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Gesture maneuvering trajectory calculation method for synchronous orbit SAR (synthetic aperture radar) satellite

A technology of satellite attitude and attitude maneuvering, which is applied in the direction of motor vehicles, attitude control, space navigation equipment, etc., and can solve the problem of unresolved yaw guidance state attitude transition problems, etc.

Active Publication Date: 2016-12-07
BEIJING INST OF CONTROL ENG
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Problems solved by technology

At present, the commonly used attitude maneuvering trajectory planning algorithm mainly solves the attitude transition problem between offset attitudes, that is, the connection problem of each isolated point in the phase plane (a fast maneuvering method for aircraft attitude based on a sinusoidal angular acceleration derivative, CN201410256156. 6), does not solve the attitude transition problem between the yaw guidance state and the yaw bias state

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  • Gesture maneuvering trajectory calculation method for synchronous orbit SAR (synthetic aperture radar) satellite
  • Gesture maneuvering trajectory calculation method for synchronous orbit SAR (synthetic aperture radar) satellite
  • Gesture maneuvering trajectory calculation method for synchronous orbit SAR (synthetic aperture radar) satellite

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Embodiment Construction

[0140] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0141] Combining the task characteristics of yaw guidance by geosynchronous orbit SAR satellites and the actual needs of avoiding occlusion through attitude offset, the invention discloses a unique attitude maneuver trajectory calculation method for geosynchronous orbit SAR satellites, which is used to solve the yaw guidance state Attitude transition problem between and yaw bias state. Before the occlusion occurs, turn the satellite from the yaw guidance state to the yaw bias state to avoid the antenna covering the solar panel; after the occlusion ends, turn the satellite from the yaw bias state to the yaw guidance state, and continue Two-dimensional SAR payload imaging.

[0142] Such as figure 2 Shown is a schematic diagram of the attitude maneuver trajectory planning method for a geosynchronous orbit SAR satellite. It can be seen from the f...

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Abstract

The invention provides a gesture maneuvering trajectory calculation method for a synchronous orbit SAR (synthetic aperture radar) satellite and relates to the field of gesture transition between a yaw guide gesture and a yaw bias gesture of a satellite. Through planning a posture motion track in a yaw angle phase plane, the problem of the gesture transition between the yaw guide gesture and the yaw bias gesture is solved. Only two points among all yaw guide gestures, with the gesture angular velocity thereof to be zero, can be adopted as the cut-in or cut-out point of a state for the gesture transition between the yaw guide gesture and the yaw bias gesture. In this way, the transition between gestures can be conducted at any moment.

Description

technical field [0001] The invention relates to the field of solving the attitude transition of a satellite between a yaw guidance attitude and a yaw offset attitude, in particular to a calculation method for an attitude maneuver trajectory of a synchronous orbit SAR satellite. Background technique [0002] In order to obtain the relative motion of the geosynchronous orbit SAR satellite and the ground target and realize the two-dimensional SAR payload imaging, the satellite attitude needs to work in the yaw guidance state for a long time. The yaw guidance law of geosynchronous orbit SAR satellites is similar to that of low-orbit optical remote sensing satellites (A method for controlling the attitude of imaging satellites in motion based on incremental drift angles, CN201410151609.9), however, due to the Working in an inclined geosynchronous orbit, the variation range of yaw steering angle and yaw steering angular velocity is significantly increased, and the yaw steering ang...

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Application Information

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IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 王楷陈守磊刘新彦汤亮石恒
Owner BEIJING INST OF CONTROL ENG
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