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Error parameter calibration method and device

A technology of error parameters and calibration methods, which is applied in directions such as navigation through velocity/acceleration measurement, and can solve the problem that the error parameters cannot meet the attitude and positioning of aircraft and spacecraft.

Active Publication Date: 2019-11-29
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] At present, the ground calibration method of the inertial system error parameters is relatively mature, but when the inertial system is actually applied to the flight mission, due to the vibration of the aircraft and the change of the space environment, the error parameters of the ground calibration cannot meet the requirements of the long-term space flight of the aircraft and spacecraft. Requirements for precise attitude determination

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  • Error parameter calibration method and device

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Embodiment 1

[0078] figure 1 It is a flowchart of an error parameter calibration method in the first embodiment of the present invention. This embodiment can be applied to the situation where the error parameters of the guidance tool need to be calibrated on orbit. The method can be executed by the error parameter calibration device, where The device can be implemented by software and / or hardware. reference figure 1 The error parameter calibration method provided in this embodiment may specifically include the following steps:

[0079] S110. Establish a state equation and a measurement equation of the aircraft navigation system. Both the state equation and the measurement equation include an error parameter vector, and the error parameter vector is composed of multiple error parameters.

[0080] Specifically, the error parameters include platform misalignment angle error, speed error, position error, gyroscope scale factor error, gyroscope drift error, accelerometer scale factor error, and ac...

Embodiment 2

[0116] figure 2 It is a structural diagram of an error parameter calibration device in the second embodiment of the present invention. This embodiment can be applied to the situation where the error parameters of the guidance tool need to be calibrated on orbit. reference figure 2 The error parameter calibration device provided in this embodiment may specifically be as follows:

[0117] The construction module 210 is used to establish the state equation and the measurement equation of the aircraft navigation system, the state equation and the measurement equation both include an error parameter vector, and the error parameter vector is composed of a plurality of error parameters;

[0118] The judgment module 220 is used to judge the observability of each of the error parameters;

[0119] The calibration module 230 is used to calibrate the observable error parameters by using Kalman filtering or adaptive filtering when there are observable error parameters.

[0120] Optionally, the...

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Abstract

The invention discloses an error parameter calibration method and device. The method comprises: establishing a state equation and a measurement equation of an aircraft navigation system, wherein both the state equation and the measurement equation comprise an error parameter vector, and the error parameter vector is formed by a plurality of error parameters; judging observability of each error parameter; when observable error parameters exist, by using a preset duration as a filtering period and utilizing Kalman filtering or adaptive filtering, calibrating out the observable error parameters. The error parameter calibration method and device disclosed by the invention fulfill the aim of calibrating out the error parameters of a guidance tool in real time in orbit.

Description

Technical field [0001] The invention relates to aircraft navigation control technology, in particular to an error parameter calibration method and device. Background technique [0002] The inertial instrument is the heart of the strapdown inertial navigation system, and the size of its error will directly affect the accuracy of the spacecraft's orbit and the size of the deviation of the landing point. For some spacecraft that perform deep space exploration, after flying to a certain altitude, they can no longer use integrated navigation to make corrections; or important strike weapons, after flying out of the homeland, in order to improve its anti-jamming ability, can perform strike missions correctly The satellite integrated navigation function will also be turned off. At this time, if the error coefficient of the inertial system guidance tool can be calibrated once, it will be an important means to improve the navigation accuracy of the spacecraft, and the core of the error co...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/16
CPCG01C21/16
Inventor 王晋麟李超兵肖称贵禹春梅祁琪徐帆徐国强
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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