齿轮齿条式构型航天器设计及其动力学仿真  

Design and Dynamic Simulation of Deployable Spacecraft Drived by Gear and Rock Mechanism

作　　者：罗浩[1] 刘更[1] 马尚君[1] 刘文彬[1] 

机构地区：[1]西北工业大学机电学院,西安710072

出　　处：《系统仿真学报》2012年第8期1606-1611,1617,共7页Journal of System Simulation

摘　　要：基于航天器结构的模块化设计概念,设计了一种新的在轨展开航天器构型,即齿轮齿条式构型。利用虚拟样机技术,在ADAMS软件中建立了这种新型航天器在轨展开的虚拟样机。首先研究了航天器本体以不同的驱动速度展开对航天器姿态角及姿态角速度的影响。其次,对航天器本体和太阳帆板的三种展开顺序进行了仿真,即本体模块和太阳帆板同时展开、太阳帆板先展开本体模块后展开、本体模块先展开太阳帆板后展开,分析了这三种展开顺序对航天器姿态角及姿态角速度的影响。仿真结果可以为未来高机动、多任务多形态的模块化航天器设计、在轨展开技术和空间姿态控制提供启发和借鉴。Based on the modular design idea of spacecraft structure, a new modular structure form which can depoly on-orbit was designed, that is the deployable spacecraft configuration drived by gear and rock mechanism. By using virtual prototyping technology, the virtual prototyping models of modular noumenon and solar sail were established in ADAMS. First of all, it was simulated that the modular noumenon was deplayed in varied speeds, and the influences on attitude angle and attitude angle velocity were obtained. Then three kinds of depoyed sequences of modular noumenon and solar sail were simulated as follows： modular noumenon and solar sail were deployed simultaneously, modular noumenon deployed after solar sail and solar sail deployed after modular noumenon. The influences on attitude angle and attitude angle velocity were obtained and analyzed. The simulation result can provide enlighten and reference for the future high-mobility, multi-pattern, multi-purpose modular spacecraft design, depolyment on-orbit technology and attitude control in space.

关 键 词：模块化设计 虚拟样机技术 姿态角 姿态角速度 航天器设计 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术]