高超声速飞行器底层性能评价指标的可行性分析

朱鸿绪; 刘燕斌; 曹瑞; 陆宇平; 汤佳骏; 衣春轮

doi:10.7527/S1000-6893.2019.23259

航空学报 >

2020 , Vol. 41 >Issue 3: 323259 - 323259

DOI: https://doi.org/10.7527/S1000-6893.2019.23259

电子电气工程与控制

高超声速飞行器底层性能评价指标的可行性分析

朱鸿绪 ,
刘燕斌 ,
曹瑞 ,
陆宇平 ,
汤佳骏 ,
衣春轮

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1. 南京航空航天大学自动化学院, 南京 211106;
2. 南京航空航天大学航天学院, 南京 210016;
3. 北京航空航天大学虚拟现实技术与系统国家重点实验室, 北京 100083

收稿日期: 2019-07-01

修回日期: 2019-12-24

网络出版日期: 2019-12-19

基金资助

国家自然科学基金（11572149）；南京航空航天大学研究生创新基地（实验室）开放基金（kfjj20180311）；虚拟现实技术与系统国家重点实验室开放基金（VRLAB2018C04）

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Feasibility analysis for underlying indictors in control performance evaluation of hypersonic vehicles

ZHU Hongxu ,
LIU Yanbin ,
CAO Rui ,
LU Yuping ,
TANG Jiajun ,
YI Chunlun

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1. College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China;
2. College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
3. State Key Laboratory of Virtual Reality Technology and Systems, Beihang University, Beijing 100083, China

Received date: 2019-07-01

Revised date: 2019-12-24

Online published: 2019-12-19

Supported by

National Natural Science Foundation of China (11572149); Open Foundation for Graduate Innovation Base of NUAA (kfjj20180311); Open Funding Project of State Key Laboratory of Virtual Reality Technology and Systems(VRLAB2018C04)

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摘要

针对控制性能指标是否适用于高超声速飞行任务评价，研究了底层指标的可行性分析方法。首先分析了高超声速飞行器的模型特性，指出底层指标具备高超声速飞行器评价可行性的两点要求。根据上述要求将可行性分析转化为对于任务变量到底层评价指标的映射分析，并提出了一种基于统计实验分析的检验方法。结合高超声速飞行器模型特点，进一步设计了可行性分析流程。然后，分别以静态任务要求和速度、高度跟踪任务要求为例，对应提出频域性能指标和时域性能指标的可行性分析方法。最后针对频域性能指标评价静态任务的可行性设计仿真实验加以验证。仿真结果表明可行性分析的结论与军标观点一致，而且所提出的分析流程具有较好的可实现性。

关键词： 高超声速飞行器; 控制性能评价; 可行性分析; 底层指标; 统计分析

本文引用格式

朱鸿绪 , 刘燕斌 , 曹瑞 , 陆宇平 , 汤佳骏 , 衣春轮 . 高超声速飞行器底层性能评价指标的可行性分析[J]. 航空学报, 2020 , 41(3) : 323259 -323259 . DOI: 10.7527/S1000-6893.2019.23259

Abstract

In order to judge whether the control performance evaluation strategy can be applied to hypersonic vehicles, a feasibility analysis of the bottom parameters is addressed. First, the modeling characteristics of hypersonic vehicles are analyzed, proposing two requirements to make sure that the underlying indictors can be applied to control the performance evaluation of hypersonic vehicles. According to the two requirements, the feasibility analysis is converted to the investigation of the map from mission variables to underlying indictors, and a method based on statistical experiments is proposed to analyze the map. Combined with the characteristics of the hypersonic vehicle model, the flow of the feasibility analysis using the underlying indicators for hypersonic flight mission evaluation is further designed. Then, following the analytic flow, hypersonic flight examples of static mission and command tracking are analyzed, proposing frequency domain indicators and time domain indicators. The simulation is conducted for the first example. Static margin and the restricted elevator deflection are set as mission requirements, while damping and frequency characteristics are set as evaluation parameters. Numerical results indicate that the conclusion of analysis is consistent with the view of military standards, and the analysis flow is relatively easy to implement.

Key words： hypersonic vehicle; control performance evaluation; feasibility analysis; underlying indictor; statistical analysis

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