An optimal guidance method for the reentry maneuverable spacecraft

Author

Yang, Jun-Chun ; Hu, Jun ; Ni, Mao-Lin

Author_Institution

National Lab. of Space Intelligent Control, Beijing Inst. of Control Eng.

Volume

1

fYear

2006

fDate

4-6 Oct. 2006

Firstpage

746

Lastpage

750

Abstract

An optimal guidance method using the range as an independent variable for the reentry maneuverable spacecraft is presented in this paper. Firstly, the aerodynamic coefficients are estimated by using the strong tracking filter (STF). Then, the linear deviation equations are formulated by linearising the original nonlinear equations of motion around the nominal trajectory. Finally, the optimal linear regulator theory is used to design the linear state feedback control law and the simulation results for a conceptual RLV are provided

Keywords

aerodynamics; aerospace control; control system synthesis; motion control; nonlinear control systems; optimal control; regulation; space vehicles; state feedback; tracking filters; aerodynamic coefficients; linear deviation equations; linear state feedback controller design; nominal trajectory; nonlinear equations; optimal guidance method; optimal linear regulator theory; reentry maneuverable spacecraft; strong tracking filter; Aerodynamics; Control systems; Earth; Navigation; Nonlinear control systems; Nonlinear equations; Regulators; Space vehicles; Systems engineering and theory; Vehicle dynamics; Strong Tracking Filter; aerodynamic coefficients; optimal guidance; reentry maneuverable spacecraft;

fLanguage

English

Publisher

ieee

Conference_Titel

Computational Engineering in Systems Applications, IMACS Multiconference on

Conference_Location

Beijing

Print_ISBN

7-302-13922-9

Electronic_ISBN

7-900718-14-1

Type

conf

DOI

10.1109/CESA.2006.4281751

Filename

4281751