Research On Long Range Air-to-Air Anti Radiation Missile General Design And Optimization

Long range air-to-air anti-radiation missile(LRAAARM) is an important weapon in attack-defense hierarchy which can attack the enemy’s airborne warning and command center. This missile propelled by ramjet, deployed two inlets on both sides of the missile body and employed to provide lift meanwhile, thus there existed complicated coupling relationship among the multidisciplinary, moreover there existed interacted between the missile flight performance and the ramjet working status, all those characteristics made the general design become a severe challenge. In order to get a reasonable and feasible missile general design, the missile baseline scheme and general parameters, ramjet performance Analysis, integrated optimization design of general design, and multidisciplinary design and optimization(MDO) have been thoroughly researched and analyzed using the theoretical analysis and numerical simulation method. The mainly work as following:Firstly, the missile’s overall technical indicators are formulated according to the missile’s fight requirements. The discipline problems such as the typical flight mission profile, aerodynamic configuration, propulsion system, the guidance and control system and the basic general parameters are analyzed and researched, the missile general scheme which employed integral liquid fuel ramjet, lateral inlets configuration is proposed. After the comprehensive multidisciplinary coordinate and iterate, the baseline scheme of the LRAAARM which has considerable practical engineering value is constructed. Those works provide a good foundation for the further research on the missile general design and optimization.Secondly, based on the quasi one-dimensional theory, the subsection processing method is adopted to study the air flow parameters between the ramjet’s two sections. The ramjet performance model including the air inlet, combustor and nozzle is established. From the general requirement, the ramjet performance is analyzed thoroughly and the effects of the ramjet design parameters on the overall performance are explored. The strong coupling relationship between the design parameters and the missile engine overall performance is revealed quantitatively. Those works provide theoretical guidance for the trajectory calculation and conception design and optimization.Thirdly, the integrated design method of missile conception design, ramjet and trajectory is researched. The static parameters optimization and trajectory optimization are extended to a mixed static and dynamic hybrid optimization problem. According to the actual engineering requirements, the appropriate objective function, reasonable constraint conditions and design variables are chosen. The integrated optimization model including the missile general design, ramjet and trajectory is established with the objective function of minimum launch-off mass. The Gauss pseudospectral method is adopted to deal with the static/dynamic optimal control problem. The simulation results show that the missile overall parameters and flight trajectory combination optimization can improve the overall performance significantly.Fourthly, the multidisciplinary design optimization problem of air breathing missile is researched. The performance of three Collaborative Optimization(CO) methods are tested and analyzed by several benchmark functions. Those work provided the basis for selection of the LRAAARM MDO framework.Based on the coupling relationship analysis of different disciplines, the MDO models based on the CO framework of the LRAAARM are constructed. The i SIGHT simulation platform is applied to integrate and solve the MDO models. The results show that the MDO framework constructed in this thesis can effectively optimize the missile overall parameters, further excavated the potential of missile general design.