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Accelerometer combination high-order error coefficient separation and compensation method and system

An accelerometer and error coefficient technology, applied in the field of inertial navigation, can solve problems such as no system-level centrifuge test method, and achieve the effects of overcoming slow convergence, improving efficiency and high confidence

Pending Publication Date: 2022-01-11
BEIJING INST OF AEROSPACE CONTROL DEVICES
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Problems solved by technology

[0005] On pages 625-630 of "Inertial Devices (Part 2)" (China Aerospace Press), centrifuge tests at the single-meter level (such as quartz accelerometers, gyro accelerometers, etc.) are introduced, but there is no system-level centrifuge test method

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  • Accelerometer combination high-order error coefficient separation and compensation method and system
  • Accelerometer combination high-order error coefficient separation and compensation method and system
  • Accelerometer combination high-order error coefficient separation and compensation method and system

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Embodiment Construction

[0076] In order to make the object, technical solution and advantages of the present invention clearer, the embodiments disclosed in the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0077] Such as figure 1 , in this embodiment, the accelerometer combines high-order error coefficient separation and compensation methods, including:

[0078] Step 101, establishing a separate test system for the high-order error coefficient of the accelerometer combination.

[0079] In this embodiment, the centrifuge lever arm 2 is installed on the base 1, the reverse platform 4 is installed on one end of the centrifuge lever arm 2, and the counterweight 5 is installed on the other end of the centrifuge lever arm 2, and then Construct the accelerometer combined high-order error coefficient separation test system, such as figure 2 shown. Wherein, the connection point between the centrifuge arm 2 and the base 1 is the center of the ...

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Abstract

The invention discloses an accelerometer combination high-order error coefficient separation and compensation method and system. The method comprises the following steps of: establishing an accelerometer combination high-order error coefficient separation test system; based on the established accelerometer combination high-order error coefficient separation test system, performing accelerometer combination high-order error coefficient separation test to obtain a test result; according to a test result, combining an accelerometer combination error model to separate various error coefficients of the accelerometer combination; and correcting the error of the accelerometer combination participating in navigation calculation according to the separated error coefficients of the accelerometer combination, thereby realizing error compensation of the inertial navigation apparent acceleration. Various error coefficients of the accelerometer combination can be separated, and the measurement precision of the accelerometer combination is improved through error compensation.

Description

technical field [0001] The invention belongs to the technical field of inertial navigation, in particular to a method and system for separating and compensating high-order error coefficients of an accelerometer combination. Background technique [0002] Inertial navigation is widely used in the fields of missiles, aircraft, ships and weapons. Its main function is to determine the position, velocity and attitude information of the carrier relative to the navigation system in real time. In the process of realizing the above-mentioned navigation functions, the accuracy of the gyroscope combination directly determines the accuracy of the attitude calculation, and the accuracy of the accelerometer combination directly determines the accuracy of the position and velocity. In order to achieve high-precision navigation, the accuracy of inertial devices must be improved from the hardware. However, it is difficult to greatly improve the accuracy of inertial devices in a short period o...

Claims

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Application Information

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IPC IPC(8): G01C25/00
CPCG01C25/005Y02T90/00
Inventor 魏宗康周姣
Owner BEIJING INST OF AEROSPACE CONTROL DEVICES
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