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On-orbit error separation method of spacecraft guidance tool

A space vehicle and error separation technology, applied in the directions of navigation calculation tools, instruments, integrated navigators, etc., can solve the problem that the error coefficient cannot meet the aircraft, and achieve the effect of simple algorithm, easy engineering, and improved confidence.

Inactive Publication Date: 2017-08-29
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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AI Technical Summary

Problems solved by technology

At present, the ground calibration method of the inertial system is relatively mature, but when the inertial system is actually applied to the flight mission, the error coefficient of the ground calibration due to the vibration of the aircraft and the change of the space environment cannot meet the requirements of the long-term flight of the aircraft and spacecraft in space. positioning requirements

Method used

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  • On-orbit error separation method of spacecraft guidance tool
  • On-orbit error separation method of spacecraft guidance tool
  • On-orbit error separation method of spacecraft guidance tool

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Embodiment

[0039] The gyroscope and accelerometer data are generated by the trajectory generator under pure inertial conditions, and the remote heterodyne method is used for simulation calibration. Drift errors from the gyroscope and accelerometer are introduced. Simulation trajectory such as Figure 1-Figure 3 As shown, the corresponding angular velocity and acceleration are as Figure 4 and Figure 5 shown.

[0040] The invention has the following beneficial effects: the invention can overcome the deficiency of "inconsistency between heaven and earth" in the existing guidance tool error separation technology, can calibrate the error coefficient of the guidance tool in real time and on-orbit, has a simple algorithm, and is convenient for engineering. In addition, this patent adopts the method of combining the least square method and the characteristic root estimation, which improves the confidence of the error coefficient estimation.

[0041] This patent introduces the drift error o...

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Abstract

The invention discloses an on-orbit error separation method of a spacecraft guidance tool. According to the difference between a real-time telemetering speed and an exterior measuring rate of a spacecraft, through combination of a least square method and latent root estimation, an error coefficient of a guidance tool is calibrated on orbit in real time and the guidance tool error is compensated. The method solves the problem that the existing guidance tool error separation method produces mismatching of the positions of the spacecraft in air and ground coordinates of the spacecraft, realizes on-orbit real-time calibration of an error coefficient of the guidance tool, utilizes a simple algorithm and is easy to industrialize. Through combination of the least square method and the latent root estimation, confidence of the error coefficient estimation is improved.

Description

technical field [0001] The invention relates to the field of guidance tools, in particular to a method for separating on-orbit errors of space vehicle guidance tools. Background technique [0002] The inertial instrument is the heart of the strapdown inertial navigation system, and its error will directly affect the spacecraft's orbital accuracy and landing point deviation. The on-orbit separation of error coefficients of SINS guidance tools is an important means to improve the navigation accuracy of spacecraft, and the core of error coefficient separation is the research of parameter estimation methods. At present, the ground calibration method of the inertial system is relatively mature, but when the inertial system is actually applied to the flight mission, the error coefficient of the ground calibration due to the vibration of the aircraft and the change of the space environment cannot meet the requirements of the long-term flight of the aircraft and spacecraft in space....

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00G01C21/20G01C21/24
CPCG01C21/20G01C21/24G01C25/005
Inventor 李超兵王晋麟肖称贵李学锋禹春梅祁琪徐帆徐国强
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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