Study On The Placement Scatter And Simulation Platform Estimate Of Falling Sphere Which Launchs A Sounding Rocket

In recent years,China’s sounding rocket launch technology has reached an international advanced level,and sounding rockets are developing toward the small-scale delivery and commercialization.However,sounding rocket development process will consume a lot of manpower,material resources and financial resources,and if there is a problem in the development process,it will directly lead to the rocket can not complete the operation very well,and even cause the launch of the failure and the waste of resources,but also Will have a great negative impact on the environment.In addition,the rocket will drop the falling sphere after it is dropped to a certain height.The falling sphere will fall back to the ground under the influence of gravity.The falling point may pose a threat to the safety of the ground.Therefore,it is necessary to be able to develop a set of simulation platforms for the sounding track of the sounding rocket and the estimation of the falling point of the falling sphere.It can import the design parameters into the platform simulation before the launch of the rocket,and modify the design parameters according to the simulation results;in addition,this set of simulation platform has certain theoretical and practical guiding significance for ensuring ground safety and the recovery of falling spheres.Based on this,the main work of this article is as follows:First,the atmospheric model of rocket trajectory calculation was selected and the influencing factors of rocket flight trajectory were analyzed.By comparing the current atmospheric models commonly used in the aerospace field,it is found that the USSA-1976 atmospheric model is suitable for the launch of this rocket from the geographical location,atmospheric composition and applicable altitude.By comparing the rocket trajectories with and without random wind disturbances and flight trajectories at different launch angles,the trajectory differences of the same rocket with,without,and different launch angles were quantitatively analyzed,and the inter-stage differences were mentioned.Separation methods,Coriolis additional forces,and the curvature of the Earth’s surface can affect the rocket’s flight trajectory.Secondly,using the control body tracking method,the momentum theorem of the variable mass particle system is derived,and the dynamic model of the rocket is established combining momentum theorem,momentum moment theorem and Newton’s theorem of motion and a high altitude combined wind field model is established.The rocket and ball falling are deduced.The trajectory differential equations were simulated by MATLAB.It was found that the simulation results of MATLAB were basically consistent with the expected launch parameters of the pre-launch rocket and the falling sphere in a space institute,which verified the correctness of the model.Finally,based on the mixed programming of C++ and MATLAB,the simulation platform for rocket trajectory and ball drop placement was developed—"The Eagle".The simulation platform has a friendly human interaction interface,a variety of parameter output forms and realistic animation presentation effects,and has a program interface for platform expansion,and can well achieve "bolt match","rocket simulation" and "falling sphere Simulation "Three basic functions.By comparing the platform simulation data with the pre-emission parameters,the correctness of the platform is verified.