Terminal guidance section simulation system
A simulation system and terminal guidance technology, applied in the directions of weapon accessories, ammunition testing, ammunition, etc., can solve the problems of small surface plane range, complex control, and high failure rate, and achieve easy fine control, large surface plane range, and platform movement. smooth effect
Inactive Publication Date: 2013-07-24
PLA AIR FORCE AVIATION UNIVERSITY
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Problems solved by technology
Disadvantages Complicated control, high failure rate, short lifespan, and a small range of surface planes for simulated missile movement
Method used
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[0010] refer to figure 1 , image 3 , the present invention comprises simulation homing head 10 and motion simulation platform, and simulation homing head is made up of cloud platform 21 and camera 22, and camera adopts digital zoom CCD camera, with the method simulation distance change of changing focal length, whole cloud platform motion and CCD camera The adjustments are all digitally controlled, and the analog seeker adopts a camera. It is recommended to use a high-speed smart dome camera, which should have at least 22 times optical zoom and 10 times digital zoom. The speed is not less than 240° / s, and the vertical is not less than 150° / s. The speed of manual control is not less than 0.8°-90° / s horizontally, and not less than 0.8°-45° / s vertically. The minimum illumination is 0.01LUX for color and 0.003LUX for black and white. It is best to have a dynamic detection function. The simulated seeker has the advantages of long service life, high performance-price ratio, and s...
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The invention relates to a terminal guidance section simulation system, which comprises a guidance head and a movement simulation platform, wherein the guidance head adopts a simulation guidance head and consists of a holder and a camera; the movement simulation platform is of a net-type supporting frame which is provided with a guide rail installation beam and a transmission belt, wherein a precise guide rail is installed on the bottom part of the guide rail installation beam, a large installation platform is installed between two guide rail installation beams, a small installation platform is installed on the side surface of the guide rail installation beam, a roll-over drag chain is installed at the left side of a stepper motor, and the simulation guidance head is installed below the large installation platform. By adopting the simulation guidance head, the terminal guidance section simulation system has the advantages of long service life, high cost performance and simple structure; and the movement simulation platform adopts a steel tube net rack as a supporting frame, adopts the precise guide rail as the movement restriction, adopts the large-power stepper motor, the high-strength transmission belt and the roll-over drag chain as the towing, and adopts the computer to carry out the movement control, so the simulation system has the advantages that the simulated range of the earth surface for missile to pass is large, the platform motion is stable and is free from jumping, and the computer can conveniently perform the precise control.
Description
technical field [0001] The invention relates to a terminal guidance stage simulation system, which meets the ground simulation, experiment and verification requirements of the precision strike process in the terminal guidance stage of a TV-guided missile by means of semi-physical simulation. Background technique [0002] At present, domestic and foreign simulation studies on the search, identification, and tracking of targets captured by the seeker at the final guidance stage generally use missile-borne optical television images to track the seeker. Using the pitching search speed of the seeker to balance the vertical movement speed of the line of sight caused by the flight speed of the missile, a search scheme with one-dimensional visual effect is obtained, so that the image on the monitor only moves smoothly in the horizontal direction. Its disadvantage is that the focus adjustment range of the seeker optical system is small, which cannot meet the requirements of ground si...
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IPC IPC(8): F42B35/00F42B15/01
Inventor 范惠林邓长春纪义国
Owner PLA AIR FORCE AVIATION UNIVERSITY