Method for resolving and determining satellite counterglow oriented object posture for effectively avoiding ground gas light influence

A target attitude and determination method technology, applied in the direction of integrated navigator, etc., can solve the problem of not being able to pre-design offline, and achieve the effects of weak avoidance ability, simple algorithm, and good real-time performance

Inactive Publication Date: 2010-10-13
AEROSPACE DONGFANGHONG SATELLITE
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AI Technical Summary

Problems solved by technology

[0004] The technical solution of the present invention is: by finding the conditions that allow the star sensor to avoid the influence of the earth, atmosphere and light interference to the greatest possible extent, combined with the requirements for pointing to the sun, using a simple analytic

Method used

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  • Method for resolving and determining satellite counterglow oriented object posture for effectively avoiding ground gas light influence
  • Method for resolving and determining satellite counterglow oriented object posture for effectively avoiding ground gas light influence
  • Method for resolving and determining satellite counterglow oriented object posture for effectively avoiding ground gas light influence

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Example Embodiment

[0046] Example: Determining the attitude of the windsurfing board to the Japanese directional target

[0047] Consider a commercial agile satellite operating in a sun-synchronous orbit at a height of 691km and a descending node at 10:30. Its configuration is similar to figure 1 The French Pleiades satellite shown, and its in-orbit mission mode ( Figure 4 Shown) is also similar to the latter (e.g. figure 2 Shown). The typical missions of the satellite in one orbital period are Figure 4 As shown, including 4 different orbital sections, the attitude maneuvers are as follows:

[0048] (1) The north pole-to-day orientation interval from point D to point A, the duration is about 17 minutes. In this interval, the satellite operates in an inertial orientation attitude to the Japan, and point D is the shadow point of the satellite in orbit;

[0049] (2) The ground imaging interval from point A to point B, the duration is about 24 minutes. In this interval, the satellite operates in a cer...

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Abstract

The invention discloses a method for determining a satellite counterglow oriented object posture based on double-vector azimuth information by using a resolving method, in particular an object posture determining method for making a star sensor effectively avoid ground gas light influence. The method can ensure an object concerned by a satellite posture orientation, and at least one star sensor is available in the whole process. The satellite counterglow oriented object posture is determined by finding a condition of making the star sensor furthest avoid the ground gas light interference influence, combining the counterglow orientation requirement and using the simple resolving method of double-vector posture fixation. The method solves the problem of a method which must combine a star rotating trial to establish the proper target posture, is favorable for reducing and controlling the complexity, cost and risk, and overcomes the defects that the conventional method cannot perform off-line pre-design and previously avoids the ground gas light interference influence.

Description

technical field [0001] The present invention relates to a method for determining the attitude of a satellite-to-sun orientation target using an analytical method based on dual-vector azimuth information, especially a method for determining the attitude of a target that enables the star sensor to effectively avoid the influence of the earth, atmosphere, and light, and can ensure that the attitude of the satellite points to the point of interest target, and at least one star sensor is available throughout. Background technique [0002] In order to perform various missions in orbit, satellites need to establish various working attitude modes. The French Pleiades satellite is a typical representative, due to the use of a fixed sail structure (such as figure 1 shown), the star needs to be adjusted from the ground-oriented working attitude in the shadow area or imaging area of ​​the orbit to the sun-facing charging attitude of the sail (the sail axis points to the sun) in order t...

Claims

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Application Information

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IPC IPC(8): G01C21/24
Inventor 黄琳阎诚杨芳
Owner AEROSPACE DONGFANGHONG SATELLITE
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