首页> 外文期刊>Progress in Aerospace Sciences >A survey of automatic control methods for liquid-propellant rocket engines
【24h】

A survey of automatic control methods for liquid-propellant rocket engines

机译:液体推进式火箭发动机自动控制方法调查

获取原文
获取原文并翻译 | 示例
           

摘要

The main purpose of this survey paper is to review the field of convergence between the liquid-propellant rocket-propulsion and automatic-control disciplines. A comprehensive collection of academic works and some industrial developments are summarised and discussed, making the link to the current context of launcher reusability. The main control problem in liquid-propellant rocket engines (LPRE), the target of this survey, generally consists in tracking set-points in combustion-chamber pressure and mixture ratio, their main operating quantities. This goal is attained via the adjustment of flow-control valves while complying with operating constraints. Each aspect of control systems, ranging from modelling to the actual control techniques, is reviewed and subsequently related to the rest of aspects. The comparison of the different approaches points to the general use of linearised models about concrete operating points for deriving steady-state controllers, which in most cases are of PID type. Other more sophisticated approaches present in the literature, incorporating some nonlinear, hybrid or robust techniques, improve certain aspects of performance and robustness. Nevertheless, no fully nonlinear or hybrid frameworks, which may allow the control of a wider throttling domain, have been published. In addition, control during the thermally and structurally demanding transient phases is usually in open loop, and hence with low correction margins. This sort of control enhancements, probably together with more sophisticated monitoring architectures, would serve to extend the life of LPRE, a significant factor in their reusability. Therefore, this survey intends to draw a path for the future control design trends which will certainly be more suitable for reusable LPRE.
机译:本调查纸的主要目的是审查液体推进剂火箭推进和自动控制学科之间的收敛领域。总结和讨论了一系列综合学术作品和一些工业发展的集合,使得目前的发射器可重用情况的联系。液体推进剂火箭发动机(LPRE)的主要控制问题,该调查的目标通常包括跟踪燃烧室压力和混合比的设定点,它们的主要操作量。通过调整流量控制阀,同时遵守操作约束,实现此目标。控制系统的每个方面,从建模到实际控制技术,都被审查并随后与其他方面相关。不同方法的比较指出了用于导出稳态控制器的具体操作点的线性操作点的一般用途,在大多数情况下都是PID型。其他更复杂的方法存在于文献中,包括一些非线性,混合或稳健的技术,改善了性能和鲁棒性的某些方面。然而,没有公布的完全非线性或混合框架,其可以允许控制更宽的节流域。另外,在热和结构上要求瞬时相位期间的控制通常在开环中,因此具有低校正边缘。这种控制增强功能,可能一起与更复杂的监控架构一起,将用于延长LPRE的寿命,这是重症的重要因素。因此,本调查打算为未来的控制设计趋势引起一条路径,这肯定会更适合可重复使用的LPRE。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱:kefu@zhangqiaokeyan.com

京公网安备:11010802029741号 ICP备案号:京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有
  • 客服微信

  • 服务号