带推力高超声速飞行器非连续点火再入轨迹研究

doi:10.3969/j.issn.1000-1093.2020.07.007

兵工学报 ›› 2020, Vol. 41 ›› Issue (7): 1307-1316.doi: 10.3969/j.issn.1000-1093.2020.07.007

带推力高超声速飞行器非连续点火再入轨迹研究

蔺君^1,2，何英姿^1,2，黄盘兴^1,2

(1.北京控制工程研究所，北京 100190； 2.空间智能控制技术重点实验室，北京 100190)

收稿日期:2019-07-27 修回日期:2019-07-27 上线日期:2020-09-23
作者简介:蔺君（1984—），男，工程师，博士后。E-mail: linjbuaa@outlook.com；
何英姿（1970—），女，研究员，博士；
黄盘兴（1986—），男，工程师，博士
基金资助:
国家自然科学基金项目（61873029）；北京市自然科学基金项目（4172070、4192068）

Research on Reentry Trajectory of Powered Hypersonic Vehicle with Discontinuous Ignition

LIN Jun^1，2, HE Yingzi^1,2, HUANG Panxing^1,2

(1.Beijing Institute of Control Engineering, Beijing 100190, China；2.Science and Technology on Space Intelligent Control Laboratory, Beijing 100190, China)

Received:2019-07-27 Revised:2019-07-27 Online:2020-09-23

摘要/Abstract

摘要： 带推力高超声速飞行器非连续点火助推可有效提高再入飞行器灵活性和机动性。为分析点火时刻和助推时长对飞行器再入轨迹的影响，根据发动机开关机状态，改进高斯伪谱法将非连续点火助推再入轨迹进行分段优化处理，实现不同点火时刻和助推时长的再入轨迹优化。发动机关机时，利用高斯伪谱法生成满足多约束条件的最优再入轨迹；发动机点火后，按照给定控制输入，由数值积分计算生成再入轨迹。在分段点处附加约束条件，保证飞行器状态在分段点处连续衔接。选取再入过程中A、B、C、D 4个典型时刻进行发动机一次点火和二次点火，以横向航程最大为目标，设计仿真算例。研究结果表明：改进的高斯伪谱法可有效求解带推力飞行器非连续点火再入轨迹优化；在助推发动机总冲一定时，点火时刻对飞行器再入轨迹影响明显。

关键词: 带推力高超声速飞行器, 再入轨迹优化, 非连续点火, 分段高斯伪谱法

Abstract: Discontinuous ignition boost for powered hypersonic vehicle could effectively improve the flexibility and maneuverability of reentry vehicle. To analyze the influences of ignition time and boost time on the reentry trajectory, the modified Gaussian pseudo-spectral method was used to optimize the reentry trajectory with different ignition time and boost duration. When the engine is off, the Gauss pseudospectral method is used to generate the optimal reentry trajectory that meets multi-constraints. After the engine is ignited, the reentry trajectory is calculated and generated by numerical integration according to the given control input. Additional constraint conditions are added to ensure the continuity of vehicle states between each pair of phases. Four typical moments (A, B, C, D) in the reentry process were selected to perform the first and second ignitions of the engine, and the simulations were designed with the target of maximum lateral range. The results show that the improved Gauss pseudospectral method could effectively solve the reentry trajectory optimization for powered hypersonic vehicle with discontinuous ignition. When the total impulse of the engine is given, the ignition timing has a significant effect on the reentry trajectory. Key

Key words: poweredhypersonicvehicle, reentrytrajectoryoptimization, discontinuousignition, multi-phaseGausspseudospectralmethod

中图分类号:

V412.4⁺4

蔺君，何英姿，黄盘兴. 带推力高超声速飞行器非连续点火再入轨迹研究[J]. 兵工学报, 2020, 41(7): 1307-1316.

LIN Jun, HE Yingzi, HUANG Panxing. Research on Reentry Trajectory of Powered Hypersonic Vehicle with Discontinuous Ignition[J]. Acta Armamentarii, 2020, 41(7): 1307-1316.

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第41卷第7期2020 年7月
兵工学报ACTA ARMAMENTARII
Vol.41No.7Jul.2020

带推力高超声速飞行器非连续点火再入轨迹研究

Research on Reentry Trajectory of Powered Hypersonic Vehicle with Discontinuous Ignition

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