A flight fault detection method and device based on multi-inertial group information assistance
A technology of fault detection and inspection method, applied in the field of inertial navigation, which can solve the problems of low accuracy of flight fault detection
Active Publication Date: 2020-12-25
HENGYANG ZHIGU TECH DEV CO LTD
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[0004] The embodiment of the present invention provides a flight fault detection method and device based on multi-inertial group information to solve the problem of low accuracy of flight fault detection
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[0036] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
[0037] see figure 1 , figure 1 It is a flow chart of a flight fault detection method based on multi-inertial group information assistance provided by an embodiment of the present invention, as shown in figure 1 shown, including the following steps:
[0038] Step 101, obtaining the prior information of the error rule of the navigation system based on the known flight trajectory;
[0039] Step 102, dividing the combination period according to the prio...
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The invention discloses a flight fault detection method and device based on the multiple inertia group information assistance. The method comprises the following steps of: obtaining the priori information of a navigation system error rule based on the known flight trajectory; dividing the combined time period according to the prior information to obtain a filter error covariance matrix stability phase and a filter error covariance matrix convergence phase; determining whether the current fault detection time is in the filter error covariance matrix stability phase; detecting the flight fault on the basis of a residual X<2> test method cooperative with multiple inertial groups if the current fault detection time is in the filter error covariance matrix stability phase; and detecting the flight fault on the basis of the maximum value inspection method of the covariance prior information if the current fault detection time is in the filter error covariance matrix convergence phase. According to the flight fault detection method and device based on the multiple inertia group information assistance, the accuracy of flight fault detection is improved, and the working reliability of multiple inertial groups can be effectively guaranteed.
Description
technical field [0001] The invention relates to the technical field of inertial navigation, in particular to a flight fault detection method and device based on multi-inertial group information assistance. Background technique [0002] Fault detection technology was developed in the 1960s to develop high-performance aircraft and ensure the reliability of aerospace systems. Fault detection technology can effectively improve system reliability and maintainability. And widely used in nuclear industry, chemical industry, aerospace and other aspects. [0003] The earliest means of fault diagnosis is the use of hardware redundancy technology. Using multiple sets of hardware with the same function (such as sensors), by checking the consistency of their output parameters, according to the election logic, the principle of minority obeying the majority is used to realize fault detection. Analytical redundancy is a method based on a mathematical model, and the system fault informati...
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IPC IPC(8): G01C25/00
CPCG01C25/00G01C25/005
Inventor 张春熹王峥卢鑫冉龙俊
Owner HENGYANG ZHIGU TECH DEV CO LTD