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Attitude maneuver dynamic optimization method based on control moment output constraint and medium

A dynamic optimization, attitude maneuvering technology, applied in attitude control, non-electric variable control, control/regulation systems, etc., can solve problems such as insufficient use of frame angular velocity

Active Publication Date: 2020-11-06
BEIJING INST OF CONTROL ENG
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Problems solved by technology

However, this kind of method fails to fully explore the control ability of the control moment gyro combination. The reason is that when solving the frame angular velocity based on planning, it needs to be calculated according to the real-time frame angular position, and the obtained frame angular velocity is generally not fully used as the output constraint. Limiting

Method used

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  • Attitude maneuver dynamic optimization method based on control moment output constraint and medium
  • Attitude maneuver dynamic optimization method based on control moment output constraint and medium
  • Attitude maneuver dynamic optimization method based on control moment output constraint and medium

Examples

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Embodiment 1

[0111] Embodiment 1: A satellite in a sun-synchronous orbit at an orbital height of 500 km, initially the satellite is in a stable operation state with zero attitude to the ground, and the attitude maneuver of rolling 60 degrees begins when the satellite time is 100 seconds. The parameters of the satellite are shown in the table below.

[0112] Table 1

[0113]

[0114]

[0115] According to the attitude maneuver dynamic optimization method based on the control moment output constraint of the present invention, the simulation results of the whole process of rolling 60 degree attitude maneuver are as follows: Figure 2 to Figure 8 shown. in figure 2 is the reference angular acceleration a ref curve. image 3 is the dynamically optimized maneuver planning angular velocity curve. Figure 4 is the dynamic optimization maneuver planning angle χ r curve. Figure 5 is the command frame angular velocity curve. Figure 6 is the δ curve of each CMG frame angle. Figu...

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Abstract

The invention discloses an attitude maneuver dynamic optimization method based on control moment output constraint and a medium, and belongs to the field of spacecraft attitude control. In an attitudemaneuver acceleration section and a deceleration section, a dynamic optimization coefficient value is calculated for a frame angular velocity combination required by maneuver according to output constraint amplitude limiting so as to fully excavate the control capability of the control moment gyroscope combination; and the time point of the deceleration section is adjusted dynamically according to the acceleration maneuvering angle. By adopting the method, the attitude maneuver dynamic optimization problem of the satellite for fully excavating the control capability of the control moment gyroscope combination is well solved.

Description

technical field [0001] The invention belongs to the field of spacecraft attitude control, and in particular relates to an attitude maneuver dynamic optimization method and a medium based on control moment output constraints. Background technique [0002] The satellite configured with the combination of control moment gyroscope as the actuator of attitude control has the ability of agile maneuvering. When the control moment gyroscope performs attitude control, it relies on the change of the frame angle to generate output torque. Its instantaneous output torque is always perpendicular to the frame axis and angular momentum direction, and its magnitude is proportional to the frame angular velocity. The direction changes continuously with the frame angle. Considering the actuator Capability and allowable control error can be given frame angular velocity limits as output constraints. At present, the general attitude maneuver method is to carry out static planning of attitude ang...

Claims

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Application Information

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IPC IPC(8): G05D1/08
CPCG05D1/0833Y02T10/40
Inventor 刘其睿袁利王淑一刘洁田科丰谌颖
Owner BEIJING INST OF CONTROL ENG
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