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Inertial measuring system error model demonstration test method

A system error, model verification technology, applied in the field of civil aviation, can solve problems such as limitations

Inactive Publication Date: 2007-08-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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AI Technical Summary

Problems solved by technology

[0003] Under normal circumstances, before the inertial navigation system is installed on the passenger plane, the airborne performance assessment test is carried out through ground tests and computer simulations; and when the inertial navigation system is installed on the passenger Incentives and their analysis are more limited in the case of

Method used

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  • Inertial measuring system error model demonstration test method
  • Inertial measuring system error model demonstration test method

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Embodiment Construction

[0030] First, design a specific flight trajectory according to the error model of the inertial sensor; fly the aircraft along the designed flight trajectory and collect the inertial sensor data of a specific track point and send it to the main navigation computer; then output the collected data and measurement reference equipment The data of the inertial sensor are compared to obtain the measurement error of the inertial sensor; the error parameters in the inertial navigation error model are calculated by the airborne inertial navigation multi-position online calibration method, so as to understand the inertial navigation performance and facilitate the compensation in the navigation solution.

[0031] 1) Collect IMU signal

[0032] Use the sensor in the six-degree-of-freedom inertial measurement unit (referred to as IMU) to sense the motion characteristics of the carrier: the IMU senses the angular velocity signal of the moving carrier along its axis through the gyro, and measu...

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Abstract

This invention relates to a test method for error model verification of an inertial measurement system, which sets up a multifunction software platform to simulate and argue the airliner load test plan directly including: designing specific flying trails based on the error model of an inertial sensor, in which, an aircraft flies along the designed flying trail and collects inertial sensor data of specific flight path points and transmits them to a master navigation computer, then the collected data are compared with the data output by a measurement primary standard device to get the measurement error of the sensor to compute and get the error parameters in the inertial navigation error model with an airborne inertial navigation space multi-position online demarcating method to understand the inertial navigation performance and is convenient for the compensation in navigation computation.

Description

technical field [0001] The invention relates to an error model verification test method of a flexible strapdown inertial navigation system under the airborne environment of a civil airliner, and belongs to the technical field of civil aviation. Background technique [0002] The inertial measurement device is an important navigation device on a civil airliner. Due to many reasons such as the principle, its own design, manufacturing process, installation, and algorithm, the device will cause errors in the navigation and positioning of the civil aviation system. How to analyze and verify the error model parameters of the inertial measurement device installed on the passenger aircraft to test the effectiveness of the inertial measurement system error modeling and compensation is of great significance for improving the navigation performance of civil passenger aircraft. [0003] Under normal circumstances, before the inertial navigation system is installed on the passenger plane,...

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Application Information

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IPC IPC(8): G06F17/50G01C21/16G01C21/18G01C25/00
Inventor 华冰刘建业赖际舟曾庆化赵伟于明清王松李方宝
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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