Research On Wind-load Decreasing Strategy And Guidance Method For Powered Phase Of Boost-Glide Vehicles

In order to reduce the influence of the interference on the ballistic characteristics of the low altitude wind field and meet the ballistic real-time emission requirement of modern warfare,in this dissertation,we mainly research the wind-load decreasing strategy of the powered phase basing on the wind field disturbance coefficient K_W and the guidance method basing on the spline curve to satisfy the multi terminal constraints.An wind-load decreasing strategy basing on the wind field disturbance coefficient is developed.Firstly,according to the design of standard trajectory,standard programmed angle model is introduced based on Newton iterative method in the given terminal constraints.And in order to amend angle model,the PD feedback control system is introduced to generate the tracking instruction which meets the terminal constraints.On this basis,we research the interference of wind load on the ballistic characteristics and propagation mechanism of wind field disturbance by adding wind disturbance to the standard trajectory.Then the wind field disturbance coefficient K_W is introduced in order to propose a real-time wind load decreasing strategy combining active load decreasing strategy and passive load decreasing strategy,and the strategy is verified by the simulation,and the effect can reach almost 50%.An guidance method of the powered phase basing on the spline curve is studied.By simplifying the dynamical model of the powered phase for boost-glide missile,the guidance method is analyzed according to the flight environment of the different three stages of the powered stage separately.Firstly,ignoring the influence of the aerodynamic force,the guidance method of the third stage basing on the geocentric distance spline curve is introduced with the combining of energy management,which meets the multi constraints of the powered phase,and the feasibility and adaptability are verified by the simulation analysis.Then the guidance method in third stage is extended to the second stage,and the guidance instruction considering the complex aerodynamic force is generated by the calculation method of dichotomy whose feasibility is verified by the simulation analysis too.Lastly,combining the programmed guidance in the first stage with the guidance method in the second and third stage,the feasibility and robustness of the guidance method are verified through the simulation of the whole trajectory and deviation test.Basing on Gauss pseudospectral method,a tracking guidance methond is proposed.Firstly,based on the principle of Gauss pseudospectral method,taking the terminal velocity of second stage as the optimization objective,the optimal guidance instruction in the previous second stage is generated.And bring it into the original dynamical equation,and the trajectory simulation verifies the effectiveness of the optimal guidance instruction.Then amend the optimal guidance instruction of the previous two stages combining with energy management guidance method in third stage,and the overall trajectory is simulated and the feasibility of guidance method is verified.Finally,we analyze the three different guidance methods by comparing the characteristics of different guidance methods.Basing on the flight environment characteristics and the requirement of guidance mission of the boost-glide missile in the low trajectory,the dissertation researches the wind-load decreasing strategy and the guidance method of the powered phase.Research shows that the dissertation's conclusion is meaningful to both the flight quality under the condition of wind disturbance and the guidance mission.