rocket ramjet 中文意思是什麼
rocket ramjet
解釋
火箭沖壓噴氣發動機- rocket : n 火箭；火箭彈，火箭發動機；火箭式投射器；〈英俚〉斥責。 a carrier [freight] rocket 載運火箭。 an...
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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。 -
Contrast study on cold - flow mixing effect and combustion efficiency of afterburning chamber of solid rocket ramjet
固沖發動機補燃室冷流摻混效果與燃燒效率對比研究 -
As the air - breathing engine, the performance of solid rocket ramjet is determined not only by structure of engine and the performance of propellant, but also by flight condition
作為吸氣式發動機，其性能不僅取決于發動機本身結構和推進劑性能，與飛行狀態也有密切的聯系。 -
For studying the performance of solid rocket ramjet under the influence of different flight conditions, it ' s significant to simulate the integrated flow field of inlet and combustor
因此，開展超聲速進氣道/補燃室流場一體化數值模擬研究對于考查飛行狀態對於火箭沖壓發動機性能的直接影響具有重要的現實意義。 -
In order to determination the thrust, the thrust definition and many control parameters are analyzed discussed, which mass flow rate and flight altitude are involved. it is difficult to measure the flight thrust of solid rocket ramjet directly
通過討論高空飛行推力與地面可測試參數的關系，得到了固體火箭沖壓發動機高空飛行狀態下推力折算方法，並開發相應的計算程序。 -
It is determined now by calculation with mathematical relationship of the flight thrust to the physical quantities which can be measured directly. the optimization of the software development platform is also analyzed inspect of the solid rocket - ramjet developmental program
其次，為滿足固體火箭沖壓發動機試驗技術進一步研究需要，在深入分析labview圖形化編程軟體優化方法的基礎上，改進了現有的固體火箭沖壓發動機試驗測控程序，並應用於發動機試驗中。 -
During the study of solid rocket ramjet ( srr ), ablation of afterburner thermal insulation is a serious problem, which cannot be ignored
固沖發動機補燃室絕熱層的燒蝕問題是目前固沖發動機研製過程中所面臨的一個重要問題。 -
The structure design and the performance research of supersonic inlet / combustor are key techniques for solid rocket ramjet
超聲速進氣道及補燃室的設計與性能研究是固體火箭沖壓發動機的兩大關鍵技術。 -
According to the definition and expression of the thrust, as well as the condition derived from them, a method of solid rocket ramjet thrust determination and its program are provided on the basis of engine ground simulation test
本文以西北工業大學固體火箭沖壓發動機直連式試車臺為研究對象，探討固體火箭沖壓發動機地面試驗技術。首先，從推力的定義出發，建立了試驗中來流空氣流量、燃料流量與固體火箭沖壓發動機推力之關系。 -
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 -
In addition, the usaf continues to fund development work of the aerojet ( formerly atlantic research ) variable flow ducted rocket ramjet system as a future propulsion option for an extended range aam
此外，美國空軍繼續投資于航空噴氣研究所（原來的大西洋研究所）的可變噴流管火箭發動機系統，將其作為增程空空導彈的未來推進選項。 -
The determination of solid rocket ramjet thrust and testing method are the important basis of the developing engine. an experimental program evaluating solid rocket - ramjet in nwpu connected - pipe facility is underway
我國發展中遠程、超音速導彈計劃已經啟動，其動力裝置首選固體火箭沖壓發動機，而地面試驗技術是發動機研究重要基礎。 -
With zonal patched grid technology and second - order zonal solver method, the numerical simulation on inlet complex flow field of solid rocket ramjet assisted range projectiles with different struts shapes was made at different mach numbers
摘要結合分區對接網格技術和二階精度區域分解演算法，對某沖壓增程彈丸進氣道在不同來流攻角和不同側向支柱形狀工況下的內外復雜流場進行了數值模擬。 -
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
（ 4 ）研究了兩種動力裝置? ?固體火箭沖壓發動機和液體燃料沖壓發動機的設計問題，建立了兩種發動機的性能分析模型和計算方法，對固體火箭沖壓發動機和液體燃料沖壓發動機的特性進行計算分析及比較，為彈道計算及總體優化設計提供依據。 -
All of the work made foundation of developing solid rocket - ramjet engine
為固體火箭沖壓發動機試驗研究打下基礎。 -
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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