基于外测数据固体火箭发动机飞行试验推力辨识方法研究  

Research on thrust identification methods of solid rocket engine flight tests based on outer-trajectory measurement data

作　　者：呼宝鹏 薛光伟 林海奇 吕仲 黄一翀 王勇 HU Baopeng;XUE Guangwei;LIN Haiqi;LYU Zhong;HUANG Yichong;WANG Yong(Beijing Institute of Astronautical System Engineering,Beijing 100076,China;Unit 92578 of the Chinese People’s Liberation Army,Beijing 100161,China)

机构地区：[1]北京宇航系统工程研究所,北京100076 [2]92578部队,北京100161

出　　处：《兵器装备工程学报》2023年第S01期132-136,共5页Journal of Ordnance Equipment Engineering

摘　　要：通过飞行试验推力辨识结果可获取固体火箭发动机天地差异性,对发动机地面预示结果修正,使发动机内弹道预示性能更接近真实情况,提高运载火箭轨道设计精度。在传统基于飞行试验遥测数据发动机推力辨识的基础上,重点研究了基于外测数据进行固体火箭发动机飞行试验推力辨识方法。建立了基于外测数据固体火箭发动机飞行试验推力辨识计算模型,通过火箭飞行试验位置、速度等外测数据复现的视加速度值及发动机质量流量修正结果进行弹道反向计算,辨识飞行试验过程中发动机真实推力值的大小。通过与传统基于飞行试验遥测数据的固体火箭发动机推力辨识方法结果对比,验证了该方法的正确性和有效性。This paper obtains the ground-to-flight performance difference of solid rocket engines through the flight test thrust identification results,and modifies the ground prediction performance so that the internal ballistic prediction performance of the engine is closer to the real situation,thus improving the accuracy of rocket orbit design.On the basis of traditional engine thrust identification based on flight test telemetry data,it also studies the thrust identification method of solid rocket engines based on outer-trajectory measurement data.Besides,the paper establishes a computational model for thrust identification of solid rocket engines based on the outer-trajectory measurement data.The trajectory reverse calculation is carried out based on the apparent acceleration value reproduced from the outer-trajectory measurement data,such as the position and velocity of the rocket flight test and the corrected result of the engine mass flow,and the real thrust value of the engine is identified during the flight test.Compared with the traditional solid rocket engine thrust identification method based on flight test telemetry data,the correctness and validity of the proposed method are verified.

关 键 词：外测数据 固体火箭发动机 推力辨识 飞行试验 弹道复现 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]