Hanging pendulum type impact buffer device of hypersonic velocity shock wave wind tunnel
A shock wave wind tunnel and hypersonic technology, applied in the direction of measuring devices, instruments, aerodynamic tests, etc., can solve the design difficulties of model support system and measurement system interference, wind tunnel components and their connection structure strength, wind tunnel Disadvantages and other problems, to achieve the effect of reducing axial displacement
Active Publication Date: 2013-05-22
INST OF MECHANICS - CHINESE ACAD OF SCI
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Problems solved by technology
[0005] The effect of such impact load and spatial displacement is very unfavorable to the operation and experimental measurement of the wind tunnel. It brings difficulties in the design of the strength of the wind tunnel components and their connection structures, and also brings difficulties to the model support system and measurement system. interference, and require the wind tunnel to return to the original set position, thus increasing the time and economic cost of wind tunnel operation
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[0017] A pendulum type impact buffering device of a hypersonic shock wave tunnel according to the present invention comprises: a truss 1 arranged at the end position of the driving section of a hypersonic shock wave wind tunnel, on which a weight-adjustable The cylindrical weight block 2 is attached to the end of the driving section of the hypersonic shock wave wind tunnel.
[0018] In the present invention, a truss 1 and a suspended heavy block 2 are arranged at the end of the driving section of the hypersonic shock tunnel, and the mass of the heavy block 2 can be adjusted as required, and one end of the heavy block is closely attached to the driving section of the shock tunnel the end of.
[0019] When the wind tunnel body moves towards the driving section, the impact force acts on the suspended weight block 2, and the gravity of the weight block 2 forms a buffering effect on the axial impulse force of the wind tunnel body. After the impact, there is a self-recovery effect ...
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The invention discloses a hanging pendulum type impact buffer device of a hypersonic velocity shock wave wind tunnel. The hanging pendulum type impact buffer device comprises a truss and a weight block. The truss is disposed at the end of a drive section of the hypersonic velocity shock wave wind tunnel. The weight block has a predetermined weight and is hung on the truss and attached to the end of the drive section of the hypersonic velocity shock wave wind tunnel. When a wind tunnel body moves towards the direction of the drive section, impact force acts on the hanging weight block, and gravity action of the weight block forms buffer action on axial surging force of the wind tunnel body. Meanwhile, after impacted, the weight block is recovered by self under the action of the weight block, backward surging force is formed to act on the wind tunnel body so that the wind tunnel body can move towards the opposite direction, axial impact load generated by the pulse mode shock tunnel is buffered, and then total axial displacement of the shock tunnel is reduced.
Description
technical field [0001] The invention relates to a technology for the development of ground wind tunnel experimental equipment for high-speed aircraft, in particular to the design of attenuation and buffering systems for the start-up impact of hypersonic shock wave wind tunnels and pulse-type wind tunnels. Background technique [0002] In the aerodynamic ground simulation test of high-speed aircraft, a commonly used equipment is the pulse type wind tunnel, and the shock wave wind tunnel is one of the most important types. [0003] The shock wave wind tunnel is mainly composed of: driving section (filled with high-pressure / high-temperature driving gas), driven section (filled with driven air with specified parameters and pressure), nozzle (used to accelerate high-pressure and high-temperature gas to supersonic speed or high Supersonic speed), test section (place aircraft model) and vacuum system (absorb test gas from nozzle and test section). [0004] The shock wave wind tunn...
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Inventor 姜宗林赵伟刘云峰
Owner INST OF MECHANICS - CHINESE ACAD OF SCI