Research on Design and Control Method of Flotation Experiment Platform on Ground Simulation
|School||Harbin Institute of Technology|
|Course||Control Science and Engineering|
|Keywords||physical simulation system air-bearing test-bed attitude dynamics and control control moment gyro|
With the development of the aerospace technology, the requirements for spacecraft rendezvous and docking related technologies are getting more and more complex. In the process of the research for rendezvous and docking related technologies, to verify the correctness of the solution control system, to improve the reliability of spacecraft in orbit, to reduce the risk of aircraft out of control, physical simulation of the system test is necessary. Space environment has two main characteristics: weight loss and vacuum. At the same time the ground simulation test facilities in the acceleration of gravity under, therefore, considering the physical simulation system, the introduction of air bearing table is necessary. By the help of the compressed air between the film of the air bearing and the bearing gap, air-bearing test-bed offsets the influence of gravity, while achieving the similar conditions of relative motion without friction. As the core components of aircraft control system physical simulation, air-bearing test-bed can simulate the weightless conditions in orbit, so it is an ideal platform for the research of spacecraft attitude dynamics and control system on ground.This thesis has researched the design and control of a air-bearing experimental system. What I have done has been listed as follows:First of all, a flotation platform attitude dynamics model has been established. The measurement method of the air-bearing test-bed’s moment of inertia has been given.Secondly, contrary to the air-bearing test-bed with four degrees of freedom, this thesis has established a mathematic model of the control systems, then the analysis and simulation were done, at last the basic experiment was performed. Contrary to the flotation platform with three degrees of freedom, has made a research of the control method of control moment gyro. Simulation results has shown that control system designed can meet the test requirements of docking.Last but not least, contrary to the spacecraft rendezvous and docking for ground simulation test system, the structure design work of the target satellite-related and part of the air bearing table have been Completed.