论文部分内容阅读
两空间飞行器在空间零重力环境下需要实现空间的多次对接和分离,为保证空间飞行器的下一次再次成功对接,需要空间飞行器在上一次分离时满足一定的分离速度、姿态角和姿态角速度。空间飞行器在空间零重力状态下具备六个自由度,在地面上由于重力的存在无法释放垂直于地面的平动自由度,因此难以通过地面全物理模型来模拟空间实际的分离过程。为此,建立了空间对接机构的分离动力学仿真数字模型,通过该动力学模型来研究两飞行器在零重力空间环境下的分离过程和运行规律,辨识空间对接机构的主要设计参数对两飞行器分离过程中运动特性的影响,为参数设计提供创新性指导和理论支撑,解决在轨分离过程中飞行器角速度及姿态过大等设计难题。同时依据仿真确定的设计参数开展工况覆盖性分析,验证设计参数的有效性和合理性,为后续工程实践奠定有力基础。
Two space vehicles need to achieve multiple docking and separation of space in the space zero gravity environment. To ensure the next successful docking of the space vehicle, the spacecraft needs to meet a certain separation speed, attitude angle and attitude angular velocity during the last separation. Space vehicles have six degrees of freedom under the condition of zero gravity in space. Due to the gravity, the freedom of translation perpendicular to the ground can not be released on the ground. Therefore, it is difficult to simulate the actual separation process of the space by the ground full physical model. Therefore, the separation dynamics simulation digital model of the space docking mechanism is established. Through this dynamic model, the separation process and operation rules of the spacecraft in zero gravity environment are studied. The main design parameters of the space docking mechanism are separated from the two aircraft The process of the movement of the characteristics of the parameters for the design to provide innovative guidance and theoretical support to solve the orbit separation process angular velocity and attitude too large and other design problems. At the same time, according to the design parameters determined by simulation, the coverage analysis of working conditions is carried out to verify the validity and rationality of the design parameters and lay a solid foundation for the subsequent engineering practice.