Research On Guidance Control Of The Rising Stage Of A Certain Launch Vehicle

The reusable launch vehicle can reduce the launch cost of the launch vehicle significantly by reusing the rocket sub-stages.Therefore,it has always been the focus of attention and research.The method of vertically recovering the launch vehicle’s sub-stage puts forward new requirements for the launch vehicle’s trajectory design and guidance control.This thesis conducts research on the issues related to the launch trajectory design and guidance control of reusable launch vehicles.The main work contents are as follows: 1)The source of the topic of the thesis,the research background and significance,the domestic and foreign research status of the launch vehicle guidance,and the main content and organizational structure of this thesis.2)According to the video materials and other data recovered by the Falcon 9 launch released by Space Exploration Company,the data of the video materials was extracted,processed,analyzed and synthesized.At the same time,by analyzing the ballistic characteristics,the ballistic reference data of the rocket from launch to separation of the first and second stages are obtained.3)The common coordinate system of the ascending segment of the launch vehicle,the mutual conversion between the coordinate systems and the dynamic model are studied.Combined with the characteristics of the reusable launch vehicle engine configuration,the equations of motion of the launch vehicle are derived.Then,the equations of motion are simplified with the characteristics of the reusable launch stage of a launch vehicle and the trajectory recovery.Finally,the longitudinal and lateral equations of motion are obtained.4)According to the public data of Falcon 9,the Datcom aerodynamic engineering calculation software is used to calculate the aerodynamic coefficient of the rocket.Also,according to the relevant knowledge of trajectory design and the requirements of related carrying tasks,the law of change of pitch angle of the program is designed and the trajectory design that meets the requirements is completed.The building of the simulation model is completed.5)Complete the guidance and control simulation of the rocket in the first stage.At the first stage of the launch vehicle,the theory of perturbation guidance is used.According to the existing trajectory model,combined with the wind field disturbance and the engine failure at a certain moment in the ascending section,the disturbance model and the perturbation guidance model are built.It is verified by simulation that the perturbation guidance model built can reduce the influence of interference factors on the flight trajectory,and the terminal trajectory parameters meet the constraints of the shutdown point.