Journal of Astronautics ›› 2021, Vol. 42 ›› Issue (6): 697-709.doi: 10.3873/j.issn.1000-1328.2021.06.003

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Analysis on Deployment Characteristics and Influence  Factors of Landing Gear for Launch Vehicle

YUE Shuai, LIN Qing, DU Zhong hua, NIE Hong, ZHANG Ming   

  1. 1. School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China;2. Aerospace System Engineering Shanghai, Shanghai 201109, China; 3. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)

  • Received:2020-07-24 Revised:2020-12-01 Online:2021-06-15 Published:2021-07-22

Abstract: The landing gear deployment mechanism and pneumatic driving system of vertical landing reusable launch vehicle featuring with retraction, locking and buffering are designed and researched in this paper. The singularity of the deployment mechanism is first analyzed. Based on this, the dynamic model of deployment mechanism and the lumped parameter model of pneumatic driving system are established. By combining two models, a co simulation model for deployment system is constructed. Then the influences of main body spinning angular velocity, vertical returning speed, regulated pressure of pressure reducing valve and strut friction are studied. The results show that the centrifugal force generated by vehicle spin can reduce the deployment time and the peak pressure of each hydraulic chamber. The growth of vertical speed which increases the aerodynamic drag force for landing gear, would greatly extend the deployment time. The increase of regulated pressure can shorten the deployment time, but would raise the peak pressure of each hydraulic chamber. The increase of strut friction would extend the deployment time slightly, but reduce the locking time.

Key words: Launch vehicle, Landing gear, Pneumatic system, Dynamics analysis, Co simulation

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