Method for refined attitude control based on output feedback for flexible spacecraft

Patent metadata

Field	Value
Publication number	US-9776741-B1
Application number	US-201615371579-A
Country	US
Kind code	B1
Filing date	Dec 7, 2016
Priority date	Jun 2, 2016
Publication date	Oct 3, 2017
Grant date	Oct 3, 2017

Abstract

The present invention provides a method for refined attitude control based on output feedback for a flexible spacecraft. The control method comprises the following steps of: a) building a flexible spacecraft dynamical system Σ 1 , converting the flexible spacecraft dynamical system Σ 1 into a flexible spacecraft dynamical system Σ 2 , and incorporating spacecraft rigid-flexible coupling dynamic disturbance into the flexible spacecraft dynamical system Σ 2 ; b) constructing an external system Σ 3 , and describing the rigid-flexible coupling dynamic disturbance through the external system Σ 3 ; c) configuring a disturbance observer for estimating the value of the rigid-flexible coupling dynamic disturbance; d) configuring a dynamic output feedback H ∞ controller; e) compounding the disturbance observer in step c) with the dynamic output feedback H ∞ controller in step d) to obtain a flexible spacecraft refined attitude control system Σ 6 ; the flexible spacecraft refined attitude control system Σ 6 compensating for the rigid-flexible coupling dynamic disturbance through the estimated value.

First claim

What is claimed is:

1. A method for refined attitude control based on output feedback for a flexible spacecraft, comprising the following steps of:
a) building a flexible spacecraft dynamical system Σ 1 , converting the flexible spacecraft dynamical system Σ 1 into a flexible spacecraft dynamical system Σ 2 , and incorporating spacecraft rigid-flexible coupling dynamic disturbance into the flexible spacecraft dynamical system Σ 2 ;
b) constructing an external system Σ 3 , and describing the rigid-flexible coupling dynamic disturbance through the external system Σ 3 ; the rigid-flexible coupling dynamic disturbance d 0 is expressed as d 0 =F(C d {dot over (η)}+Λη), in which F is a rigid-flexible coupling matrix of a flexible appendage and a body, C d is a modal damping matrix, Λ is a rigidity matrix, η is a mode of the flexible appendage, and {dot over (η)} is a derivative of the mode {dot over (η)} of the flexible appendage;
the external system Σ 3 describing the rigid-flexible coupling dynamic disturbance d 0 as:

Σ
3

:

{

w
.

=

Ww
+

H
⁡

(

u
+

d
1

)

d
0

=
Vw

⁢

⁢
in
⁢

⁢
which

,

w
⁡

[

η
T

η
.

T

]

T

,

W
=

[

0

I

-

M

-
1

⁢
Λ

-

M

-
1

⁢

C
d

]

,

⁢

H
=

[

0

-

1
J

⁢

M

-
1

⁢

F
T

]

,

V
=

[

F
⁢

⁢
Λ

FC
d

]

w is a disturbance state variable of the external system Σ 3 , {dot over (w)} is a derivative of w, W, H and V are defin

Assignees

• Univ Beihang

Inventors

• Guo Lei
• Qiao Jianzhong
• Zhang Ran
• Zhang Peixi
• Zhang Dafa

Classifications

• B64G1/24 Primary

  Guiding or controlling apparatus, e.g. for attitude control · CPC title

• B64G2001/245

  Operations & Transport · mapped topic

• G06F17/16

  Matrix or vector computation {, e.g. matrix-matrix or matrix-vector multiplication, matrix factorization (matrix transposition G06F7/78)} · CPC title

• G05D1/0883

  Physics · mapped topic

• G05D1/0825 Primary

  using mathematical models · CPC title