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An analytical method for solving the desired attitude of sunlight reflection staring for spacecraft in low-Earth orbit

A low-earth orbit and spacecraft technology, which is applied in the direction of attitude control and independent decision-making process, can solve the problems of reducing control accuracy and magnifying errors, and achieve the effect of improving attitude control accuracy

Active Publication Date: 2020-09-08
BEIHANG UNIV
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Problems solved by technology

However, the differential also has the effect of amplifying errors, thereby reducing control accuracy

Method used

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  • An analytical method for solving the desired attitude of sunlight reflection staring for spacecraft in low-Earth orbit
  • An analytical method for solving the desired attitude of sunlight reflection staring for spacecraft in low-Earth orbit
  • An analytical method for solving the desired attitude of sunlight reflection staring for spacecraft in low-Earth orbit

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Embodiment Construction

[0093] Attached below Figure 1-5 As shown, taking a certain type of low-earth orbit spacecraft as an example, the implementation process of the present invention will be described in detail. Assume that the orbital parameters of the spacecraft at the initial moment are as follows:

[0094]

[0095] Assume that the longitude and latitude of the staring target point where the light is expected to be reflected are: Λ T =108deg, Φ T =0deg, the initial time is 2:30 on October 4, 2018. Determining the expression of the sun direction vector in the earth-centered inertial coordinate system according to orbital information and ephemeris I S sun (unit vector, backlight direction), orbital parameters evolve with time. The following describes the target attitude calculation process at the initial moment in detail according to the instructions.

[0096] 1. Establish the target coordinate system according to the orbit information of the spacecraft and the latitude and longitude in...

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Abstract

The invention discloses a method for analyzing and solving an expected attitude of near-earth orbit spacecraft sunlight in reflection staring. The method comprises the following steps of establishinga target coordinate system according to orbit information of a spacecraft and target longitude and latitude information; establishing components of three axes of the target coordinate system under aninertial coordinate system so as to establish an expected quaternion of the target coordinate system relative to the inertial coordinate system; and further combining a rigid body dynamics basic theory, and finally determining an angular speed and an angular acceleration of the target coordinate system by solving a primary derivative and a secondary derivative so as to determine an integral analysis form of target attitude information. According to the invention, when the spacecraft executes a sunlight reflection staring task, the target angular speed and the angular acceleration do not need to be solved by methods such as difference, and the defects of large error and the like generated by the traditional difference method are overcome; and when the target attitude is solved, shape factors such as the oblateness of the earth and the like are considered, and the method is not based on the spherical assumption of the earth any more and is more in line with the engineering practice.

Description

【Technical field】 [0001] The present invention relates to an analytical solution method for the expected attitude of sunlight reflection gaze of a spacecraft in low-earth orbit, and especially provides a new method for solving the analytical solution of expected attitude when a spacecraft in low-earth orbit performs the task of sunlight reflection gaze. It belongs to the field of spacecraft attitude dynamics. 【Background technique】 [0002] With the development of aerospace technology, the tasks faced by spacecraft are becoming more and more complex. In recent years, video satellites have received extensive attention and rapid development, mainly because they can output continuous video signals, realize real-time monitoring of ground target points, and assist in dealing with natural disasters and other functions. The staring task is the core working mode of the video satellite. By adjusting the attitude of the spacecraft in real time, it is ensured that the staring compone...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
CPCG05D1/0088
Inventor 张福桢金磊
Owner BEIHANG UNIV
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