The study of ejection mechanism and drop-test in high-speed wind tunnel

WANG Shuai; DONG Jingang; ZHANG Chenkai; ZHAO Xingyu; XIE Feng

doi:10.11729/syltlx20200149

Volume 35 Issue 6

Dec. 2021

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Article Navigation > Journal of Experiments in Fluid Mechanics > 2021 > 35(6): 73-78

WANG S，DONG J G，ZHANG C K，et al. The study of ejection mechanism and drop-test in high-speed wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2021，35（6）：73-78. doi: 10.11729/syltlx20200149

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The study of ejection mechanism and drop-test in high-speed wind tunnel

doi: 10.11729/syltlx20200149

China Academy of Aerospace Aerodynamics, Beijing　100074, China

Received Date: 2020-12-01
Rev Recd Date: 2021-03-09

Available Online: 2021-11-12

Publish Date: 2021-12-30

Abstract

Abstract

It is necessary to evaluate the separation safety of supersonic embedded weapons for the new generation fighter. According to the requirements of high-speed wind tunnel launching test of embedded weapons, a new type of double cylinder ejection mechanism is designed, which can realize the continuously adjustment of the initial velocity and the initial angular velocity. Firstly, the NX modeling software is used to design the structural and three-dimensional modeling of the ejection mechanism. Secondly, based on the pressure equations of the cylinder rod free cavity and rod cavity, and the flow equation of the rod free cavity and rod cavity connected with the atmosphere and the piston driving force equation, the mathematical model of the ejection process was established, and the design of the ejection mechanism was simulated and analyzed by using the motion simulation software to verify the rationality of the structure. According to the control requirements of the ejection mechanism, the servo control system of the ejection mechanism was designed by using the electric servo valve and related control elements. Finally, the wind tunnel test of Mach 1.5 was carried out. The experiment shows that the maximum ejection speed of the model can reach 5.68 m/s under the condition that the air pressure is not more than 1.0 MPa, and the initial attitude of the carrier is close to the simulation results, which can meet the design and use requirements.
- jettison testing,
- ejection mechanism,
- wind tunnel test,
- motion simulation,
- embedded weapon

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References(15)

References

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