Non-linear Dynamic Research Of Cubesat's On-orbit Deployment

After more than ten years of development,CubeSat as a micro-nano satellite standardization products,has been widely used,the frequency of launch is continuous increasing,the application scene is increasingly rich.However,as a new type of satellite platform standards,related theoretical research about CubeSat is not enough to meet the needs of the project.In this paper,a dynamics model is built to analyze its nonlinear phenomenon systematically and the abstract dynamic model is established.Based on the analysis results,the theoretical basis of the design of the CubeSat deployer is provided.A three-degree-of-freedom vibro-impact dynamics model with clearance is established to simulate the motion process of CubeSat deployment reasonably.The onedegree-of-freedom dynamics model of the system is constructed,and its dynamical differential equation is established.The initial condition when the system is in a periodic motion is obtained.Based on the one-degree-of-freedom dynamics model,the threedegree-of-freedom model is constructed.The translational and rotational movements of the satellites in three dimensions are considered,including the horizontal vibro-impact motion,the separation movement along the guide rail direction and the rotational movement around the centroid of CubeSat.The one-degree-of-freedom and the three-degree-of-freedom dynamics models were numerically simulated by MATLAB software.The stability of the fix-point was determined according to the Lyapunov stability definition.The Poincaré cross-sectional projection of the impact surface was plotted to analyze the effect of nonlinearity during the motion of CubeSat deployment on orbit.In this paper,the important parameters such as the angular velocity and the separation speed of the satellite under different design parameters are compared with the design parameters of the three-degree-of-freedom dynamics model,which provides the theoretical basis for the design of the cube satellite release device.