The Design And Dynamics Simulation Of Satellite Structure And Mechanism With Complex Constraints

The space technology is a high-tech with challenges in our world, it has become the symbol of a country’s comprehensive strength and the fate of a country and the national political. The spacecraft is a kind of vehicle that it can explore the universe and take specific space task outside the earth’s atmosphere. The design of spacecraft structure and mechanism system and the analysis of structure dynamic simulation are the important spacecraft technical problems. These important technologies have a key role to ensure the successful implementation ofspace science and exploration missions.Today, the intensive spacecraft with small volume, light weight, strong function and high reliability is getting more and more attention. Because of its strict design constraints, its design of the structure and mechanism becomes very difficult. The design and structural dynamics problem of spacecraft structure and mechanism system with complex constraints is badly in need of a set of practical and feasible overall ideas or design method.This paper takes the spacecraft structure design of the DSL project and the separated payload project as the application background. The spacecraft structure and mechanism in the two projects are designed and analyzed under complex constraints by the "Core design constraints" method. The satisfactory design scheme of spacecraft structure and mechanism in the two projects is obtained. The feasibility and practicability of the design method has been verified. This paper takes the square solar sail spacecraft space exploration project as the application background. A calculation method of the coupling coefficient of spacecraft structure and attitude is arrived by the Finite element simulation in three models of the square solar sail spacecraft. The coupling coefficient provides the basic parameters for the attitude control system design.The main work and innovation parts:1、 Based on the basic theory of the spacecraft structure and mechanism design, the "Core design constraints" design method is obtained. This methodis for the design of spacecraft structure and mechanism with complex constraints in the overall design level. There are two innovative links in this method, one is the self-constraint analysis, and the other one is the coupling constraints analysis. The design work takes the spacecraft structure design of the DSL project and the separated payload project as the application background, the self-constraint analysis and the coupling constraints analysis of the main satellite and the daughter satellite are arrived, the key constraints and the core constraint are obtained. The complexity of the iterative design process is reduced by this theory. This method can decouple the coupling of these complex constraints at a certain extent. Also, it can accelerate the speed of iterative process, and obtain satisfactory design results of structure and mechanism. In a word, some design problems of the complex structure and mechanism with multi constraints are solved through this method.2、 A calculation method of the coupling coefficient of spacecraft structure and attitude with model simplification, theoretical calculation and verification parts is obtained. This method is for the square solar sail spacecraft with a intensive modal mass percentage. First, two simplified models of square solar sail spacecraft are acquired, the nonlinear finite element analysis of static simulation and modal simulation with preload about the two simplifies models are obtained. The final coupling coefficient matrix with nice inertia completeness is acquired by the theory of finite element calculation of flexible spacecraft with central rigid body and flexible appendages. This method solves the problem of the coupling coefficient calculation of the complete model of the square solar sail spacecraft.The design of structure and mechanism with complex constraints and the coupling coefficient calculation of flexible structure in this paper solve the problems in the design of spacecraft with specific application, its results have some academic reference value for the theory research on the design of spacecraft structure and mechanism and the structure dynamics of spacecraft. It is significant for the development of China’s spacecraft technology.