Time-to-go online estimation method

A technology of flight time and estimated value, which is applied in the field of aircraft control, can solve the problems of low calculation efficiency and increased calculation amount, and achieve the effects of ensuring estimation accuracy, avoiding inaccuracy, and strong robustness

Active Publication Date: 2018-04-20
XI AN JIAOTONG UNIV
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Problems solved by technology

[0008] (2) A large number of guidance system performance parameters are required to participate in the calculation, that is, the calculation amount is increased and the calculation efficiency is not high

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Embodiment Construction

[0060] The present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments.

[0061] 1) Using the measured projectile-to-target relative distance and using the system identification method and regression analysis method to establish the model respectively, the specific process is as follows:

[0062] Assume that the relative distance between projectiles and targets can be measured from time 0 to the current time m and recorded as Where m is the current moment value. According to the relative distance sequence of projectiles that have been obtained The corresponding first-order difference sequence can be obtained, denoted as and have ΔR i = R i+1 -R i . The model built by the jth modeling method at the mth moment is f j,m (·), where j=1,...,n. Here, the modeling method is system identification method and regression analysis method, n=2.

[0063] 2) Use the established model and the currently known re...

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Abstract

Provided is a time-to-go online estimation method, which is characterized by establishing models through measured missile-target relative distance and a system identification method and a regression analysis method; estimating miss distance through the established models and the currently known missile-target relative distance to obtain a miss distance estimated value, time corresponding to the miss distance estimated value being intercept time of a predicting missile for a target; calculating a time interval value between missile-target relative distance estimation time and the intercept timeof the predicting missile for the target, and multiplying the time interval value with a sampling period to obtain a time-to-go estimation component of the current time; and obtaining a time-to-go fusion estimation value through a Fisher information fusion method. The time-to-go online estimation method only needs the missile-target relative distance and the sampling period, wherein the missile-target relative distance is obtained through measurement and the sampling period is given by a guiding system, so that the method has better calculation efficiency and feasibility; and besides, the method has higher robustness.

Description

technical field [0001] The invention belongs to the field of aircraft control, in particular to an online estimation method for remaining flight time. Background technique [0002] As an important parameter of guidance system, remaining flight time is widely used in aircraft guidance. Especially in the process of the terminal guidance of the aircraft, in addition to realizing the target attack or interception of the missile, it is also necessary to restrict the incident angle and energy consumption. The optimal guidance law is a better and widely used guidance scheme at present, and the accurate estimation of the remaining flight time is the key factor to realize this guidance law and play its role. At the same time, the remaining flight time is also an important basis for the design of the weapon warhead and the judgment of the actual interception effect. The accuracy of the estimation of this parameter will directly affect the guidance performance such as control force, m...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/10
CPCG05D1/107
Inventor 蔡远利李红霞
Owner XI AN JIAOTONG UNIV
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