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A Method of Improving the Accuracy of Inertial Guidance

An inertial guidance and precision technology, applied in the field of inertial navigation, to achieve the effects of improving real-time performance, simplifying recursive algorithm, wide application range and engineering value

Active Publication Date: 2021-12-07
BEIJING INST OF AEROSPACE CONTROL DEVICES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technology of the present invention solves the problem: overcomes the deficiencies of the prior art, provides a recursive situation that can satisfy the observation dimension change, solves the real-time problem and improves the inertial guidance precision

Method used

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  • A Method of Improving the Accuracy of Inertial Guidance
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  • A Method of Improving the Accuracy of Inertial Guidance

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Embodiment 1

[0050] When the ballistic missile uses the remote measurement data to separate the tool error, there is a set of numbers in each outer measurement period, which are the velocity errors δv in the X, Y, and Z axis directions respectively. x , δv y , δv z , using the recursive least squares method to separate the error coefficients.

[0051] First, determine the error model of the accelerometer installed in the three orthogonal directions as

[0052]

[0053] In the formula, δf x , δf y , δf z is the measurement error of the X, Y, Z axis accelerometer; k 0x , k 0y , k 0z is the zero offset of the X, Y, Z axis accelerometer; δk y , k yz is the first-order error coefficient of the Y and Z-axis accelerometers; a y is the apparent acceleration of the Y axis.

[0054] The gyroscope error model is

[0055]

[0056] In the formula, δε x , δε z is the measurement error of the X and Z axis gyroscopes; D Fz is the zero-order drift of the Z-axis gyroscope; D 1x , D 1z i...

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Abstract

The invention relates to a method for improving the precision of inertial guidance: (1), constructing a guidance tool error model according to inertial guidance remote observations and flight environment functions, and the guidance tool error model satisfies a linear relationship; (2) The error model of the guidance tool is processed to determine the recursive formula of the multidimensional observation quantity least squares method; (3) perform recursive initialization, that is, set (m+1)×(m+1) dimensional information inverse matrix P(n) and the initial value of the (m+1)×1-dimensional parameter, which is the tool error coefficient in the guidance tool error model; (4) in real time according to the current inertial guidance telemetry observation y combined with the The recursion formula determines the tool error coefficient corresponding to each recursion moment, and uses the tool error coefficient to compensate the inertial guidance telemetry observation.

Description

technical field [0001] The invention relates to a method for improving inertial guidance accuracy, and belongs to the technical field of inertial navigation. Background technique [0002] At present, the inertial navigation of spacecraft mainly adopts strapdown system or platform system composed of gyroscope and accelerometer. Before the flight of live ammunition, the error coefficients of the gyroscope and accelerometer need to be calibrated on the ground. According to the calibration results, the error compensation can effectively improve the accuracy of inertial navigation. At present, for the inertial devices calibrated on the ground, in the actual flight navigation test, there is still a large deviation between the theoretical value of the speed and position calculated based on the telemetry data and the actual flight speed and position value obtained by the external measurement. The situation of "inconsistency between heaven and earth". After analysis, the reason for...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/16G01C21/20G01C21/24
CPCG01C21/16G01C21/20G01C21/24
Inventor 魏宗康
Owner BEIJING INST OF AEROSPACE CONTROL DEVICES