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首页> 外文期刊>Journal of propulsion and power >Liquid-Propellant Rocket Engine Throttling: A Comprehensive Review
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Liquid-Propellant Rocket Engine Throttling: A Comprehensive Review

机译：液体火箭发动机节流：全面综述

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摘要

Liquid-propellant rocket engines are capable of on-command variable thrust or thrust modulation, an operability advantage that has been studied intermittently since the late 1930s. Throttleable liquid-propellant rocket engines can be used for planetary entry and descent, space rendezvous, orbital maneuvering including orientation and stabilization in space, and hovering and hazard avoidance during planetary landing. Other applications have included control of aircraft rocket engines, limiting of vehicle acceleration or velocity using retrograde rockets, and ballistic missile defense trajectory control. Throttleable liquid-propellant rocket engines can also continuously follow the most economical thrust curve in a given situation, as opposed to making discrete throttling changes over a few select operating points. The effects of variable thrust on the mechanics and dynamics of an liquid-propellant rocket engine as well as difficulties and issues surrounding the throttling process are important aspects of throttling behavior. This review provides a detailed survey of liquid-propellant rocket engine throttling centered around engines from the United States. Several liquid-propellant rocket engine throttling methods are discussed, including high-pressure-drop systems, dual-injector manifolds, gas injection, multiple chambers, pulse modulation, throat throttling, movable injector components, and hydrodynamically dissipative injectors. Concerns and issues surrounding each method are examined, and the advantages and shortcomings compared.
机译：液体推进火箭发动机能够按指令进行可变推力或推力调制，这是一种可操作性优势，自1930年代后期以来就已经进行了间歇性研究。可节流的液体推进剂火箭发动机可用于行星进入和下降，空间交会，轨道操纵（包括空间定向和稳定）以及在行星着陆过程中的盘旋和避免危险。其他应用包括控制飞机火箭发动机，使用逆行火箭限制车辆的加速度或速度以及弹道导弹防御轨迹控制。在给定的情况下，可节流的液体推进剂火箭发动机也可以连续遵循最经济的推力曲线，这与在几个选定的工作点上进行离散的节流变化相反。可变推力对液体推进火箭发动机的力学和动力学的影响以及节流过程中的困难和问题是节流行为的重要方面。这篇评论提供了以美国发动机为中心的液体推进火箭发动机节流的详细调查。讨论了几种液体推进剂火箭发动机的节流方法，包括高压降系统，双喷射器歧管，气体喷射，多个腔室，脉冲调制，喉道节流，可移动喷射器组件和流体动力耗散喷射器。研究了每种方法的顾虑和问题，并比较了优点和缺点。

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