Guidance method based on virtual three-point method and aircraft applying guidance method

A technology of aircraft and three-point method, applied in the field of aircraft, can solve problems such as high cost, reduced survival rate on the battlefield, and increased possibility of exposure of one's own personnel

Inactive Publication Date: 2021-07-06
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] Among the equipment used by individual soldiers at close range within 1km, when targeting typical moving targets such as armored vehicles and personnel carriers, the equipment that can be selected can be roughly divided into two types: guided and unguided. Among the guided equipment, if there is Guided individual anti-tank missiles, which are equipped with guidance devices, are expensive and costly, and it is difficult to install them on a large scale. Moreover, after th...

Method used

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  • Guidance method based on virtual three-point method and aircraft applying guidance method
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  • Guidance method based on virtual three-point method and aircraft applying guidance method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0101] To strike a moving target with an aircraft, the relevant parameters are as follows:

[0102] θ T =180°, that is, the angle between the target travel direction and the positive direction of the z-axis is 180 degrees,

[0103] The rotational angular rate ω of the line connecting the launching device and the target T =0.024rad / s,

[0104] The distance between the launching device and the target at the moment of launch of the aircraft is 500 meters,

[0105] So as to solve the target speed V T =12m / s,

[0106] The flight speed of the aircraft is calculated according to the uniform flight, that is, V=250m / s.

[0107] Through the formula (1) to solve the guidance instruction in real time,

[0108] a c =N·(q M -q T ) (one)

[0109] Then control the flight of the aircraft according to the guidance instruction until it hits the target; the obtained trajectory curve of the aircraft is as follows: figure 2 shown in . According to the ballistic curve diagram, i...

Embodiment 2

[0111]The moving target is attacked by the aircraft, and the relevant parameters are basically the same as those in Example 1, the difference lies in the distance between the launching device and the target Not sure, will Respectively set to 100m, 200m, 300m, 400m, because Different, the target speed calculated by the solution is also different, as follows:

[0112]

[0113] Obtain the ballistic curves of the aircraft in the above four cases respectively, and call out the coordinate points on the four ballistic curves, as shown in the following table:

[0114]

[0115] by table and figure 1 It can be seen that the ballistic trajectories obtained in the above four cases are basically superimposed on the trajectories in Example 1, and the abscissa values ​​of each vertical coordinate value are equal, so it can be known that the ballistic trajectory generation is only related to the angular velocity obtained during the aiming process. distance to target It is only t...

Embodiment 3

[0117] The moving target is struck by the aircraft, and the relevant parameters are basically the same as those in Example 1, except that the angle θ between the direction of travel of the target and the positive direction of the z-axis T Not 180 degrees, the target speed V T =12m / s. For the convenience of observation, set θ=270°-θ T .

[0118]

[0119]

[0120] The minimum distance between the impact point and the target is obtained through formula (6) and formula (7); among them, (x 1 ,z 1 ) represents the position coordinates of the target in the coordinate system when the aircraft lands, and (x, z) represents the position coordinates of the landing point in the coordinate system when the aircraft lands;

[0121] Δ represents the minimum distance between the impact point and the target.

[0122] θ T The value of , from 265 degrees to 100 degrees, takes the value every 5 degrees, and solves Δ, and obtains the minimum distance between the impact point and the ta...

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Abstract

The invention discloses a guidance method based on a virtual three-point method and an aircraft applying the guidance method. Before the aircraft is launched, a launching device is used for aiming at and tracking a target, and the rotation angular rate of a connecting line of the launching device and the target is obtained; and an inertial measuring device is arranged in the aircraft so that the aircraft can obtain speed information and angular speed information of the itself in real time, then a guidance instruction can be generated according to the virtual three-point method guidance law by combining the distance between the launching device and the target and the speed direction of the target and assuming that the speed of the target is kept unchanged, and therefore the aircraft is controlled to fly to the target.

Description

technical field [0001] The invention relates to a guidance method and an aircraft applying the method, in particular to a guidance method based on a virtual three-point method and an aircraft applying the same. Background technique [0002] Among the equipment used by individual soldiers at close range within 1km, when targeting typical moving targets such as armored vehicles and personnel carriers, the equipment that can be selected can be roughly divided into two types: guided and unguided. Among the guided equipment, if there is Guided individual anti-tank missiles, which are equipped with guidance devices, are expensive and expensive, and it is difficult to install them on a large scale. Moreover, after the missiles are launched, the launcher or other personnel are required to cooperate with the guidance near the target, which increases the The possibility of one's own personnel being exposed reduces the survival rate on the battlefield. For unguided weapons, the operat...

Claims

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Application Information

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IPC IPC(8): F42B15/00F42B15/01G01C21/16G01C21/20
CPCF42B15/00F42B15/01G01C21/16G01C21/20
Inventor 段鑫尧王江林德福王亚东
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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