Variable-stiffness damping supporting mechanism for reusable rocket

Abstract

The invention relates to a variable-stiffness damping supporting mechanism for a reusable rocket. The variable-stiffness damping supporting mechanism comprises a swing arm component, a supporting rod component, a telescopic bent beam component and a mounting base component, wherein the swing arm component comprises a swing arm connector and a swing arm; the two ends of the swing arm are fixedly connected with the swing arm connector to form the swing arm component; the swing arm connector at one end of the swing arm component is connected with a mounting base; the swing arm connector at the other end is simultaneously connected with a supporting rod and a telescopic bent beam; the mounting base component comprises a mounting base and a spring piece; when the whole supporting mechanism is in a contraction state, the spring piece is in a pressed state; and when the mechanism needs to be unfolded, an external locking device releases locking of the swing arm, and the swing arm rotates around the mounting base under the action of the spring piece to drive the bent beam to contract and rise and drive the supporting rod to extend and rise. On the basis of meeting the requirements of the geometric boundary dimension and the interface of the mounting of a rocket fairing and a cabin section structure which are repeatedly used, the original structural form of the shell section or the fairing and other rocket structures is not changed, and the overall stiffness of the structure is improved by adopting the form of a movement mechanism.

Description

technical field [0001] The invention relates to a variable stiffness damping support mechanism for reusable rockets, which is used to improve the structural rigidity of reusable rocket fairings and cabin structures during reentry and return, and provide damping and impact reduction effects to increase the integrity of the rocket structure sexual capacity. Background technique [0002] The reusability of launch vehicles is an important way to reduce launch costs, increase launch frequency, and establish normal space access capabilities. At the same time, improving the availability of landing zones is also an important factor in reducing the design constraints of launch vehicle flight trajectories. While improving the safety of landing zones, it is also It can improve the carrying capacity of the rocket, and the exploration and practice of the non-destructive recovery and reuse technology of the launch vehicle can drive the exploration and development of aerospace technology. ...

AI Technical Summary

Problems solved by technology

Therefore, it is easy to be subjected to separation vibration and external excitation to produce large deformation such as breathing effect. After repeated large deformation, the structure is prone to plastic deformation and fatigue fracture, resulting in structural damage.

[0004] To reuse the rocket fairing structure and part of the cabin structure, it is necessary to design related structures and mechanisms to improve the overall rigidity of the structure. It can be done from two aspects. On the one hand, honeycomb clips can be used The core / composite skin sandwich structure improves the overall rigidity on the premise of ensuring light weight. The disadvantages are complex manufacturing process, high cost and low pass rate; on the other hand, a support mechanism is added inside the structure to form a box-shaped closed structure

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