耦合飛行 的英文怎麼說

中文拼音 [ǒugěfēiháng]
耦合飛行 英文
coupled flight
  • 耦 : Ⅰ動詞[書面語] （兩人並耕） plough side by sideⅡ名詞1 （古農具名） plough2 [書面語] （兩人一組） a...
  • 合 : 合量詞（容量單位） ge, a unit of dry measure for grain （=1 decilitre）
  • 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...
  • 耦合 : [物理學] coupling; interconnection; catena; linkage; linking
  • 飛行 : flight; flying; aviate; voyage; volitate; hop
  1. The flying stability of the unguided projectile with wrap around fins could be influenced by the self - induced rolling characteristics and the cross coupling effects of the waf badly. it is necessary to study further on this special aerodynamic problems

    卷弧翼存在自誘導滾轉特性、較嚴重的交叉耦合效應等特殊氣動問題，對于無控的卷弧尾翼彈而言，這很大程度上影響飛行穩定性。
  2. We establishes iffcs model, computes fire control, and designs " fly / fire " coupler 。 finally, based on the model that mentioned above, a simulation is carried out

    建立綜合飛行/火力控制系統模型，並進行火控解算、並設計飛行/火力耦合器。最後在對前面模型分析的基礎上進行模擬驗證。
  3. But fcs and " fly / fire " coupler is the key technique of iffc 。 in this paper, a fire control system of armed helicopters for ground attack is proposed based on the attack system of fix - wing. we stress on our research of fcs, iffc and " fly / fire " coupler for armed helicopters

    本文在參考固定翼飛機攻擊系統的基礎上，建立武裝直升機對地攻擊的火控系統，重點對直升機飛行控制系統、綜合飛行/火力控制系統、以及飛行/火力耦合器等進行了研究。
  4. Pitch-yaw coupling can be neglected only for nearly axisymmetric vehicles.

    只有對接近於軸對稱的飛行器，俯仰與偏航的耦合才能略去。
  5. 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。
  6. Then in allusion to biased momentum wheel system, based on classical control system a pid controller was design about pitching channel. according to specialty of roll - yawing channel, this paper discuss long - time cycle movement and short - time cycle movement. when design the control method of long - time cycle movement, whiff thruster is used to assistant the control system. when design the control method of short - time cycle movemen, in order to sovle the problem of coundn ’ t abtain the angular velocity signal, nonminimum phase controller advanced by terasaki is used

    然後針對偏置動量飛輪系統，基於經典控制理論設計俯仰通道的pid控制律，根據滾動?偏航通道耦合的特點，分別討論了由軌道角頻率和章動頻率引起的長周期運動和短周期運動。其中長周期運動控制律設計時，結合了噴氣推力控制來輔助偏置動量控制;短周期運動控制中，為了解決不能獲得角速度信號的問題，採用terasaki提出的非最小相位控制器進行控制。
  7. With the development of material technology, information technology, automation control technology, aeronautics and astronautics technology, the modern flight vehicles are required of high velocity, light structure, great flexibility and super maneuverability, which lead to the serious aeroelastic effects such as aeroservoelasticity, the coupling among the aerodynamics, structure, and control system

    隨著材料技術、信息技術、控制技術以及航空航天技術本身的飛速發展，飛行器開始向高速度、輕結構、大柔性、超機動的方向發展，氣動彈性效應更加嚴重，從而引發了氣動、結構、控制系統相互耦合的氣動伺服彈性力學問題。
  8. Then the steady and unsteady subsonic, transonic and supersonic viscous flows around airfoil and some aircraft are numerically simulated. the 3 - dimensional unsteady navier - stokes equations are solved using the implicit lu - nnd algorithm, with baldwin - lomax turbulent model. on the basis of simulating unsteady viscous flow, coupling the structure dynamics equations, the problems of static aeroelasticity and flutter are investigated for wings and elevator

    在模擬非定常粘性繞流的基礎上，與顫振運動方程相耦合，分別對機翼和全機流固耦合現象中顫振問題進行了研究，準確求解跨音速顫振臨界速度，分析機翼和全機的從亞音速到超音速范圍的顫振規律，並研究分析了機翼飛行迎角變化對顫振速度的影響。
  9. It is a crucial question to stabilize missiles under stronger interactions, which has been hardly studied before. in this dissertation many significant result are given from the research of several correlative dynamic and control topics. an exhaustive summarization is made for free flight motion of spinning missiles

    導彈自旋飛行引起的運動耦合、控制耦合及其它效應容易導致彈體失穩，實現較強耦合作用下彈道導彈自旋飛行姿態穩定控制是亟待解決的問題。
  10. Control system design for hypersonic vehicles will be complicated by coupling effects between aerodynamics, propulsion, and structure

    高超聲速飛行器的飛行控制系統由於空氣動力學、推進系統以及結構之間的相互耦合影響而變得非常的復雜。
  11. In chapter two, using the hydrodynamical equations for electrons and maxwell equation and through complicated calculation, we finally obtain a set of equations which describe the non - steady and nonlinear interactions between plasma and field in the wake region of a moving body in space

    第二章是從描述電子的磁流體方程和麥克斯韋方程出發，通過計算，最後得到了一組在考慮非靜態極限下描述空間飛行器遠尾區內等離子體與場之間的非穩態非線性相互作用耦合方程。
  12. In the surveillance system of cns / atm, secondary surveillance radar ( ssr ) is used in busy air space, and automatic dependent surveillance ( ads ) is used in other air spaces. ssr and ads can also be integrated. and ads can improve the efficiency of air space in the areas of ocean and desert where there is less flight route and large separation between aircrafts

    在新航行系統的監視系統中，主要發展雷達監視和自動相關監視，在繁忙空域採用二次雷達監視，其它空域採用自動相關監視，並且可以實現二者的數據耦合；通過自動相關監視，可以克服海洋、荒漠空域航線少，飛機間隔大的缺點，提高空域利用率。
  13. The research of this dissertation is focused on how to simulate numerically the steady and unsteady subsonic, transonic and supersonic viscous flows around wing and aircraft by computational fluid dynamics method. on this basis, several kinds of aeroelastic problems of aircraft are investigated

    本文的主要工作是利用計算流體力學（ cfd ）方法，數值模擬機翼和全機的定常及非定常粘性繞流，並在此基礎上耦合結構動力學方程研究了飛行器的多種氣動彈性問題。
  14. This paper, in advantage of modern control theories, designed the pitch control system and the altitude holding system of the x armed helicopter, and present digital simulation, coupling analysis, sensitivity analysis, system performance analysis under different input and initial condition

    本文應用現代控制理論設計了某型武裝直升機的俯仰角控制系統和高度保持系統，並進行了數字模擬、耦合分析、飛行狀態變化對控制系統性能的影響分析，及在不同輸入初始條件下的系統性能分析。
  15. The ml converter is a multi - input and multi - output, strongly coupled nonlinearly system, its control elements ( duty cycles ) and the controlled elements ( output voltage and flying capacitor voltages ) of the ml converter are strongly coupled, so the system should be decoupled to multiple single - input and single - output sub - systems such that each output can be controlled independently

    多電平變換器的控制量（各開關管占空比）和被控量（輸出電壓及各飛跨電容電壓）之間存在耦合關系，它是一個多輸入多輸出、強耦合的非線性系統，因此需要將其解耦成多個單輸入單輸出系統，以對被控量進行獨立的閉環控制。
  16. Using h and synthesis techniques, these features can be modeled as uncertainties and incorporated into the design procedure of a flight control system

    應用h和綜合方法后，這種耦合特徵就可以作為模型的不確定性來處理，進而能形成一個整體的飛行控制系統設計過程。
  17. The influence of optical source chirp on femtosecond soliton interaction is studied numerically, and the unequal amplitude method can reduce the interaction. in addition high - order coupled equations governing the evolution of two orthogonal polarization components of the same wave are derived by using multi - dimension derivation expansion method of singular perturbation theory and the dispersion relation. furthermore, a class of optical solitary wave solutions, such as the bright - bright, dark - dark, bright - dark, and combined solitary waves are found under certain parametric conditions

    數值研究了源啁啾飛秒孤子間相互作用，提出了抑制該作用的可能方案；用奇異攝動多重尺度導數展開法和色散關系推導了耦合高階非線性薛定諤方程（ chnlse ） ，並用行波變換法得到了一系列孤波解析解，分析了它們在光纖中傳輸的必要條件，也討論了它們的穩定性，為實現飛秒光脈沖在光纖中的無畸變傳輸作理論上的探索。
  18. As the wing - pivot frequency decreases, it couples with the vehicle short - period mode resulting in dynamic instability. a similar instability sometimes occurs when the pivot mode couples with the fuselage - bending mode

    隨其頻率降低，它與飛行器短周期模態耦合時會導致飛行器動不穩定，而與機身彎曲模態耦合時同樣會導致模型動不穩定性。
  19. 6. utilizing the new robust decoupling control method which is put forward above, the design problem of decoupling controller for large angle of attack reentry missile ' s attitude control system is mainly investigated

    6 、針對大攻角再入飛行導彈通道間存在的氣動耦合現象，以及實際飛行中存在的個確定因素，分析了其進行解耦控制的必要性；探討了本文提出的基於互補靈敏度成形和h 。
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