航天器的可重构性与自主重构方法

doi:doi:10.7527/S1000-6893.2023.28855

Abstract

Abstract:

In response to the urgent need for safe and reliable autonomous operation of multiple types of spacecraft， such as rockets， missiles， and satellites， in-depth research has been conducted on the reconfigurability and autonomous reconfiguration methods of spacecraft， aiming to improve the system reconfiguration capability of spacecraft under faults. Firstly， considering various practical disturbance factors such as aerodynamic torque， geomagnetic torque， gravity gradient torque， and process noise， a reconfigurability evaluation method for disturbed systems is proposed， which realizes the determination and quantification of reconfiguration capability. Then， a passive/active combined autonomous reconfiguration method is proposed， which balances the implementation effectiveness and difficulty of the reconfiguration scheme. When designing specific reconfiguration algorithms， an integrated design method of normal and fault modes is proposed， which balances the nominal performance and reconfigurability of the system and reduces the over-conservativeness of the reconfiguration scheme. Finally， the effectiveness of the proposed methods is verified through a simulation example.

Key words: spacecraft, reconfigurability, autonomous reconfiguration, passive/active combination, integrated design of normal and fault modes

CLC Number:

V467

Yuanyuan TU, Dayi WANG, Xiangyan ZHANG, Jiaxing LI, Xiaofeng HUANG. Reconfigurability and autonomous reconfiguration methods of spacecraft[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(23): 628855-628855.

Figures/Tables 7

Fig.1

Table 1

Possible actuator configurations

编号	配置	编号	配置
$C 0$	abcd	$C 8$	bc
$C 1$	abc	$C 9$	bd
$C 2$	abd	$C 10$	cd
$C 3$	acd	$C 11$	a
$C 4$	bcd	$C 12$	b
$C 5$	ab	$C 13$	c
$C 6$	ac	$C 14$	d
$C 7$	ad	$C ∅$	$∅$

Table 1

Fig.2

Table 2

Reconfigurable degree of system with different actuator structures in different configurations

配置编号	“4s”构型可重构度	“3o+1s” 构型可重构度
$C 0$	0.469 2	0.474 9
$C 1$	0.147 6	0.342 3
$C 2$	0.149 2	0.024 8
$C 3$	0.147 6	0
$C 4$	0.149 2	0
$C 5$ ~C₁₄	0	0
$C ∅$	0	0

Table 2

Table 3

Table 4

Convergence processes of BUE controllers over different configuration subsets

迭代步 $i$	$E C 1$		$E C 2$		$E C 3$		$E C 4$
迭代步 $i$	$p 1 i$	BRD₁	$p 2 i$	BRD₂	$p 3 i$	BRD₃	$p 4 i$	BRD₄
BRD提升程度/%		25.964 2		25.913 5		25.964 2		25.913 5
1	1.000 0	0.357 8	1.000 0	0.358 5	1.000 0	0.357 8	1.000 0	0.358 5
2	0.152 0	0.446 4	0.170 0	0.446 6	0.152 0	0.446 4	0.170 0	0.446 6
3	0	0.450 7	0	0.451 4	0	0.450 7	0	0.451 4
4	0	0.450 7	0	0.451 4	0	0.450 7	0	0.451 4

Table 4

Fig.3

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指标	“4s”构型	“3o+1s”构型
最优标称性能	6.900 0	6.826 3
1级可重构率/%	100	50
2级可重构率/%	0	0
1级综合可重构度	0.451 0	0.208 7

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Reconfigurability and autonomous reconfiguration methods of spacecraft

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