推力發動機 的英文怎麼說

中文拼音 [tuīlìfādòngjī]
推力發動機 英文
thrust engine
  • 推 : 動詞1 （向外用力使物體移動） push; shove 2 （磨或碾） turn a mill or grindstone; grind 3 （剪或削...
  • 力 : Ⅰ名1 （力量; 能力） power; strength; ability; capacity 2 [物理學] （改變物體運動狀態的作用） forc...
  • 發 : 名詞（頭發） hair
  • 機 : machineengine
  • 推力 : visatergo; soot; propulsive force; thrust; momentum thrust
  1. The main works and achievements are described : ( 1 ) the application of direct lateral force on the exoatmosphere kinetic - kill vehicle. at first, the collectivity project of the exoatmosphere kinetic - kill vehicle is specified, the motive model of the exoatmosphere kinetic - kill vehicle and target are constructed, and the thrust performance of trajectory - control engine and attitude - control engine are presented

    研究的內容及成果主要表現在以下幾個方面： （一）直接側向力在大氣層外動能攔截器中的應用首先確定了動能攔截器的總體方案，分別建立目標運動和動能攔截器運動的數學模型，以及軌控和姿控發動機的推力模型。
  2. Jet engines with which most modern high-speed aircrafts are equipped develop thrust on the same principle as the propellers of conventional aero-engines.

    大多數現代高速飛機裝備的噴氣發動機產生推力的原理，與普通航空發動機的螺旋槳相同。
  3. A 3 - d viscosity turbulence model is used to analyze the unsteady around flow field of the thrust - vectoring engine of the jet vane, and results of the area including vane base, vane flake and motor shell are presented

    摘要以推力矢量發動機的燃氣舵為研究對象，採用三維、粘性、湍流流動模型和數值分析的接觸網格技術，在定常流動計算的基礎上，對包含舵基、舵片和發動機殼體的區域進行詳細數值分析。
  4. The suggestion of speeding up the development of a large thrust lox lh2 engine and taking vigorous action to research advanced propulsion technology are proposed

    提出應加快我國大推力氫氧發動機的研製，並積極開展各項先進技術的預先研究工作。
  5. Three main problems caused by normal force when linear motor was used in machine tool were presented

    發現了法向吸力在直線電機的實際應用中導致的推力波動問題、裝配問題和機床隔磁問題。
  6. 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。
  7. Abstract : solid propellant rocket motors are preferred for most ballistic missiles because they need simple maintenance and can be launched quickly. but the conventional thrust termination devices limit the depletion of every stage ' s grain and increase some extra - weight. an improved method for designing a multi - stage solid rocket based depleted shutdown was provided. in order to solve the problem of lack of thrust termination devices, a device to adjust the burnout angle will match the final burnout velocity and satisfy the desired range. the method can also limit the detection from anti - ballistic missile system

    文摘:由於維護簡單和發射快速，彈道導彈多用固體火箭發動機，但繁雜的推力終止裝置使各級裝藥不能耗盡並讓結構增重.提出了一種對基於耗盡關機多級固體火箭概念設計的改進方法，此方法滿足導彈系統主要的戰技要求.為解決無推力終止裝置的末速不準問題，可在末級發動機採用姿態調整裝置，對射角進行調整，配合末速以滿足射程要求.本方法還可抑制敵方反導探測
  8. Thrust vector control is one of objects being seeked by engineers in rocket propulsion area

    流場控制以及基於此的發動機推力方向控制長期以來都是國內外火箭推進領域廣大工程技術人員追尋的目標之一。
  9. A mathematical model reflecting the tilt rotor unsteady and nonlinear aerodynamic characteristics in the longitudinal channel is presented in the paper. in the full flight envelope, the rotor thrust continues tilting and the aerodynamic forces of each component change as a function of airspeed and nacelle angle

    在整個飛行包線內，旋翼的推力矢量方向不斷變化，飛機各部件的氣動力隨發動機短艙傾角和空速的變化而變化，因而飛機的飛行動力學有很強的非定常、非線性特性。
  10. By 1955 the sea hawk performance was already considered mediocre which led to the installation of the more powerful 5, 200 lb thrust nene 103 and the use of the sea hawk as a ground attack aircraft, cleared to carry external stores, a task at which the sea hawk excelled

    到1955年，因為「海鷹」的表現只能說是差強人意，所以換裝了推力為5 ， 200磅的「尼恩」 103發動機，同時， 「海鷹」的角色也轉變為一架對地攻擊機， 「海鷹」攜帶的外掛武器完全可以勝任。
  11. Because the propellant grain is viscoelastic material, the liner and adiabatic layer are also viscoelastic one, the interface debond problem is actually interface crack about elastic - viscoelastic or bi - viscoelastic materials. research about this problem relates to the knowledge of viscoelastic mechanics and interface fracture and combustion. numerical analysis method about interface debond on solid rocket motor is researched in this paper

    由於固體火箭發動機的推進劑藥柱是一種粘彈性材料，襯層和絕熱層也具有粘彈性性質，因此其界面脫粘問題實際上是彈性-粘彈性或雙粘彈性各向同性材料界面裂紋問題，對該問題的研究涉及到粘彈性力學、界面斷裂力學和燃燒學等相關學科。
  12. By adjusting many variable geometry components of the engine, bypass ratio can be changed during large range ( the most 0. 25 of military fighter ). the high specific thrust characteristic of turbojet engine and the low specific fuel consumption characteristic of the turbofan engine can be realized during different flight phase by the usage of vce technology

    變幾何變循環發動機是應用於第四代多用途戰斗機的理想動力裝置，通過多個部件幾何的調節在較大范圍內改變涵道比，能夠使發動機在不同航段分別實現渦噴發動機的高單位推力性能和渦扇發動機的低油耗性能。
  13. As to the modelling of integrated flight / propulsion system, this paper mainly investigated and the modelling methods of flight kinetics and propulsion system thermodynamics, building up the real - time models of body kinetics. then we integrated the component - level thermodynamics model of engine, solved the problem of matching of initial points in the integrated simulation of flight / engine and the interactive parts of flight system and propulsion system

    對于綜合飛行/推進系統建模，本文主要研究的是飛行動力學和推進系統熱力學的建模方法，建立了飛機動力學實時模擬模型。並結合前人已建立的發動機部件級熱力學模型，本課題在解決了飛機/發動機綜合模擬中的起始點匹配問題的基礎上，完成飛行系統和推進系統的交互部分，最終建立飛行/發動機綜合實時模擬模型。
  14. 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。
  15. 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。
  16. Focusing on the performance evaluating and the design of tripropellant injector, adopting the cold test rig with background pressure supply, malvem particle analyzer, ccd photography system, tripropellant hot test - bed, numerical simulation software and auxiliary theoretical a nalysis, the d ischarge c haracteristic a s w ell a s a tomization p erformance o f the injector and the combustion performance as well as the mode - transition characteristic of thrust chamber are studied detailedly based on the 3 different structures of coaxial tripropellant injector, large numbers of important conclusions are gained

    本文圍繞三組元噴嘴的性能評定及設計方法。採用反壓冷試臺、馬爾文測粒儀、 ccd高速攝影系統、三組元發動機熱態試驗臺、數值模擬程序及輔助理論分析等多種技術手段和研究方法，對三種結構的同軸式三組元噴嘴深入進行了噴嘴流量特性和霧化特性、推力室燃燒性能和轉工況性能研究，得到了大量重要結果。
  17. What ’ s more, the precision of thrust vector measurement is also calculated, depending upon the error analysis of nine - component model. a large - scale srm hot test is successfully done on the nine - component thrust vector stand. and the satisfactory results validate that the nine - component model is reasonable and the nine - component thrust vector stand design is feasible

    在九分力推力矢量試車臺上成功地進行了一次大型固體火箭發動機地面熱試車，得到了滿意的試驗結果，驗證了九分力模型的合理性和九分力推力矢量試車臺設計的可行性。
  18. ( 9 ) by studying matching between catalytic converter and exhaust gas system, the conclusions having been gotten as follow : " purifying step by step and driving step by step " and " mental substrate and chinaware substrate being used in same engine " being the laying principles in exhaust gas system, which can solve the contradiction between high converting efficiency of exhaust emission and small loss of power, fuel economics, the rapid light - off and laying difficulty of catalyst

    （ 9 ）進行了催化轉化器與排氣系統的匹配研究，對于催化劑的布置，提出了「分級凈化，逐級推動」的原則；對于載體形式的選擇，提出了「金屬載體和陶瓷載體復合」使用的原則。這樣可以良好的解訣催化轉化器與發動機匹配時，排氣污染物高凈化率與動力性經濟性損失小之間的矛盾、快速起燃和結構布置困難的矛盾。
  19. An on - line minimum - variance estimator was developed for thrust acceleration applied to orbit transfer using discrete - time radar measurements. the mass - flow - rate of propellant was selected as a state variant, which was estimated by employing an integral state model and ekf filter. the variation equations for measurement vector to mass - flow - rate have been established to linearize the discrete - time measurement equations. the algorithm has applied successfully to maneuver process in commanding satellite into geo - stationary orbit. the results show that the algorithm developed here can monitor and determine whether engine works well or failure precisely and quickly during orbit transfer process

    飛行器軌道機動過程中，為跟蹤、定位機動目標和干預機動控制過程，需要統計處理離散的雷達觀測量實時估計推進發動機的推力，進而確定飛行器的瞬時軌道參數.本文所述演算法是該工程問題的探討和解決方案.文章建立了軌道機動過程中連續變質量運動模型和離散雷達量測模型，推進發動機的質量秒耗量作為表徵推力加速度的一個近似常量，應用擴展卡爾曼濾波對離散的雷達測量數據進行順序統計處理給出秒耗量的最小方差估計;文章詳細地推導了線性化量測模型的變分方程和觀測矩陣;模擬結果表明該演算法能快速、準確地估計推進發動機的質量秒耗量和向機動目標施加的實際推力
  20. Dual - thrust motor

    雙推力發動機
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