Self-rotation stabilized satellite attitude prediction method based on equal-inclination-angle attitude control

A satellite attitude and spin stabilization technology, applied in space navigation equipment, space navigation vehicles, space navigation vehicle guidance devices, etc., can solve the problem of inability to understand attitude, infrared chord width angle and sun angle change trend, and inability to choose the correct one. Issues such as start-up time

Active Publication Date: 2019-11-19
PLA NO 63686 CORPS
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Problems solved by technology

If there is no attitude prediction method before the attitude maneuver, it is impossible to understand the change trend of attitude, infrared chord width angle and sun angle, and it is impossible to choose the correct start control time

Method used

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  • Self-rotation stabilized satellite attitude prediction method based on equal-inclination-angle attitude control
  • Self-rotation stabilized satellite attitude prediction method based on equal-inclination-angle attitude control
  • Self-rotation stabilized satellite attitude prediction method based on equal-inclination-angle attitude control

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Embodiment Construction

[0081] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0082] The invention relates to a method for predicting the attitude of a spin-stabilized satellite based on equal-tilt attitude control, the method comprising the following steps:

[0083] Step A, determine the reference datum of isoclinic attitude control, if the reference datum is the sun datum, go to step B; otherwise go to step M.

[0084] Step B, if |θ 0 -θ f When |0 , θ f are the colatitude angles of the initial and target attitudes of the satellite in the solar reference system), and perform attitude prediction according to formula (1); otherwise, go to step C.

[0085]

[0086] In the formula, k(k=0,1,2,...,N) is the kth injection; ψ 0 is the longitude angle of the initial attitude of the satellite; θ(k), ψ(k) are the attitude of the satellite at the kth jet, 0L is the phase control angle on the star; ΔS is the theoretical angu...

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Abstract

The invention relates to a self-rotation stabilized satellite attitude prediction method based on equal-inclination-angle attitude control. According to the method, by taking an initial attitude, a target attitude and an attitude control amount of a self-rotation stabilized satellite in a reference coordinate system as input, a satellite attitude is predicted, an Mercato graph coordinate is calculated, a sun angle, the north infrared outer chord width and the south infrared outer chord width are predicted, according to a calculated attitude control parameter (the attitude control amount) and agiven control mode, the attitude changing trend of the satellite attitude caused by the control is calculated, and meanwhile, the changing trends of the infrared outer chord wide angel and the sun angle due to the attitude change are calculated. The method is suitable for attitude prediction of the attitude control of a self-rotation stabilized satellite in an equal-inclination-angle precession manner.

Description

technical field [0001] The present invention relates to a spin-stabilized satellite attitude prediction method (AF, AttitudeForecast) with equal tilt angle attitude control. According to the calculated attitude control parameters (attitude control amount) and the given control mode, the satellite attitude is calculated due to being controlled. The trend of attitude changes occurs, and at the same time, the change trends of infrared chord width angle and sun angle caused by attitude changes are calculated to provide a reference for monitoring the attitude adjustment process. Background technique [0002] Attitude control is the process of acquiring and maintaining the orientation of a satellite in space. For example, when a satellite communicates or observes the ground, the antenna or remote sensor must point to the ground target; when the satellite performs orbit control, the engine must be aligned with the thrust direction to be rescued; when the satellite re-enters the atm...

Claims

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Application Information

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IPC IPC(8): B64G1/24
CPCB64G1/24B64G1/245
Inventor 王恒李永刚李祥明郭力兵胡上成侯亚威冯朝阳苏春梅汪毅张龙
Owner PLA NO 63686 CORPS
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