Английская Википедия:CE-7.5

Материал из Онлайн справочника
Перейти к навигацииПерейти к поиску

Шаблон:Short description Шаблон:Use dmy dates Шаблон:Infobox rocket engine The CE-7.5 is a cryogenic rocket engine developed by the Indian Space Research Organisation 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.[1]

Overview

CE-7.5 is a regeneratively-cooled, variable-thrust, fuel-rich staged combustion cycle rocket engine.[2][3]

Specifications

The specifications and key characteristics of the engine are:

  • Operating Cycle – Staged combustion[4]
  • Propellant Combination – LOX / LH2[5]
  • Maximum thrust (Vacuum) – 73.55 kN[6]
  • Operating Thrust Range (as demonstrated during GSLV Mk2 D5 flight) – 73.55 kN to 82 kN [7][8]
  • Engine Specific Impulse - Шаблон:Convert[2][4]
  • Engine Burn Duration (Nom) – 720 seconds[6]
  • Propellant Mass – 12,800 kg[6]
  • Two independent regulators: thrust control and mixture ratio control[5]
  • Steering during thrust: provided by two gimballed steering engines[5]

Development

Indian Space Research Organisation (ISRO) formally started the Cryogenic Upper Stage Project in 1994.[9] The engine successfully completed the Flight Acceptance Hot Test in 2008,[4] and was integrated with propellant tanks, third-stage structures and associated feed lines for the first launch. The first flight attempt took place in April 2010 during the GSLV Mk.II D3/GSAT-3 mission. The engine ignited, but the ignition did not sustain as the Fuel Booster Turbo Pump (FBTP) shut down after reaching a speed of about 34,500 rpm 480 milliseconds after ignition, due to the FBTP being starved of Liquid Hydrogen (LH2).[7] 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 in the GSLV-D5/GSAT-14 mission.[10][11]

In GSLV-F14 mission, a new white coloured C15 stage was introduced which has more environmental-friendly manufacturing processes, better insulation properties and the use of lightweight materials.[12]

Applications

CE-7.5 is being used in the third stage of ISRO's GSLV Mk.II rocket.[13]

See also

Шаблон:Portal

References

Шаблон:Reflist

Шаблон:Indian space programme Шаблон:Rocket engines

Шаблон:Use Indian English

Партнерские ресурсы
Криптовалюты
Магазины
Хостинг
Разное

  1. ↑ Шаблон:Cite web
  2. ↑ 2,0 2,1 Шаблон:Cite web
  3. ↑ Шаблон:Cite news
  4. ↑ 4,0 4,1 4,2 Шаблон:Cite web
  5. ↑ 5,0 5,1 5,2 Шаблон:Cite web
  6. ↑ 6,0 6,1 6,2 Шаблон:Cite web
  7. ↑ 7,0 7,1 Ошибка цитирования Неверный тег <ref>; для сносок gslvd3 не указан текст
  8. ↑ Шаблон:Cite webШаблон:Cbignore
  9. ↑ Шаблон:Cite web
  10. ↑ Шаблон:Cite web
  11. ↑ Шаблон:Cite web
  12. ↑ Шаблон:Cite web
  13. ↑ Шаблон:Cite web
Источник — http://wikihandbk.com/ruwiki/index.php?title=Английская_Википедия:CE-7.5&oldid=13709723