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Full-range coverage guidance system of remote guidance aircraft with strapdown laser seeker

A guidance system and aircraft technology, applied in the field of guidance systems, can solve problems such as difficult medium-range and short-range target processing, inability to accurately strike medium-range targets, and impossible transfer

Active Publication Date: 2020-07-10
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Also due to the above-mentioned modules, the remote guidance and control aircraft cannot accurately strike medium-range targets, and even cannot strike short-range targets at all. Specifically, for medium-range targets, due to the existence of the rocket-range extension module, It is already close to the target when starting the control, and at this time the satellite signal receiving module and the inertial navigation module have just been powered on, the satellite signal receiving module needs a long time to obtain stable satellite signals, and the inertial navigation module cannot perform zero Position alignment, the sensitive attitude error is large when the power is just turned on, so it is difficult to accurately strike the medium-range target; for the short-range target, due to the existence of the rocket’s range-extending module, it may have flown over the short-range target when the control is launched. Target, it is basically impossible to turn 360 degrees to strike
[0004] However, for some specific situations, such as when the short-range guided aircraft has been exhausted and only long-range guided aircraft are left, it is naturally difficult to properly handle the sudden appearance of medium-range and short-range targets

Method used

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  • Full-range coverage guidance system of remote guidance aircraft with strapdown laser seeker
  • Full-range coverage guidance system of remote guidance aircraft with strapdown laser seeker
  • Full-range coverage guidance system of remote guidance aircraft with strapdown laser seeker

Examples

Experimental program
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Effect test

experiment example 1

[0180] In order to verify that the full-range coverage guidance system of the remote guidance aircraft provided by the application can make the aircraft have the actual capability of taking into account the full range, through simulation, the guidance system of the present invention is installed in the aircraft, Go to a plurality of ballistics / flight trajectories respectively for targets in different ranges, specifically, for targets at 9km, 13km, 23km, 28km, and 40km respectively, launch the aircraft that the guidance system of the present invention is installed respectively, obtain as follows image 3 The 5 flight trajectory diagrams shown in, from image 3 It can be seen from the figure that all the aircraft can land at the predetermined range and hit the target, that is, the aircraft provided by the application can also hit the medium-range target or even the short-range target on the basis of being able to hit the long-range target.

experiment example 2

[0182] In order to verify that the iterative module in the full-range coverage guidance system of the long-range guidance aircraft with the strapdown seeker provided by this application can obtain the line-of-sight angular rate close to the real value, specifically,

[0183] In the simulated ammunition, input the real projectile line of sight angle of the ammunition in real time by the simulation equipment, the iterative module of the present invention is stored in the simulated simulated ammunition, and the projectile visual line of sight angle rate is obtained by the iterative module iteration, in the iterative process , the state variable x 1 and x 2 The initial values ​​of all take the value of 0, k 1 The value is 0.5, k 2 The value is 0.5, k 3 The value is 0.1; the iteration frequency is 50Hz; input the ammunition’s real sight angle of the ammunition at a frequency of 50Hz; receive the state variable x delivered by the iteration module 2 The value of the state variabl...

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Abstract

The invention discloses a full-range coverage guidance system of a remote guidance aircraft with a strapdown laser seeker. The guidance system can control the aircraft to strike a remote target, a medium-range target or a short-range target, and has important engineering significance. Specifically, the guidance system comprises a decision module and a central processing module, wherein the decision module is used for selecting a guidance starting control module for executing work according to range information before launching; different guidance starting control modules can control differentcomponent modules to start work, so that corresponding component modules are controlled according to different ranges; and the central processing module generates a rudder deviation instruction by receiving information transmitted by the component modules, and controls the aircraft to fly to the target.

Description

technical field [0001] The invention relates to a guidance system of a remote guidance aircraft, in particular to a full range coverage guidance system of a remote guidance aircraft with a strapdown laser seeker. Background technique [0002] Long-range guided aircraft can carry out precise strikes on long-distance targets. In order to achieve long-distance precise strikes, remote-guided aircrafts are generally equipped with rocket range-extending modules, satellite signal receiving modules, and inertial navigation modules. The module increases the range of the aircraft, especially the range before control, and receives satellite signals through the satellite signal receiving module, so as to calculate the position information of the aircraft and the speed information of the aircraft in real time, and sense the attitude information of the aircraft through the inertial navigation module; [0003] Also due to the above-mentioned modules, the remote guidance and control aircraf...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F41G3/22F41G11/00
CPCF41G3/22F41G11/00
Inventor 王雨辰王伟林德福王江王辉师兴伟裴培程文伯
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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