Structure/damping integrated design method suitable for novel spacecraft

Abstract

The invention provides a structure / damping integrated design method suitable for a novel spacecraft. The method comprises the following steps: (1) establishing a simulation model; (2) determining a response peak value when the spacecraft structure needs to reduce vibration; (3) determining principal oscillation corresponding to the response peak value when the spacecraft structure needs to reduce vibration; (4) determining optimal laying position of a spacecraft damping; (5) determining a damping material, damping thickness, and structural parameters of a restraint layer, to complete integrated design of structure / damping. The spacecraft structure / damping integrated design method is simple and feasible, and prevents development cost for repeated design and repeated tests, and can effectively develop damping buffer effect of an aircraft.

Description

technical field [0001] The invention relates to a structure / damping integrated design method suitable for a new space vehicle, which can be used for simultaneously performing vibration reduction design at the initial stage of the structure design of the new space vehicle, and belongs to the technical field of space vehicle structure design and damping vibration reduction. Background technique [0002] Engineering structures are not only subjected to static loads during use, but many structures are often subjected to strong dynamic loads. For example, various space vehicles are often in harsh environments, subject to strong vibrations and shocks, resulting in reduced structural life and instrument failures, which induce a series of serious accidents and cause huge losses to the country and people's lives and property. According to relevant statistics, 40% of the major accidents of aircraft are related to vibration. How to avoid severe vibration of the structure, reduce the r...

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Problems solved by technology

[0004] (1) After the ground test, the initial structural scheme of the aircraft is optimized or changed according to the vibration reduction requirements, resulting in repeated design or even repeated testing of the structural scheme, which seriously affects the development progress and increases the development cost;

[0005] (2) For the design of damping and vibration reduction of aircraft, there is no unified specification yet, and there is no method to obtain the optimal laying position of damping and vibration reduction. Traditional methods often apply damping in large areas, resulting in unnecessary waste of damping materials

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