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CLC number: TP27; V24

On-line Access: 2017-07-31

Received: 2016-06-25

Revision Accepted: 2016-10-14

Crosschecked: 2022-04-22

Cited: 0

Clicked: 17835

Citations:  Bibtex RefMan EndNote GB/T7714

 ORCID:

Lin Cao

http://orcid.org/0000-0002-8943-9479

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Article info.

Frontiers of Information Technology & Electronic Engineering  2017 Vol.18 No.7 P.882-897

http://doi.org/10.1631/FITEE.1601363


Flight control for air-breathing hypersonic vehicles using linear quadratic regulator design based on stochastic robustness analysis


Author(s):  Lin Cao, Shuo Tang, Dong Zhang

Affiliation(s):  College of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China; more

Corresponding email(s):   zhangdong@nwpu.edu.cn

Key Words:  Air-breathing hypersonic vehicles (AHVs), Stochastic robustness analysis, Linear-quadratic regulator (LQR), Particle swarm optimization (PSO), Improved hybrid PSO algorithm


Lin Cao, Shuo Tang, Dong Zhang. Flight control for air-breathing hypersonic vehicles using linear quadratic regulator design based on stochastic robustness analysis[J]. Frontiers of Information Technology & Electronic Engineering, 2017, 18(7): 882-897.

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Abstract: 
The flight dynamics model of air-breathing hypersonic vehicles (AHVs) is highly nonlinear and multivariable coupling, and includes inertial uncertainties and external disturbances that require strong, robust, and high-accuracy controllers. In this paper, we propose a linear-quadratic regulator (LQR) design method based on stochastic robustness analysis for the longitudinal dynamics of AHVs. First, input/output feedback linearization is used to design LQRs. Second, subject to various system parameter uncertainties, system robustness is characterized by the probability of stability and desired performance. Then, the mapping relationship between system robustness and LQR parameters is established. Particularly, to maximize system robustness, a novel hybrid particle swarm optimization algorithm is proposed to search for the optimal LQR parameters. During the search iteration, a Chernoff bound algorithm is applied to determine the finite sample size of Monte Carlo evaluation with the given probability levels. Finally, simulation results show that the optimization algorithm can effectively find the optimal solution to the LQR parameters.

基于随機魯棒性分(fēn)析的吸氣式高超聲速飛行器線性二次調節器設計

概要:吸氣式高超聲速飛行器(air-breathing hypersonic vehicle, AHV)的飛行動力學模型具有高度非線性與多變量耦合等特性,且受到内部不确定性與外(wài)部幹擾的綜合影響,因此需要具有強魯棒性與高精度的控制器。本文介紹了一(yī)種改進的基于随機魯棒性分(fēn)析的線性二次調節器(linear-quadratic regulator, LQR)設計方法,用于AHV的縱向飛行控制器設計。首先,應用輸入輸出反饋線性化技術設計LQR控制器。其次,基于系統參數的不确定性,将系統魯棒性表征爲滿足穩定性與設計指标要求的概率,并構建系統魯棒性與LQR參數之間的映射關系。爲了實現系統魯棒性最大(dà)化的目标,提出一(yī)種全新的混合粒子群優化算法對LQR的控制參數進行尋優計算。在優化叠代的過程中(zhōng),使用切諾夫邊界理論确定蒙特卡洛估計的随機樣本量。最後,仿真結果表明該優化算法可以高效地獲取滿足設計要求的LQR控制參數最優解。

關鍵詞:吸氣式高超聲速飛行器;随機魯棒性分(fēn)析;二次線性調節器;粒子群優化;改進混合粒子群算法

Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article

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