The Operation Characteristics Of Solid-propellant Ducted Rocket

High speed, high specific impulse, long range, high maneuver, simple structure are ideal objects, which designers of missile propulsion aspire after for ever. Owing to predominant characteristics, solid-propellant ducted rocket has been paying more attention to by scholars all over the world. It has become one of the major directions of propulsion system of supersonic missile. The integral design of system/motor and the system design of motor are key techniques for developing solid-propellant ducted rocket. In order to explore these key techniques, this thesis is aimed at discussing the operation characteristics of solid-propellant ducted rocket.The aim of the study is to develop an engineering method completing the design and performance prediction of solid-propellant ducted rocket.Based on thermal calculation, the theoretical performance of solid-propellant ducted rocket is investigated. The design method and content of solid-propellant ducted rocket is provided in preliminary design phase. Analysis shows that air and fuel ration of solid-propellant ducted rocket, total pressure of second combustor need design well. The method selecting air-fuel ratio under the influence of combustion efficiency is proposed. The performance of solid-propellant ducted rocket at design point and off-design point is analyzed. The attitude characteristics, velocity characteristics and stability of solid-propellant ducted rocket are theoretically studied. The simulation module of flight envelope of missile with solid-propellant ducted rocket is established based on integral calculation, In this paper, the interior ballistics of end-burning grain gas generator embedded with silver-wire are analyzed. The foreground applying end-burning grain embedded with silver-wire to solid-propellant ducted rocket is discussed. Results show that the end-burning grain embedded with silver-wire is not suitable for unchecked solid-propellant ducted rockets unless it can work steadily. In addition, the design and simulation computer program is completed successfully.The content and some significative conclusions in this thesis could supply valuable reference to the engineering development of solid-propellant ducted rocket.