Indian Space Transportation SystemIndian Space Transportation SystemPresent Scenario and Future Directions Present Scenario and Future Directions Indian Space Transportation SystemIndian Space Transportation SystemPresent Scenario and Future Directions Present Scenario and Future Directions

Dr. B. N. SureshDirector

Indian Institute of Space Science and Technology(Former Director, VSSC)

TIFR Mumbai – 19th June 20091

Rocket by Tippu Sultan

He used world’s first war rocket against the British. A long bamboo stick using 2 kg gun powder as rocket & sword as its weapon. Each rocket weighed 3.5 kg and traveled 1.5 km. An outstanding performance. Multiple rockets fired at the same time pierced through the British cavalry.

Tippu’s rocket is displayed at the Artillery Museum in Woolwich, London.

2

November 21, 1963

SLV-3 ASLV

TODAY, 2006

PSLV

GSLV

ARYABHATA19.04.75

GSAT-208.05.03

KALPANA-112.09.02 INSAT-2E

03.04.99

INSAT-3B22.03.00

INSAT-3A10.04.03

IRS-1C28.12.95

IRS-P321.03.96

IRS-1D29.09.97

IRS-P617.10.03

INSAT-3E28.09.03

TES22.10.01

INSAT-3C24.01.02

IRS-P426.05.99

One among the six Nations

8

2

Four decades of indian RocketryFour decades of indian RocketryLA

UN

CH

VEH

ICLE

SA

TELLIT

EA

PP

LIC

ATIO

NS

Humble beginning : 28 launches so farFirst launch of Nike

Apache on 21st Nov 1963

Evolution of Rocketry in India

3

Sounding Rockets of ISRO

4

ISRO Launch Vehicle Family

SLV ASLV PSLV GSLV GSLV Mk-III

Height (m) 22 23.5 44 49 42.43

Lift-off wt(t) 17 39 295 414 632

Payload kg 40 150 1400 2000 4000

Orbit LEO LEO POLAR GTO GTO

Height (m) 22 23.5 44 49 42.43

Lift-off wt(t) 17 39 295 414 632

Payload kg 40 150 1400 2000 4000

Orbit LEO LEO POLAR GTO GTO

Aug 1979 /July 1980 May 1992 Oct 1994 Apr 2001 Middle 2010

5

4(1) 4(2) 15(1) 5(1)

Basics in TechnologiesAvionics,Aerodynamics, O/L Guidance Propulsion,Structures,etc.

Closed Loop & Strap-on Technology

Bulbous Heat Shield

Liquid Propulsion, Large Booster & Liquid Upper Stage

Cryogenic Technology, GTO Mission1960-1970s

1980s1990s

Beyond 2000

Heavy CryogenicsLarge Boosters

LAUNCH VEHICLE EVOLUTION

Two Launch Pads

Technology Progression in Launch Vehicle Development

6

PSLV Configuration

6S9 + S139 + PL40 + HPS3 +L2.5

Gross weight : 294 T Overall height: 44 m Diameter : 2.8 m Heatshield: 3.2 m Features :

4 stage vehicle Multiple satellite launch capability Multi orbit capability Performance :

o GTO : 1.2 To SSPO : 1.7 T

Satellite

7

1. Payload2. Heat shield3. Payload adapter4. Equipment bay5. Auxiliary payload6. 4th stage tank7. 4th stage engine8. Antennae9. Reaction thruster10. Interstage 3/411. 3rd stage adapter12. 3rd stage motor13. Flex nozzle control14. Interstage 2/3 U . Interstage 2/3 L

16. 2nd stage tank17. Interstage ½ U18. 2nd stage retros19. Ullage rocket (4)20. Gimbal control21. Interstage ½ L22. 2nd stage engine23. 1st stage retro24. First stage motor25. TVC injectant tank26. Strap-on motor27. TVC system28. Core base shroud29. Roll control engine

Important elements of PSLV

A

A

B

B

C

C

D

D13

1415

15

16

17,19

21,23

20,22

24

25,27

26

2829

8

CARTOSAT – 2 CARTOSAT – 2 INDIA 686 kg INDIA 686 kg

CARTOSAT – 2 CARTOSAT – 2 INDIA 686 kg INDIA 686 kg

IMS -1IMS -1INDIA 83 kgINDIA 83 kg

IMS -1IMS -1INDIA 83 kgINDIA 83 kg

CAN X-2CAN X-2CANADACANADACAN X-2CAN X-2CANADACANADA

NLS-5 CAN X-6NLS-5 CAN X-6CANADACANADA

NLS-5 CAN X-6NLS-5 CAN X-6CANADACANADA

COMPASS -1COMPASS -1GERMANYGERMANY

COMPASS -1COMPASS -1GERMANYGERMANY

CUTE 1.7CUTE 1.7JAPANJAPAN

CUTE 1.7CUTE 1.7JAPANJAPAN

DELFI – C3DELFI – C3NETHERLANDS NETHERLANDS

DELFI – C3DELFI – C3NETHERLANDS NETHERLANDS

AAUSAT – llAAUSAT – llDENMARKDENMARK

AAUSAT – llAAUSAT – llDENMARKDENMARK

SEEDSSEEDSJAPANJAPANSEEDSSEEDSJAPANJAPAN

RUBIN 8RUBIN 8GERMANYGERMANY

RUBIN 8RUBIN 8GERMANYGERMANYDeployment of

ten

Satellites

PSLV C9

PSLV : Commercial phase

9

NLS-5NLS-5NLS-5NLS-5

PSLV C9: Spacecraft accommodation

RUBIN 8RUBIN 8GERMANYGERMANY

RUBIN 8RUBIN 8GERMANYGERMANY

CARTOSAT – 2 CARTOSAT – 2 INDIA 686 kgINDIA 686 kg

CARTOSAT – 2 CARTOSAT – 2 INDIA 686 kgINDIA 686 kg

IMS -1IMS -1INDIA 83 kgINDIA 83 kg

IMS -1IMS -1INDIA 83 kgINDIA 83 kg 10

11

PSLV

Inte

grati

on a

nd L

aunc

h

GSLV Configuration

4L40 + S125 + L37.5 + C12 LOW : 414 T Diameter : 3.4 m Heatshield : 3.8 m

Features : 3 stage vehicle Performance : GTO : 2 t.

Performance growth Potential : 2.5 t ( with

indigenous Cryo stage

12

Payload fairing

SatellitePayload adaptor

Equipment bay

Inter stage

GS3, Cryo stage (C12)

GS2, Liquid stage (L37.5)

Liquid strap on, (L40), 4 Nos.

Inter stage

Vented Inter stage

An exploded view of a vehicle

Solid motor (S139)

Lift off Wt. : 418 tOverall length : 49 mVehicle dia. : 2.8 mGTO P/L : 2 T

Lift off Wt. : 418 tOverall length : 49 mVehicle dia. : 2.8 mGTO P/L : 2 T

13

14

Flight Sequence

L110 Burnout &Cryo stage ignitiont = 310sh = 135kmV = 4.8km/s = 85

Payload fairingSeparationt = 253sh = 115km

S200 Separationt = 149.3sh = 67kmV = 2.2km/s = 72°

L110 Ignitiont = 110sh = 36.8km

Cryo 1st shut offt = 763sh = 151kmV = 8.37km/s = 90°

Cryo re-startt = 1063sh = 202kmV = 8.3km/s = 87°

Cryo burn outt = 1188sh = 273kmV =10.18km/s = 85°Orbit: 180 x 36000 km

7000 km

30002000 4000 50006000

1000

50

350

100

200

150

250

Lift off

Indigenous Cryo Stage Development Detailed qualifications tests have been carried out in engine in several ground tests. Flight stage is getting ready and expected to fly by September 2009.

15

Chandrayaan 1 Launched by PSLV 11: 313 tLaunched by PSLV 11: 313 t

Date of Launch : 22Date of Launch : 22ndnd Oct Oct

20082008

Chandrayaan 1Chandrayaan 1India 1380 kgIndia 1380 kgChandrayaan 1Chandrayaan 1India 1380 kgIndia 1380 kg

16

Sir 2 (Infrared spectrometer )

HYSI(Hyper spectral Imager)

Mini SAR

SWIM (Solar Wind Montor)

LLRI (Lunar laser ranging instrument)

HEX (High energy x-ray)

MIP (Moon Impact probe)

RDM (Radiation Dose Monitor)CENA (Chandrayaan energetic

Neutral Analyser)

TMC(Terrain Mapping camera)

M3(Moon mineralogy mapper)

(Miniature synthetic aperture radar)

(Compact imaging x-ray spectrometer)

Chandrayaan-1 Payloads

CIXS

17

254x 22932 km

LC : 508 x 7510 km

LBN-1 : 201 x 7502 km

LBN-2 : 183 x 255 km

LBN-3 : 102 x 255 km

LBN-4 : 102 x 103 km

IO : 254x 22,932 km

EBN-1 : 301 x 37,832 km

EBN-2 : 336 x 74,716 km

EBN-3 : 348 x 1,65,016 km

EBN-4 : 460 x 2,66,509 km

EBN-5 : 977 x 3,80,513 km

Moon

8th Nov 2008

18

Chandrayaan 1 Mission Profile

Chandrayaan1: 3D-view of crater on moon

Terrain Mapping Camera : 5M resolution; Date of pass - Nov 23, 2008

Area – 5 X 4.5 Km;

Crater

Rilles

19

Orbital Capabilities (kg)

Mars Venus Asteroid

PSLV 172-213 107-146 80-186

GSLV 402-584 247-328 150-443

Mk III 882-1060 542-719 182-972

Flyby Capabilities (kg)

Mars Venus Asteroid

728-777 717-766 556-862

1219-1302 1260-1346 625-1514

2617-2793 2705-2890 1342-3250

Missions to Mars, Venus, Asteroids

20

Space CraftSpace Craft

Equipment Equipment BayBay

C25C25

S200S200

GSLV MK-III

2S200 + L110 + C25 GLOW : 620 T MAX Dia :4 m Features :

3 stage vehicle Safe impact of all stages Performance : GTO P/L : 4.5 t 400 km LEO : 10 T Performance growth

potential : 5 to 6 t

L110

21

SRE -Configuration

22

Space capsule Recovery Experiment (SRE) Mission Sequence

635 Km

5 Km

2 Km

0 Km

100 Km

0

Altitude

Ground range (Km)

Time, s

Micro gravity

Expt.

De-boost

Main chute deployment

Velocity

0

93.2 m/s

47.4 m/s

Re-entry

Drogue chute deployment

Splash down

M 0.14

M 0.3

8.04 Km/s

M 30.2

2098.5

14919

2462.86

16303

2679

12 m/s

PSLV – L1.6

Launch capability - 1250 kg (min.)

(in 625 km SSPO)

Co passenger - 600 kg

SRE - 530 kg

16303 16303

2510.5

1600s

23

SRE-

1 Re

turn

to e

arth

20

07SR

E-1

Retu

rn to

ear

th

2007

24

Reusable Launch Vehicle

… for repeated use of the costly hardware

25

Reusable Launch Vehicle using Air Breathing Propulsion

26

Aero thermodynamic characterisation of

the winged body

NG&C during re-entry, gliding, cruise, approach & landing regimes

Thermal management (TPS Design & Evaluation), Blackout management.Unmanned autonomousLanding technology

Reusable structures

Reusable Semicryo/ Cryo Propulsion Systems

Landing using parachute /thrusters/ airbags

Two Stage To Orbit (TSTO)

27

Manoeuvers

SatelliteDeployment

Turn

Cruise at M 0.8

Lift offHorizontalLanding

Parachute deployment

Re-entry

Deorbit

Landing manoeuvers &

landing on legs

Fully reusable TSTO flight profile

Down/cross range manoeuvers

Re-orientation

Separation at 80-100 km, M 10-12

Re-entry

28

Indian Human Space Flight Programme

To develop a space vehicle to carry crew of two to LEO and return safely to a predetermined destination on earth

Orbital vehicle

Crew module

Service module

Crew escape system (ces)

• Mission duration up to 7 days• Emergency mission abort and

crew rescue provision• Crew module designed for re-

entry and service module for mission management.

• Mission duration up to 7 days• Emergency mission abort and

crew rescue provision• Crew module designed for re-

entry and service module for mission management. 29

GSLV MkII Manned Configuration

Launch Escape

System

Crew Module

Service Module

Vehicle Height : 51.5 mLift-off Mass : 417 t

Manned capsule

Human Space Mission : Vehicle configuration

30

Take off

First Stage Separation

Second StageSeparation

LEO Injection Re-orienting& Retro Firing

Aero Braking

Parachute Deployment

Retro Firing & Splashing in Water

Floatation SystemDeployment

CS Separation

Mission profile

31

Robust Thermal Protection Systems

Redundant NGC System/Advanced

Power Bus

Crew Escape System

Environment Control and Life

Support Systems

Manned mission - New TechnologiesManned mission - New Technologies

Mission Management with

Human in Loop

Crew Module Design and Aerodynamic

Control

Crew Health Monitoring

Systems

Space Suit & Crew Seat

Crew Training & Facilities

Manned Space

Vehicle Simulators

Man – Rating of Launch Vehicle

32

GSLV MKIII : 3 stage2S200+L110+C25

LEO : 10 t Lunar circular orbit : 2 t

ISRO HEAVY LIFT VEHICLE(4SC460+SC800)+SC460+C100

LEO : 100 t Lunar circular orbit : 20 t

To reach Moon by human and return...

42 m

73 m

Long - Term PerspectiveLong - Term Perspective 4t LEO 20 t in Lunar Orbit

10.2 km/s 19.2 km/s

GSLV MKIII can be used to carry crew of 4 to 6 for demonstrating

• Rendezvous, Docking and EVA

• Long duration missions

Manned Mission to Moon/Mars

Heavy lift launch vehicle, engines

ΔV : 10.23 km/sGTO P/L : 4 t

ΔV : 19.2 km/sLunar P/L : 20t

33

Semi cryogenic Engines

Indigenous Cryogenic Upper Stage (CUS)

Two Stage To Orbit to reduce the Cost

Geo Synchronous Launch Vehicle MK III

Indian Human Space Mission

High thrust cryogenic Engine Boosters

Interplanetary Mission to beyond MARS

Air- breathing Engines

Advanced Propulsion for Planetary Exploration

Single Stage To Orbit using Air breathing Propulsion2025

2009

2010

2015

Reusable Launch Vehicle 2016

2020

2018

Indian Space Transportation Vision 2025

2017

34

Thank You

35