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Temperature compensation method for inertia measurement units

A technology of inertial measurement and temperature compensation, which is applied in directions such as navigation through speed/acceleration measurement, which can solve the problems of large size, high power consumption, and difficulty in realizing rapid response, and achieve the effect of simple operation and strong applicability

Active Publication Date: 2014-11-05
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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Problems solved by technology

[0004] The purpose of the present invention is to solve the problems of the existing inertial measurement combined temperature control scheme, such as large power consumption, large volume, long output accuracy stabilization time, and difficulty in realizing rapid response in the actual operation process, and propose a simple and convenient operation, strong applicability, Inertial measurement combined with temperature compensation method capable of fast response during actual operation

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  • Temperature compensation method for inertia measurement units
  • Temperature compensation method for inertia measurement units
  • Temperature compensation method for inertia measurement units

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Embodiment Construction

[0013] The present invention will be described in detail below in conjunction with the accompanying drawings and embodiments.

[0014] The devices that play a measurement role in the inertial measurement combination described in this specification are inertial sensitive devices, and the inertial sensitive devices include accelerometers and gyroscopes.

[0015] The invention provides an inertial measurement combined temperature compensation method, the method is:

[0016] Step 1) Record the inertial measurement combined temperature characteristic parameters through experiments, specifically:

[0017] Place the inertial measurement combination in the temperature control turntable that can realize the functions of heating, cooling and heat preservation, set the standard temperature T°C, and when the temperature in the temperature control turntable temperature box reaches the standard temperature T°C, the inertial measurement combination stays at the following On the twenty-four ...

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Abstract

The invention discloses a temperature compensation method for inertia measurement units, which includes installing the inertia measurement units on a temperature control turntable; adjusting the temperature control turntable to keep the inertia measurement units in different temperature environments, rotating the temperature control turntable from different angles and at different speeds, and recording accelerometer passage output data, gyro passage output data and measured temperatures of each measuring point during the process; establishing a temperature characteristic mathematical model of the inertia measurement units after processing all the data, and performing temperature compensation according to the temperature characteristic mathematical model of the inertia measurement units. The temperature compensation method for the inertia measurement units has the advantages that operation is simple, applicability is strong, rapid equal-precision output of the inertia measurement units which adapt to different working temperatures after short-time charging can be realized, important technical guarantee is provided for rapid system reaction, rapid motion and accurate positioning of aircrafts.

Description

technical field [0001] The invention belongs to the technical field of inertial measurement combination design, in particular to an inertial measurement combination temperature compensation method. Background technique [0002] The inertial measurement combination is the core component of the aircraft control system. It is mainly used to measure the angular rate of the aircraft's rotation around the three axes of the projectile and the apparent acceleration of the center of mass along the three axes of the projectile during flight. The measurement accuracy of the inertial measurement combination is an important factor that directly affects the positioning accuracy of the aircraft. In addition, whether the inertial measurement combination can meet the high-precision measurement output after a short period of work under different ambient temperatures will directly affect the rapid response and rapid movement of the aircraft system. . At present, the inertial measurement combi...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/16
Inventor 陆俊清万志江高辉文
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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