Spacecraft Attitude Dynamics of multibody systems and control research

Title: Spacecraft Attitude Dynamics of multibody systems and control researchAuthor: Liu YunpingDegree awarded: Nanjing University of Aeronautics and AstronauticsKeywords: spacecraft;; topology;; attitude dynamics;; pseudo-velocity;; manifold;; nonholonomicSummary:This paper studies the multi-body system of spacecraft attitude dynamics and control problems, the spacecraft multi-body system kinematics and dynamics analysis of the fundamental purpose is to provide products and equipment in these areas of mechanical design and control body to provide support to achieve high efficiency, low-cost product development purposes. Aerospace engineering is a high input, high-risk areas, which cover a wide range of subject areas, Rare earth magnets related to Aerospace Science and Technology, Control Science and Engineering, Information and Communication Engineering, Electronic Science and Technology, weapons science and technology, materials science and engineering and instrumentation science and technology. Spacecraft multibody mechanical many-body system is an important branch of the system, the space station, space robots, to start with solar panels and other spacecraft, a satellite organization of multi-body systems are all rootless tree multi-body system. Satellite's solar panels to start the process, the space station and other spacecraft docking process, the service space robot in orbit during the mission so the spacecraft will cause changes in body posture, and connected to the satellite's solar panels on the body should always be toward the sun, toward the ground receiver to the antenna, which requires the attitude of the spacecraft body to http://www.chinamagnets.biz/faq.php adjust. With China's manned space and spacecraft rendezvous and docking technology, making the spacecraft, the increasing scale of multi-body system, more and more degrees of freedom, attitude dynamics and control systems become more and more problems complex, so the spacecraft multibody system modeling and analysis techniques will toward the high-efficiency, high precision, automation and adaptive direction. Therefore, large-scale, complex multi-body spacecraft system modeling and analysis of the research work in order to achieve optimal design and operation of control optimization results, this work is imminent.Attitude motion of spacecraft, including spacecraft as a whole around its center of mass movement, and various components of the spacecraft relative motion between components. This article from the following aspects were studied: (a) topology described methods, including correlation matrix, channel matrix, the low-order physical array, the father and daughter body array, the shift operator and so on. Using correlation matrix contains, access matrix describes the topology and other characteristics of the shift operator method to describe the spacecraft topology multi-body system in the form of simple possession of memory space is small, easy-to-computer programming. (B) the kinematic and dynamic modeling. Theory of operator algebras in the space based on the study of the spacecraft's high-efficiency multi-body system kinematics and dynamics modeling method, and the method with kinematics, dynamics equivalent arm of the multi-body system for spacecraft motion and Dynamics modeling; and the speed and spin by the amount of pseudo-recursive combination of high speed through the pseudo-dynamic modeling efficiency. Pseudo-rate addition to greater freedom selecting independent variables, and contains the kinematic parameters or kinetic parameters directly obtained for computing first-order differential kinetic equation, to avoid unnecessary cross-operation, saving the computer's computing time and space. And can be used to design the decoupling control or non-interactive control; (c) attitude maneuver and stability analysis. Study of the spacecraft model is defined as the manifold SO (3) (?) T ~ M on non-drift model, using the Lie algebraic method to get control of arguments and structure of the program, and to study the dynamics and shape of the spacecraft attitude change the dynamics between, on the spacecraft through the hinged attachment (flywheel or arm) to adjust the body posture; (d) of the non-complete spacecraft attitude of many-body systems optimal control problem and Hamilton-based Gordon equation of nonholonomic spacecraft system stability issues; (e) spacecraft multibody system dynamics and symbolic software, programming software mathematica achieved through symbols spacecraft kinematics, dynamics, control, etc.; (f) for Magnetic spacecraft attitude control of the entire physical simulation system design.The main innovation of the paper: (1) contains the correlation matrix used, channel structure of the matrix method described in the characteristics of the shift operator to describe spacecraft topology multi-body system in the form of simple possession of memory space is small, easy-to-computer programming . (2) computer programming through easy-to-the addition, multiplication instead of the traditional kinetic modeling of time-consuming, laborious derivative operations, to achieve spacecraft multibody system dynamics modeling of automated reasoning. (3) by the amount of pseudo-recursive calculation speed and spin combination, to achieve the speed of the spacecraft through the pseudo-high-efficiency method of dynamic modeling to achieve O (N)-order algorithm. (4) on the basis of the manifold, on the spacecraft through the hinged attachment (flywheel or arm) to adjust the body posture. (5) in the quaternion based on the study of non-complete spacecraft attitude of many-body systems optimal control problems and Hamiltonian equations of spacecraft based on non-complete system stability issues; (6) applications to achieve magnetic levitation spacecraft attitude control all physical simulation system.Degree Year: 2009