Research On Overall Scheme And Trajectory Simulation Of Small Guidance Rocket

Guided rockets effectively fill the vacancy between the uncontrolled rockets and missiles, and achieve the ideal accuracy, collateral damage and combat effectiveness at a lower cost. This thesis focuses on the research of the guided rocket’s overall design and trajectory simulation, mainly for the following five aspects.First, based on objective analysis and military requirement, the preliminary design of the guided rocket’s overall scheme is formulated, which includes canard pneumatic layout with the rear linkage ailerons, the multi-purpose warhead, the rocket engine of one single chamber and double thrusts, TV guidance system and three-channel control method, etc.Second, after the establishment of the three-dimensional entity model and unstructured meshing, the numerical simulation of aerodynamic force is completed by Fluent software. According to the calculation results, the aerodynamic characteristics and surface pressure distribution of the canard rocket are further analyzed and summed up.Third, rolling moment coefficient on the whole missile and linkage aileron are investigated by numerical calculation respectively, to verify that the aerodynamic layout with the linkage ailerons can generate enough rolling moment to control the rolling movement of elastic body. In addition, the roll channel is designed independently, and the simulation results show that the roll control system has good property to restrain interference.Fourth, according to the geometrical parameters and aerodynamic parameters of the guided rocket, trajectory simulation about uncontrolled flight, unfixed targets and maneuvering targets is carried out respectively by MATLAB/Simulink simulation software. The simulation results meet the design requirements.Fifth, after the simulation model of pitch loop established, the design of related parameters and stability analysis are accomplished to meet the performance index requirements. In addition, the rocket mobility and maneuverability are also investigated in this paper, including estimation of overload and operation-stability ratio.The research results of this paper on the overall design of guided rockets can provide the corresponding theoretical basis and technical support for development of small guided rockets.