火箭分級 的英文怎麼說
中文拼音 [huǒjiànfēnjí]
火箭分級
英文
rocket staging-
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 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Contact analysis of stage separation surface of carrier rocket
運載火箭級間分離面接觸分析In the condition of non - axisymmetrical stage separation in hypersonic flight, the problems of dynamics and kinematics of the validating vechicle and the launch vechicle are primarily analysised. it includes the movement of the center of mass and the rigid body of the vechicles, the relative movement of the different vechicles, the relative movement of the special parts of the different vechicles, the load analysis and the probable collision in the process of stage separation
研究了在高超聲速狀態下非對稱級間分離過程中，驗證飛行器與運載火箭分離時的相關運動學和動力學問題。包括:飛行體質心運動和剛體運動;不同飛行體之間的相對運動;不同飛行體上特殊部位之間的相對運動;分離過程中各相關飛行體上的載荷分析和分離過程中可能發生的碰撞問題。The channel scale on transpiration cooling for the platelet thrust chamber of liquid propellant rocket engine is approaching micron dimension. it is very possible that micro - scale effects will occur in the flow and heat transfer of the channel. in the past, researchs on flow and heat transfer in the platelet micro - channel are mostly based on macro - scale theory
液體火箭發動機推力室壁面發汗冷卻通道的尺度已達微米量級，通道內的流動與換熱很可能存在微尺度效應，以前的相關研究都以宏觀尺度的理論為依據，其研究結果的合理性需要進行微尺度效應的分析。The multi - stage rocket will jettison its aft stages when fuel in these stages is exhausted. this reduces the weight of the rocket and increases its speed
多級火箭會把燃料用完的尾一級火箭依次分離丟掉，以減輕火箭的重量及增加速度。Numerical simulation the process of the rocket booster separating form spaceship
火箭助推器從芯級飛行器動態分離過程的數值模擬Separation of the first stage with the second stage
火箭一二級分離成功，一級墜落。分享友人