Development Of Pico-satellite Orbital Deployer For Interval Ejection

Pico-satellite and other small satellite by more and more researchers attention based on MEMS technology.The satellites with different functional characteristics can be combined for on-orbit formation flight,near-space imaging of the target,observation of the Arctic channel and participation in constellation construction.In the future of space missions,Pico-satellite and other small satellite in orbit separation deployment will become a trend,a master satellite carrying multiple small satellites will become mainstream.In order to achieve the loading and release of Pico-satellite,it must have a reliable deployer in orbit.Based on this and combined with ‘863 Program' project ‘xxx satellite group bearing and directional release technology',the research work of this dissertation is carried out through the methods of theory modeling,structural optimization,simulation analysis,experimental verification and other methods to develop the Picosatellite orbital deployer.Based on the research status,this paper puts forward four design schemes of box structure bearing and memory alloy material drive.Compare the design scheme and choose the best solution.Some parameters of the spring may change randomly during the separation and the governing equations are nonlinear,it is tough to obtain the exact effects of elastic devices.In order to constitute a simplified metric,it is a novel idea to tackle the issue by using elastic potential energy,which is a scalar depending on the deformation of elastic devices.Established the dynamic model of the collision between satellite and guide rail.The analysis of the force and movement in the separation process of the Pico-satellite is carried out.The influence of different rail clearance on the separation posture of the Picosatellite is analyzed under the spring limit error condition.Based on the design of the deployer program,the structural design was carried out in combination with the theoretical analysis.In order to ensure the Pico-satellite in orbit on the deployment of a good posture,combined with the heat analysis to determine the guide rail clearance.Consider deployer miniaturization,lightweight design requirements,this paper to carry out topology optimization for the deployer.The simulation analysis and kinematic simulation analysis of the deployer is carried out to verify the rationality of the structural design and the correctness of the model.Finally this paper developed the Pico-satellite orbital deployer,and carried out functional test.Verifies the reliability of the separation and locking of the deployer lid.The velocity and the angular velocity of the satellite ejection are tested.At the same time,the angular velocity measurement test under the condition of the separation limit of the spring is carried out,and validated the correctness of theoretical analysis.Determine the impact on the deployer during the separation of the Pico-satellite.Bulid the vibration test systems of the deployer,obtained the fundamental frequency characteristics of simulate payload and the dynamic response of key parts,validated the system design specifications.