推力分量 的英文怎麼說

中文拼音 [tuīlìfēnliáng]
推力分量 英文
thrust component
  • 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...
  • 分 : 分Ⅰ名詞1. （成分） component 2. （職責和權利的限度） what is within one's duty or rights Ⅱ同 「份」Ⅲ動詞[書面語] （料想） judge
  • 量 : 量動1. （度量） measure 2. （估量） estimate; size up
  • 推力 : visatergo; soot; propulsive force; thrust; momentum thrust
  1. The complex nonlinear pursuit - evasion model of two spacecraft in near - earth coplanar orbit is simplified to linear model, the circular region the radius of which is equal to capture radius is defined as target set, capture is achieved when the evader come into the target set and the game is over ; the boundary of useable part ( bup ) is determined, and the analytical form solution of the linear equations is obtained by backward integration of the state variables from the bup, the linear barrier of the pursuit - evasion model and the optimum thrust of the both sides are thus obtained

    本文將近地共面軌道內運動的兩飛行器非線性追逃模型簡化為線性模型，以捕獲半徑的圓域定為目標集，確定目標集邊界上的可用部分，並以此為各狀態變量的起點，對時間進行倒向積分，求得線性方程組的解析解，從而確定了該追逃模型的線性界柵，以及界柵上對策雙方的最優推力，即求得了滿足最優策略時相對運動的軌跡和推力。
  2. 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。
  3. The study in the paper starts with beam distortions, and it treats the plastic deformation area as pure bending sect, rest of the beam as rigid bodies. according to different shapes of the external tendons, it divides into three structural forms familiar in projects, that is the beams with no deviator, with a deviator and with two deviators, and studies the relation between the deformation of the external prestressing tendons and that of the beams, and derives the formulas of the ultimate stress increment of external tendons. in the formulas, the ultimate angle corresponding to half of the plastic deformation area is considered as a variable parameter

    本文首先從梁極限狀態下的變形入手，將塑性鉸區看作純彎段，將塑性鉸以外的區域看作剛體，按照體外預應力筋的形狀不同，分工程中最常見的三種體外結構形式，即無轉向塊的直線型體外筋混凝土梁、具有一個轉向塊的單折線型梁和具有兩個轉向塊的雙折線型梁，研究體外預應力筋變形和梁體的變形間的關系，推導出以極限狀態下塑性鉸區之半對應的轉角為參數的計算體外預應力混凝土簡支梁以及連續梁的體外筋應力增量計算公式，並進一步求得梁的極限承載力。
  4. On the part of the design of nine - component thrust vector stand, an automatic hydraulic pressure original position calibration system, a scheme of original position calibration, and the great rigidity universal flexible combinatorial underprop are designed. by using the scheme of “ universal flexible combinatorial underprop plus software digital filter ”, the inherent frequency of test stand is improved, and the problem of test stand libration is solved. then, the resolving method of the disturbance between underprops of the moveable frame is proposed, and the disturbance revise equation is deduced

    在推力矢量試車臺設計方面，設計了自動液壓原位校準系統、原位校準方案以及大剛度萬向柔性組合支撐;採用「萬向柔性組合支撐+軟體數字濾波」的方案，提高了試車臺動架的固有頻率，解決了試車臺動架的振動問題;提出了動架約束互擾問題的解決方法，推導了互擾修正方程;研究了九分力推力矢量測量誤差分析方法，並計算了推力矢量測量精度。
  5. To adapt the circumstance in which the crankshaft torsional vibration generally exists, the new method ( tvrs method ) in which the cylinder power is inversely solved according to the torsional vibration curve is put forward and deduced in this paper, that is, the average effective pressure of each cylinder i. e. power condition of each cylinder is estimated based on a crankshaft torsional vibration curve according to the elasticity model of the actual shafting of engine and by use of the i. c. engine dynamics, the numerical calculations and the signal theory etc. although the computing workload is more, the method makes full use of the now available data of the torsional vibration of the i. c. engine, and can be used to all kinds of i. c. engine on any kind of operating condition, so it has higher application value

    為適應內燃機普遍存在曲軸扭振的情況，本文提出並推導了利用扭振信號反算的新方法（ tvrs法） ，即採用軸系中某一測點的扭轉振動信號，按軸系實際的彈性模型，依據內燃機動力學、數值計算方法和信號理論等，反算各缸的平均有效壓力，定量判斷各缸的作功狀況。此法充分利用內燃機現有的扭振資料，雖然計算工作量較大，但普遍適用於各種類型各種工況的內燃機，有較高的實用價值。
  6. Abstract : in this study distributions of block compression force on the driving and driven pulleys were measured using a ting load - cell inserted between two blocks and a telementer system, under several constant speed ratios

    文摘:本研究採用超小型測力儀插入兩推塊和遙測裝置之間在幾種固定速比下測量主動和從動帶輪上推塊壓縮力分佈。
  7. 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。
  8. In this thesis, the mechanism analysis and numerical simulation on the coupling flow field of microwave plasma within resonant cavity of mpt was discussed and the subsystem of small thrust measurement as well as the vacuum experimental study of mpt were completed

    在航天飛行器上有廣闊的應用前景。本論文對mpt微波等離子體耦合流場進行了機理分析和數值模擬，建立了mpt的小推力測量系統，協同進行了mpt真空環境實驗研究。
  9. The application background of thrust vectoring technology on aircraft and its advantages are analyzed. the main characteristics of some type of vectoring nozzles are discussed, the expression of thrust vectoring force and moment are set up. then, the nonlinear motion equations of aircraft with three axes of thrust vectoring are deduced

    本文主要針對推力矢量飛機非線性飛行控制的理論和應用問題進行了一定的探索和研究，進行的主要工作有： 1 、研究了推力矢量在飛機上的應用背景和收益，分析了現有推力矢量噴管的主要形式和特點，給出了推力矢量力、力矩的數學模型，並在此基礎上推導了帶三軸推力矢量飛機的非線性運動方程，為控制律的設計奠定基礎。
  10. In order to know the relationship between gas - content and pipeline ' s pressure drop, the thesis deduces the pressure drop calculating equations based on uniform flow pattern and separating flow pattern. the equations show that pressure drop is made up of three parts, that is, friction resistance effect, gas acceleration effect and the gravity effect. and the research has shown that the gas has little effect on pressure drop. in the horizontal pipeline, the resistance effect must be overmatched the acceleration effect

    為探討加入的氣體對管道壓力的影響，本文基於分相流和均相流兩種模型分別推導了三相流管道的壓降公式，表明無論是分相流模型，還是均勻流模型，管道內流體總的壓降是由三項組成的，即摩擦項、加速項和重力項，並得出了加氣對管壓變化不大的結論，所以認為在水平管道中，要獲得有效的減阻，則要使摩擦阻力分量的減小效應大於漿體加氣的加速效應。
  11. The study shows that the nine - component model and nine - component thrust vector stand can improve the precision of thrust vector measurement greatly

    研究表明，九分力模型和九分力推力矢量試車臺提高了推力矢量測量的精度，適合用於測量大型固體火箭發動機的推力矢量。
  12. On the part of thrust vector measurement theory, some problems that exist in the six - component model and the six - component thrust vector stand are analyzed, and the solving methods of six - component model are studied. the thrust vector measurement nine - component model is established, and the design idea of curve rail can benefit the nine - component model solving is proposed

    在推力矢量測量理論方面，分析了六分力模型及六分力試車臺存在的問題，研究了六分力模型的方程求解方法;建立了推力矢量測量九分力模型，提出了弧形軌的設計思想，解決了九分力模型方程求解問題。
  13. 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。
  14. The two - dimensional axisymmetric subsonic - transonic - supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method. the profiles of density, velocity, temperature, pressure and mach number can be obtained by the computation. the computation grid and some computed results are given here. the test equipment such as power supply system, ignition system, propellant supply system, arcjet thruster, thrust measuring device and vacuum system are introduced briefly. some working phenomena of the arcjet are observed and discussed. three different kinds of instability appeared in the process of the experiments. except some important parameters are measured, it is found that the operating stability of argon is better than that of nitrogen

    對一實驗電弧加熱式發動機二維軸對稱亞跨超音速流動進行了數值模擬，所採用的方法是矢通量分裂演算法.通過計算可以得出密度、速度、溫度、壓力和馬赫數的分佈.給出了計算所使用的網格和一些計算結果.簡要介紹了實驗所使用的設備，如電源系統、點火系統、推進劑供給系統、電弧加熱式發動機、推力測量裝置和真空系統.對所觀察到的一些工作現象進行了討論.有三種不同的不穩定性出現于實驗過程.除了所測量的一些重要參數，通過實驗發現氬比氮工作更穩定
  15. Two key problems were solved : 1 ) to cancel the disturb of microwave cable rigidity on small thrust measurement of mpt adopting soft wave - guide without jacket as elastic linker, 2 ) to successfully realized separation of self - weight and thrust of mpt adopting small thrust measurement device of balance type, electromagnetic feedback and automatically compensation. so, the measurement precision and stability were greatly raised in actually application of small thrust measurement device

    採用無護套的金屬軟波導管作為微波傳輸系統的彈性連件、天平式電磁反饋自動補償的小推力測量裝置，成功地實現了mpt自重與其產生的推力分離、解決了微波傳輸電纜對mpt小推力測量干擾的關鍵問題，在實現mpt小推力測量的實際應用中提高了測量精度和穩定性。
  16. Adding injection on bottom or fore wall of cavity, based on chief injections on upstream, provides worse lean flameholding performance. experiments on the drag of cavity flame holder were conducted by force measurement system

    利用直連式試驗臺推力測量系統，對凹腔火焰穩定器的阻力特性進行了試驗研究，主要對不同噴注方式、不同當量比時的熱試阻力特性進行了對比和分析。
  17. 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。
  18. Using the optimal control theory an optimal control law of agile turn is proposed enabling to eliminate velocity component in vertical director of initial sight under thrust vector control

    應用最優控制理論，提出一種最佳快速轉彎控制律，能在推力矢量控制下消除終端時刻垂直於初始視線方向上的速度分量。
  19. And establishing the model of the thrust vectoring nozzle is the base for researching thrust vectoring technique and engine performance with vectoring nozzle, especially the integration of flight and propulsion system control ( ifpsc ). so thrust vector modeling is very important and meaningful

    矢量噴管是實現推力矢量的關鍵部件，建立其數學模型是推力矢量技術尤其是開展帶矢量噴管的發動機研究以及飛推一體化綜合控制研究的基礎，具有十分重要的意義。
  20. The mechanism of two possible ways of thrust vectoring control : force and moment control are analyzed. the effects of thrust vectoring on aircraft supersonic performance, take - off and landing performance, low speed and high angle of attack performance are studied. the air combat effectiveness of thrust vectoring control and post - stall maneuvers are also analyzed

    5 、分析了推力矢量的兩種應用方式：力控制和力矩控制的機理，研究了推力矢量對飛機超音速性能、起降性能、低速大迎角性能的影響，討論了推力矢量與過失速機動對空戰效能的影響。
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