火箭發動機組 的英文怎麼說
中文拼音 [huǒjiànfādòngjīzǔ]
火箭發動機組
英文
multiple rocket engine-
In this thesis, based on pershing ii surface to surface missile, a new kind of ballistic missile was designed with an additional rocket engine, which can be ignited twice. firstly, aerodynamic computational models of missile body and warhead which reentry with supersonic are built according to the task requirements ; secondly, the propulsion system model of missile is built whose first two stages are solid rocket engines and the third stage is liquid - solid combined rocket engine. the nozzle and the shape of the engine are designed to meet the needs of the populsion project ; thirdly, the trajectory model of the mass point is built and a wavy trajectory is designed & optimized ; finally, the ability of a missile ' s breaking through defence is analyzed
以美國潘興導彈為原型，增加可兩次點火的末級發動機，改裝成具有跳躍能力的地地彈道導彈；首先，根據任務需求，建立了導彈的氣動模型，並建立了彈頭再入時高超聲速氣動模型；其次，建立了導彈推進系統模型，前兩級採用了固體火箭發動機，第三級採用了固?液組合火箭發動機，並在總體方案要求下，對發動機噴管和外形進行了設計；第三部分，建立了導彈質點彈道模型，設計了一條跳躍式彈道，並對跳躍式彈道進行了優化設計；最後，對導彈進行了突防能力分析，從分析的結果可以看出，跳躍式彈道的突防能力比常規的拋物線彈道要強。Rocket based combined cycle ( rbcc ) will be one of the promising propulsion systems for single stage to orbit vehicle, and has extensively application foreground in both military and civil usage
火箭基組合循環發動機（ rbcc ： rocketbasedcombinedcycle ）是單級入軌最有潛力的動力方案之一，具有廣泛的軍事和民用航天應用前景，受到世界各國航天界的矚目。Both advantages of rocket engine and air - breathing engine are integrated into one kind of propulsion system, called rocket - based - combined - cycle ( rbcc ), which has multiple operating woke modes, including ejecting, subsonic combustion, supersonic combustion and rocket mode, with each mode operating at varying flying stage. rbcc has prominent potential of high efficiency and low cost, and so it is recognized as an advanced propulsion system of future single - stage - to - orbit reusable spacecraft and hipper - sonic missile. it has been broadly investigated in foreign countries and has been progressed into small and full - scale flying stage
火箭基組合動力循環（ rbcc ， rocketbasedcombinedcycle ）將傳統的火箭發動機和吸氣式發動機的優點集中組合到一個具有多種工作模態（包括引射、亞燃、超燃及火箭模態）的發動機里，在不同的飛行階段啟用不同的工作模態，因此具有大幅提高航天推進系統經濟性與高效性的潛在優勢，並可能發展成為下一代單級可重復使用航天器以及高超聲速導彈武器的動力系統。Through malfunction of the tests of 810 research institute, the combustion performance of the hybrid motor and model about regression rate have been studied in the dissertation. the main aspects are as follows : the performance of the hno3 + n2o4 - htpb hybrid rocket motor were all discussed
本文結合航天科技集團公司810研究所正在研製的ak - 20l / htpb + al組合固液火箭發動機，開展了固液火箭發動機混合燃燒特性的數值模擬工作，在此基礎上給出固體燃料退移速率預示模型及預示結果。New developments in decision theory, artificial theory and dynamic analysis method are applied to evaluation the possible projects. the main contents in this paper are included as follows : first, has improved an format reasoning method based on multiple attribute utility model and knowledgebase theory ; second, has proposed complex utility model by improving the theory of multiple attribute utility ; third, has presented a kind of weapon intelligent decision support system, based on the complex utility model and developed with com / dcom criterion ; forth, this paper also has build the dynamic simulation model for long - rang multiple tube rocket launcher system, and the tire dynamic model has applied in the rocket launcher system dynamic simulation model ; fifth, through building the rocket - launcher contact model, this paper has analyzed the dynamic forces between the rocket and launcher ; finally, this paper has build the evaluation model of the project about improving existing rocket launcher to the launcher that using canister, and get the conclusion through using the widss. the studies in this paper not only proposed scientific warrant to the choice of projects in this pre - studied national defense task about improving existing rocket launcher to the launcher that using canister, but also can give other studied tasks with decision supported
主要內容包括：在總結決策分析與專家系統規則庫技術的基礎上，提出了融決策分析與專家系統規則庫技術於一體的形式化推理機制，該機制能有效的將定量計算和定性知識融為一體，將規范的決策分析解題過程與專家系統特有的演化推理方法有機結合起來；在多屬性效用理論的基礎上，建立了一般形式的復式效用模型，並實用化了全相關乘式效用模型，提供了較完善的通用建模、分析和解釋功能：引入了com dcom組件技術，開發了基於組件的widss系統，該系統基於形式化推理機制，易於擴展，能夠面向多種決策問題，具有較強的通用性；建立了遠程多管火箭炮全炮動力學模擬模型，將充氣輪胎動力學模型、輪胎和路面的相互作用模型運用於多管火箭炮動力學模擬計算中；利用碰撞接觸理論，對火箭彈在定向器管內的運動受力情況進行了模擬計算；建立了遠程多管火箭炮箱式發射改進方案模型，並利用動力學模擬計算結果在widss系統中進行了方案性能評估。They would be built from shuttle booster rockets fuel tanks and main engines as well as moon rocket engines
新型運載火箭將由飛船助推火箭燃料箱主發動機以及月球火箭發動機組成。They would be built from shuttle booster rockets, fuel tanks and main engines, as well as moon rocket engines
新型運載火箭將由飛船助推火箭燃料箱主發動機以及月球火箭發動機組成。When escape system is activated, the grille wings at the upper fairing will open, supporting frame will pick up the orbit and returning modules, the lock between the returning and propelling modules will release, the lock between the upper and lower fairings will release, escape rocket will be ignited and finally pull the escape flight vehicle away from the rocket
該系統由逃逸塔和上部整流罩組成，逃逸系統加上飛船的軌道艙和返回艙構成逃逸飛行器。當需要逃逸時，上部整流罩上的柵格翼打開，支撐機構夾住飛船軌道艙和返回艙，然後返回艙與推進艙解鎖上下整流罩解鎖逃逸發動機點火，逃逸飛行器飛離運載火箭。In the thesis, the combustions ( ejector ' s first combustion and ramjet ' s secondary combustion ) organization of a typical structure of rbcc jet ? strutjet, was studied and analyzed, to get a better and dynamic method, to organize such kind of combustions
論文從rbcc發動機的一種典型結構- - - -支板引射火箭發動機（ strutjet ）出發，分析了這種組合發動機的燃燒（引射火箭的一次燃燒與沖壓補燃室中的二次燃燒）組織，獲得了組織這類燃燒的較好方法?實時、動態的智能組織。As an advanced propulsion system, rbcc ( rocke based combined cycle ) motor is now abstracting more and more attention of most of the major space countries in the world
作為一種先進的推進系統，火箭基組合循環（ rbcc ）發動機以其優良的整體性能越來越受到世界航天大國的普遍關注。It is of great significance to investigate performance characteristics and thrust augmentation mechanism in rbcc engine. this dissertation just deals with the mixing and combustion flow in a experimental strutjet rbcc in ejecting mode to investigate its performance characteristics and thrust augmentation mechanism by applying numerical simulation technique. the detail is as follows : 1
本文應用數值技術對支板式rbcc發動機，即支板火箭引射沖壓組合發動機，引射模態的燃燒與流動現象進行了研究，探討了rbcc引射模態的性能增強機理，主要有以下幾方面： 1This thesis fully discusses the solid rocket motor ( srm ) metal case cad system. a srm metal case design, calculation and analysis system is developed by use of object - oriented programming ( oop ) technique and powerful finite element analysis software ansys. several key techniques have been solved successfully
本文系統地研究了固體火箭發動機金屬殼體cad系統的組成，應用面向對象技術和大型有限元分析軟體ansys的二次開發技術建立開發了固體火箭發動機金屬殼體設計、計算與分析系統，較為成功地解決了如下幾個關鍵問題： 1In this paper, the characteristics of tripropellant rocket engine was studied in two different ways : experiment and simulation
本文從實驗、模擬兩個方面對三組元液體火箭發動機推力室的工作過程進行了研究。Solid rocket motor ( srm ) grain is casted integrally from solid propellants. it is one of the important structural components and also provides fuels for srm. the reliability of srm grain should be paid great attention
固體火箭發動機藥柱是由固體推進劑整體澆鑄而成的，既為發動機提供燃料，又是重要的結構組成部分，其安全性不容忽視。分享友人