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

A technology of error coefficient and compensation method, applied in the field of inertial navigation, can solve problems such as no gyroscope centrifuge test method, no system-level centrifuge test method, etc., achieve high confidence, achieve precise strikes, and improve the accuracy of landing points Effect

Active Publication Date: 2021-12-31
BEIJING INST OF AEROSPACE CONTROL DEVICES
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Problems solved by technology

[0005] "Inertial Devices (Part 2)" (China Aerospace Press), pages 625 to 630, introduces the centrifuge test of single-meter level (such as quartz accelerometer, gyro accelerometer, etc.), but there is no centrifuge test of gyroscope method, and there is no system-level centrifuge test method

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

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Embodiment Construction

[0077] 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.

[0078] like figure 1 , in this embodiment, the gyroscope combines high-order error coefficient separation and compensation methods, including:

[0079] Step 101, establishing a separate test system for high-order error coefficients of gyroscope combinations.

[0080] In this embodiment, the centrifuge lever arm 2 is installed on the base 1, the inverting 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. Get the gyroscope 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 centrifuge arm 2; the counterweigh...

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Abstract

The invention discloses a gyroscope combination high-order error coefficient separation and compensation method and system. The method comprises the following steps: establishing a gyroscope combination high-order error coefficient separation test system; based on the established gyroscope combination high-order error coefficient separation test system, carrying out gyroscope combination high-order error coefficient separation test to obtain a test result; according to a test result, separating various error coefficients of the gyroscope combination in combination with a gyroscope combination error model; and according to the separated error coefficients of the gyroscope combination, correcting the error of the gyroscope combination participating in navigation solution so as to realize compensation of the inertial navigation gyroscope measurement error. According to the method, various error coefficients of the gyroscope combination can be separated, and the measurement precision of the gyroscope combination is improved through error compensation.

Description

technical field [0001] The invention belongs to the technical field of inertial navigation, and in particular relates to a method and system for separating and compensating high-order error coefficients of a gyroscope 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 p...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/16G01C25/00
CPCG01C21/183G01C25/005Y02T90/00
Inventor 魏宗康周姣
Owner BEIJING INST OF AEROSPACE CONTROL DEVICES
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