A device and method for pendant conversion of the first sub-stage rocket body of a launch vehicle based on metal honeycomb buffer

Abstract

A metal honeycomb buffer-based launch vehicle first sub-stage rocket body suspension conversion device and method, used for parachute recovery of the launch vehicle first sub-stage rocket body (1) to realize the vertical suspension conversion, including: a suspension damper (2), a short Hanging sling (3), long hanging sling (4). The hanging damper (2) is installed in the rocket body interstage section (5), and is connected to the load-bearing structure of the rocket body through the transfer structure (6); one end of the short hanging sling (3) is connected to the load-bearing hanger at the engine end of the launch vehicle point (7), the other end is connected to the parachute joint (8); the long hanging sling (4) is connected to the hanging damper (2) at one end, and the other end is also connected to the parachute joint (8); connect the long (4), The parachute joint (8) of the short hanging sling (3) is fixedly connected to the parachute sling (9); the present invention can moderate the impact load that the first sub-stage rocket body of the launch vehicle receives during the hanging conversion process.

Description

technical field [0001] The invention relates to a metal honeycomb buffer-based hang conversion device and method for the first sub-stage rocket body of a launch vehicle, and belongs to the technical field of spacecraft return and deceleration landing. Background technique [0002] At home and abroad, there is no realization and verification of the launch vehicle sub-stage parachute recovery and pendant conversion technology with cushioning. In China, the Shenzhou spacecraft uses steel wire ropes as the main load-bearing structure to realize the vertical suspension conversion from single-point force to double-point force. However, its product structure and vertical suspension conversion load cannot meet the load-bearing requirements of the launch vehicle body. The main reason is that compared with the return capsule of the Shenzhou spacecraft, the rocket body of the launch vehicle has a larger recovery weight and slenderness ratio, and a larger unbuffered hanging conversion l...

AI Technical Summary

Problems solved by technology

In China, the Shenzhou spacecraft adopts the steel wire rope as the main load-bearing structure to realize the vertical suspension conversion from single-point force to double-point force. However, its product structure and vertical suspension conversion load cannot meet the load-carrying requirements of the rocket body.

The main reason is that compared with the return capsule of the Shenzhou spacecraft, the rocket body of the launch vehicle has a larger recovery weight and slenderness ratio, and a larger unbuffered hanging conversion load, but the overall structural strength and stiffness of the rocket body are smaller than that of the return capsule. cannot meet the carrying requirements

[0003] The sub-stage of the launch vehicle recovered by parachute initially falls in a vertical posture. If the vertical suspension conversion is not carried out, since the engine nozzle lands first, it will not be possible to use the buffer device for landing buffer

At the same time, due to the high position of the center of mass of the rocket body that lands vertically, there will be a great risk of tipping and damage to the rocket body, which will make it impossible to achieve a sub-level recovery and reuse

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