressurant Tank Spacecraft Propulsion Thrusters 11N AOCS Mono-propellant Thrusters Thrust Propellant :1 N / 11 N : N2H4 TPG3 FDF NCF1 TPF NOF2 MMH NCF4 NCF3 LVG1 PF NCF2 R1 R2 R3 R4 FF1 NOF1 FF2 FOF LVG2 LAM NCO1 FO1 NOO1 FO2 OOF PO NCO3 R5 R6 R7 R8 MON-3 NCO4 TPG2 FDO NCO2 TPO NOO MEOP of Propellant Tank LAM inlet pressure AOCS inlet pressure Propellant Mass (Nominal) 16.5 bar 14.3 bar (nominal) with PR bar (nominal) with PR & kg, 1.65 MR Additional Pressure measurement between the Pressure Regulators Hard ware redundancy to LVG in addition to reverse polarity provision LAM feed line pressure sensors are removed One additional set of two NO & NC pyros incorporated to re-use of LAM for Mars burns. 440N engine Liquid Apogee Motor (LAM) - Pressure fed engine This thruster is used for orbit raising operation of INSAT/GSAT series of satellites. ENGINE THRUST (VAC) : 440 N PROPELLANTS SPECIFIC IMPULSE : 310 s : MON-3/MMH 22 N thruster Attitude & Orbital Control Thruster (AOCS) Bi propellant thrusters of 22N and 10N thrust are used in INSAT / GSAT satellites for attitude & orbit corrections and station keeping ENGINE THRUST (VAC) : 22 N / 10 N PROPELLANTS : MON-3/MMH SPECIFIC IMPULSE : 285 s Specific Impulse : 220 s 1 N Thruster 5

6 MARS ORBITER MISSION PROPULSION SYSTEM Indian Mars Orbiter Mission (MOM) BURN PERIGEE (km) APOGEE (km) LEB ,826.4 LEB ,182.5 LEB ,622.8 LEB ,708.2 LEB-4A ,18,632.3 LEB ,92,918.6 TMI MOI ,872.0 Propellants OX (kg) FU (kg) Accomplishments: Five Earth bunrs(ebns) Trans Mars Insertion(TMI) Two Trajectory Correction Manuevers (TCM) LAM calibration firing (4 sec) Mars Orbit Insertion (MOI) Manuever Loaded Total Consumption till MOI end 53.8* 18.7* end of MOI * including holdup & uncertainties EARTH TO ORBIT THE MOST DIFFICULT AND COSTLY FIRST STEP IN SPACE TRAVEL IN TERMS OF ENERGY AND MASS MANAGEMENT. Earth Mars Panorama of Martian Surface as obtained from Pathfinder Radius 6378 km 3397 km Density 5515 kg/m kg/m 3 Gravity 9.8 m/s m/s 2 Year days days Eccentricity Day 24 hours 24 hr 39 min Obliquity 23.45º 25.19º 6

7 Spacecraft On-orbit Configuration *Thermal implementation on spacecraft is not shown WATER ICE ON MARS ISROs Launch Vehicles Growth of Capability ASLV LVM3 GSLV SLV-3 PSLV DEMONSTRATION OF LAUNCH VEHICLE TECHNOLOGIES LEO PAYLOADS (KG) Launch Vehicle SLV-3 ASLV PSLV GSLV LVM3 (Under development) Lift-off weight (kg) Payload (kg) 40 (LEO) 150 (LEO) 1700 (SSO) 2500 (GTO) 4000 (GTO) PSLV TO GSLV 3rd & 4th STAGE BY CRYO I & II STAGES DERIVED FROM PSLV GSLV D5 Launch Demonstrated Indigenous Cryo engine technology Indigenous GSLV capable of launching 2.2t satellite in orbit Robust vehicle with high level of accuracy India joins select group of space faring nations with Cryogenic technology Culmination of over 20 years of intensive efforts Taking forward ISRO s vision of sustained self-reliance Stepping stone for future growth in launch capacity SOLID STRAP-ONS BY LIQUID - DERIVED FROM PSLV II-STAGE GSAT-14 Orbit Spec Achieved Δ hp 180 ± 5 km km 0.13 km ha ± 675 km km 31 km i 19.3 ±

8 LVM3-X Vehicle at Launch Pad HUMAN SPACEFLIGHT TECHNOLOGY INITIATIVE Crew Module Atmospheric Re-entry Experiment [CARE] Crew Module Preparations for Encapsulation LVM3-X VEHICLE ON LAUNCHPAD WITH INDIAN CREW MODULE AERO REENTRY EXPERIMENT (CARE) CAPSULE ASSEMBLED INSIDE NOSE-CONE LVM3-X Vehicle during Lift-off Flight Profile for LVM3-X/CARE Mission LVM3-X LIFT-OFF FROM SECOND LAUNCHPAD (SLP) AT SATHISH DHAWAN SPACE CENTRE / SHAR 18 th DECEMBER Hrs IST LVM3-D1 HS SEPARAION T = s h = km S200 SEPARATION T = s h = km L110 IGNITION T = s h = km S200 IGNITION Missions to Mars, Venus & Asteroids Photos/Deimos Fly-by Capabilities ( Kg ) (kg) Mars Venus Asteroid Orbital Capability (Kg) Mars Venus Asteroid PSLV GSLV LVM

9 MOON IMPACT PROBE Design, develop and demonstrate technologies for impacting a probe at the desired location on the Moon Mass spectrometer to assess the lunar atmosphere Radar altimeter to measure the altitude with a resolution of 5m Video imaging system (VIS) to take photographs of Moon s surface From 100km orbit, took continuous imagery for 25 minutes before hitting the Moon surface on 14 th Nov, Lander with Orbiter (Launch configuration) SOFT LANDING ON A PLANET Orbiter Craft Upper Adaptor Lander Lower Adaptor 7/27/2015 CHANDRAYAN CONTROLLED DESCENT & PRECISE TOUCH DOWN SOLAR SYSTEM PLANETS NASA SPACECRAFT NEW HORIZONS FLIES PAST PLUTO DISTANCES NOT TO SCALE - COMPRESSED TO CONTAIN WITHIN FRAME 9

10 CHARON COMPANION OF PLUTO AS SEEN BY NASA s NEW HORIZON THE CHALLENGE OF INTERPLANETARY TRAVEL A PROBLEM OF DISTANCE & TIME.... Mission V, Km/s Earth Surface to LEO 7.6 LEO to GEO 4.2 LEO to Earth escape 3.2 LEO to lunar Orbit (7days) 3.9 LEO to Mars Orbit (0.7yrs) 5.7 LEO to Mars Orbit (40 days) 85.0 LEO to Neptune Orbit (29.9 yrs) 13.4 LEO to Neptune Orbit (5.0 yrs) 70 LEO to Solar Escape 8.7 LEO to 1000 AU (50 yrs) 142 LEO to α-centauri (50 yrs) 30,000 SURVIVAL AWAY FROM HOME EARTH - AN ABODE IN SPACE INTERNATIONAL SPACE STATION - ISS FREEDOM The Moon Can Be A Development Site for Both Moon & Mars Hardware LUNAR BASE AS A STEPPING STONE 10

11 IN-SITU RESOURCE UTILISATION 11

12 ASTEROID EXPLORATOTION FOR MINERALS MINING TOWING AN ASTEROID 12

13 Launching of Satellite is the first step in Accessing Space SOUNDING ROCKETS SLV ASLV PSLV Assured access to space through operational PSLV / GSLV India : equitable player in Global Missions GSLV LVM3 THE FUTURE Thank you for Your attention 13