The boost-glide missile is a kind of precision guided weapons, which flies in complex and changeable flight conditions with high requirements for the guidance law. The flight state variation model of the missile was established, the improved optimal guidance law with the impact angle constraint was derived by the optimal control method, and the longitudinal guidance coefficients and lateral guidance coefficients were introduced into the guidance law. The influence of single guidance coefficient on guidance precision was analyzed and the selection method of guidance coefficients was determined. The influence of fixed impact angle constraint and dynamic impact angle constraint on guidance precision were analyzed according to the requirements of different flight missions. The numerical simulation and the hardware-in-the-loop simulation were finished with a small solid propellant boost-glide test vehicle. Simulated results show that the improved optimal guidance law is reasonable with high guidance precision.

In order to solve the problem of the real-time parameter adjustment when suppressing redundant force by the structural invariance compensation method, a mathematical model and a simulation model of a servo actuation system performance test platform were established, respectively. A decoupling control method for speed feedforward compensator was proposed, and a fuzzy controller was designed to suppress the redundant force. The inhibition effects of the three control methods including the traditional PI (proportional-integral) control, traditional PI feedforward compensation control and fuzzy PI feedforward compensation control on the redundant force of the test platform were compared. Simulation results show that the loading accuracy of the test platform can be improved by the fuzzy PI feedforward compensation control method with the most significant suppression effect on the redundant force. The effectiveness of the proposed control method was verified by the comparison between the experiments and simulations, which provides a theoretical reference for the servo actuation system test platform to loading with heavy thrust and high precision.

To address the aerodynamic load reduction requirement when the launch vehicle flying in high wind zone during the ascending phase, an intelligent attitude control method with adaptive learning rate was proposed. Taking a certain type of launch vehicle as the research object, the dynamic model in the pitch plane was established. A deep reinforcement learning framework suitable for flight control of the launch vehicle during the ascending phase was developed based on soft actor-critic, and a reward function that comprehensively considers attitude tacking accuracy and stability, and load reduction effectiveness was designed. On this basis, an adaptive iteration of learning rate was implemented based on a step-size learning rate scheduler to quickly improve the convergence velocity and find the optimal solution of the controller. Besides, an early stopping mechanism which can automatically end the training process was designed to enhance the training efficiency. Simulations show that the proposed method can effectively achieve load reduction of the launch vehicle while ensuring attitude tracking accuracy and stability. Additionally, it has strong robustness and adaptability to random wind disturbance.

Since the thrust characteristics directly affect the launch speed, altitude and flight range of the water rocket, in order to improve the thrust performance of the water rocket, a flexible and deformable self-pressurized elastic air pressure cabin scheme was designed on the basis of the existing fixed volume pressure chamber, and its performance was evaluated. With Bernoulli′s theorem and deformation coordination relation, a coupled model of internal pressure, nozzle velocity and thrust of water rocket was established. Moreover, the influence of different initial states (water volume ratio and inflation air pressure) on water rocket thrust was also studied with the numerical calculation method, and the thrust difference was compared and analyzed further between the fixed air pressure cabin and the elastic air pressure cabin under the same initial conditions. The research results show that the improved flexible and deformable self-pressurized elastic air pressure cabin can effectively increase the water jet velocity during the launch, and the thrust generated by the water rocket in the same initial state increases significantly by 46.95%. The designed scheme can provide important reference for improving the flight performance of water rockets and the optimal design of new flexible deformation water rocket scheme.