Polar Satellite Launch Vehicle

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Polar Satellite Launch Vehicle
PSLV.svg
Model of the standard PSLV rocket
Function Medium lift launch system
Manufacturer ISRO
Country of origin India
Cost per launch PSLV-CA ₹90 crore($15M)[1]
Size
Height 44 metres (144 ft)
Diameter 2.8 metres (9 ft 2 in)
Mass PSLV: 295,000 kg (650,000 lb)
PSLV-CA: 230,000 kg (510,000 lb)
PSLV-XL: 320,000 kg (710,000 lb)[2]
Stages 4
Capacity
Payload to LEO 3,250 kg (7,170 lb)
Payload to SSO 1,750 kg (3,860 lb)[2]
Payload to Sub-GTO/GTO 1,425 kg (3,142 lb)[2]
Launch history
Status Active
Launch sites Sriharikota
Total launches 32
PSLV: 11
PSLV-CA: 11
PSLV-XL: 10
Successes 30
PSLV: 9
PSLV-CA: 11
PSLV-XL: 10
Failures 1 (PSLV)
Partial failures 1 (PSLV)
First flight PSLV: 20 September 1993
PSLV-CA: 23 April 2007
PSLV-XL: 22 October 2008
Notable payloads Chandrayaan-1, Mars Orbiter Mission, Astrosat
Boosters (PSLV) - S9
No. boosters 6
Thrust 510 kN (110,000 lbf)[2]
Specific impulse 262 s (2.57 km/s)
Burn time 44 seconds
Fuel HTPB
Boosters (PSLV-XL) - S12
No. boosters 6
Thrust 719 kN (162,000 lbf)[2]
Specific impulse 262 s (2.57 km/s)
Burn time 49 seconds
Fuel HTPB
First stage
Engines S139
Thrust 4,800 kN (1,100,000 lbf)
Specific impulse 237 s (2.32 km/s) (sea level)
269 s (2.64 km/s) (vacuum)
Burn time 105 seconds
Fuel HTPB
Second stage
Engines 1 Vikas
Thrust 799 kN (180,000 lbf)
Specific impulse 293 s (2.87 km/s)
Burn time 158 seconds
Fuel N2O4/UDMH
Third stage
Engines S7
Thrust 240 kN (54,000 lbf)
Specific impulse 294 s (2.88 km/s)
Burn time 83 seconds
Fuel HTPB
Fourth stage
Engines 2 x L-2-5[3]
Thrust 15.2 kN (3,400 lbf)
Specific impulse 308 s (3.02 km/s)
Burn time 425 seconds
Fuel MMH/MON

The Polar Satellite Launch Vehicle (Hindi: ध्रुवीय उपग्रह प्रक्षेपण 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, 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).

As of 2015 the PSLV has launched 93 satellites (36 Indian and 57 foreign satellites) into a variety of orbits.[4] 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.[2]

Development

PSLV was designed and developed in the early 1990s at Vikram Sarabhai Space Centre near Thiruvananthapuram, Kerala. The inertial systems are developed by ISRO Inertial Systems Unit (IISU) at Thiruvananthapuram. The liquid propulsion stages for the second and fourth stages of PSLV as well as the reaction control systems are developed by the Liquid Propulsion Systems Centre (LPSC) at Mahendragiri near Tirunelveli, Tamil Nadu. The solid propellant motors are processed at Satish Dhawan Space Centre (SHAR)at Sriharikota, Andhra Pradesh which also carries out launch operations.

The PSLV was first launched on 20 September 1993. The first and second stages performed as expected, but an attitude control problem led to the collision of the second and third stages at separation, and the payload failed to reach orbit.[5] After this initial setback, the PSLV successfully completed its second mission in 1994.[6] The fourth launch of PSLV suffered a partial failure in 1997, leaving its payload in a lower than planned orbit. Since then, the PSLV has launched 24 times with no further failures.[7]

PSLV continues to support Indian and foreign satellite launches especially for low Earth orbit (LEO) satellites. It has undergone several improvements with each subsequent version, especially those involving thrust, efficiency as well as weight. In November 2013, it was used to launch the Mars Orbiter Mission, India's first interplanetary probe.[8]

Vehicle description

The PSLV has four stages using solid and liquid propulsion systems alternately. The first stage, one of the largest solid rocket motors in the world, carries 138 tonnes of hydroxyl-terminated polybutadiene urethane-bound (HTPB) propellant and develops a maximum thrust of about 4,800 kN. The 2.8-m diameter motor case is made of maraging steel and has an empty mass of 30,200 kg.[3] Pitch and yaw control during first stage flight is provided by the Secondary Injection Thrust Vector Control System (SITVC), which injects an aqueous solution of strontium perchlorate into the nozzle to produce asymmetric thrust. The solution is stored in two cylindrical aluminum tanks strapped to the solid rocket motor and pressurized with nitrogen. Roll control is provided by two small liquid engines on opposite sides of the stage, the Roll Control Thrusters (RCT).

On the PSLV and PSLV-XL, first stage thrust is augmented by six strap-on solid boosters. Four boosters are ground-lit and the remaining two ignite 25 seconds after launch. In the standard PSLV, each booster carries nine tonnes of propellant and produces 510 kN thrust. The PSLV-XL uses larger boosters which carry 12 tonnes of propellant and produce 719 kN thrust. Two strap-on boosters are equipped with SITVC for additional attitude control.[3] The PSLV-CA uses no strap-on boosters.

The second stage employs the Vikas engine and carries 41.5 tonnes (40 tonnes till C-5 mission) of liquid propellant – unsymmetrical dimethylhydrazine (UDMH) as fuel and nitrogen tetroxide (N2O4) as oxidizer. It generates a maximum thrust of 800 kN (724 till C-5 mission). The engine is hydraulically gimbaled (±4°) to provide pitch and yaw control, while roll control is provided by two hot gas reaction control motors.

The third stage uses 7 tonnes of HTPB-based solid propellant and produces a maximum thrust of 240 kN. It has a Kevlar-polyamide fiber case and a submerged nozzle equipped with a flex-bearing-seal gimbaled nozzle (±2°) thrust-vector engine for pitch & yaw control. Roll control is provided by the fourth stage reaction control system (RCS).[3]

The fourth stage is powered by twin engines burning monomethylhydrazine (MMH) and mixed oxides of nitrogen (MON). Each engine generates 7.4 kN thrust and is gimbaled (±3°) to provide pitch, yaw & roll control during powered flight. Coast phase attitude control is provided by RCS. The stage carries 2,500 kg of propellant in the PSLV and PSLV-XL and 2,100 kg in the PSLV-CA.[9]

PSLV is developed with a group of wide-range control units.

Stage 1 Stage 2 Stage 3 Stage 4
Pitch SITVC Engine Gimbal Flex Nozzle Engine Gimbal
Yaw SITVC Engine Gimbal Flex Nozzle Engine Gimbal
Roll RCT and SITVC in 2 PSOMs HRCM Hot Gas Reaction Control Motor PS4 RCS PS4 RCS

Variants

ISRO has envisaged a number of variants of PSLV to cater to different mission requirements. There are currently three operational versions of the PSLV — the standard (PSLV), the core-alone (PSLV-CA) without the six strap-on booster motors, and the (PSLV-XL) version, which carries more solid fuel in its strap-on motors than the standard version.[10] These configurations provide wide variations in payload capabilities ranging from 3800 kg in LEO to 1800 kg in Sun synchronous orbit.

PSLV (Operational)

The standard version of the PSLV has four stages using solid and liquid propulsion systems alternately and six strap-on boosters. It currently has capability to launch 1,678 kg to 622 km into Sun synchronous orbit.

PSLV-CA (Operational)

The PSLV-CA, CA meaning "Core Alone", model premiered on 23 April 2007. The CA model does not include the six strap-on boosters used by the PSLV standard variant. Two small roll control modules and two first-stage motor control injection tanks were still attached to the side of the first stage.[9] The fourth stage of the CA variant has 400 kg less propellant when compared to its standard version.[9] It currently has capability to launch 1,100 kg to 622 km Sun synchronous orbit.[11]

PSLV-XL (Operational)

PSLV-XL is the uprated version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful, stretched strap-on boosters.[9] 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.[12] 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.[11] Other launches include the RISAT Radar Imaging Satellite and GSAT-12.[13]

Variant Launches Successes Failures Partial failures Remarks
PSLV (Standard) 11 9 1 1
PSLV-CA (Core Alone) 11 11 0 0
PSLV-XL (Extended)[2] 10 10 0 0
PSLV-3S (Under development / Proposed)

ISRO is also considering the development of a three-stage version of the rocket without six strap-on boosters (with the second stage of the four-stage version removed) which will be capable of placing 500 kg to LEO.[11][14]

Launch history

As of 16 December 2015 the PSLV has made 32 launches, with 30 successfully reaching their planned orbits, one outright failure and one partial failure. All launches have occurred from the Satish Dhawan Space Centre (SDSC), known before 2002 as the Sriharikota Range (SHAR).

PSLV (Launch history)
Flight Variant Launch date/time (UTC) Launch pad Payload Payload mass Result Note(s) References
D1 PSLV 20 September 1993
05:12
First India IRS 1E 846 kg Failure Maiden flight; attitude control failure at second stage separation [15]
D2 PSLV 15 October 1994
05:05
First India IRS-P2 804 kg Success [16]
D3 PSLV 21 March 1996
04:53
First India IRS-P3 920 kg Success [17]
C1 PSLV 29 September 1997
04:47
First India IRS 1D 1250 kg Partial failure First operational flight; fourth stage under-performed resulting in lower than planned orbit. Satellite used own propulsion to move to correct orbit. [18]
C2 PSLV 26 May 1999
06:22
First India Oceansat-1
Germany DLR-Tubsat
South Korea KitSat 3
1050 kg
45 kg
107 kg
Success First launch to have foreign satellites, and first to carry multiple satellites [19][20]
C3 PSLV 22 October 2001
04:53
First India TES
Europe PROBA
Germany BIRD
1108 kg
94 kg
92 kg
Success [21]
C4 PSLV 12 September 2002
10:23
First India METSAT 1 (Kalpana 1) 1060 kg Success India's first launch to GTO, GTO payload capability has reached 1200 kg from 2002 onward, compared to 1050 kg previously. First use of lightweight carbon composite payload adapter. [22][23][24]
C5 PSLV 17 October 2003
04:52
First India ResourceSat 1 1360 kg Success Payload capability had been progressively increased by more than 600 kg since the first PSLV launch. Launch took place despite heavy rain. [25][26]
C6 PSLV 5 May 2005
04:45
Second India CartoSat 1
India HAMSAT
1560 kg
42.5 kg
Success First PSLV launch from the second launch pad [27]
C7 PSLV 10 January 2007
03:54
First India CartoSat 2
India SRE
Indonesia LAPAN-TUBsat
Argentina PEHUENSAT-1
680 kg
500 kg
56 kg
6 kg
Success First flight of hardware upgrade, first launch of reentry capsule (SRE) [28]
C8 PSLV-CA 23 April 2007
10:00
Second Italy AGILE
India AAM
352 kg
185 kg
Success First flight of the 'Core-Alone' configuration.
ISRO's first commercial launch (foreign satellite as the main payload).
[29][30]
C10 PSLV-CA 21 January 2008
03:45
First Israel TecSAR 295 kg Success ISRO's second commercial launch (foreign satellite as the main payload). [31][32]
C9 PSLV-CA 28 April 2008
03:53
Second India Cartosat-2A
India IMS-1/TWSAT
Germany RUBIN-8
Canada CanX-6/NTS
Canada CanX-2
Japan Cute-1.7+APD II
Netherlands Delfi-C3
Japan SEEDS-2
Germany COMPASS-1
Denmark AAUSAT-II
690 kg
83 kg
8 kg
6.5 kg
3.5 kg
3 kg
2.2 kg
1 kg
1 kg
0.75 kg
Success [33][34]
C11 PSLV-XL 22 October 2008
00:52
Second India Chandrayaan-1 1380 kg Success First flight of the PSLV-XL configuration, first Indian Lunar probe. [35][36]
C12 PSLV-CA 20 April 2009
01:15
Second India RISAT-2
India ANUSAT
300 kg
40 kg
Success India's first radar imaging satellite (RISAT). [37][38]
C14 PSLV-CA 23 September 2009
06:21
First India Oceansat-2

GermanyLuxembourg Rubin 9.1
GermanyLuxembourgRubin 9.2
Switzerland SwissCube-1
Germany BeeSat
Germany UWE-2
Turkey ITUpSAT1

960 kg
8 kg
8 kg
1 kg
1 kg
1 kg
1 kg
Success Rubin 9.1 and 9.2 intentionally remained attached to the fourth stage. SwissCube-1 was the first Swiss satellite, and ITUpSAT1 was the first satellite to be constructed in Turkey. [39][40][41]
[42][43][44]
C15 PSLV-CA 12 July 2010
03:52
First India Cartosat-2B

Algeria ALSAT-2A
Norway AISSat-1
Switzerland TIsat-1
India STUDSAT

694 kg
117 kg
6.5 kg
1 kg
0.95 kg
Success AISSat-1 and TIsat are part of NLS-6. [45][46][47][48]
[49][50][51]
C16 PSLV 20 April 2011
04:42
First India ResourceSat-2
Singapore X-Sat
IndiaRussia YouthSat
1206 kg
106 kg
92 kg
Success [52]
C17 PSLV-XL 15 July 2011
11:18
Second India GSAT-12 1410 kg Success First use of Vikram flight computer. [53][54]
C18 PSLV-CA 12 October 2011
05:31
First IndiaFrance Megha-Tropiques

India SRMSAT
India Jugnu
Luxembourg VesselSat-1

1000 kg
10.9 kg
3 kg
28.7 kg
Success [55][56]
C19 PSLV-XL 26 April 2012
00:17
First IndiaRISAT-1 1850 kg Success [57]
C21 PSLV-CA 9 September 2012
04:23
First France SPOT-6
India mRESINS

Japan PROITERES

720 kg
50 kg
15 kg
Success mRESINS tested avionics for future PSLV launches. ISRO's third commercial launch (foreign satellite as the main payload). Isro's 100th mission. [58]
C20 PSLV-CA 25 February 2013
12:31
First IndiaFrance SARAL

Canada Sapphire
Canada NEOSSat
Austria TUGSAT-1
Austria UniBRITE-1
United Kingdom STRaND-1
Denmark AAUSAT3

409 kg
148 kg
74 kg
14 kg
14 kg
6.5 kg
0.8 kg
Success TUGSAT-1 and UniBRITE were the first Austrian satellites. [59][60][61]
C22 PSLV-XL 1 July 2013
18:11
First India IRNSS-1A 1425 kg Success India’s first regional navigation satellite [62]
C25 PSLV-XL 5 November 2013
09:08
First India Mars Orbiter Mission 1350 kg Success India's first Mars mission. [63][64]
C24 PSLV-XL 4 April 2014
11:44
First India IRNSS-1B 1432 kg Success India's second regional navigation satellite [65][66]
C23 PSLV-CA 30 June 2014
04:22
First France SPOT-7
Canada CanX-4
Canada CanX-5
Germany AISAT
Singapore VELOX-1
714 kg
15 kg
15 kg
14 kg
7 kg
Success ISRO's fourth commercial launch (foreign satellite as the main payload). [67]
C26 PSLV-XL 16 October 2014
20:02
First India IRNSS-1C 1425.4 kg Success Seventh PSLV XL and third Navigation Satellite launch. [68][69]
C27 PSLV-XL 28 March 2015
11:49
Second India IRNSS-1D 1425 kg Success Eighth PSLV XL and fourth Navigation Satellite launch. [70]
C28 PSLV-XL 10 July 2015
16:28
First United Kingdom UK-DMC3A
United Kingdom UK-DMC3B
United Kingdom UK-DMC3C
United Kingdom CBNT-1
United Kingdom DeOrbitSail
447 kg
447 kg
447 kg
91 kg
7 kg
Success At the time it was the heaviest commercial mission (1439 kg) successfully accomplished using a launch vehicle assembled by ISRO. [71][72]
C30 PSLV-XL 28 September 2015
04:30
First India Astrosat
Indonesia LAPAN-A2
Canada ExactView 9
United States Lemur 2
United States Lemur 3
United States Lemur 4
United States Lemur 5
1650 kg
68 kg
5.5 kg
4 kg
4 kg
4 kg
4 kg
Success Launch of India's first dedicated multi-wavelength space observatory and ISRO's first launch of US satellites. [73]
C29 PSLV-CA 16 December 2015
12:30
First Singapore TeLEOS-1
Singapore VELOX C1

Singapore VELOX 2
Singapore Kent Ridge 1
Singapore Galassia
Singapore Athenoxat-1[74]

400 kg
123 kg
13 kg

78  kg
3.4 kg
-

Success Commercial launch of 6 Singaporean satellites

Fourth stage re-ignition demonstrated successfully after payload deployment.

[75][76][77]

Planned launches

PSLV (Planned launches)
Flight Variant Launch date/time (UTC) Launch pad Payload Payload mass Result Note(s) References
C31 PSLV-XL 20 January 2016

04:01

Second India IRNSS-1E 1425 kg
Planned [78][79][80]
C34 PSLV-XL February 2016
India IRNSS-1F 1425 kg
Planned [78]
C32 PSLV-XL March 2016
India IRNSS-1G 1425 kg
Planned [78]
C33 PSLV September 2016
India Cartosat-2C Planned [81]
C35 PSLV December 2016
India Resourcesat-2A Planned [81]
CXX PSLV 2016 Germany Aisat 900 kg Planned [82]

Launch Frequency



1
2
3
4
1993
1994
1995
1996
1997
1998
1999
2000
2001
2002
2003
2004
2005
2006
2007
2008
2009
2010
2011
2012
2013
2014
2015
2016

Notable flights

PSLV flight D1

This was the first developmental flight of the PSLV d1.[15] The IRS-1E satellite which was proposed to be launched was derived from the engineering model of IRS-1A incorporating a similar camera and an additional German-built monocular electro-optical stereo scanner. Even though the mission was a failure, the launch team and an expert committee appointed thereafter noted that the mission had validated many technologies and that most sub-systems had performed optimally.[83][84]

PSLV flight C1

The launch was witnessed by the former Prime Minister I.K. Gujral and also marked India's first launch vehicle built without Russian assistance.[85][86]

PSLV flight C2

In the flight sequence, IRS-P4 was injected first, followed by KITSAT-3 and DLR-TUBSAT in that order.[19] The mission was supported by ISTRAC network of ground stations located at Bangalore, Sriharikota, Lucknow, Mauritius, Bearslake, Russia and Biak, Indonesia. During the initial phase of the mission the ground station at Wilhem in Germany also provided network support. Upon injection of the satellites, data from the IRS-P4 was received at Hyderabad while KITSAT-3 data was received at the ground station in Korea and the data from the TUBSAT was received at the university ground station in Berlin.[20][87]

PSLV flight C5

The launch took place despite heavy rain which commenced half an hour before the scheduled launch. However, ISRO decided to go ahead with the launch as despite rain, there were no strong winds and there were weather reports suggested that the monsoons would set in by the next day.[26] Following the launch, a press statement released by the Minister of State (Space) announced that the PSLV has been proposed for the Chandrayan 1 moon mission.

PSLV flight C6

The former President, Dr. Abdul Kalam, witnessed the launch from the Mission Control Centre.[88] It was the first PSLV launch from second pad, using integrate-transfer-and-launch technology. After its integration in the Vehicle Assembly Building, the PSLV-C6 was transported on rails to the Umbilical Tower (UT) located one km away using the Mobile Launch Pedestal where the final operations were carried out.[88]

PSLV flight C7

The following hardware changes[89][90] were made since PSLV flight C6:

  • first use of DLA (Dual Payload Adapter) to launch 2 primary satellites in time
  • reduction of propellant from 2.5 tonne to 2 tonne in the fourth liquid propellant stage
  • incorporation of a video imaging system to capture payload and DLA separation events
  • altitude based day of launch wind-biased steering programme during Open Loop Guidance
  • removal of Secondary Injection Thrust Vector Control (SITVC) system for one of the strapons ignited in the air.

PSLV flight C9

The fourth stage first fired Cartosat-2A into orbit at an altitude of 637 km about 885 seconds after lift-off. About 45 seconds later, it propelled IMS-1 into the orbit. Then the six nano satellites belonging to a cluster called NLS-4 were injected into orbit at intervals of 20 seconds each. NLS-5, a single satellite, flew out and finally the tenth satellite Rubin-8 went along with the fourth stage into orbit. Two satellites belonged to India and the remaining were nanosatellites built by universities in different countries.[91] This was the maximum number of satellites placed in orbit, in a single PSLV launch.[92][93][94]

PSLV flight C21

Launch attended by the former Prime Minister Manmohan Singh.[95] mRESINS ( mini Redundant Strapdown Inertial Navigation System) bolted to the vehicle's fourth stage, have tested avionics for future PSLV missions.[96]

PSLV flight C22

Earlier launch date for PSLV C22 was fixed as 12 June 2013 (1.01AM) but the launch had been postponed because of a technical snag in the 2nd stage.[97]

The launch of the first satellite in the Indian Regional Navigation Satellite System of the Indian Space Research Organization (ISRO), scheduled for 12 June from Sriharikota, has been postponed by 14 days after an anomaly was discovered just 11 days before launch. The satellite IRNSS-1A, which would be the first in a series of seven navigation satellites was scheduled to be launched on board the Polar Satellite Launch Vehicle (PSLV) C22 at 1.01 am on 12 June. The satellite has undergone its pre-launch checks successfully. However, ISRO said the launch vehicle had an anomaly in one electro-hydraulic control actuators. "During the electrical checks of the launch vehicle, an anomaly was observed in one of the electro-hydraulic control actuators in the second stage. It has been decided to replace this actuator," a statement by ISRO said. Officials added that the replacement of the actuator would take two weeks and it would be carried out at the launch pad and vehicle assembly area.

ISRO then replaced a faulty component in the PSLV-C22 rocket and rescheduled the flight of the IRNSS-1A satellite on it for 11:41 p.m. on 1 July.[98] PSLV-C22, successfully launched IRNSS-1A, the first satellite in the Indian Regional Navigation Satellite System (IRNSS).

At the completion of the countdown, PSLV-C22 lifted off from the First Launch Pad at 23:41 hrs 1 July 2013 with the ignition of the first stage and four strap-on motors of the launch vehicle.[62]

PSLV flight C25

The Mars Orbiter Mission (MOM), informally called Mangalyaan is a Mars orbiter that was successfully injected into Earth orbit on 5 November 2013 at 2:38 PM IST (9:08 UTC) atop a PSLV-XL launch vehicle from Satish Dhawan Space Centre, Shriharikota (SHAR).

PSLV flight C23

PSLV-C23 was launched at 9:52 a.m. [IST] on 30 June 2014. It carried five foreign satellites - SPOT-7, NLS-7.1 (CanX-4), NLS-7.2 (CanX-5), AISat and VELOX-1. All five satellites were released successfully.[99] The launch was attended by Prime minister Narendra Modi, the 15th Prime minister of India. The lift-off time was originally planned to be at 9.49 a.m.[IST], but was later rescheduled to 9:52 a.m. [IST] due to debris getting in the trajectory.[100] and

PSLV flight C29

PSLV-C29 lifted off from the First Launch Pad (FLP) of SDSC SHAR at 1800 hrs [IST] on 16 December 2015. It successfully deployed six satellites it carried with gross weight of 624 kg. After fourth stage engines were cut off primary payload TeLEOS-1 was injected in orbit at about 18 min 12 seconds after lift-off. This was followed by the deployment of other five satellites, namely Kent Ridge-1, VELOX-C1, VELOX-II, Galassia and Athenoxat-1 in quick succession in the subsequent three minutes.[101] 67 minutes into flight fourth stage re-ignition capability was demonstrated successfully by firing its engines for duration of nearly five seconds. This capability would enable multiple satellite deployment in varying orbits on same flight.[77]

Launch failures

IRS 1E

On 20 September 1993 a PSLV-D1, the first developmental flight rocket, failed during launch. A significant attitude disturbance occurred during second to third-stage separation, causing the attitude control command to exceed its maximum value. Because of the programming error in the pitch control loop of the digital autopilot software in the guidance and control processor, the required reversal of command polarity did not take place, causing the pitch loop to become unstable, resulted in loss of attitude control and failure to achieve orbit. The attitude control disturbance was traced to failure of one of the retro rockets designed to pull the burnt second stage away from the third stage. The vehicle crashed into the Bay of Bengal 700 seconds after take off.[84]

IRS 1D

On 29 September 1997 a PSLV-C1 rocket failed during launch. Anomalous interaction between the primary and secondary pressure regulators of the fourth stage caused a reduction in propellant flow and thrust after 250 s of burn time. As a result, the fourth stage was shut down by a software override timer after burning 435 s, before reaching the target orbit or depleting propellant. The injection velocity was 140 m/s low, resulting in an orbit of 301x823 km instead of the planned 817 km circular SSO.[102] Initially, a leak of helium gas from one of the components in the fourth stage was suspected,[85][103] similar to recent Long March 3 launch failure, but later ruled out. Resulting orbit was partially corrected using satellite's on-board thrusters, thereby raising the perigee to 737 km, while the apogee remained at 821 km.[84]

See also

References

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External links