Research on lateral-directional stability augmentation system of flying wing aircraft based on reliability model

Abstract

Poor lateral-directional stability is a great risk to the design of flying wing aircraft due to the absence of vertical stabilizer. In order to improve the lateral-directional flying quality of this configuration aircraft, eigenstructure assignment technique by state feedback is adopted to design the stability augmentation system. The influence of eigenstructure on energy consumption of the control system is analyzed by citing energy consumption index in this paper. In addition, a reliability model is established to measure the reliability of the control system under uncertain factors. In order to assign eigenvalues and eigenvectors to obtain the control law of the system, a nested optimization model based on coupling degree, energy consumption and reliability is proposed. The outer optimization is used to optimize the eigenstructure, and inner optimization is used to compute the reliability of the control system in optimization process. A flying wing aircraft is used as a basis for the design of the stability augmentation system through the suggested optimization strategy. The optimization results demonstrate the validity of the method, and the lateral-directional flying quality of the aircraft has been improved greatly.

Keywords

Flying wing eigenstructure assignment stability augmentation system energy consumption reliability model

Get full access to this article

View all access options for this article.

References

Song

Yang

Zhang

, et al. Dihedral influence on lateral–directional dynamic stability on large aspect ratio tailless flying wing aircraft. Chinese J Aeronaut 2014; 27: 1149–1155.

Song

Yang

Xie

, et al. Method for improving the natural lateral-directional stability of flying wings. J Aerosp Eng 2016; 29: 06016003.

Snyder

Weisshaar

. Flutter and directional stability of aircraft with wing-tip fins: Conflicts and compromises. J Aircraft 2013; 50: 615–625.

Wise KA. X-45 program overview and flight test status. AIAA paper 2003-6645, 2003.

Davidson R. Flight control design and test of the joint unmanned combat air system (J-UCAS) X-45A. AIAA paper 2004-6557, 2004.

Stenfelt

Ringertz

. Yaw control of a tailless aircraft configuration. J Aircraft 2010; 47: 1807–1811.

Peng

Wang

Qiu

. Research on control augmentation system for a flying wing aircraft. Adv Mater Res 2014; 1049: 953–956.

Satoh

Sugimoto

. Partial eigenstructure assignment approach for robust flight control. J Guid Control Dynam 2004; 27: 145–150.

Nieto-Wire C and Sobel K. Eigenstructure assignment for a tailless aircraft. AIAA paper 2007-6417, 2007.

10.

Clarke

Davies

. Robust eigenstructure assignment using the genetic algorithm and constrained state feedback. Proc IMechE, Part I: J Systems and Control Engineering 1997; 211: 53–61.

11.

Munoz-Mansilla

Aranda

Diaz

, et al. Robust control for high-speed crafts using QFT and eigenstructure assignment. IET Control Theory Appl 2010; 4: 1265–1276.

12.

Gao

Yang

Shen

. Robust eigenstructure assignment based on μ-analysis applied to flight control law design. J Beijing Univ Aeronaut Astronaut 2012; 38: 111–115.

13.

Gahinet

Apkarian

. A linear matrix inequality approach to H∞ control. Int J Robust Nonlinear Control 1994; 4: 421–448.

14.

Peng

Xinmin

Tianli

, et al. Design on stability augmentation system of flying wing aircraft using improved eigenstructure assignment with output feedback. Control Decis 2016; 31: 1111–1117.

15.

Zhang

. Parametric eigenstructure assignment for descriptor systems via proportional plus derivative state feedback. Int J Control Automat Syst 2011; 9: 15–22.

16.

Crespo

Aranda

. Eigenstructure assignment-based controllers applied to flexible spacecraft. Proc IMechE, Part G: J Aerospace Engineering 2011; 225: 709–720.

17.

Choi

Lee

Zhu

. Decoupling and tracking control using eigenstructure assignment for linear time-varying systems. Int J Control 2001; 74: 453–464.

18.

Sutha S and Thyagarajan T. Eigenstructure assignment based Multiobjective Dynamic State feedback controller design for MIMO system using NSGA-II. In: Proceedings of the 2010 international conference on modelling, identification and control, Okayama, Japan, 17–19 July 2010, paper no. 11488678, pp.870-875.

19.

Sobel

Shapiro

. Application of eigenstructure assignment to flight control design: some extensions. J Guid Control Dynam 1987; 10: 73–81.

20.

Andry

Shapiro

Chung

. Eigenstructure assignment for linear systems. IEEE Transact Aerosp Electronic Syst 1983; 19: 711–729.

21.

Kim

. Partial eigenstructure assignment algorithm in flight control system design. IEEE Transact Aerosp Electronic Syst 1999; 35: 1403–1409.

22.

Satoh

Sugimoto

. Partial eigenstructure assignment approach for robust flight control. J Guid Control Dynam 2004; 27: 145–150.

23.

Wilson

Cloutier

Yedavalli

. Control design for robust eigenstructure assignment in linear uncertain systems. IEEE Control Syst 1992; 12: 29–34.

24.

Wei

Grimble

. Robust MIMO control-system design using eigenstructure assignment and QFT. IEE Proc-Control Theory Appl 2004; 151: 198–209.

25.

Tan Z. Aerodynamic optimization of aircraft design with flying wing configuration based on stability analysis. Master Theses, Beihang University, 2016.

26.

Moorhouse

Woodcock

. Us military specification mil–f–8785c, Washington DC: US Department of Defense, 1980.

27.

Pan

Huang

, et al. Aerodynamic robust optimization of flying wing aircraft based on interval method. Aircraft Eng Aerosp Technol 2017; 89: 491–497.