推進發動機 的英文怎麼說
中文拼音 [tuījìnfādòngjī]
推進發動機
英文
propelling engine-
The first modern torpedo ( 1866 ) carried an 18 - lb ( 8 - kg ) charge of dynamite in its nose and was powered by a compressed - air engine driving a single propeller ; its range was 200 - 700 yards ( 180 - 640 m )
第一枚現代魚雷（ 1866 ）在其頭部裝載了8公斤的炸藥，並用壓縮空氣發動機帶動單螺旋槳推進;射程為180 640公尺。Bipropellant liquid rocket motor
二元推進劑液體火箭發動機By utilizing self - diagnosis method and diagnosis method based on dt, it become more convenience for fault orientation. considering about fuzzy relation between fault cause and symptom, commix fuzzy diagnosis module was set up by means of fuzzy synthesize judge
將診斷樹應用於電噴發動機故障診斷專家系統可以優化搜索過程，實現對故障起因的最佳搜索。採用模糊綜合評判的方法進行模糊推理，有效地解決了故障原因與徵兆之間不確定性問題。Because of the great quantity, strong specialization, wide involved range of the knowledge of engine, this paper introduces the construction of the repository, reasoning machine, program interface and the knowledge acquirement of dmas wearing fault integrated diagnostician system, puts forward the method of storing and managing the fault diagnostic knowledge by database, carries out fault diagnostic with proper reasoning strategy, and discusses the realization of the system from the view of the theory and engineering. 3, the research on the remote fault diagnostic system
2 、 dmas故障診斷專家系統的研究本文主要針對發動機的知識具有數量大、專業性強、經驗成分多、涉及面廣等特點，介紹了dmas磨損故障綜合診斷專家系統的知識庫、推理機、人機界面和知識獲取的實現，並提出把故障領域知識存入相應的數據庫，運用數據庫技術進行管理，結合合適的推理策略進行故障診斷，並從理論和具體方法上對系統的實現過程進行了探討。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。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。Thermal control of monopropellant catalytic decomposition hydrazine engines in important portion of space propulsive system
單組元肼分解發動機的熱控制與熱分析是空間推進系統重要組成部分。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。The propulsion system consists of five f-1 engines.
推進系統包括五個F-1發動機。The liquids employed for rocket propulsion are called propergols.
用於火箭發動機的液體稱為液體火箭推進劑。The propulsion system consists of five f - 1 engines
推進系統包括五個f - 1發動機。Small crafts - engine and propulsive systems - vocabulary
小船.發動機和推進系統.詞匯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。The evolution course of chinese solid rocket propulsion technology for space missions since 1950s is presented. the technical features, development process, ground tests and flight records of nine typical solid motors are described. these motors were developed for sounding rockets, upper stages of launch vehicles and orbit transfer systems in application satellites respectively. the evolution of basic technology of chinese solid rocket motors and future developing concept are briefly introduced. the information in the paper are all based on the published literatures
敘述了20世紀50年代以來中國航天固體火箭推進技術的發展歷程，介紹了9種最具代表性的固體火箭發動機的技術特徵、研製過程、地面試驗和飛行情況，這些發動機分別應用於中國的探空火箭、運載火箭上面級和應用衛星變軌系統.文中還簡要地評述了中國固體推進各單項技術的發展水平Abstract : the evolution course of chinese solid rocket propulsion technology for space missions since 1950s is presented. the technical features, development process, ground tests and flight records of nine typical solid motors are described. these motors were developed for sounding rockets, upper stages of launch vehicles and orbit transfer systems in application satellites respectively. the evolution of basic technology of chinese solid rocket motors and future developing concept are briefly introduced. the information in the paper are all based on the published literatures
文摘:敘述了20世紀50年代以來中國航天固體火箭推進技術的發展歷程，介紹了9種最具代表性的固體火箭發動機的技術特徵、研製過程、地面試驗和飛行情況，這些發動機分別應用於中國的探空火箭、運載火箭上面級和應用衛星變軌系統.文中還簡要地評述了中國固體推進各單項技術的發展水平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Small craft. marine propulsion engines and systems. power measurements and declarations
小艇.船用推進發動機和裝置.功率測量和說明Shipbuilding - terminology and definition of output of internal combustion propulsion engines
造船.內燃推進發動機輸出的定義和術語Small craft - marine propulsion engines and systems - power measurements and declarations
小船.船舶推進發動機和系統.功率測量和申報分享友人