Fault-tolerant CKF filtering fusion method applied to flight test data analysis

A technology for data analysis and flight testing, applied in the field of target tracking, which can solve problems such as the inability to continue fusion estimation, the waste of sensor resources, and the impact of fusion stability.

Pending Publication Date: 2020-07-24
SHENZHEN INST OF GUANGDONG OCEAN UNIV
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Problems solved by technology

However, the traditional non-reset federated filter also faces two problems: First, after the fault subsystem is isolated, because the fault subsystem cannot obtain the result of fusion estimation, it can no longer perform fault detection and will always be isolated resulting in Waste of sensor resources will also affect fusion stability
Second, in the event that all subsystems fail, fusion estimation will not be able to continue

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  • Fault-tolerant CKF filtering fusion method applied to flight test data analysis
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  • Fault-tolerant CKF filtering fusion method applied to flight test data analysis

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Embodiment Construction

[0071] The invention proposes a fault-tolerant CKF filter fusion method applied in flight test data analysis. The invention first establishes a model according to the motion state of an actual target, secondly provides the steps of a fault-tolerant CKF filter algorithm related to multiplicative noise of a sub-filter, and finally provides a main filter fusion algorithm and an information feedback strategy. The flow chart of multiplicative noise-related fault-tolerant CKF filtering algorithm is as follows: figure 1 As shown, the fault-tolerant CKF filter fusion algorithm structure diagram is as follows figure 2 shown, including the following steps:

[0072] Step 1. System modeling, assuming that the system has N sensors, each sensor constitutes a filtering sub-filter, and the state variables of the sub-filter and the main filter are the same, consider the following discrete-time nonlinear system with multiplicative noise correlation , its state equation and the measurement eq...

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Abstract

The invention relates to a fault-tolerant CKF filtering fusion method applied to flight test data analysis. The method generally comprises the following three parts: in the first part, system modelingis performed according to an actual moving target; in the second part, a fault-tolerant CKF filter related to multiplicative noise is designed according to multiplicative noise correlation and faultproblems existing in the measurement system in the complex engineering environment; and in the third part, an improved filtering fusion method is provided according to the defects of a non-reset federated filter. According to the method, the filtering estimation problem related to multiplicative noise can be solved, the situation that the system breaks down can be dealt with, meanwhile, the extreme situation that all sub-filters break down can be dealt with, the fault tolerance of the system is greatly improved, and the precision of flight test data is guaranteed.

Description

technical field [0001] The invention relates to a fault-tolerant CKF filter fusion method applied in flight test data analysis, belonging to the field of target tracking. Background technique [0002] The flight experiment test is of great significance in evaluating the quality and performance of the aircraft. Using the actual flight data collected during the measurement process to analyze the state tracking trajectory of the aircraft is an important means to evaluate the performance of the aircraft. High-precision target tracking data is essential for evaluation and It is extremely important to analyze the quality and stability of the aircraft during operation. [0003] Aircraft and measurement equipment will be interfered by complex environment, equipment range and communication electromagnetic waves during operation, so that the actual flight test data obtained will be polluted by noise and cannot be used directly. In order to solve the problem of noise interference, the...

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Application Information

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IPC IPC(8): G06F17/18B64F5/60G01M99/00
CPCG06F17/18B64F5/60G01M99/005
Inventor 马中骋付东洋葛泉波申兴发刘洺辛
Owner SHENZHEN INST OF GUANGDONG OCEAN UNIV
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