Method for calculating earth's surface-orientated target attitude angle of spacecraft

A target attitude and calculation method technology, applied in attitude control, space navigation aircraft, aircraft, etc., can solve the problem that there is no need for mature algorithms for directional target attitude angle calculations

Active Publication Date: 2018-08-21
BEIJING INST OF CONTROL ENG
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AI Technical Summary

Problems solved by technology

[0004] At present, there is no mature algorithm for the calculation of the attitude angle of the surface oriented target in practice.

Method used

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  • Method for calculating earth's surface-orientated target attitude angle of spacecraft
  • Method for calculating earth's surface-orientated target attitude angle of spacecraft
  • Method for calculating earth's surface-orientated target attitude angle of spacecraft

Examples

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Embodiment 1

[0089] Embodiment 1: Take the 500km sun-synchronous orbit satellite at a certain orbital height as an example, a kind of spacecraft is specifically implemented as follows to the attitude angle calculation method of the directional target on the ground:

[0090] The accuracy threshold is set to 0.01 degrees, and the following steps are the implementation process in one control cycle when the method of the present invention is applied:

[0091] (1) First calculate the coordinates of the star in the geocentric inertial system according to the orbit information;

[0092] Direction cosine array C from J2000 inertial system to orbital system OI and distance r from the center of the earth, and from the J2000 inertial

[0093] The precession nutation matrix C of the system to the instantaneous geocentric inertial system PR They are:

[0094]

[0095]

[0096] r=6895.326381,

[0097] Calculate the coordinates of a star in the instantaneous geocentric inertial system

[0098]...

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Abstract

The invention discloses a method for calculating an earth's surface-orientated target attitude angle of a spacecraft. The method comprises the steps that the position coordinates of a satellite in a geocentric inertial system are computed according to satellite orbital information to obtain a value of a vector of the satellite pointing to the geocenter in the geocentric inertial system to be takenas an initial value of the target-pointed vector of the satellite, the coordinates of an intersection point of the target-pointed vector of the satellite and a spherical surface of an Earth ellipsoidal model are calculated according to the position coordinates of the satellite in the geocentric inertial system to further obtain a negative normal vector of the Earth ellipsoidal model on a tangentplane at the intersection point, and finally the angle between the negative normal vector and the target-pointed vector of the satellite is calculated to conduct optimization on the target-pointed vector of the satellite. According to the method, a vector value of the target-pointed vector of the satellite in a satellite orbital system is obtained by computing according to the target-pointed vector of the satellite and the satellite orbital information to further perform computing to obtain the earth's surface-orientated target attitude angle and an earth's surface-orientated target pitching attitude angle.

Description

technical field [0001] The invention relates to the field of spacecraft attitude determination and control, in particular to a method for calculating the attitude angle of a spacecraft to an orientation target on the ground. Background technique [0002] The workload of ocean observation satellites generally has attitude control requirements for surface orientation. For example, the ocean wave spectrometer is a microwave sensor specially used to measure the wave direction spectrum. It works at a small incident angle and scans 360 degrees through the antenna. It is used to observe the sea surface for a large area and for a long time to obtain the wave direction spectrum. , wind speed and wave height and other sea surface parameter information. As another example, the altimeter is used to transmit pulse signals vertically to the sea surface, and the wind speed is determined by the amplitude of the echo pulse reflected by the sea surface. This requires the attitude control to...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 刘其睿王淑一王新民张俊玲刘新彦宗红韩冬柯旗田科丰董筠张屹峰
Owner BEIJING INST OF CONTROL ENG
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