Development Of An Air-floating Ground Verification System For On-rail Separation Of Aircraft

With the booming development of astronautical technology,the types of space launch missions have become increasingly complex.The separation of spacecraft,which has essential effect on the space launch missions,has become diversified in its manner.The spacecraft on-orbit separation experiments are not only inefficient but also extremely expensive.Hence,it is significant to discuss and analyze the on-orbit separation characteristics of the spacecraft on the ground.In this paper,the on-orbit separation characteristics are researched on the basis of a specific spacecraft.And the theoretical analysis and experimental investigation are combined in order to sufficiently discuss and evaluate the on-orbit separation characteristics.Firstly,a set of comprehensive evaluation index are proposed for the analysis and evaluation of the on-orbit separation characteristics.And the relationship between the evaluation index and the force status of the spacecraft are established according to the research.Based on the requirements of ground verification system,a set of different programs are proposed at the same time to satisfy the needs.And after the examination of optimization index,the most proper one is selected.Secondly,this paper discusses the development of the ground verification system.Through the development of the simulation system,the goal for simulation of typical aircraft weighing 10 kg to 25 kg is achieved.Through the development of the air-floated support system,the goal for the micro-gravity and low resistance environment was achieved.Through the development of the detection and analysis system,the goal for the detection of the simulation system movement state was realized,and the relationship between the observation and measurement characteristics is established.And through the development of the auxiliary system,the function of connecting and buffering is realized.Finally,the dynamic simulation analysis of the air-floated ground verification system was carried out via ADAMS,providing basis for the parameter setting in the experiments.The three-point support method and three-wire pendulum method are used to test the mass,centroid position,and rotating modulus of the aircraft simulation system.The test results show that all index meet the design requirements.Moreover,the research on the on-orbit separation characteristics based on the air-floated ground testing system are proposed,the detection and evaluation of the stimulant are finished,and measurement of press-release system and air-floated system is achieved.And the purpose of analysis on the on-orbit separation characteristics of the aircraft through the ground verification test is achieved through all these efforts.