Integrated Design Of Integral Rocket-Ramjet Missile

Integral rocket-ramjet is a propulsion system with great potential. Using missile-engine integrated design method to realize the conceptual design of integral rocket-ramjet missile is of great significance to improve quality and efficiency of missile design. Integrated design of rocket-ramjet is investigated systematically in this paper. Based on step optimization pattern,proper matching for missile and engine is solved satisfactorily. Also the relationship between guidance system and optimal trajectory is settled. The primary work of this paper is as follow:Three aspects are analyzed in detail as to the characteristics of integral rocket-ramjet,which include:a. the matching for inlet shape and missile configuration;b. the influence on missile conceptual performance caused by the number and position of inlet;c. integral design of rocket-ramjet and solid booster.Optimization methods are investigated systematically. The theory,framework and specific mathematical description of MDO (Multidisciplinary Design Optimization) are studied. Collaborative optimization method is studied in depth,the causes leading to computational difficulty of this method are discussed by optimization theory and computation examples,and improve method which may solve this problem is presented. Based on the comparison of several optimization methods and the characteristics of modern rocket-ramjet,step optimization pattern-a new integrated design mode is presented and is used to realize integrated design of rocket-ramjet.Inner and outer fiowfield of a certain integral rocket-ramjet missile is simulated numerically using N-S equation. Also longitudinal aerodynamic characteristics of missile are investigated. The traditional dependence on wind tunnel experiment is changed greatly:firstly,the aerodynamic characteristics of missiles with complex configuration are solved satisfactorily,especially integral rocket-ramjet missile;secondly,feasibility of N-S equation to numerical simulation of inner and outer fiowfield of missile with complex configuration is discussed.Design of two propulsion systems is studied -solid rocket ramjet and liquid ramjet. The performance analysis models and design methods are set up for these two kinds of engines. The different characteristics are analyzed and compared,which provide basis for farther trajectory computation and conceptual optimization design.The key technology in integrated design of rocket-ramjet missile is discussed --interference and restriction,also the method and framework of this integrateddesign are presented. Based on each subsystem models,a computer aided integrated design system isset up for integral rocket-ramjet anti-ship missile. This design system can beapplied to MDO because of its modular structure.Aerodynamic characteristics,propulsion system and integrated design aspects related to integral rocket-ramjet missile are studied thoroughly in this paper,which has important reference value and instructional significance in the development of integral rocket-ramjet missile.