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Method for improving inertial guidance precision with observable attitude errors

An inertial guidance and error technology, applied in the fields of inertial navigation and inertial guidance, can solve problems such as inaccurate error coefficients and unobservable attitude angle errors

Active Publication Date: 2020-10-16
BEIJING INST OF AEROSPACE CONTROL DEVICES
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0007] The technical solution of the present invention is to overcome the problem that the existing attitude angle error cannot be observed, which leads to inaccurate error coefficients of separation, and then cannot accurately compensate the inertial guidance tool error coefficient, which causes relatively low guidance accuracy, and proposes a method with considerable attitude angle error Method of Improving Inertial Guidance Accuracy

Method used

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  • Method for improving inertial guidance precision with observable attitude errors
  • Method for improving inertial guidance precision with observable attitude errors
  • Method for improving inertial guidance precision with observable attitude errors

Examples

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Embodiment 1

[0220] The landing point accuracy of an inertial guided missile mainly depends on the error of the guidance tool. During the flight, the telemetry navigation speed includes the error of the guidance tool caused by inertial devices such as gyroscopes and accelerometers. information. The speed error can be obtained by calculating the difference of the flight telemetry speed (such as image 3 shown by the solid line in the center), and the attitude angle error can be obtained by solving the star sensor (such as Figure 4 shown).

[0221] In order to observe the attitude angle error, a starlight observation method is given below.

[0222] (1) Starlight Observation System

[0223] A starlight observation system with two degrees of freedom of rotation (hereinafter referred to as a dual-axis platform) using a gimbal structure. The schematic diagram of the platform frame and its body is shown in Figure 5 shown.

[0224] The dynamic gyro and the stabilization circuit are used tog...

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Abstract

The invention discloses a method for improving inertial guidance precision with observable attitude errors. The method comprises the following steps of (1) acquiring an inertial guidance remote external measurement speed error and a position error,(2) acquiring an inertial guidance attitude angle error,(3) separating a gyroscope error coefficient according to the attitude angle error,(4) separating an accelerometer error coefficient according to the remote external measurement speed error, and (5) compensating the observed quantity of the inertial guidance remote external measurement speed byutilizing the determined value of the tool error.

Description

technical field [0001] The invention relates to a method for improving inertial guidance precision with observable attitude errors, and belongs to the technical fields of inertial navigation and inertial guidance. Background technique [0002] At present, the inertial navigation of spacecraft mainly uses the inertial measurement system (strapdown system or platform system) composed of gyroscope and accelerometer as the motion information measurement component, and its accuracy directly determines the guidance accuracy of the spacecraft. Therefore, the inertial measurement system Errors are generally referred to as inertial guidance tool errors. [0003] Since the error of the inertial measurement system cannot be directly observed, the error of the inertial measurement system must be compensated or corrected by the externally measured speed, attitude and other information to improve the guidance accuracy, which involves how to separate the error coefficient of the inertial m...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/16G01C21/02G06F17/16
CPCG01C21/165G01C21/02G06F17/16
Inventor 魏宗康
Owner BEIJING INST OF AEROSPACE CONTROL DEVICES