ВНИМАНИЕ! На форуме началось голосование в конкурсе "Астрофотография месяца - МАЙ"
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Скорее все-таки сначала отделение второй ступени
This main engine, and two smaller (cryogenic) steering engines together develop a nominal thrust of 73.55 kN in vacuum. The main engine of CUS achieves a specific impulse of 452 seconds. During the flight, CUS fires for a nominal duration of 720 seconds.
Along with the main engine and the two steering engines, the other stage systems of CUS include insulated propellant tanks, booster pumps, inter-stage structures, fill and drain systems, pressurisation systems,gas bottles, command block, igniters, pyro valves and cold gas orientation and stabilisation system.Liquid Oxygen (LOX) and Liquid Hydrogen (LH2) from the respective tanks are fed by individual booster pumps to the main turbo-pump, which rotates at 39,000 rpm to ensure a high flow rate of 16.6 kg/sec of propellants into the combustion chamber. The main turbine is driven by the hot gas produced in a pre-burner. Thrust control and mixture ratio control are achieved by two independent regulators. LOX and Gaseous Hydrogen (GH2) are ignited by pyrogen type igniters in the pre-burner as well as in the main and steering engines during initial stages.
"The cryo stage ignition was issued as planned by the on-board computer," Radhakrishnan said. "Indications are that the cryo engine ignited. This is to be confirmed after detailed analysis of the data. We saw the vehicle was tumbling, indicating the controllability was lost, most probably [because] the two vernier engines, small cryo engines, would not have ignited and developed the necessary control force."The two vernier, or steering, engines were supposed to provide small amounts of force to keep the rocket on track during the third stage's 12-minute burn.But tracking graphics showed the rocket began losing altitude seconds after officials announced third stage ignition. The vehicle reached a maximum altitude of about 87 miles and was traveling approximately 11,000 mph at the time of the mishap, according to displays in the launch control center.Launch controllers lost tracking data on the uncontrolled rocket a few minutes later as it plunged back into the atmosphere over the Indian Ocean. The final tracking fix on the launcher indicated the vehicle was descending at an altitude of 41 miles about 1,000 miles southeast of the Satish Dhawan Space Center on India's east coast.
Ха... А эти дополнительные движки оказывается отнюдь не самостийные!
Цитата: ...а с платформы говорят: от 15.04.2010 [19:38:23]Ха... А эти дополнительные движки оказывается отнюдь не самостийные! Этому сотрудничеству по криогенным движкам уже лет 20 как стукнуло.
Но я так и не понял - осаждение топлива чем?
Along with the main engine and the two steering engines, the other stage systems of CUS include insulated propellant tanks, booster pumps, inter-stage structures, fill and drain systems, pressurisation systems, gas bottles, command block, igniters, pyro valves and cold gas orientation and stabilisation system.
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Тема: Космические новости из Индии (Прочитано 3914 раз)
