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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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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 analytical method for determining the attitude of the satellite to the sun to determine the attitude of the satellite to the sun, and to overcome the The original method has the disadvantage of not being able to pre-design offline and avoid the influence of ground, air and light interference in advance

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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Embodiment

[0046] Embodiment: Determination of the orientation target attitude of sailboard to the sun

[0047] Consider a commercial agile satellite operating in a sun-synchronous orbit at 10:30 descending node local time at an altitude of 691 km, with a configuration similar to figure 1 The French Pleiades satellite shown, with its in-orbit mission mode ( Figure 4 shown) is also similar to the latter (as in figure 2 shown). A typical flight mission on the star in one orbital period is as follows: Figure 4 As shown, it includes 4 different orbital intervals, and its attitude maneuvering method is as follows:

[0048] (1) The North Pole orientation to the sun interval from point D to point A lasts about 17 minutes. In this interval, the satellite operates in the inertial orientation attitude mode towards the sun, and point D is the shadow point where the satellite is in orbit and out of the earth;

[0049] (2) The duration of the ground imaging interval from point A to point B is...

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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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