节流式燃/氧分离发动机准一维内弹道数值研究  

Numerical study on quasi⁃one⁃dimensional internal ballistics of throttling segregated fuel⁃oxidizer systems

作　　者：王革[1] 王志邦 王富祺 关奔[1] 王立民[2,3] 宁浩然 WANG Ge;WANG Zhibang;WANG Fuqi;GUAN Ben;WANG Limin;NING Haoran(College of Aerospace and Civil Engineering,Harbin Engineering University,Harbin 150001,China;College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China;Inner Mongolia Dynamic and Mechanical Institute,Hohhot 010011,China;School of Energy and Civil Engineering,Harbin University of Commerce,Harbin 150028,China)

机构地区：[1]哈尔滨工程大学航天与建筑工程学院,哈尔滨150001 [2]国防科技大学空天科学学院,长沙410073 [3]内蒙动力机械研究所,呼和浩特010011 [4]哈尔滨商业大学能源与建筑工程学院,哈尔滨150028

出　　处：《航空学报》2024年第7期134-153,共20页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(12002102);黑龙江省自然科学基金(LH2021E089)。

摘　　要：针对节流式燃/氧分离发动机建立非定常准一维内弹道数值模型和性能调控机理关系式,以对发动机推力调控过程进行预示。数值模型考虑燃烧室中的燃气注入、壁面摩擦和推进剂燃面退移,采用有限速率化学反应模型描述化学非平衡过程。利用该数值模型,计算得到了节流式燃/氧分离发动机的调控性能参数及内部流动参数分布情况。结果显示,当流量调节阀喉部半径由2.89 mm调节至1.65 mm时,发动机推力可由105.09 N增至432.18 N,推力提升至调节前推力的411.25%,验证了节流式燃/氧分离发动机的推力调控能力。发动机在流量调节阀作动过程中出现负调现象,调节阀作动速度越大,负调量越大,但性能参数的响应时间越短。发动机性能调控影响因素分析表明:推进剂压力指数增大和喷管喉部半径减小均有助于节流式燃/氧分离发动机性能调控能力的提升,从而提出了喷管可调的节流式燃/氧分离发动机方案。其工作过程的仿真结果表明:在特定的推力调节比要求下,减小喷管喉部半径能够有效降低富燃燃烧室承压水平,为发动机性能调控提供更多可行方案。A predictive unsteady quasi-one-dimensional internal ballistic numerical model and a set of performance regulation mechanism formulas are established for throttling segregated fuel-oxidizer systems.The numerical model considers combustion gas injection,wall friction,and propellant surface regression,using a finite-rate chemical reac⁃tion model to describe the non-equilibrium process.With this model,performance parameters and internal flow param⁃eter distributions of the throttling segregated fuel-oxidizer system can be well demonstrated.Results show that,adjust⁃ment of the throat radius of the throttle valve from 2.89 mm to 1.65 mm increases the thrust of the system from 105.09 N to 432.18 N,by 411.25%from the original thrust,verifying the regulation capability of the throttling segre⁃gated fuel-oxidizer system.During the dynamic operation of the throttle valve,the system experiences antiregulations.Faster actuation of the valve leads to larger anti-regulation amplitude and shorter response period of the performance parameters.Analysis of the influencing factors of performance regulation reveals that the increase of pro⁃pellant pressure index and the decrease of nozzle throat radius both contribute to the improvement in performance regulation ability of the throttling segregated fuel-oxidizer system.Accordingly,a new arrangement of throttling segre⁃gated fuel-oxidizer system with an adjustable nozzle is proposed.Simulation of this arrangement suggests that,for a specified thrust adjustment ratio,reducing the nozzle throat radius can effectively alleviate the pressure level of the fuelrich combustion chamber of the system,thus providing more feasible performance regulation schemes for the system operation.

关 键 词：固体火箭发动机 燃/氧分离发动机 准一维内弹道 推力调控 性能调控机理 

分 类 号：V438.2[航空宇航科学与技术—航空宇航推进理论与工程]