Landing buffer test system

Abstract

The application provides a landing buffer test system, including a frame, a test area is arranged in the surrounding area of ​​the frame; a first driving device is arranged on the top of the frame, and is used to drive the test carrier to move horizontally and linearly along the frame; the second The driving device is arranged at the bottom of the first driving device, and is used to drive the test carrier to rotate around the vertical line passing through the rotation center of the second driving device; the suspension device includes a rope and a separation component, and one end of the rope is detachably connected to the second driving device. 2. On the driving device, the other end of the rope is used to connect the test carrier, and the separation component is arranged on the rope; the fan device is arranged on the side of the test area; and the control device. The landing buffer device test system provided by this application simulates various landing scenarios of the test carrier through the first driving device, the second driving device, the suspension device and the fan device, so that the landing buffer device can complete buffering under these various landing scenarios task, so as to realize the performance test of the landing buffer device.

Description

technical field [0001] The present application belongs to the technical field of device performance testing, and more specifically relates to a test system for a landing buffer device. Background technique [0002] The main function of the landing buffer device is to reduce the peak impact load and deceleration of the protected object by prolonging the duration of the impact load, thereby ensuring the safety of the protected object structure; in the landing of reusable rockets, landers, aircraft and other spacecraft During the process, it is generally necessary to use the landing buffer device to produce non-recoverable or controllable recovery deformation to dissipate the kinetic energy of tens of thousands of joules of the spacecraft, so that the spacecraft changes from a moving state to a static state. [0003] The landing process of a spacecraft generally has the following two characteristics: 1. There are many uncertain factors. The topography and soil mechanical proper...

AI Technical Summary

Problems solved by technology

[0003] The landing process of a spacecraft generally has the following two characteristics: 1. There are many uncertain factors. The topography and soil mechanical properties of the landing area surface have certain randomness. It is difficult to accurately control the landing speed and landing attitude. Further considering the impact of weather conditions such as wind speed in the landing area, the uncertain factors will greatly increase; 2. Active control is difficult, and the duration of the landing buffer device from contacting the surface of the landing area to the completion of landing is very short, mostly in milliseconds. During this time, the spacecraft can only perform relevant actions according to the predetermined procedures, which further increases the risk of safe landing of the spacecraft

Therefore, whether the performance of the landing buffer device is reliable or not is directly related to the success or failure of the spacecraft reuse plan. Currently, there is no relatively complete test system for testing the core performance of the landing buffer device.

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