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基于气动谐振点火技术的氢/氧变轨发动机是一项新型的液体火箭推进技术,尤其适用于空间站应用。通过氢氧推力室理论热力计算以及同轴氢氧谐振点火试验研究,采用了同轴氢氧谐振点火器加氧气补燃喷嘴的发动机头部结构方案。在同轴氢氧谐振点火器进行性能试验研究基础上,依次成功进行了发动机头部的谐振点火及氧气补燃试验。最后,成功完成了包括单脉冲、连续双脉冲及3.0s持续工作几种形式下的发动机地面试车试验,验证了发动机工作的可靠性及可行性。发送机起动时间达到0.2s以内。
The hydrogen / oxygen orbiter based on the aerodynamic resonance ignition technology is a new type of liquid propellant propulsion technology that is especially suitable for space station applications. Through the theoretical calculation of the thermodynamic force in the thrust chamber and the experimental study of the coaxial oxyhydrogen resonance ignition, a scheme of the engine head structure of the coaxial oxyhydrogen resonance igniter and the oxygen refueling nozzle is adopted. Based on the performance experiment of coaxial oxyhydrogen resonance igniter, the resonance ignition and oxygen backburning test of the engine head were successively carried out. Finally, the successful completion of the engine ground test running under several forms, including single pulse, continuous double pulse and 3.0s continuous work, verified the reliability and feasibility of the engine work. Transmitter start time of less than 0.2s.