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Ce-7.5

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Title: Ce-7.5  
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Subject: CE-20, Comparison of orbital rocket engines, ISRO Propulsion Complex, Rocket engines, RD-120
Collection: Rocket Engines, Rocket Engines Using Hydrogen Propellant, Space Programme of India
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Ce-7.5

CE-7.5
Country of origin India
Date 2002
Designer Indian Space Research Organisation
Manufacturer Hindustan Aeronautics Limited,Godrej & Boyce,MTAR Technologies
Application Upper-stage booster
Status In use
Liquid-fuel engine
Propellant LOX / LH2[1]
Cycle Staged combustion
Configuration
Chamber 1
Performance
Thrust (vac.) 73.5 kN[2]
Chamber pressure 5.8 MPa / 7.5 MPa
Isp (vac.) 454 seconds (4.45 km/s)
Dimensions
Length 2.14 m (7.02 ft)
Diameter 1.56 m (5.11 ft)
Dry weight 435 kg

The CE-7.5 is a cryogenic rocket engine developed by ISRO to power the upper stage of its GSLV Mk-2 launch vehicle. The engine was developed as a part of the Cryogenic Upper Stage Project (CUSP). It replaced the KVD-1 (RD-56) Russian cryogenic engine that powered the upper stage of GSLV Mk-1.

Contents

  • Overview 1
  • Specifications 2
  • Development 3
  • Applications 4
  • See also 5
  • References 6

Overview

CE-7.5 is a regeneratively cooled, variable thrust, staged combustion cycle[3][4] engine.

Specifications

The specifications and key characteristics of the engine are:

  • Operating Cycle – Staged combustion[5]
  • Propellant Combination – LOX / LH2[6]
  • Maximum thrust (Vacuum) – 75 kN[7]
  • Operating Thrust Range (as demonstrated during GSLV Mk2 D5 flight) – 73.55 kN to 82 kN [8][2]
  • Chamber Pressure (Nom) – 58 bar
  • Engine Mixture ratio (Oxidizer/Fuel by mass) – 5.05
  • Engine Specific Impulse - 454 ± 3 seconds (4.452 ± 0.029 km/s)[5][3]
  • Engine Burn Duration (Nom) – 720 seconds[7]
  • Propellant Mass – 12800 kg[7]
  • Two independent regulators: thrust control and mixture ratio control[6]
  • Steering during thrust: provided by two gimbaled steering engines[6]

Development

ISRO formally started the Cryogenic Upper Stage Project in 1994.[9] The engine successfully completed the Flight Acceptance Hot Test in 2008,[5] and was integrated with propellant tanks, third-stage structures and associated feed lines for the first launch. First flight attempt took place in April 2010 using GSLV Mk-2 D3 launch vehicle. However the engine failed to ignite.[2] On 27 March 2013 the engine was successfully tested under vacuum conditions. The engine performed as expected and was qualified to power the third stage of the GSLV Mk-2 rocket. On 5 January 2014 the cryogenic engine performed successfully and launched the GSAT-14 satellite using GSLV D5.[10][11]

Applications

CE-7.5 is being used in the third stage of ISRO's GSLV Mk-2 rocket.

See also

References

  1. ^
  2. ^ a b c
  3. ^ a b
  4. ^
  5. ^ a b c
  6. ^ a b c
  7. ^ a b c
  8. ^
  9. ^
  10. ^ http://www.isro.gov.in/gslv-d5/mission.aspx
  11. ^
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