飛行推力 的英文怎麼說

中文拼音 [fēihángtuīlì]
飛行推力 英文
flight thrust
  • 飛 : Ⅰ動詞1 （鳥、蟲等在空中活動） fly; flit 2 （利用動力機械在空中行動） fly 3 （在空中飄浮遊動） fly...
  • 行 : 行Ⅰ名詞1 （行列） line; row 2 （排行） seniority among brothers and sisters:你行幾? 我行三。where...
  • 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...
  • 飛行 : flight; flying; aviate; voyage; volitate; hop
  • 推力 : visatergo; soot; propulsive force; thrust; momentum thrust
  1. This includes both the fundamental bending characteristics of the airframes and the propellant dynamics.

    這包括飛行器結構的基本彎曲特性和推進劑動力學。
  2. 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。
  3. Realising the training potential of the reserve as part of the ramsar site so as to promote wetland conservation and wise use in the east asian - australasian flyway, in particular china

    發展保護區作為拉姆薩爾濕地的培訓潛力，以推廣保育和善用東亞澳大拉西亞飛行航道上，尤其是位於中國境內的濕地
  4. A mathematical model reflecting the tilt rotor unsteady and nonlinear aerodynamic characteristics in the longitudinal channel is presented in the paper. in the full flight envelope, the rotor thrust continues tilting and the aerodynamic forces of each component change as a function of airspeed and nacelle angle

    在整個飛行包線內，旋翼的推力矢量方向不斷變化，飛機各部件的氣動力隨發動機短艙傾角和空速的變化而變化，因而飛機的飛行動力學有很強的非定常、非線性特性。
  5. The paper has founded the model of laser transmission in launch process and the movement model of laser - powered vehicle, and has analyzed the influence on performance of launch system, which was raised by some factors, for instance, the performance of thruster, the attenuation in transmission, the height of mode - transform, the laser power, the air drag force, the launch height, and so on

    本文研究了激光推進微小衛星發射系統的概念和性能。建立了發射過程激光傳輸和激光推進運載器運動模型，分析了推進系統性能、大氣傳輸衰減、模式轉換高度、激光器功率、大氣飛行阻力、發射點高度等因素對發射系統性能的影響。
  6. The disclosure project, a crozet, va. based research organization that has been gathering government witnesses for several years, says its reason for going public is because the u. s. government has long had information on anti - gravity propulsion systems

    設在弗吉尼亞州克羅澤特的研究組織"揭發計劃" - -數年來一直在徵集曾在政府機構工作的不明飛行物目擊者說，它之所以要讓公眾了解不明飛行物的真相，是因為美國政府早已掌握了反重力推進系統的信息。
  7. The modern unmanned helicopter flight control system is generally composed of the flight control computer, the servo driving mechanism, the sensor, and the ground monitor control system etc. in this thesis the research to the helicopter flight characteristics was conducted at first, and its flight dynamic model was preliminary discussed, especially the mathematic model under hung - stop condition was formulated and the algorithm of the controller was designed in detail

    現代無人直升機飛行控制系統一般由飛行控制計算機、伺服驅動機構、傳感器、地面監測控制等分系統組成。本文首先對直升機的飛行特性進行了研究，並且對飛行動力數學模型做了初步探討，尤其對在懸停狀態下的數學模型做了較為詳盡的公式推導和控制器的演算法設計。
  8. The application of thrust vectoring control technology makes the aircraft possess the ability to fly in post - stall domain, therefore the flight envelope is extended

    推力矢量控制技術在戰斗機上的應用，使戰斗機有能力進入過失速飛行領域，使飛機的飛行包線得以擴展。
  9. As to the modelling of integrated flight / propulsion system, this paper mainly investigated and the modelling methods of flight kinetics and propulsion system thermodynamics, building up the real - time models of body kinetics. then we integrated the component - level thermodynamics model of engine, solved the problem of matching of initial points in the integrated simulation of flight / engine and the interactive parts of flight system and propulsion system

    對于綜合飛行/推進系統建模，本文主要研究的是飛行動力學和推進系統熱力學的建模方法，建立了飛機動力學實時模擬模型。並結合前人已建立的發動機部件級熱力學模型，本課題在解決了飛機/發動機綜合模擬中的起始點匹配問題的基礎上，完成飛行系統和推進系統的交互部分，最終建立飛行/發動機綜合實時模擬模型。
  10. In order to determination the thrust, the thrust definition and many control parameters are analyzed discussed, which mass flow rate and flight altitude are involved. it is difficult to measure the flight thrust of solid rocket ramjet directly

    通過討論高空飛行推力與地面可測試參數的關系，得到了固體火箭沖壓發動機高空飛行狀態下推力折算方法，並開發相應的計算程序。
  11. 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。
  12. The aerospace indu * * * y is the complex of manufacturing concerns engaged in the production of flight vehicles, including unpowered gliders and sailplanes, lighter than air - craft, ground - effect machines, heavier than air craft of both fixed - wing and rotary - wing varieties, military missiles, space launch vehicles, and manned or unmanned spacecraft ; propulsion systems and other thrusting devices ; on board equipment essential to the design purpose of the flight vehicle ; and ground - based support equipment needed for the operation and maintenance of the flight vehicle

    航天工業是一個綜合製造行業，從事各種飛行器的生產，包括：各種無動力滑翔機，輕于空氣的飛行器，地面效應機械設備，重於空氣的各種固定和旋轉機翼飛行器，軍用導彈，太空發射器，載人或無人飛行器，推進系統或其他助推設備，對飛行器的設計至關重要的艙內設備，控制和維護飛行器的地面設備。
  13. For example, it can be used to drag make - up and solar pressure cancellation of low orbit spacecraft, formation flying and precise positioning of small satellite, repos

    同時， mpt也可用於低軌道（ 300 500km ）航天器的大氣阻力補償，星際航行航天器的主推進，以及星座和小型衛星的編隊飛行和精確定位等，具有廣闊的應用前景。
  14. Abstract : in this paper, the lightcraft vehicle without on - board chemical fuel was analyzed sending manned craft into space on satellite laser - beams powered by solar energy in next age was speculated

    文摘:分析了勿需化學燃料的光動力飛行器，並概述了下個世紀從衛星上用太陽光泵浦的激光束推進星際飛行器的設想。
  15. But the variation of its aerodynamic forces will induce flapping motion and produce the cyclic pitch on the main rotor blades by the bell mixing mechanism. in order to study the effect of bell - hiller stabilizer bar on helicopter stability and control, this paper first analyze the function and the principles, give the flapping equation and a flight dynamic model with bell - hiller stabilizer bar. and then works over the stability and control of uav r - 50 in hover and cruise condition, and analyzed the influence from parameters of the bar to it

    為了深入研究希勒伺服旋翼對直升機穩定性和操縱性的影響，本文首先分析了希勒伺服旋翼的功能和工作原理，推導了伺服旋翼的揮舞運動方程，建立了帶有希勒伺服旋翼直升機的飛行動力學模型，然後以yamahar - 50無人直升機為例，分析該直升機在懸停和前飛時的平衡、穩定性和操縱性，在此基礎上進一步研究希勒伺服旋翼設計參數變化對直升機穩定性和操縱性的影響。
  16. On the basis of designing robust flight control system of the new generation fighter, this dissertation is devoted to the design of the integrated fire / flight control system and the integrated flight / propulsion control system and the integrated fire / flight / propulsion control system

    以研究新一代殲擊機的魯棒飛行控制系統為前提，進一步研究其綜合火力飛行控制系統、綜合飛行推進控制系統以及綜合火力飛行推進控制系統的魯棒控制問題。
  17. With above principles, take domestic and abroad research works as foundation, this paper try to improve the degree of integration and automatization of aircraft based on currently available technology and equipment. the study focus on how to realize auto - flight and auto - attack through the integration of flight control, fire control and propulsion control system, a satisfied result wold be feasible system integration schemas that could improve the mission performance and enhance the aircraft combat automation

    基於以上考慮，本文參考國內外已經完成的工作，致力於在現有技術基礎上提高飛機綜合化、自動化程度，研究通過飛行、推進、火控等系統的綜合實現自動飛行、自動攻擊的原理、演算法，提供可以工程應用的系統綜合方案。
  18. According to flight dynamics, a particle model and an attitude model in launching coordinate system and in quasi missile body coordinate system are established, the influence imposed by constant wind, thrust bias of the motor and connection bias are analyzed

    應用飛行動力學理論，建立了發射坐標系與準彈體系下助推段和分離過程質點運動和姿態動力學模型，分析常風干擾、發動機推力偏差和裝配誤差影響等。
  19. Now people pay more attention to the issue of integrated flight / propulsion control, which is an unnegligible newcome trend

    人們開始把注意力集中到飛行/推進綜合控制課題上來。這個不可忽視的新趨勢正在進展之中。
  20. To accomplish the complicated missions safely and effectively, it must have an advanced integrated fire / flight / propulsion system for the new generation fighter. synchronously, the integrated fire / flight / propulsion system is a complicated, uncertain and multi - variable nonlinear large - scale system. so its control problem is an active subject in the modern control area

    而新一代殲擊機的綜合火力飛行推進系統是其能夠安全、有效地完成復雜戰術戰略使命的基本前提，同時新一代殲擊機的綜合火力飛行推進系統是一個復雜的、具有不確定性的、多變量非線性大系統，因此它的設計與控制問題是現代控制領域所面臨的一大挑戰。
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