力偶式星箭分离装置方案设计及参数影响分析

Scheme design and parameter influence analysis of force-couple satellite-rocket separation device

以一箭四星发射任务为研究背景,设计一种集合分离功能与卫星起旋功能的力偶式星箭分离方案。该方案由4套对称布置的力偶式分离装置组成,每套分离装置上包含作用点对称的两个分离冲量装置和接触面相关结构。基于ADAMS软件,建立了以气动作动筒为分离冲量装置的星箭分离动力学模型,采用正交设计方法分析了分离系统设计参数对分离过程的影响。结果表明:最大活塞行程和峰值推力增大可有效增大卫星起旋角速度与相对分离速度;增大推力夹角和作用点直径提高了卫星起旋角速度,但会减小相对分离速度。最后,综合考虑各设计参数的影响与卫星结构限制,确定了一组合适的分离系统参数。

Taking the one-rocket-four-satellite launch mission as the research background,a force couple satellite-rocket separation scheme is designed,which integrates the separation function and the satellite spin function.The scheme consists of four sets of symmetrically arranged force-couple separation devices,and each set of separation devices includes two separation impulse devices with symmetrical action points and related structures on the contact surface.Based on ADAMS software,a satellite-rocket separation dynamic model is established with the pneumatic cylinder as the separation impulse device,and the orthogonal design method is used to analyze the influence of the design parameters of the separation system on the separation process.The results show that the increase of the maximum piston stroke and the peak thrust can effectively increase the spin-up angular velocity and the relative separation velocity.The increase of the thrust angle and the diameter of the acting point can increase the spin-up angular velocity,but reduce the relative separation velocity.Finally,considering the influence of design parameters and the limitation of satellite structure,a set of suitable separation system parameters is determined.