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Trajectory Acquisition Test System for Machine-Bullet Separation

A technology of trajectory capture and test system, applied in aerodynamic test, machine/structural component test, measurement device, etc., can solve the long-term stop blowing and stop preparation time of wind tunnel, increase wind tunnel blockage, reduce wind tunnel Blowing efficiency and other issues to achieve high position accuracy, averaging effect, and increasing accuracy

Active Publication Date: 2018-04-10
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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  • Trajectory Acquisition Test System for Machine-Bullet Separation
  • Trajectory Acquisition Test System for Machine-Bullet Separation
  • Trajectory Acquisition Test System for Machine-Bullet Separation

Examples

Experimental program
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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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Abstract

The invention provides a machine-bullet separation trajectory capture test system, which includes a separation body model support drive mechanism, a measurement mechanism and a matrix model support mechanism. The supporting driving mechanism of the separated body model includes a roll control device and a linear motion control device. The linear motion control device includes a linear drive, a track, a universal hinge at the end of the track, a connecting rod, a multi-claw arm and a tail rod, and there are multiple tracks, and The wall of the wind tunnel test section is installed parallel to the central axis of the wind tunnel, and a universal hinge at the end of the track is installed on each track through a slider. The linear drive and the track are installed outside the inner wall of the wind tunnel test section. The universal hinges at each track end are connected with a connecting rod, and the other end of each connecting rod is respectively connected with the multi-claw arm through a universal hinge. The multi-claw arm is rigidly connected to the tail strut that supports the split body model. The roll control unit is mounted inside the tail boom. The system has the characteristics of high rigidity, high position accuracy 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, it is very nec...

Claims

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Application Information

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Patent Type & Authority Patents(China)
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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