节流式燃/氧分离发动机准一维内弹道数值研究

王革; 王志邦; 王富祺; 关奔; 王立民; 宁浩然

doi:10.7527/S1000-6893.2023.29111

航空学报 >

2024 , Vol. 45 >Issue 7: 129111 - 129111

DOI: https://doi.org/10.7527/S1000-6893.2023.29111

流体力学与飞行力学

节流式燃/氧分离发动机准一维内弹道数值研究

王革 ,
王志邦 ,
王富祺 ,
关奔 ,
王立民 ,
宁浩然

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^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

．E-mail： guanben@hrbeu.edu.cn

收稿日期: 2023-06-02

修回日期: 2023-06-26

录用日期: 2023-09-27

网络出版日期: 2023-10-08

基金资助

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

收起

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

Ge WANG ,
Zhibang WANG ,
Fuqi WANG ,
Ben GUAN ,
Limin WANG ,
Haoran NING

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^1.College of Aerospace and Civil Engineering，Harbin Engineering University，Harbin 150001，China
^2.College of Aerospace Science and Engineering，National University of Defense Technology，Changsha 410073，China
^3.Inner Mongolia Dynamic and Mechanical Institute，Hohhot 010011，China
^4.School of Energy and Civil Engineering，Harbin University of Commerce，Harbin 150028，China

E-mail： guanben@hrbeu.edu.cn

Received date: 2023-06-02

Revised date: 2023-06-26

Accepted date: 2023-09-27

Online published: 2023-10-08

Supported by

National Natural Science Foundation of China(12002102);Natural Science Foundation of Heilongjiang Province(LH2021E089)

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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。

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

本文引用格式

王革 , 王志邦 , 王富祺 , 关奔 , 王立民 , 宁浩然 . 节流式燃/氧分离发动机准一维内弹道数值研究[J]. 航空学报, 2024 , 45(7) : 129111 -129111 . DOI: 10.7527/S1000-6893.2023.29111

Abstract

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 reaction model to describe the non-equilibrium process. With this model， performance parameters and internal flow parameter distributions of the throttling segregated fuel-oxidizer system can be well demonstrated.Results show that， adjustment 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 segregated fuel-oxidizer system. During the dynamic operation of the throttle valve， the system experiences anti-regulations. 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 propellant 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 segregated 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 fuel-rich combustion chamber of the system， thus providing more feasible performance regulation schemes for the system operation.

Key words： solid rocket motor; segregated fuel-oxidizer system; quasi-one-dimensional internal ballistics; thrust regulation; performance regulation mechanism

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