Method for simultaneously realizing attitude maneuver and suppressing vibration of spacecraft with flexible accessory

A technology for attitude maneuvering and vibration suppression, applied in attitude control and other directions, can solve problems such as inability to suppress vibration and waste of jet resources, and achieve the effects of easy on-orbit real-time calculation, fuel saving, and high engineering feasibility.

Inactive Publication Date: 2010-09-15
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to solve the problems of wasting jet resources and being unable to suppress vibration in the existing attitude maneuver control method,

Method used

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  • Method for simultaneously realizing attitude maneuver and suppressing vibration of spacecraft with flexible accessory
  • Method for simultaneously realizing attitude maneuver and suppressing vibration of spacecraft with flexible accessory
  • Method for simultaneously realizing attitude maneuver and suppressing vibration of spacecraft with flexible accessory

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specific Embodiment approach 1

[0016] Specific implementation mode one, to combine figure 1 and Image 6 Describe this embodiment, a method of attitude maneuvering while suppressing vibration of a spacecraft with flexible appendages, which is realized based on the maneuvering control system of a spacecraft with flexible appendages, and the maneuvering control system of a spacecraft with flexible appendages includes an attitude feedback controller 1. Jet control logic 2, spacecraft with flexible attachment 3 and spacecraft jet thruster 4, the attitude signal output end of the spacecraft 3 with flexible attachment is connected with the attitude signal input end of attitude feedback controller 1, and the attitude feedback controller The control torque signal output terminal of 1 is connected with the control torque signal input terminal of the jet control logic 2, and the jet switch command signal output terminal of the jet control logic 2 is connected with the jet switch command signal input terminal of the...

specific Embodiment approach 2

[0026] Specific implementation mode two, to combine Figure 2 to Figure 5 This embodiment is described. This embodiment is a further description of Embodiment 1. The four jet switch sequences described in Step 2 are positive opening sequence, positive closing sequence, negative opening sequence, and negative closing sequence.

[0027] Figure 2 to Figure 5 middle T is the first-order modal vibration period of the spacecraft with flexible attachment 3 in step 1. like Figure 2 to Figure 5 As shown, the schematic diagrams of the four switch command sequences of the present invention are respectively "positive opening sequence", "positive closing sequence", "negative opening sequence", and "negative closing sequence", which sequentially realize the positive opening and positive closing of the jet , Reverse open, reverse close command output, change a single switch command into multiple outputs, after such processing can avoid the vibration of the flexible attachment when the...

specific Embodiment approach 3

[0028] Specific implementation mode three, This implementation mode is a further description of the specific implementation mode 1. The minimum action time of the switch sequence in step 3 t min = T / 3 +T h ,in T h is the response time of the jet thruster hardware, T is the first-order modal vibration period of spacecraft 3 with flexible attachments.

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Abstract

The invention discloses a method for simultaneously realizing attitude maneuver and suppressing vibration of a spacecraft with a flexible accessory, relating to a control method of a spacecraft with a flexible accessory and solving the problems of jet resource waste and vibration suppression incapability of the traditional attitude maneuver control method. The method for simultaneously realizing attitude maneuver and suppressing the vibration comprises the following steps of: (1) measuring the vibration modal information of a flexible spacecraft structure; (2) generating four types of jet switching sequences; (3) setting a minimum action time of the switching sequences; (4) acquiring an attitude angle and the angular velocity of the spacecraft; (5) setting an expected angle value of the attitude maneuver and generating a continuous control moment quantity of the attitude maneuver of the spacecraft according to the attitude angle and the angular velocity; (6) executing the four types of jet switching sequences according to a jet control logic and generating a non-linear switching command acted on a jet thrustor of the spacecraft; and (7) realizing the attitude maneuver of the spacecraft with the flexible accessory to the expected angle value. The invention is suitable for the field of the control of spacecrafts with flexible accessories.

Description

technical field [0001] The invention relates to a jet control method of a spacecraft with flexible accessories. In particular, it relates to a method for using a jet thruster to realize a large-angle attitude maneuver for a spacecraft while effectively suppressing the vibration of a flexible attachment. Background technique [0002] With the development of aerospace technology, modern spacecraft often have large flexible accessories such as solar panels and antennas. There is a strong rigid-flexible coupling between the central rigid body and the flexible appendages of this type of spacecraft with flexible appendages. When the spacecraft is in orbit, especially when the jet thruster is used for rapid attitude maneuvering, the nonlinear switch control is likely to arouse the continuous vibration of the flexible attachment, which will affect the stability and accuracy of the attitude maneuver, and may even damage related equipment. [0003] Usually, when the spacecraft jet t...

Claims

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Application Information

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IPC IPC(8): G05D1/08
Inventor 孔宪仁杨正贤陈雪芹董晓光叶东张锦绣廖俊徐大富张也驰许海玉
Owner HARBIN INST OF TECH
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