基于固体火箭发动机耗尽关机的混合轨道自适应制导方案研究  

Study on hybrid orbit self-adaptive guidance scheme of solid rocket motor based on depleted shutdown

作　　者：康建斌[1] 赵建亭[1] 王明海[2] 赵久奋[2] 

机构地区：[1]江苏自动化研究所,连云港222006 [2]第二炮兵工程学院,西安710025

出　　处：《固体火箭技术》2006年第6期407-411,共5页Journal of Solid Rocket Technology

摘　　要：针对固体火箭发动机在指令关机后存在量级小但顽固的后效冲量及推力偏差大等问题,提出了将速度增益制导(VIC)、末速匹配修正二者结合的混合轨道自适应制导方案。通过Lambert定理给出了VIC方案中需要速度的计算模型,并采用非线性的推力矢量控制(TVC)方法分析了增益速度的导引算法。为了克服固体发动机关机后仍存在量级小但顽固的后效冲量问题,并更有效地实施机动变轨,通过预测推进剂的剩余能量,并结合VIC的计算模型,建立了以增益速度匹配当前固体推进剂耗尽时产生的可能速度增量、并直至发动机自然耗尽的末速匹配修正方案。初步仿真结果表明,该制导方案具有更大的可伸缩性和广泛用途。Aiming at the obstinate after-working impulse and big thrust deviation of motor after depleted shutdown, a new hybrid orbit self-adaptive guidance scheme which combines velocity increment cutoff（VIC） and terminal velocity matching correction was put forward. Calculation model of velocity in the VIC scheme was presented by means of the Lambert theorem, and guide algorithm of velocity gain was analyzed by using non-linear thrust vector control （VIC） method. In order to overcome small but obstinate after-working impulse problem and accomplish maneuver orbit, terminal velocity matching correction scheme which makes gain velocity match possible velocity increment produced by depleted propellant was established by predicting residual energy of propellant and using calculation model of velocity gain guidance until motor depletes naturally. The simulation results show that design scheme is of great flexibility and wide application.

关 键 词：固体火箭发动机 自适应制导 需要速度 末速匹配修正 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]