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Spacecraft attitude control method under multi-constraint condition

A technology of attitude control and spacecraft, which is applied in the field of spacecraft attitude control under multi-constraint conditions, can solve problems such as difficult problems of attitude control, and achieve the effect of small amount of calculation

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Problems solved by technology

These factors have brought difficulties to its attitude control problem.

Method used

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  • Spacecraft attitude control method under multi-constraint condition
  • Spacecraft attitude control method under multi-constraint condition
  • Spacecraft attitude control method under multi-constraint condition

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Experimental program
Comparison scheme
Effect test

Embodiment

[0081] The effectiveness of the method of the present invention is illustrated below through simulation.

[0082] The coordinate system of the spacecraft body is defined as: the origin is at the center of mass, the X axis coincides with the roll axis, the Y axis coincides with the yaw axis, the Z axis coincides with the pitch axis, and the X, Y, and Z axes satisfy the right-hand rule, then in this coordinate system The solid engine array equipped below is as follows:

[0083] (1) Pitch / yaw direction

[0084] As shown in Figure 2(a) and Figure 2(b): four engine arrays are configured in the pitch direction, namely E3, E4, E7, E8; four engine arrays are configured in the yaw direction, respectively E1, E2, E5, E6

[0085] As shown in Figure 2(c), the single solid motor array is 80mm long and 40mm wide, and the motors are arranged in 9 columns and 21 rows, totaling 189, and the single-machine impulse is 1mNs.

[0086]

[0087]

[0088] (2) Scroll direction

[0089] As sh...

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Abstract

The invention relates to a spacecraft attitude control method under a multi-constraint condition, which can be applied to a spacecraft attitude control law implementation process for attitude control based on a solid engine. The method comprises the following steps: firstly, determining a solid engine for attitude control and an installation coordinate of an array in a spacecraft body coordinate system; secondly, calculating the required control impulse moment according to the attitude error of each axis; then, according to the direction in which the impulse can be provided by the solid engine to be fixed, judging the solid engine array needing to be ignited; and finally, selecting the solid engine needing to be ignited through a traversal method. According to the method, the advantages of the solid engine are fully utilized, the characteristics and constraints of the solid engine are considered in the control law implementation process, and the feasible attitude control method is given in combination with the actual situation.

Description

technical field [0001] The invention relates to a spacecraft attitude control method under multi-constraint conditions. Solid motors have the advantages of light weight, fast impulse generation, and less impact on the environment, and are suitable for inexpensive small spacecraft that only perform one space mission. The method of the invention can be used for the attitude control law design of the spacecraft which utilizes the solid motor for attitude control. It belongs to the technical field of spacecraft attitude control. Background technique [0002] At present, the attitude control of spacecraft entering orbit and eliminating initial deflection usually adopts the jet method, which requires the spacecraft to carry tanks to store fuel. Although this attitude control method has been widely used in practice, it is not suitable for attitude control of small spacecraft because of the heavy fuel and storage tanks, which increase the mass of the spacecraft. In addition, duri...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0808G05D1/101Y02T90/00
Inventor 严晗刘磊黄元郝仁剑魏春岭
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