CAJ | 학술논문

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3.0 s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0.2 s以内.
기우기동해진점화기술적경/양변궤발동궤시일항신형적액체화전추진기술,우기괄용우공간참응용.통과경양추력실이론열력계산이급동축경양해진점화시험연구,채용료동축경양해진점화기가양기보연분취적발동궤두부결구방안.재동축경양해진점화기진행성능시험연구기출상,의차성공진행료발동궤두부적해진점화급양기보연시험.최후,성공완성료포괄단맥충、련속쌍맥충급3.0 s지속공작궤충형식하적발동궤지면시차시험,험증료발동궤공작적가고성급가행성.발송궤기동시간체도0.2 s이내.
Hydrogen and oxygen orbital maneuver thruster, based on gas-dynamic resonance ignition, is a new liquid rocket propulsion technology, and is especially applicable to space station. By means of theoretic thermodynamic calculation of the hydrogen and oxygen thruster, combined with the experimental exploration on the coaxial hydrogen and oxygen resonance ignition, a scheme of the thruster head configuration is designed as the combination of a coaxial hydrogen/oxygen resonance igniter and an oxygen augmentation injector. Through ignition tests on coaxial hydrogen/oxygen resonance igniter characterization, the thruster head ignition tests have been conducted successfully in sequence of resonance ignition and oxygen augmentation combustion. Finally, the thruster ground tests are successfully carried out in forms of single impulse, successive double impulses and 3.0 seconds continuous running, which verify the reliability and feasibility of the thruster. The response time of the thruster starting is restricted within 0.2 second.