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

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

doi:10.7527/S1000-6893.2019.23259

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

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

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

Electronics and Electrical Engineering and Control

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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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

Cite this article

ZHU Hongxu , LIU Yanbin , CAO Rui , LU Yuping , TANG Jiajun , YI Chunlun . Feasibility analysis for underlying indictors in control performance evaluation of hypersonic vehicles[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020 , 41(3) : 323259 -323259 . DOI: 10.7527/S1000-6893.2019.23259

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