GSAT-14

GSLV-D5/GSAT-14 MISSIONGLIMPSES OF LAUNCH CAMPAIGN

The GSAT-14 is a communicati on spacecraft with primarily C and Ku band payloads. There are 6 transponders each operati ng in C and Ku bands. There is also a Ka band payload component. The spacecraft employs I-2K bus structure. The objecti ve of the spacecraft will be conti nuati on of the services provided by GSAT-3 Spacecraft , enhance Ku band transponders and provide a platf orm for Ka band propagati on studies.

GSAT-14 Spacecraft

Published by : Documentation and Information Services-LV Projects, VSSC, ThiruvananthapuramPrinted at : Akshara Off set, Thiruvananthapuram. #2471174

GS1 STACKING

GS2 STACKING

ENCAPSULATED ASSEMBLY

GS1 SEGMENT ASSEMBLY

CUS ASSEMBLY

FULLY ASSEMBLED VEHICLE AT VAB

L40 STAGE ASSEMBLY

SATELLITE ASSEMBLY

VEHICLE MOVEMENT TO UT

Satellite OverviewI-2K Bus74 deg E longitude orbital slot Communicati on Payloads• 6 extended C band & 6 Ku band transpondersExperiments• 2 Ka band beacons, Thermal Control Coati ng Experiment (TCCE), Fiber

Opti c Gyro (FOG), Acti ve Pixel Sun Sensor (APSS) based Digital Sun Sensor (DSS), Field Programmable Gate Array (FPGA) based earth sensor & aero-thermal fl ux sensor

850 kg dry mass & 1982 kg lift off mass Around 2600 W power generati on

Events Time (s)

Alti tude (km)

Relati ve velocity

(m/s)

Inerti al velocity

(m/s)

4L40H Igniti on -4.8 0.03 0 451.9

S139 Igniti on 0 0.03 0 451.9

4L40H Shut off 148.94 69.97 2398.9 2822.7

GS2 Igniti on 149.54 70.44 2399.8 2823.8

GS1 Separati on 151.14 71.66 2398.2 2822.9

IS 1/2 M Separati on 156.94 75.98 2451.0 2878.2

PLF Separati on 228.26 115.00 3422.2 3866.6

GS2 Shut off 289.32 131.34 4928.5 5375.9

GS2 Separati on 292.82 131.94 4946.6 5393.8

CUS Igniti on 293.82 132.11 4946.3 5393.5

CUS Shut off 1012.48 204.07 9777.3 10228.4

CUS Burn out 1014.82 205.43 9785.6 10236.6

GSAT-14 Separati on 1027.48 213.37 9778.1 10229.5

GSLV-D5 Flight Sequence

GSLV-D5 vehicle is confi gured, similar to GSLV-F01/F04 vehicles fl own earlier, with 3.4 m diameter metallic PayLoad Fairing and with 12 t indigenous cryogenic stage. The overall vehicle length is 49.1 m with a lift -off mass of 416 t.

The enti re aerodynamic characterizati on of GSLV has been revisited. More than 900 blow-downs have been carried out in the wind tunnels of NAL, Bangalore & GK, Russia to characterize the vehicle in terms of aerodynamic forces and moments, steady & unsteady aerodynamic loads and aero-elasti c contributi ons. The wind tunnel test results were augmented with the theoreti cal esti mated loads on protrusions through extensive CFD simulati ons. The aerodynamic load changes due to jet eff ects were also studied. Vehicle structural and control system design margins were established with revised aerodynamic data.

The Cryogenic Engine develops a nominal thrust of 73.6 kN (vacuum) with a specifi c impulse of 452 seconds. The engine works on Stage Combusti on Cycle in the pump-fed mode with an integrated turbopump running at around 40,000 rpm. The steering engine with the thrust of 2.2 kN provides three-axis control of the vehicle during thrusti ng phase. During coast phase, the OSS provides the required control to the vehicle. The unique feature of this engine is the closed loop control of both thrust and mixture rati os, which ensures opti mum propellant management during the mission. The overall stage length is 8469 mm and the stage dry mass is 2548 kg.

CUS Engine characteristi csParameter Nominal Uprated (9.5%)

Thrust (kN) 73.6 80.5Thrust - Main Engine (kN) 69.3 75.8Thrust - Steering Engine (kN) 2.2 2.4Total Burning Durati on (s) 722.12 (Uprati ng:398 s)Specifi c Impulse (s) 452±3 452±3Propellant fl ow rate (kg/s) 16.6 18.2

Fuel Booster Turbo Pump (FBTP): o Seal clearances increased to ensure smooth running of

turbine shaft without seizure.o 40 micron fi lter introduced in the booster turbine inlet to

prevent entry of contaminants. o Functi onal tests carried out with cryo fl uids simulati ng fl ight

operati ng conditi ons.

Thrust Frame: o Subjected to cold treatment to improve the load carrying

capability. Improvement in yield strength demonstrated through integrated structural test.

Modifi cati on of Igniti on Sequenceo An orifi ce is introduced in the booster turbine inlet and

igniti on sequence has been tuned to reduce the igniti on pressure peak.

o High Alti tude Tests (HAT) simulati ng the fl ight environment was conducted successfully demonstrati ng the igniti on of Main Engine (ME), Steering Engine (SE) and Gas Generator (GG) in fl ight confi gurati on.

Vehicle Confi guration

GS2-Cryo Stage Separati on

GS2 Tank

Wind Tunnel Model in Tunnel

FBTP

LH2 PAS

HAT Facility CUS Engine in HAT Facility

Polyimide Pipelines

Mission Specifi cati on

Perigee : 180 ± 5 km

Apogee : 35975 ± 675 km

Inclinati on : 19.29 ± 0.1°

Argument of Perigee : 178 ± 0.2°

Level Sensors

LH2 Propellant Acquisiti on System (LH2-PAS): This propellant intake device has been indigenously developed and successfully qualifi ed through rigorous tests.

Polyimide pipelines: 27 polyimide pipelines of diff erent profi les and sizes have been used in CUS-05, out of which 16 numbers are indigenously realized.

Level sensors: LOX and LH2level sensors, which control and maintain quanti ty of propellant during fi lling and ti ll lift -off , have been indigenously developed and qualifi ed.

The launch att empt of GSLV-D5 on August 19, 2013, was aborted due to a leak observed in the UH25 fuel system of the Liquid Second Stage (GS2) during the fi nal phase of the countdown at 1:30 hrs before lift -off (T0). The Failure analysis board (FAB) concluded that a crack, att ributed to Stress Corrosion Cracking (SCC), in the parent metal region of UH25 tank (material: Aluminium alloy AA7020) was the cause for the leak during the prefl ight pressurizati on of tank at T0-1:47 hr. Based on the impact assessment of the UH25 spillage on the vehicle systems, the GSLV-D5 vehicle for the next mission was prepared with new stages of GS2, L40 and GS1 (including core base shroud, interstages IS1/2V and IS1/2M). The Cryo stage, Payload fairing, Equipment bay and the GSAT-14 spacecraft were preserved and reused.

GSLV-D5/GSAT-14 Mission

GSLV-D5 is the fourth developmental fl ight of ISRO’s Geosynchronous Satellite Launch Vehicle (GSLV) with the objecti ve of demonstrati ng successful fl ight test of indigenously developed cryogenic stage (third stage) of GSLV and inject GSAT-14 spacecraft into a Geostati onary Transfer Orbit (GTO).

GSLV-D5 Vehicle Confi guration

GSLV-D5 stage characteristi cs

Parameters

Stages

GS1 (4L40H & S139) GS2 GS3

4L40H S139 L37.5H CUS12

Length (m) 19.7 20.1 11.6 8.7

Diameter (m) 2.1 2.8 2.8 2.8

Propellants UH25 & N2O4 HTPB UH25 & N2O4 LH2 & LOX

Propellant mass (t) 4x42.6 138.1 39.4 12.8

Stage mass at lift -off (t)

190.7 161.1 44.4 15.4

• Redesign of the Cryo stage lower shroud (which protects the cryogenic engine bay during atmospheric fl ight phase) and wire tunnel for higher fl ight loads and qualifi cati on through pressure tests, integrated acousti c tests and separati on tests.

Design Improvements of vehicle systems

• Relocati on of GS2-Cryo stage separati on plane electrical connector lanyard mounti ng bracket from lower shroud to the lower truss structural members to prevent inadvertent connector de-mati ng due to aerodynamic disturbance.

• GSLV Video Imaging System (GVIS) introduced to view the lower shroud movement during transonic regime, GS2 sep-arati on and CUS igniti on.

• The tank material for the new GS2 stage is changed from

AFNOR7020 to AA2219, which has bett er resistance to Stress Corrosion Cracking (SCC). The mass increase for the GSLV-D5 GS2 tank is 120 Kg which is mainly due to the tank constructi on with variable thickness in chemically milled area and increase in number of petals in fore end, aft end and common bulkhead domes.

Aerodynamic characterization and design validation

Design improvements in cryogenic stage systems

Indigenous elements in CUS-05

CUS HAT Facility Establishment

Thrust Chamber Test facility (TCT) established for C25 engine at LPSC Mahendragiri Faciliti es (LMF) was augmented to perform High Alti tude Test (HAT) of CUS engine.

PLFØ 3400

Ø 2900

��3 �����

Ø 2900

��2 �L3�����

Ø 2�00

Ø 2�00

��� ���39�4 L40��

CUS systems • Main engine• Steering engines – 2 no.• LOX & LH2 insulated propellant tanks and tank

internals• LOX & LH2 booster turbo pumps• Inter stage structures• Fluid control components / module• Pyro systems• Stage separati on systems• Stage fl uid ground servicing systems• Orientati on and Stabilizati on Systems (OSS)

CUS Engine Hot Test

CUS Side View

CUS Front View

Cryogenic Upper Stage (CUS-05) for GSLV-D5

CUS-05 is dimensionally and functi onally identi cal to the CUS-03 stage fl own in GSLV-D3 mission.

Cryo Stage Lower Shroud

3400

2900

2800

2100

GS1 (S139+4L40H)

GS2 (L37.5H)

GS3 (CUS12)

PLF

GSLV-D5 vehicle is confi gured, similar to GSLV-F01/F04 vehicles fl own earlier, with 3.4 m diameter metallic PayLoad Fairing and with 12 t indigenous cryogenic stage. The overall vehicle length is 49.1 m with a lift -off mass of 416 t.

The enti re aerodynamic characterizati on of GSLV has been revisited. More than 900 blow-downs have been carried out in the wind tunnels of NAL, Bangalore & GK, Russia to characterize the vehicle in terms of aerodynamic forces and moments, steady & unsteady aerodynamic loads and aero-elasti c contributi ons. The wind tunnel test results were augmented with the theoreti cal esti mated loads on protrusions through extensive CFD simulati ons. The aerodynamic load changes due to jet eff ects were also studied. Vehicle structural and control system design margins were established with revised aerodynamic data.

The Cryogenic Engine develops a nominal thrust of 73.6 kN (vacuum) with a specifi c impulse of 452 seconds. The engine works on Stage Combusti on Cycle in the pump-fed mode with an integrated turbopump running at around 40,000 rpm. The steering engine with the thrust of 2.2 kN provides three-axis control of the vehicle during thrusti ng phase. During coast phase, the OSS provides the required control to the vehicle. The unique feature of this engine is the closed loop control of both thrust and mixture rati os, which ensures opti mum propellant management during the mission. The overall stage length is 8469 mm and the stage dry mass is 2548 kg.

CUS Engine characteristi csParameter Nominal Uprated (9.5%)

Thrust (kN) 73.6 80.5Thrust - Main Engine (kN) 69.3 75.8Thrust - Steering Engine (kN) 2.2 2.4Total Burning Durati on (s) 722.12 (Uprati ng:398 s)Specifi c Impulse (s) 452±3 452±3Propellant fl ow rate (kg/s) 16.6 18.2

Fuel Booster Turbo Pump (FBTP): o Seal clearances increased to ensure smooth running of

turbine shaft without seizure.o 40 micron fi lter introduced in the booster turbine inlet to

prevent entry of contaminants. o Functi onal tests carried out with cryo fl uids simulati ng fl ight

operati ng conditi ons.

Thrust Frame: o Subjected to cold treatment to improve the load carrying

capability. Improvement in yield strength demonstrated through integrated structural test.

Modifi cati on of Igniti on Sequenceo An orifi ce is introduced in the booster turbine inlet and

igniti on sequence has been tuned to reduce the igniti on pressure peak.

o High Alti tude Tests (HAT) simulati ng the fl ight environment was conducted successfully demonstrati ng the igniti on of Main Engine (ME), Steering Engine (SE) and Gas Generator (GG) in fl ight confi gurati on.

Vehicle Confi guration

GS2-Cryo Stage Separati on

GS2 Tank

Wind Tunnel Model in Tunnel

FBTP

LH2 PAS

HAT Facility CUS Engine in HAT Facility

Polyimide Pipelines

Mission Specifi cati on

Perigee : 180 ± 5 km

Apogee : 35975 ± 675 km

Inclinati on : 19.29 ± 0.1°

Argument of Perigee : 178 ± 0.2°

Level Sensors

LH2 Propellant Acquisiti on System (LH2-PAS): This propellant intake device has been indigenously developed and successfully qualifi ed through rigorous tests.

Polyimide pipelines: 27 polyimide pipelines of diff erent profi les and sizes have been used in CUS-05, out of which 16 numbers are indigenously realized.

Level sensors: LOX and LH2level sensors, which control and maintain quanti ty of propellant during fi lling and ti ll lift -off , have been indigenously developed and qualifi ed.

The launch att empt of GSLV-D5 on August 19, 2013, was aborted due to a leak observed in the UH25 fuel system of the Liquid Second Stage (GS2) during the fi nal phase of the countdown at 1:30 hrs before lift -off (T0). The Failure analysis board (FAB) concluded that a crack, att ributed to Stress Corrosion Cracking (SCC), in the parent metal region of UH25 tank (material: Aluminium alloy AA7020) was the cause for the leak during the prefl ight pressurizati on of tank at T0-1:47 hr. Based on the impact assessment of the UH25 spillage on the vehicle systems, the GSLV-D5 vehicle for the next mission was prepared with new stages of GS2, L40 and GS1 (including core base shroud, interstages IS1/2V and IS1/2M). The Cryo stage, Payload fairing, Equipment bay and the GSAT-14 spacecraft were preserved and reused.

GSLV-D5/GSAT-14 Mission

GSLV-D5 is the fourth developmental fl ight of ISRO’s Geosynchronous Satellite Launch Vehicle (GSLV) with the objecti ve of demonstrati ng successful fl ight test of indigenously developed cryogenic stage (third stage) of GSLV and inject GSAT-14 spacecraft into a Geostati onary Transfer Orbit (GTO).

GSLV-D5 Vehicle Confi guration

GSLV-D5 stage characteristi cs

Parameters

Stages

GS1 (4L40H & S139) GS2 GS3

4L40H S139 L37.5H CUS12

Length (m) 19.7 20.1 11.6 8.7

Diameter (m) 2.1 2.8 2.8 2.8

Propellants UH25 & N2O4 HTPB UH25 & N2O4 LH2 & LOX

Propellant mass (t) 4x42.6 138.1 39.4 12.8

Stage mass at lift -off (t)

190.7 161.1 44.4 15.4

• Redesign of the Cryo stage lower shroud (which protects the cryogenic engine bay during atmospheric fl ight phase) and wire tunnel for higher fl ight loads and qualifi cati on through pressure tests, integrated acousti c tests and separati on tests.

Design Improvements of vehicle systems

• Relocati on of GS2-Cryo stage separati on plane electrical connector lanyard mounti ng bracket from lower shroud to the lower truss structural members to prevent inadvertent connector de-mati ng due to aerodynamic disturbance.

• GSLV Video Imaging System (GVIS) introduced to view the lower shroud movement during transonic regime, GS2 sep-arati on and CUS igniti on.

• The tank material for the new GS2 stage is changed from

AFNOR7020 to AA2219, which has bett er resistance to Stress Corrosion Cracking (SCC). The mass increase for the GSLV-D5 GS2 tank is 120 Kg which is mainly due to the tank constructi on with variable thickness in chemically milled area and increase in number of petals in fore end, aft end and common bulkhead domes.

Aerodynamic characterization and design validation

Design improvements in cryogenic stage systems

Indigenous elements in CUS-05

CUS HAT Facility Establishment

Thrust Chamber Test facility (TCT) established for C25 engine at LPSC Mahendragiri Faciliti es (LMF) was augmented to perform High Alti tude Test (HAT) of CUS engine.

PLFØ 3400

Ø 2900

��3 �����

Ø 2900

��2 �L3�����

Ø 2�00

Ø 2�00

��� ���39�4 L40��

CUS systems • Main engine• Steering engines – 2 no.• LOX & LH2 insulated propellant tanks and tank

internals• LOX & LH2 booster turbo pumps• Inter stage structures• Fluid control components / module• Pyro systems• Stage separati on systems• Stage fl uid ground servicing systems• Orientati on and Stabilizati on Systems (OSS)

CUS Engine Hot Test

CUS Side View

CUS Front View

Cryogenic Upper Stage (CUS-05) for GSLV-D5

CUS-05 is dimensionally and functi onally identi cal to the CUS-03 stage fl own in GSLV-D3 mission.

Cryo Stage Lower Shroud

3400

2900

2800

2100

GS1 (S139+4L40H)

GS2 (L37.5H)

GS3 (CUS12)

PLF

GSLV-D5 vehicle is confi gured, similar to GSLV-F01/F04 vehicles fl own earlier, with 3.4 m diameter metallic PayLoad Fairing and with 12 t indigenous cryogenic stage. The overall vehicle length is 49.1 m with a lift -off mass of 416 t.

The enti re aerodynamic characterizati on of GSLV has been revisited. More than 900 blow-downs have been carried out in the wind tunnels of NAL, Bangalore & GK, Russia to characterize the vehicle in terms of aerodynamic forces and moments, steady & unsteady aerodynamic loads and aero-elasti c contributi ons. The wind tunnel test results were augmented with the theoreti cal esti mated loads on protrusions through extensive CFD simulati ons. The aerodynamic load changes due to jet eff ects were also studied. Vehicle structural and control system design margins were established with revised aerodynamic data.

The Cryogenic Engine develops a nominal thrust of 73.6 kN (vacuum) with a specifi c impulse of 452 seconds. The engine works on Stage Combusti on Cycle in the pump-fed mode with an integrated turbopump running at around 40,000 rpm. The steering engine with the thrust of 2.2 kN provides three-axis control of the vehicle during thrusti ng phase. During coast phase, the OSS provides the required control to the vehicle. The unique feature of this engine is the closed loop control of both thrust and mixture rati os, which ensures opti mum propellant management during the mission. The overall stage length is 8469 mm and the stage dry mass is 2548 kg.

CUS Engine characteristi csParameter Nominal Uprated (9.5%)

Thrust (kN) 73.6 80.5Thrust - Main Engine (kN) 69.3 75.8Thrust - Steering Engine (kN) 2.2 2.4Total Burning Durati on (s) 722.12 (Uprati ng:398 s)Specifi c Impulse (s) 452±3 452±3Propellant fl ow rate (kg/s) 16.6 18.2

Fuel Booster Turbo Pump (FBTP): o Seal clearances increased to ensure smooth running of

turbine shaft without seizure.o 40 micron fi lter introduced in the booster turbine inlet to

prevent entry of contaminants. o Functi onal tests carried out with cryo fl uids simulati ng fl ight

operati ng conditi ons.

Thrust Frame: o Subjected to cold treatment to improve the load carrying

capability. Improvement in yield strength demonstrated through integrated structural test.

Modifi cati on of Igniti on Sequenceo An orifi ce is introduced in the booster turbine inlet and

igniti on sequence has been tuned to reduce the igniti on pressure peak.

o High Alti tude Tests (HAT) simulati ng the fl ight environment was conducted successfully demonstrati ng the igniti on of Main Engine (ME), Steering Engine (SE) and Gas Generator (GG) in fl ight confi gurati on.

Vehicle Confi guration

GS2-Cryo Stage Separati on

GS2 Tank

Wind Tunnel Model in Tunnel

FBTP

LH2 PAS

HAT Facility CUS Engine in HAT Facility

Polyimide Pipelines

Mission Specifi cati on

Perigee : 180 ± 5 km

Apogee : 35975 ± 675 km

Inclinati on : 19.29 ± 0.1°

Argument of Perigee : 178 ± 0.2°

Level Sensors

LH2 Propellant Acquisiti on System (LH2-PAS): This propellant intake device has been indigenously developed and successfully qualifi ed through rigorous tests.

Polyimide pipelines: 27 polyimide pipelines of diff erent profi les and sizes have been used in CUS-05, out of which 16 numbers are indigenously realized.

Level sensors: LOX and LH2level sensors, which control and maintain quanti ty of propellant during fi lling and ti ll lift -off , have been indigenously developed and qualifi ed.

The launch att empt of GSLV-D5 on August 19, 2013, was aborted due to a leak observed in the UH25 fuel system of the Liquid Second Stage (GS2) during the fi nal phase of the countdown at 1:30 hrs before lift -off (T0). The Failure analysis board (FAB) concluded that a crack, att ributed to Stress Corrosion Cracking (SCC), in the parent metal region of UH25 tank (material: Aluminium alloy AA7020) was the cause for the leak during the prefl ight pressurizati on of tank at T0-1:47 hr. Based on the impact assessment of the UH25 spillage on the vehicle systems, the GSLV-D5 vehicle for the next mission was prepared with new stages of GS2, L40 and GS1 (including core base shroud, interstages IS1/2V and IS1/2M). The Cryo stage, Payload fairing, Equipment bay and the GSAT-14 spacecraft were preserved and reused.

GSLV-D5/GSAT-14 Mission

GSLV-D5 is the fourth developmental fl ight of ISRO’s Geosynchronous Satellite Launch Vehicle (GSLV) with the objecti ve of demonstrati ng successful fl ight test of indigenously developed cryogenic stage (third stage) of GSLV and inject GSAT-14 spacecraft into a Geostati onary Transfer Orbit (GTO).

GSLV-D5 Vehicle Confi guration

GSLV-D5 stage characteristi cs

Parameters

Stages

GS1 (4L40H & S139) GS2 GS3

4L40H S139 L37.5H CUS12

Length (m) 19.7 20.1 11.6 8.7

Diameter (m) 2.1 2.8 2.8 2.8

Propellants UH25 & N2O4 HTPB UH25 & N2O4 LH2 & LOX

Propellant mass (t) 4x42.6 138.1 39.4 12.8

Stage mass at lift -off (t)

190.7 161.1 44.4 15.4

• Redesign of the Cryo stage lower shroud (which protects the cryogenic engine bay during atmospheric fl ight phase) and wire tunnel for higher fl ight loads and qualifi cati on through pressure tests, integrated acousti c tests and separati on tests.

Design Improvements of vehicle systems

• Relocati on of GS2-Cryo stage separati on plane electrical connector lanyard mounti ng bracket from lower shroud to the lower truss structural members to prevent inadvertent connector de-mati ng due to aerodynamic disturbance.

• GSLV Video Imaging System (GVIS) introduced to view the lower shroud movement during transonic regime, GS2 sep-arati on and CUS igniti on.

• The tank material for the new GS2 stage is changed from

AFNOR7020 to AA2219, which has bett er resistance to Stress Corrosion Cracking (SCC). The mass increase for the GSLV-D5 GS2 tank is 120 Kg which is mainly due to the tank constructi on with variable thickness in chemically milled area and increase in number of petals in fore end, aft end and common bulkhead domes.

Aerodynamic characterization and design validation

Design improvements in cryogenic stage systems

Indigenous elements in CUS-05

CUS HAT Facility Establishment

Thrust Chamber Test facility (TCT) established for C25 engine at LPSC Mahendragiri Faciliti es (LMF) was augmented to perform High Alti tude Test (HAT) of CUS engine.

PLFØ 3400

Ø 2900

��3 �����

Ø 2900

��2 �L3�����

Ø 2�00

Ø 2�00

��� ���39�4 L40��

CUS systems • Main engine• Steering engines – 2 no.• LOX & LH2 insulated propellant tanks and tank

internals• LOX & LH2 booster turbo pumps• Inter stage structures• Fluid control components / module• Pyro systems• Stage separati on systems• Stage fl uid ground servicing systems• Orientati on and Stabilizati on Systems (OSS)

CUS Engine Hot Test

CUS Side View

CUS Front View

Cryogenic Upper Stage (CUS-05) for GSLV-D5

CUS-05 is dimensionally and functi onally identi cal to the CUS-03 stage fl own in GSLV-D3 mission.

Cryo Stage Lower Shroud

3400

2900

2800

2100

GS1 (S139+4L40H)

GS2 (L37.5H)

GS3 (CUS12)

PLF

GSLV-D5 vehicle is confi gured, similar to GSLV-F01/F04 vehicles fl own earlier, with 3.4 m diameter metallic PayLoad Fairing and with 12 t indigenous cryogenic stage. The overall vehicle length is 49.1 m with a lift -off mass of 416 t.

The enti re aerodynamic characterizati on of GSLV has been revisited. More than 900 blow-downs have been carried out in the wind tunnels of NAL, Bangalore & GK, Russia to characterize the vehicle in terms of aerodynamic forces and moments, steady & unsteady aerodynamic loads and aero-elasti c contributi ons. The wind tunnel test results were augmented with the theoreti cal esti mated loads on protrusions through extensive CFD simulati ons. The aerodynamic load changes due to jet eff ects were also studied. Vehicle structural and control system design margins were established with revised aerodynamic data.

The Cryogenic Engine develops a nominal thrust of 73.6 kN (vacuum) with a specifi c impulse of 452 seconds. The engine works on Stage Combusti on Cycle in the pump-fed mode with an integrated turbopump running at around 40,000 rpm. The steering engine with the thrust of 2.2 kN provides three-axis control of the vehicle during thrusti ng phase. During coast phase, the OSS provides the required control to the vehicle. The unique feature of this engine is the closed loop control of both thrust and mixture rati os, which ensures opti mum propellant management during the mission. The overall stage length is 8469 mm and the stage dry mass is 2548 kg.

CUS Engine characteristi csParameter Nominal Uprated (9.5%)

Thrust (kN) 73.6 80.5Thrust - Main Engine (kN) 69.3 75.8Thrust - Steering Engine (kN) 2.2 2.4Total Burning Durati on (s) 722.12 (Uprati ng:398 s)Specifi c Impulse (s) 452±3 452±3Propellant fl ow rate (kg/s) 16.6 18.2

Fuel Booster Turbo Pump (FBTP): o Seal clearances increased to ensure smooth running of

turbine shaft without seizure.o 40 micron fi lter introduced in the booster turbine inlet to

prevent entry of contaminants. o Functi onal tests carried out with cryo fl uids simulati ng fl ight

operati ng conditi ons.

Thrust Frame: o Subjected to cold treatment to improve the load carrying

capability. Improvement in yield strength demonstrated through integrated structural test.

Modifi cati on of Igniti on Sequenceo An orifi ce is introduced in the booster turbine inlet and

igniti on sequence has been tuned to reduce the igniti on pressure peak.

o High Alti tude Tests (HAT) simulati ng the fl ight environment was conducted successfully demonstrati ng the igniti on of Main Engine (ME), Steering Engine (SE) and Gas Generator (GG) in fl ight confi gurati on.

Vehicle Confi guration

GS2-Cryo Stage Separati on

GS2 Tank

Wind Tunnel Model in Tunnel

FBTP

LH2 PAS

HAT Facility CUS Engine in HAT Facility

Polyimide Pipelines

Mission Specifi cati on

Perigee : 180 ± 5 km

Apogee : 35975 ± 675 km

Inclinati on : 19.29 ± 0.1°

Argument of Perigee : 178 ± 0.2°

Level Sensors

LH2 Propellant Acquisiti on System (LH2-PAS): This propellant intake device has been indigenously developed and successfully qualifi ed through rigorous tests.

Polyimide pipelines: 27 polyimide pipelines of diff erent profi les and sizes have been used in CUS-05, out of which 16 numbers are indigenously realized.

Level sensors: LOX and LH2level sensors, which control and maintain quanti ty of propellant during fi lling and ti ll lift -off , have been indigenously developed and qualifi ed.

The launch att empt of GSLV-D5 on August 19, 2013, was aborted due to a leak observed in the UH25 fuel system of the Liquid Second Stage (GS2) during the fi nal phase of the countdown at 1:30 hrs before lift -off (T0). The Failure analysis board (FAB) concluded that a crack, att ributed to Stress Corrosion Cracking (SCC), in the parent metal region of UH25 tank (material: Aluminium alloy AA7020) was the cause for the leak during the prefl ight pressurizati on of tank at T0-1:47 hr. Based on the impact assessment of the UH25 spillage on the vehicle systems, the GSLV-D5 vehicle for the next mission was prepared with new stages of GS2, L40 and GS1 (including core base shroud, interstages IS1/2V and IS1/2M). The Cryo stage, Payload fairing, Equipment bay and the GSAT-14 spacecraft were preserved and reused.

GSLV-D5/GSAT-14 Mission

GSLV-D5 is the fourth developmental fl ight of ISRO’s Geosynchronous Satellite Launch Vehicle (GSLV) with the objecti ve of demonstrati ng successful fl ight test of indigenously developed cryogenic stage (third stage) of GSLV and inject GSAT-14 spacecraft into a Geostati onary Transfer Orbit (GTO).

GSLV-D5 Vehicle Confi guration

GSLV-D5 stage characteristi cs

Parameters

Stages

GS1 (4L40H & S139) GS2 GS3

4L40H S139 L37.5H CUS12

Length (m) 19.7 20.1 11.6 8.7

Diameter (m) 2.1 2.8 2.8 2.8

Propellants UH25 & N2O4 HTPB UH25 & N2O4 LH2 & LOX

Propellant mass (t) 4x42.6 138.1 39.4 12.8

Stage mass at lift -off (t)

190.7 161.1 44.4 15.4

• Redesign of the Cryo stage lower shroud (which protects the cryogenic engine bay during atmospheric fl ight phase) and wire tunnel for higher fl ight loads and qualifi cati on through pressure tests, integrated acousti c tests and separati on tests.

Design Improvements of vehicle systems

• Relocati on of GS2-Cryo stage separati on plane electrical connector lanyard mounti ng bracket from lower shroud to the lower truss structural members to prevent inadvertent connector de-mati ng due to aerodynamic disturbance.

• GSLV Video Imaging System (GVIS) introduced to view the lower shroud movement during transonic regime, GS2 sep-arati on and CUS igniti on.

• The tank material for the new GS2 stage is changed from

AFNOR7020 to AA2219, which has bett er resistance to Stress Corrosion Cracking (SCC). The mass increase for the GSLV-D5 GS2 tank is 120 Kg which is mainly due to the tank constructi on with variable thickness in chemically milled area and increase in number of petals in fore end, aft end and common bulkhead domes.

Aerodynamic characterization and design validation

Design improvements in cryogenic stage systems

Indigenous elements in CUS-05

CUS HAT Facility Establishment

Thrust Chamber Test facility (TCT) established for C25 engine at LPSC Mahendragiri Faciliti es (LMF) was augmented to perform High Alti tude Test (HAT) of CUS engine.

PLFØ 3400

Ø 2900

��3 �����

Ø 2900

��2 �L3�����

Ø 2�00

Ø 2�00

��� ���39�4 L40��

CUS systems • Main engine• Steering engines – 2 no.• LOX & LH2 insulated propellant tanks and tank

internals• LOX & LH2 booster turbo pumps• Inter stage structures• Fluid control components / module• Pyro systems• Stage separati on systems• Stage fl uid ground servicing systems• Orientati on and Stabilizati on Systems (OSS)

CUS Engine Hot Test

CUS Side View

CUS Front View

Cryogenic Upper Stage (CUS-05) for GSLV-D5

CUS-05 is dimensionally and functi onally identi cal to the CUS-03 stage fl own in GSLV-D3 mission.

Cryo Stage Lower Shroud

3400

2900

2800

2100

GS1 (S139+4L40H)

GS2 (L37.5H)

GS3 (CUS12)

PLF

GSAT-14

GSLV-D5/GSAT-14 MISSIONGLIMPSES OF LAUNCH CAMPAIGN

The GSAT-14 is a communicati on spacecraft with primarily C and Ku band payloads. There are 6 transponders each operati ng in C and Ku bands. There is also a Ka band payload component. The spacecraft employs I-2K bus structure. The objecti ve of the spacecraft will be conti nuati on of the services provided by GSAT-3 Spacecraft , enhance Ku band transponders and provide a platf orm for Ka band propagati on studies.

GSAT-14 Spacecraft

Published by : Documentation and Information Services-LV Projects, VSSC, ThiruvananthapuramPrinted at : Akshara Off set, Thiruvananthapuram. #2471174

GS1 STACKING

GS2 STACKING

ENCAPSULATED ASSEMBLY

GS1 SEGMENT ASSEMBLY

CUS ASSEMBLY

FULLY ASSEMBLED VEHICLE AT VAB

L40 STAGE ASSEMBLY

SATELLITE ASSEMBLY

VEHICLE MOVEMENT TO UT

Satellite OverviewI-2K Bus74 deg E longitude orbital slot Communicati on Payloads• 6 extended C band & 6 Ku band transpondersExperiments• 2 Ka band beacons, Thermal Control Coati ng Experiment (TCCE), Fiber

Opti c Gyro (FOG), Acti ve Pixel Sun Sensor (APSS) based Digital Sun Sensor (DSS), Field Programmable Gate Array (FPGA) based earth sensor & aero-thermal fl ux sensor

850 kg dry mass & 1982 kg lift off mass Around 2600 W power generati on

Events Time (s)

Alti tude (km)

Relati ve velocity

(m/s)

Inerti al velocity

(m/s)

4L40H Igniti on -4.8 0.03 0 451.9

S139 Igniti on 0 0.03 0 451.9

4L40H Shut off 148.94 69.97 2398.9 2822.7

GS2 Igniti on 149.54 70.44 2399.8 2823.8

GS1 Separati on 151.14 71.66 2398.2 2822.9

IS 1/2 M Separati on 156.94 75.98 2451.0 2878.2

PLF Separati on 228.26 115.00 3422.2 3866.6

GS2 Shut off 289.32 131.34 4928.5 5375.9

GS2 Separati on 292.82 131.94 4946.6 5393.8

CUS Igniti on 293.82 132.11 4946.3 5393.5

CUS Shut off 1012.48 204.07 9777.3 10228.4

CUS Burn out 1014.82 205.43 9785.6 10236.6

GSAT-14 Separati on 1027.48 213.37 9778.1 10229.5

GSLV-D5 Flight Sequence

GSAT-14

GSLV-D5/GSAT-14 MISSIONGLIMPSES OF LAUNCH CAMPAIGN

The GSAT-14 is a communicati on spacecraft with primarily C and Ku band payloads. There are 6 transponders each operati ng in C and Ku bands. There is also a Ka band payload component. The spacecraft employs I-2K bus structure. The objecti ve of the spacecraft will be conti nuati on of the services provided by GSAT-3 Spacecraft , enhance Ku band transponders and provide a platf orm for Ka band propagati on studies.

GSAT-14 Spacecraft

Published by : Documentation and Information Services-LV Projects, VSSC, ThiruvananthapuramPrinted at : Akshara Off set, Thiruvananthapuram. #2471174

GS1 STACKING

GS2 STACKING

ENCAPSULATED ASSEMBLY

GS1 SEGMENT ASSEMBLY

CUS ASSEMBLY

FULLY ASSEMBLED VEHICLE AT VAB

L40 STAGE ASSEMBLY

SATELLITE ASSEMBLY

VEHICLE MOVEMENT TO UT

Satellite OverviewI-2K Bus74 deg E longitude orbital slot Communicati on Payloads• 6 extended C band & 6 Ku band transpondersExperiments• 2 Ka band beacons, Thermal Control Coati ng Experiment (TCCE), Fiber

Opti c Gyro (FOG), Acti ve Pixel Sun Sensor (APSS) based Digital Sun Sensor (DSS), Field Programmable Gate Array (FPGA) based earth sensor & aero-thermal fl ux sensor

850 kg dry mass & 1982 kg lift off mass Around 2600 W power generati on

Events Time (s)

Alti tude (km)

Relati ve velocity

(m/s)

Inerti al velocity

(m/s)

4L40H Igniti on -4.8 0.03 0 451.9

S139 Igniti on 0 0.03 0 451.9

4L40H Shut off 148.94 69.97 2398.9 2822.7

GS2 Igniti on 149.54 70.44 2399.8 2823.8

GS1 Separati on 151.14 71.66 2398.2 2822.9

IS 1/2 M Separati on 156.94 75.98 2451.0 2878.2

PLF Separati on 228.26 115.00 3422.2 3866.6

GS2 Shut off 289.32 131.34 4928.5 5375.9

GS2 Separati on 292.82 131.94 4946.6 5393.8

CUS Igniti on 293.82 132.11 4946.3 5393.5

CUS Shut off 1012.48 204.07 9777.3 10228.4

CUS Burn out 1014.82 205.43 9785.6 10236.6

GSAT-14 Separati on 1027.48 213.37 9778.1 10229.5

GSLV-D5 Flight Sequence

GSAT-14

GSLV-D5/GSAT-14 MISSIONGLIMPSES OF LAUNCH CAMPAIGN

The GSAT-14 is a communicati on spacecraft with primarily C and Ku band payloads. There are 6 transponders each operati ng in C and Ku bands. There is also a Ka band payload component. The spacecraft employs I-2K bus structure. The objecti ve of the spacecraft will be conti nuati on of the services provided by GSAT-3 Spacecraft , enhance Ku band transponders and provide a platf orm for Ka band propagati on studies.

GSAT-14 Spacecraft

Published by : Documentation and Information Services-LV Projects, VSSC, ThiruvananthapuramPrinted at : Akshara Off set, Thiruvananthapuram. #2471174

GS1 STACKING

GS2 STACKING

ENCAPSULATED ASSEMBLY

GS1 SEGMENT ASSEMBLY

CUS ASSEMBLY

FULLY ASSEMBLED VEHICLE AT VAB

L40 STAGE ASSEMBLY

SATELLITE ASSEMBLY

VEHICLE MOVEMENT TO UT

Satellite OverviewI-2K Bus74 deg E longitude orbital slot Communicati on Payloads• 6 extended C band & 6 Ku band transpondersExperiments• 2 Ka band beacons, Thermal Control Coati ng Experiment (TCCE), Fiber

Opti c Gyro (FOG), Acti ve Pixel Sun Sensor (APSS) based Digital Sun Sensor (DSS), Field Programmable Gate Array (FPGA) based earth sensor & aero-thermal fl ux sensor

850 kg dry mass & 1982 kg lift off mass Around 2600 W power generati on

Events Time (s)

Alti tude (km)

Relati ve velocity

(m/s)

Inerti al velocity

(m/s)

4L40H Igniti on -4.8 0.03 0 451.9

S139 Igniti on 0 0.03 0 451.9

4L40H Shut off 148.94 69.97 2398.9 2822.7

GS2 Igniti on 149.54 70.44 2399.8 2823.8

GS1 Separati on 151.14 71.66 2398.2 2822.9

IS 1/2 M Separati on 156.94 75.98 2451.0 2878.2

PLF Separati on 228.26 115.00 3422.2 3866.6

GS2 Shut off 289.32 131.34 4928.5 5375.9

GS2 Separati on 292.82 131.94 4946.6 5393.8

CUS Igniti on 293.82 132.11 4946.3 5393.5

CUS Shut off 1012.48 204.07 9777.3 10228.4

CUS Burn out 1014.82 205.43 9785.6 10236.6

GSAT-14 Separati on 1027.48 213.37 9778.1 10229.5

GSLV-D5 Flight Sequence