火箭系統推力 的英文怎麼說

中文拼音 [huǒjiànxìtǒngtuīlì]
火箭系統推力 英文
system thrust
  • 火 : fire
  • 箭 : 名詞（古代兵器） arrow
  • 系 : 系動詞（打結; 扣） tie; fasten; do up; button up
  • 統 : Ⅰ名詞1 （事物間連續的關系） interconnected system 2 （衣服等的筒狀部分） any tube shaped part of ...
  • 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...
  • 火箭 : [航空] rocket; fire arrow; bird
  • 系統 : 1. （按一定關系組成的同類事物） system 2. （有條理的;有系統的） systematic
  • 推力 : visatergo; soot; propulsive force; thrust; momentum thrust
  1. 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。
  2. 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
  3. 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。
  4. 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。
  5. Abstract : this paper briefly presents th e application of advanced brazing techniques for a larye number of assemblies of space vehicles, such as thrust chamber and turbine rotor of launch rock et engine, titanium tube of satellite, attitude control engine injector and wave guide component of satell ite, reflector, tube and honeycomb panel of manned spacecraft, main engine nozzl e and preburner of space shuttle as well as the pipeline systems of space statio n

    文摘:簡略地介紹了先進釬焊技術在航天器部件，例如運載火箭發動機的推力室和渦輪轉子、人造衛星的鈦導管、姿控發動機噴注器和波導器件、載人飛船的反射器、導管和蜂窩壁板、航天飛機的主發動機噴管和預燃室以及空間站的管路系統等的廣泛應用情況。
  6. Abstract : introduces a method to eliminate influence of power supply and air - feed system on exact measurement of micro - thrust of electric rocket in the gravity field, so micro - thrust can be measured accuratelg and automatically

    文摘:介紹了在重力場中，消除電火箭自重及其供電供氣系統對微小推力測量影響的方法，從而實現電火箭微小推力自動準確的測量。
  7. Rocket ejector is the alternative power of rbcc during low - speed operation. the utilization of rocket ejector will be important for structural integration, and will decrease weight and complexity of the motor

    引射火箭模態作為rbcc推進方案低速階段的起飛動力，對于實現rbcc結構一體化、減輕結構重量和系統復雜度具有重要的意義。
  8. It has a large region of application in solid rocket motor grain design and has made new improvements compared with other available codes. user can easily and rapidly build his initial grain shapes and then obtain geometric information of his design. according to the theory describeds in the paper, the regressions of the burning surface area and the pressure are obtainded

    該系統擴展了固體火箭發動機裝藥的設計能力，用戶可利用它簡捷地構造出三維藥柱的初始形狀，並獲得設計所需的各個幾何參數，進而依據本論文提出的復雜三維藥柱內腔燃燒推移和燃面計算的方法，計算出燃面變化和壓強變化，得到推力隨時間變化的曲線，再依據這些計算結果進行再設計，直至達到滿意的結果為止。
  9. Based on widely assimilating the internal and overseas researches, the theory and methods of solid rocket motor ( srm ) thrust vector measurement and the automatic test technology are studied detailedly and comprehensively by means of theoretical analysis, engineering implement and experimental validation. the results attained are as follows

    論文在廣泛吸收國內外研究成果的基礎上，藉助理論分析、工程實現和試驗驗證等手段，對火箭發動機地面試驗中的推力矢量測量理論與方法以及自動測試技術進行了系統深入的研究，取得了一系列研究成果。
  10. When an engine works under the vacuum condition. so existing experimental products can be proof - tested by it and all test results obtained will be used for reference for the aero craft. accordingly, the technology studied in the thesis is quite significative to improve the efficiency of the engines of space propulsion system, economize limited resources on the spacecrafts, and prolong their lives

    其目的是建立一個能滿足小推力液體火箭發動機動態推力測試的系統，以便能夠根據空間推進系統對發動機越來越高的工作性能要求，真實有效地反映發動機在真空環境下的工作狀態等，對已經設計和生產出的發動機在高空模擬條件下進行實際測試，從而提供發動機的動態性能指標，為發動機的定型提供試驗數據和依據。
  11. Changzheng long march 2f consists of ten subsystems : rocket body, control system, propulsion system, malfunctioning detection and management system, escape system, remote monitoring system, telemetry safety system, propellant utilization system, additional system and ground facilities

    運載火箭有箭體結構控制系統動力裝置故障檢測處理系統逃逸系統遙測系統外測安全系統推進劑利用系統附加系統地面設備等十個分系統。
  12. In this paper, based on the viscoelasticity theory and the dynamics theory, the finite element method ( fem ) is used to the structural integrality analysis of the grain in rocket engine of the base - bleed and rocket compound extended range projectile in chamber

    本文基於粘彈性理論和動力學理論，運用ansys對某型號底排?火箭復合增程彈助推火箭發動機藥柱在膛內的結構完整性進行了系統的分析。
  13. Rocket - based combined cycle ( rbcc ) will be promising propulsion system to achieve hypersonic flight, and has extensively application foreground in both military and civil usage

    火箭基組合循環（ rbcc ）推進系統是實現高超聲速飛行的最有潛力的動力方案，具有廣泛的軍事和民用航天應用前景，因而備受矚目。
  14. Under the base of the parameter characteristics of the engine thermodynamics and the air - inlet simulation, the measurement and control schemes are designed with virtual instrument technology

    本文在深入分析討論固體火箭沖壓發動機試驗參數特點以及進氣模擬對控制系統要求的基礎上，提出了發動機溫度、壓力、流量及其推力測量的總體方案和進氣模擬總體控制方案。
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