rocket ramjet missile 中文意思是什麼
rocket ramjet missile
解釋
沖壓式火箭發動機導彈-
The solid rocket ramjet, which combines the techniques of ramjet propulsion and solid rocket propulsion, offers the following advantages for missile propulsion : high specific impulse, simple configuration, high credibility, convenient using and high maneuverability
固體火箭沖壓發動機結合了沖壓技術和固體火箭技術，具有比沖高、結構緊湊、工作可靠、使用方便、機動性好等優點，是新一代超聲速戰術導彈的優選動力裝置。 -
The solid - propullant ducted rocket, which combines the advantages of solid propullant rocket and ramjet propulsion, is a new kind of combined propulsion system. it offers considerable advantages for missile propulsion, such as high specific impulse, high speed, light weight, long range, high maneuver and simple structure. as the major direction of the propulsion system for supersonic missile, the ducted rocket has good prospects
它將固體火箭技術和沖壓技術有機結合在一起，具有比沖高、速度快、重量輕、射程遠、機動性能好和結構簡單等諸多優點，最大限度地滿足了新一代導彈對其動力裝置提出的要求，是超聲速導彈動力裝置的一個主要發展方向，有著廣闊的研究前景。 -
Genetic algorithm applied to integral design optimization of missile propelled by solid rocket ramjet
固體火箭沖壓發動機導彈一體化遺傳演算法優化設計 -
The research project of the middle - long and hypersonic missile with solid rocket - ramjet engine has been launched. the measurement and control technologies are the important basis of developing engine, which is one of the key technologies of the research
我國發展中遠程、高超聲速固體沖壓導彈已經啟動，其關鍵技術之一是研製性能優良的固體火箭沖壓發動機，而試驗測控技術是發動機研製中不可或缺的重要基礎。 -
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
（ 3 ）採用n - s方程方法數值模擬某型整體式沖壓發動機導彈的全彈內外流場，研究了導彈的縱向氣動特性，改變了過去依賴于地面風洞試驗結果的傳統做法。 -
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
（ 2 ）系統地研究了導彈總體優化設計方法，探討了多學科設計優化的原理、框架結構、具體表述形式，深入研究了協作優化方法的原理，從優化原理和算例兩方面討論了造成協作優化方法計算困難的原因，提出了可能克服這種計算困難的改進途徑；在比較幾種優化方法的基礎上，針對新一代沖壓式導彈的特點，提出了一體化設計的模式? ?分步優化模式，進行了整體式火箭沖壓發動機反艦導彈總體參數的一體化設計。 -
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
整體式火箭沖壓發動機是一種很有前途的動力裝置，採用導彈和發動機一體化設計方法進行整體沖壓式導彈的總體設計，對于提高導彈的設計質量和設計效率具有重要的意義。 -
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
具體表現在如下幾個方面： （ 1 ）針對整體式沖壓發動機的特點，詳細分析了進氣道型式與導彈總體布局的匹配關系、進氣道數目及其安裝位置對導彈總體性能的影響、沖壓發動機和固體助推器的一體化等彈機一體化設計的問題。
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