Research On Longitudinal Guidance And Control Technology Of Terminal Area Energy Management For Reusable Launch Vehicle

The Terminal Area Energy Management of the Reusable Launch Vehicle is a connecting link between the reentry phase and the automatic landing phase,it is also the key phase of reentry.The guidance scheme for Terminal Area Energy Management of space shuttle has been realized in engineering,but its supersonic guidance strategy is too complicated,for this problem,Simajun proposed a mixed guidance scheme,which simplifies the supersonic guidance strategy,and has the value of further research,but Simajun did not complete the mixed guidance scheme,the mixed guidance scheme can not be applied in practical engineering.Therefore,this thesis focuses on the improvement of mixed guidance scheme and the design of control scheme.In this thesis,the three-freedom-degree model and six-freedom-degree model of RLV are built,and object characteristic of RLV is analyzed.Then,based on the particle dynamics equation,the trajectory design algorithm is designed,based on this algorithm,the flight capability of the RLV and nominal trajectory are analyzed.The establishment of the model and the design of the nominal trajectory laid a solid foundation for the subsequent work.In order to evaluate the performance of mixed guidance scheme,a complete guidance performance evaluation scheme is established,and the evaluation result show that the mixed guidance scheme is insufficient,then proposed mixed guidance scheme of height feedback and mixed guidance scheme of energy feedback,the performance of the mixed guidance scheme of energy feedback is evaluated,the evaluation result show that the mixed guidance scheme of energy feedback can maximize the capacity of the aircraft without reservation.So far,the guidance scheme of TAEM has been completed.According to the guidance loop indicated airspeed instruction,the pitch angle to achieve indicated airspeed control,in this thesis,two kinds of pitch angle control laws are proposed,then the performances of the two control laws are compared from three aspects,finally,the pitch angle control law suitable for the sample aircraft is selected.Finally,equivalent simulation environment is developed,Typical simulation case is designed to validate the guidance and control system,the simulation results show that the guidance and control system is perfect,can maximize the capacity of the aircraft without reservation.