火箭彈體 的英文怎麼說

中文拼音 [huǒjiàndàntǐ]
火箭彈體 英文
rocket airframe
  • 火 : fire
  • 箭 : 名詞（古代兵器） arrow
  • 彈 : 彈名詞1. （彈子; 小球形的東西） ball; pellet 2. （內裝爆炸物, 具有破壞和殺傷能力的東西） bullet; bomb
  • 體 : 體構詞成分。
  • 火箭彈 : jet projectile
  • 火箭 : [航空] rocket; fire arrow; bird
  1. The 3 - d complex flowfield of rocket - missile with wings and empennages induced by the interaction between by base jet and the flow around the body has been numerically simulated. the main work is as follows : first, the gordon - mcbride program was developed to make it more friendly and efficient to the users

    本文對帶彈翼/尾翼彈箭的三維噴流繞流復雜流場進行了數值模擬，其主要研究內容有：首先，對gordon - mcbride火箭程序作了改進，使改進后的軟體具有了非常友好的人機交互界面。
  2. 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。
  3. 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
  4. Analysis of nozzleless solid propellant rocket motor performance

    無噴管固體火箭發動機內彈道計算
  5. The solid rocket ramjet, which combines the techniques of ramjet propulsion and solid rocket propulsion, offers the following advantages for missile propulsion : high specific impulse, simple configuration, high credibility, convenient using and high maneuverability

    固體火箭沖壓發動機結合了沖壓技術和固體火箭技術，具有比沖高、結構緊湊、工作可靠、使用方便、機動性好等優點，是新一代超聲速戰術導彈的優選動力裝置。
  6. Fifth, vpm is real - time digital simulation system software of launch vehicle and missile

    5 、 vpm是運載火箭和導彈的實時數字模擬軟體系統。
  7. Other experts, and the iraqis themselves, argue that they are really to produce the rocket bodies for a conventional weapon, a multiple rocket launcher

    另一些專家認為和伊拉克辯解稱，他們是用於製造常規武器的火箭彈彈體。
  8. Crew - served weapons are heavy machineguns, mortars, grenade machineguns, anti - tank missile systems, and other weapons which require more than one person to operate due to their bulk and weight

    重武器包括重機槍，迫擊炮，榴彈發射器，方坦克火箭系統，以及其他應為其體積或重量而需要多人操作的武器。
  9. 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。
  10. Without any foreign assistance, china has independently developed intermediate and short - range missiles, long - range rockets, submarine - launched solid - propellant rockets, recoverable satellites, the technology to launch multiple satellites atop a single rocket, and geostationary communication satellites

    中國的中近程導彈、遠程火箭、潛艇水下發射固體燃料火箭、返回式衛星、一箭多星、地球靜止軌道通信衛星都是在沒有任何外國幫助下獨自完成的。
  11. During its storage, transportation, maintenance and service, the solid rocket motor ( srm ) may encounter many incidents such as being dropped onto the ground while being hoisted up, crashing when vehicle turns over during transportation, being struck heavily in takeoff or landing accident while being carried by airplane, impacting with launch platform or buildings when there is abnormality during launch of multiple - stage rocket. impact of great intensity takes place in such accidents, which will lead to srm ignition or explosion

    固體火箭發動機在貯存、運輸、維護及使用過程中可能遇到各種意外機械撞擊激勵，例如:吊裝過程中跌落，運輸過程中因交通事故發生翻覆碰撞，機載固體導彈掛飛時因載機發生起降事故導致高速沖撞，多級火箭發射初期因發射異常與發射架或地面建築物發生碰撞等，固體火箭發動機將受到劇烈機械撞擊載荷作用，導致其著火燃燒甚至爆炸。
  12. The improvement to internal ballistic calculation precision of solid rocket motor ( srm ) is important to capture target of missile. and to accomplish it ' s task. calculation of burning surface of propellant grain is essential to interinal ballistic performance calculation

    提高固體火箭發動機內彈道的計算精度對導彈準確捕獲目標、完成任務有著重要的作用，而發動機工作時瞬態燃面計算是內彈道性能計算的基礎。
  13. The solid - propullant ducted rocket, which combines the advantages of solid propullant rocket and ramjet propulsion, is a new kind of combined propulsion system. it offers considerable advantages for missile propulsion, such as high specific impulse, high speed, light weight, long range, high maneuver and simple structure. as the major direction of the propulsion system for supersonic missile, the ducted rocket has good prospects

    它將固體火箭技術和沖壓技術有機結合在一起，具有比沖高、速度快、重量輕、射程遠、機動性能好和結構簡單等諸多優點，最大限度地滿足了新一代導彈對其動力裝置提出的要求，是超聲速導彈動力裝置的一個主要發展方向，有著廣闊的研究前景。
  14. 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。
  15. Liquid oxygen is used as an oxidant for liquid fuels in the propellant systems of missiles and rockets

    在導彈和火箭的推進系統中氧用作液體燃料的氧化劑。
  16. In this paper, the application of advanced composite in space shuttle, aviation engine, radar antenna mask, aviation hot insulation material, space satellite solid rocket engine and strategic missile are discussed

    摘要討論了先進復合材料在航天飛機、航空發動機、機用雷達天線罩、航天隔熱材料、航天衛星和宇航器、固體火箭發動機殼體、戰略導彈等方面的應用情況。
  17. For the research requirement of the high g - load mobile missile srm, the work process of solid rocket motor under lateral overload is investigated by the use of theoretical analysis and numerical simulation methods involving the calculation of internal ballistics, the simulation of flow field and the analysis of structural integrity

    本文以高速機動防空導彈固體發動機研製需求為背景，採用理論分析和數值模擬方法，從內彈道計算、內流場模擬、結構完整性分析等幾個方面對橫向過載作用下固體火箭發動機工作過程進行了研究。
  18. In view of the fact that there are three types of a hybrid base - bleed - rocket extended - range projectile and they are different from each other in the general structural layout, their structural characteristics and the work performance of the two propellant units is analyzed in this paper

    本文針對三種總體結構布局形式不同的底排?火箭復合增程彈，分析了它們的結構特點和底排裝置、火箭裝置的工作特性，詳細討論了復合增程彈底排?火箭工作時序選擇對彈道特性的影響以及實現理論上最佳彈道的匹配條件。
  19. Rocketcad system has been proved to be an excellent prior and posterior cad system of rocket designing in practice. it can automate the rocket design process, provide the academic foundation to improve the structural design of rocket accessory, and also it can be used as a cai software for students of rocket weapon

    實際應用證明，使用rocketcad系統可以較好解決火箭彈前設計和后設計問題，實現了設計過程的自動化，為優化結構設計提供了理論依據，同時也可以做為火箭武器專業的計算機輔助教學（ cai ）軟體使用。
  20. This thesis has done the following research : 1. the mathematical model of rolling missile was established

    具體在本文中，完成了如下工作： 1建立了包含已分解的控制力的火箭彈數學模型。
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