Research On The Navigation Guidance And Control Of Reusable Boost Vehicle

Fully reusable launch systems have been the dream of researchers and engineers for years. Over the past 30 years, numerous studies have already identified that fully reusable two-stage-to-orbit (TSTO) concept space launch system could be one of the best solutions for meeting economical and technical objectives of second-generation reusable launch vehicle (RLV). There are many kinds of research programs about TSTO reusable space launch system, during which the reusable boost vehicle (RBV) has become one of the most noteworthy and paramount research points.The options for the return back of RBV, the solutions and key technologies for the guidance, navigation and control (GNC) of rocket back RBV are studied in the thesis.Comparisons between the most famous return options as unpowered flyback, aeropowered flybakc, boost back and hybrid back is carried out and analyzed, then rocket powered boostback RBV is selected to be the focus here and the details of rocket back flight profile are introduced. The complete flight models are presented in which the phenomenon of attitude singularity is averted effectively and a typical reference return trajectory is designed.Solution for the dynamic integrated navigation of RBV is put forward with SINS/GNSS/ADS/Doppler radar/Radar altimeter /Laser ranger, and the navigation models are built in detail. Through the comparison between three kinds of fault detection methods and kinds of improved information fusion algorithms, the fault detection and information fusion algorithms are selected. After that, the strong tracking unscented kalman filter (STUKF) is used for navigation estimation, and the active and dynamic information fusion technology based on Dynamic Bayesian Networks (DBNs) is introduced for active and dynamic global information fusion.According to the special flight characters of RBV, the improved proportional feedback guidance method based on the typically used guidance algorithms is put forward. To address the defections of feedback methods, a kind of guidance algorithm based on differential flatness and nonlinear dynamic inversion (NDI) is adopt. Simulations validate that the flatness-based guidance is more effective and with better performance.After building the control models, the phases during which aero surfaces could be used solely are defined. The Daisy-Chaining conrol allocation methode and Multi-modal transient suppression controller are used for the control allocation and switching between RCS and aero surfaces.The controllers for RBV are designed using gain scheduling and NDI respectively, and the comparison between control results indicate that NDI is more suited to RBV return flight than gain scheduling.The integrated simulation models with modular architectures for GNC of RBV is built, the flight simulations under different disturbances indicate that the designed solutions for GNC of RBV are effective and of perfect performance. And the comparison with Shuttle Orbiter validate that the GNC system if feasible for realization.