Integrated Design Of Integral Solid Propellant Ramjet Air-to-Surface Missile

Multidisciplinary Design Optimization(MDO)is a development trend of flight vehicle design.The multifidelity method is an effective way to solve MDO problems.This research aiming at the needs of overall optimization design of Integral Solid Propellant Ramjet(ISPR)air-to-surface missiles.The application of multifidelity method in MDO problems is studied.The research content of the thesis includes:First,a parameterized model of air-to-surface missile with inlets is established.As a basis of MDO,the parameterized model is widely used in aerodynamics,mass,and propellant disciplines.According to the parameterized modeling results,the aerodynamics layout of the missile is selected.Second,a multifidelity method basing Co-Kriging of aerodynamics calculation is designed.By comparing,the medium-fidelity aerodynamic calculation method is formed based on Co-Kriging method.It is tested that it has higher calculation accuracy.Third,an internal and external ballistic integration calculation model of ISPR basing engineering calculation methods is established,and multifidelity mass discipline model using different fidelity geometric model are proposed.Fourth,a multifidelity MDO strategy is proposed,MDO platform MID(Missile Integrated Design)is perfected.Different fidelity strategies are proposed for different models.The integrated design of air-to-surface missile is completed.These strategies can meet the needs of all disciplinary models and completely establish a multifidelity MDO framework.The MDO framework and the MID platform are verified according to practical problems.The MDO problem and the integrated design of air-to-surface missile problem can be solved by using the MDO framework and MID platform.The research results of the paper can guide the overall integrated design of the airto-surface missile,and can also be applied to other flight vehicle design to provide new technical support.