Actual navigation performance evaluation improvement method based on numerical integration

A numerical integration and practical technology, applied in the direction of complex mathematical operations, etc., can solve the problems of flight safety hazards, ANP value cannot accurately reflect the actual accuracy performance of the navigation system, etc., to achieve the guarantee of safe operation, fast and accurate estimation, and good applicability Effect

Inactive Publication Date: 2021-04-30
JINLING INST OF TECH
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Problems solved by technology

However, in the traditional method, the distribution of the position error is assumed to be a zero-mean normal distribution. When the aircraft is in the actual operation process, the navigation system has a deviation in the estimated position, and the ANP value calculated by the above method cannot accurately reflect the current navigation system. Therefore, it is necessary to consider the performance evaluation under the position estimation bias

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  • Actual navigation performance evaluation improvement method based on numerical integration
  • Actual navigation performance evaluation improvement method based on numerical integration
  • Actual navigation performance evaluation improvement method based on numerical integration

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[0042] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0043] The present invention provides an improved method for assessing actual navigation performance based on numerical integration. When there is a deviation in the position estimation of the integrated navigation system, the center of the error distribution in the horizontal position domain is no longer located at the origin centered on the estimated position, but at the At the position deviation, the ANP value calculated according to the above-mentioned traditional method can no longer meet the 95% inclusion interval probability. On this basis, the method of bisection iteration is used to obtain the radius value of the integral circle under the specified probability, so as to realize the evaluation of ANP. The actual navigation performance evaluation described in the present invention is schematically shown as figure 1 shown.

[0044] Accor...

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Abstract

An actual navigation performance evaluation and improvement method based on numerical integration comprises the following specific steps: 1, constructing a navigation system position error distribution model; 2, performing integral calculation of binary normal distribution on the circular area by adopting an efficient approximation method; and 3, solving the radius of the circular domain under the specified probability by using a binary iteration method, thereby obtaining the evaluation of the ANP value of the aircraft. The invention aims to provide the actual navigation performance evaluation and improvement method based on numerical integration, a navigation system position error distribution model is constructed, an efficient binary normal distribution integral solving method is adopted for integral calculation under the deviation condition, an integral circular domain radius value under the specified probability is obtained according to a binary iteration method, and the integral circular domain radius value under the specified probability is obtained. And evaluation of actual navigation performance is realized.

Description

technical field [0001] The invention relates to the field of actual navigation performance evaluation, in particular to an improved method for evaluating actual navigation performance based on numerical integration. Background technique [0002] With the gradual popularization and use of area navigation technology, the improvement of aircraft onboard equipment capabilities, and the continuous development of advanced technologies such as satellite navigation, the Required Navigation Performance (RNP) standard has emerged. RNP requires that the aircraft and its configured systems must meet the navigation accuracy required in the designated airspace. The navigation performance accuracy is the landmark to determine the RNP type, and its definition is based on the total system error allowed within the horizontal range. Taking the specified RNP1 type of route as an example, in For 95% of the total flight time, the true position of the aircraft must be guaranteed to be within 1 nau...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/18
CPCG06F17/18
Inventor 陈维娜杨忠顾姗姗王逸之唐玉娟
Owner JINLING INST OF TECH
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