Simulation Research And Overall Design For Autonomous Homing Reusable Boost Vehicle

This paper has briefly studied the reusable booster system of LM-2F(CZ-RBV).The study mainly includes: the CZ-RBV's preliminary design,the outline design, the aerodynamic configuration design, the reference return trajectory design.By analyzing and summarizing the characteristic of the foreign reusable booster and the development status of the trajectory optimization techniques,the paper designs the scheme of the vertically taking-off and horizontally landing about CZ-RBV; CZ-RBV would be equipped with a folding wing, which is stored along the fuselage of CZ-RBV during the booster stage of the flight, in order to cluster around the main rocket and deploy the wing after separation from the upper; the main engine is the liquid engine,its fuels is a low level of environmental contamination and the vacuum specific impulse is larger;CZ-RBV would be also equipped with an air-breathing jet engine fitted in the nose section of the rocket, which would provide a powered horizontal landing of the vehicle on the runway; the power system is the air-breathing jet engine in the return scheme, the range of the return maneuvers is extensive;the flight control strategy based on the fuzzy sliding mode control system,the controller has excellent robustness to the system uncertainties and the external disturbance and perfect dynamic performance.Based on CZ-RBV's preliminary design,the paper designs the main parameters,including wing loading and other parameters.Then,by Solidworks and Fluent,the paper simplifies the aerodynamic configuration of CZ-RBV and evaluates the aerodynamic performance of CZ-RBV.According to the evaluation result,the aerodynamic configuration is relatively reasonable.According to the return scheme,a three degree-of-freedom(3 DOF) simulation model is presented,and the Gauss pseudospectral method(GPM) is used to solve the reentry trajectory of CZ-RBV. Simulation results shows that the GPM can generate a continuous,viable and optimal trajectory satisfying various complicated constraints.The study accomplished in this paper could provide references to analysis and research on the key technology of reusable launch vehicle, along with the study of relative problems.