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Projectile separation trajectory captive test system

A trajectory capture and test system technology, applied in the direction of aerodynamic test, machine/structural component test, measuring device, etc., can solve the problem of reducing wind tunnel blowing efficiency, wind tunnel long stop blowing and parking preparation time, increasing wind tunnel Problems such as blockage, achieve high position accuracy, average effect, and improve positioning accuracy

Active Publication Date: 2015-09-23
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The three angle drives, control and detection equipment in the wind tunnel also increase the degree of blockage of the wind tunnel
In addition, the special installation and commissioning of this equipment will also allow the wind tunnel to have a longer time for stopping the blowing and parking preparations, reducing the blowing efficiency of the wind tunnel

Method used

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  • Projectile separation trajectory captive test system
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Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0043] The present invention will be described in detail below with reference to the accompanying drawings.

[0044] Such as figure 1 As shown, six rails 102 are installed parallel to the axial direction in the wind tunnel on the outside of the wind tunnel test section wall 101. Long slots corresponding to each rail 102 are provided on the wall 101 of the wind tunnel test section, and the number of the rails 102 can be changed as required. A universal hinge 104 is installed on each track 102 , and each universal hinge 104 can be driven by a linear driver installed outside the wind tunnel test section to make a linear motion back and forth on the track 102 . A linear displacement sensor 103 is installed on each track 102 for measuring the linear displacement of the universal hinge 104 on the track 102 . Each universal hinge 104 is all connected with a connecting rod 106, and each connecting rod 106 all passes through the above-mentioned long slot and stretches into the wind ...

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PUM

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Abstract

The invention provides a projectile separation trajectory captive test system, comprising a separation body model support driving mechanism, a measuring mechanism and a matrix model support mechanism. The separation body model support driving mechanism comprises a rolling control device and a rectilinear motion control device, wherein the rectilinear motion control device comprises a rectilinear driver, tracks, track end universal hinges, connecting rods, a multi-pawl arm and a tail pole, and the plurality of tracks are installed on the experimental section wall of a wind tunnel and are parallel with the central shaft of the wind tunnel; each track is provided with a track end universal hinge through a sliding block; the rectilinear driver and the tracks are all installed outside the experimental section inner wall of the wind tunnel; each track end universal hinge is in connection with a connecting rod; the other end of each connecting rod is in connection with the multi-pawl arm through a universal hinge. The multi-pawl arm is in rigid connection with the tail pole supporting a separation body model. The rolling control device is installed in the tail pole. The projectile separation trajectory captive test system has the characteristics of high rigidity, high position precision and high speed.

Description

technical field [0001] The invention relates to a parallel multi-degree-of-freedom trajectory capture test system for aircraft-bullet separation, which is used for the separation between stages of aerospace and aviation vehicles, and the trajectory capture wind tunnel test for the separation of aircraft bombs and external objects, and belongs to the high-speed wind tunnel test technology, The field of aircraft flight mechanics. Background technique [0002] In the flight phases of separation between spacecraft and rocket stages, launch and release of aircraft external storage, drop of submunitions, and separation of sabot and armor-piercing projectiles from the carrier, the separation body and the parent body are in a complex and mutually interfering flow field, and the poor separation characteristics Not only will it affect the effect, but it will also lead to collisions between multiple bodies, and even endanger the safety of the parent aircraft. Therefore, the trajectory...

Claims

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Application Information

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IPC IPC(8): G01M9/00
Inventor 黄兴中魏忠武张江秦永明董金刚刘晓伟胡浩尼文斌谢峰李广良彭程蔡琛芳
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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