Design Of Separation Platform And Simulation Of Inter-stage Separation Process

Stage separation is a crucial step in launching a launch vehicle.The performance of the inter-stage separation device also directly determines the success or failure of the launch mission.In order for the launch of the rocket to be completed smoothly,it is necessary to research the performance of the inter-stage separation device under interference factors.Separation device generally includes three parts: connection unlock,power device and guide device,in order to improve the success rate and reliability of rocket stage separation motion,it is necessary to consider the performance of the separator under deviation disturbance and various complex operating conditions.First of all,on the basis of summarizing the research status of missile separation,separation schemes and separation simulation at home and abroad,by analyzed the working principle of rocket stage separation motion,clarified the function of the separation platform,formulated the technical specifications and overall design scheme of the separation platform,then designed the separation platform in detail according to the design requirements,and introduced the mechanical structure design,hardware selection of control system and software design of control system in detail.The separation power system is one of the most important components of the inter-stage separation device,therefore the influence of power output deviation on the separation motion between stages is also an important consideration in the separation scheme between stages.In this paper analyzed the forces acting on the separation between stages,and established the kinematic model of stage separation under deviation factor.Then,used ADAMS simulation software to simulation analysis of different thrust loads of thrust rocket,emphatically studied the effect of thrust load on the separation motion between stages.Because the change of rocket's structure mass and external disturbance factors is random in the process of separation,it is not possible to obtain accurate data values,in the case of multiple factors influence,the separation movement often needs a lot of data analysis and research,therefore,established a general collision detection model for internal separation,and combined with Monte Carlo method and MATLAB software,numerically analyzed the separation motion between stages under multiple factors interference.Through a lot ofrepetitive simulation experiments,obtained the relative transverse motion of the two-stage rocket's center point at the time of separating danger.Further studied the influence of multiple factors interference on the separation motion between stages and the collision problem.Finally,according to the overall structure and control system model of the design separation platform,complete the structure and software of the test platform,then did the experiments.According to the conditions and loads that may occur during the separation between stages,did three groups of repetitive separation tests,also collected the friction force between the guide mechanism and the separator under different working conditions and the attitude angle of the separator changes at the end of the guidance.By summarizing and analyzing the test results,it is confirmed that the thrust load deviation of the thrust rocket will increase the guiding friction between the two stages remarkably.With the increase of deviation,the change of the attitude angle of the separator is more obvious at the time of separation.This verified the correctness of the simulation analysis and also test the reliability of the structure of the separation test bed and the stability of the control system.