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Remote sensing satellite star sensor thermo-elastic error estimation method

A technology of star sensor and error estimation, applied in the field of satellites, can solve the problems of no explanation or report, and data not yet collected, so as to achieve the effect of improving the application ability and the measurement accuracy.

Active Publication Date: 2019-04-30
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] At present, there is no description or report of the similar technology of the present invention, and no similar data at home and abroad have been collected yet.

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  • Remote sensing satellite star sensor thermo-elastic error estimation method
  • Remote sensing satellite star sensor thermo-elastic error estimation method
  • Remote sensing satellite star sensor thermo-elastic error estimation method

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Embodiment Construction

[0010] A method for estimating thermoelastic error of a remote sensing satellite star sensor, characterized in that the method comprises the steps of:

[0011] Described step one, establishes the measurement model of star sensor that comprises star sensor thermoelasticity error, concrete steps are as follows:

[0012] Step 1-1, establish the thermoelastic error model of the star sensor, as follows:

[0013]

[0014] where ω represents the angular velocity of the satellite, t represents time, and the constant f i0 Indicates the constant error, A φi , A θi , is the amplitude of the periodic change caused by thermal deformation. φ h , θ h , ψ h is the angular change of the three-axis attitude caused by the thermal change caused by the orbital period.

[0015] Step 1-2. Add the star sensor thermoelastic error model in step 3-1 to the star sensor measurement model middle;

[0016]

[0017] where C s 3×3 matrix constructed for star sensor sensor output angles, C ...

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Abstract

The invention discloses a remote sensing satellite star sensor thermo-elastic error estimation method. The method comprises the following steps: 1) establishing a star sensor measurement model including star sensor thermo-elastic errors; 2) converting the unit direction vector from the center of mass of a satellite to a landmark under a satellite body coordinate system and obtained through load observation to an inertial coordinate system through the star sensor measurement model established in the step 1); and 3)obtaining unit direction vector from the center of mass of the satellite to the landmark in the inertial coordinate system by utilizing the satellite GPS data and geographic data of the landmark and combining coordinate system conversion, and establishing equality relationship with the unit direction vector from the center of mass of the satellite to the landmark under the inertial system comprising the star sensor measurement model, obtaining a star sensor measurement model through multiple measurement of load and estimating star sensor thermo-elastic errors.

Description

technical field [0001] The invention relates to the field of satellites, in particular to a thermoelastic error estimation method for a star sensor of a remote sensing satellite. Background technique [0002] With the development of remote sensing satellite technology, the number of remote sensing satellites is gradually increasing, the ground resolution of remote sensing satellites and the performance of remote sensing satellites are rapidly improving, as well as the number and accuracy of ground control points. The thermoelastic error estimation of star sensors improves the measurement accuracy of star sensors. [0003] Do not find description or report similar to the present invention at present, also do not collect similar data both at home and abroad. Contents of the invention [0004] In order to estimate the thermoelastic error of the star sensor due to thermal influence, the present invention proposes a method for estimating the thermoelastic error of the remote s...

Claims

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Application Information

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IPC IPC(8): G01C25/00
CPCG01C25/00
Inventor 孙俊彭杨陈文王兆龙龙小祥
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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