Guidance method and system for an aircraft

A technology of aircraft and guidance law, which is applied in the field of aircraft guidance methods and systems, can solve the problems of large amount of misses, easy loss of targets at the guidance end, etc., and achieve the effect of improving versatility and simplifying computational complexity

Active Publication Date: 2022-04-05
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this method is proposed for stationary targets. If the target is a different type of maneuvering target, it will easily produce a large amount of misses.
At the same time, this method is easy to lose the target at the end of the guidance

Method used

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  • Guidance method and system for an aircraft
  • Guidance method and system for an aircraft
  • Guidance method and system for an aircraft

Examples

Experimental program
Comparison scheme
Effect test

experiment example 1

[0108] Original target (initial target) T 0 and three comparison targets T within 300m distance from the original target 1-3 , the preset threshold C=1,

[0109] Original target T 0 The attribute value of is (5), and the three comparison targets T 1-3 The attribute values ​​of are (3, 5, 7).

[0110] Original target T 0 The maneuverability is (20m / s 2 ), three comparison targets T 1-3 The maneuverability of each is (30m / s 2 ,20m / s 2 ,10m / s 2 ).

[0111] Original target T 0 The distance from the aircraft is (5km), and the three comparison targets T 1-3 The distances to the aircraft are (3km, 4km, 5km).

[0112] Calculate the three comparison targets separately (1), (e 2 ), will (T 3 ) as the target.

experiment example 2

[0114] In order to verify that the guidance method of an aircraft provided by this application has a higher hit rate compared with the traditional guidance law, the simulation simulation is carried out in this application, and the simulation results are as follows: image 3 Shown:

[0115] First, set the initial motion parameters of the aircraft and the target:

[0116] Aircraft speed: 2000m / s 2 , the moving speed of the target: 340m / s 2 , target initial track angle: -10°, aircraft initial track angle: 20°, terminal expected landing angle: 20°, target initial position: (10000, 10000)m, aircraft initial position: (0, 4000)m, Target maneuvering acceleration: a T =9gsin(πt), guidance coefficient: N=3; M=2.

[0117] Set the relative motion parameters according to the above initial motion parameters;

[0118] Let K=V T / V M , V R =V M -V T , at this time the relative motion equation is obtained:

[0119]

[0120] Convert relative acceleration to a proportional guidanc...

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Abstract

The invention discloses an aircraft guidance method and system, wherein the guidance method comprises: step 1: obtaining the relative motion parameters between the aircraft and the target according to the motion parameters of the aircraft and the target; step 2: converting the relative acceleration is the proportional guidance guidance law with offset term; step 3: get the guidance command of the aircraft according to the proportional guidance guidance law with offset term, relative motion parameters and motion parameters. The guidance method of the aircraft provided by the invention can update the position of the maneuvering target in real time, realize the attack on the maneuvering target and avoid the situation that the aircraft loses the target at the end.

Description

technical field [0001] The invention relates to the technical field of guidance and control, in particular to an aircraft guidance method and system. Background technique [0002] With the iterative development of guidance technology, the new requirements for guidance tasks have led to the vigorous development of subdivided guidance theories such as cooperative guidance, computational guidance, and nonlinear guidance with multi-constraints as the basic requirements. In recent years, the multi-dimensionalization of tactical and technical indicators has made zero misses no longer the only guidance constraint. For example, anti-tank guided aircraft are required to be able to perform top-sweeping attacks on targets; anti-ship guided aircraft can conduct sideways vertical attacks; For aircraft, it is required to be able to directional destroy fighter fuel tanks and guided aircraft warheads; for targets with great value such as deep underground targets and command centers, it is n...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/10
CPCG05D1/101
Inventor 林德福王亚宁王辉王伟王江臧路尧
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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