設計飛行速度 的英文怎麼說

中文拼音 [shèjìfēihángsùdù]
設計飛行速度 英文
design flying speed
  • 設 : Ⅰ動詞1 （設立; 布置） set up; establish; found 2 （籌劃） work out : 設計陷害 plot a frame up; fr...
  • 計 : Ⅰ動詞1 （計算） count; compute; calculate; number 2 （設想; 打算） plan; plot Ⅱ名詞1 （測量或計算...
  • 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...
  • 速 : Ⅰ形容詞（迅速; 快） fast; rapid; quick; speedy Ⅱ名詞1 （速度） speed; velocity 2 （姓氏） a surna...
  • 度 : 度動詞[書面語] （推測; 估計） surmise; estimate
  • 設計 : devise; project; plan; design; excogitation; layout; layout work; styling
  • 飛行 : flight; flying; aviate; voyage; volitate; hop
  • 速度 : 1. [物理學] velocity; speed; blast; bat 2. [音樂] tempo3. （快慢的程度） speed; rate; pace; tempo
  1. The method of wing shape optimization of space shutlle has been developed with penalty function approach in which the objective function is the mass of the wing and the constraints are the hypersonic re - entry flight cross range, lift / drag ratio, and subsonic flight lift / drag ratio, the margin of the longitudial static stability and the magnitude of the horizontal landing speed etc

    摘要介紹了在滿足高超音速再入橫向機動航程，高超音速再入飛行時的升阻比，亞音速進場飛行時的升阻比，縱向靜穩定性裕度和水平著陸速度等飛行性能設計要求下，用罰函數法尋求使航天飛機機翼質量為最小的外形優化方法並給出了算例。
  2. Although aircraft designers and engineers continued to employ wing - warping techniques for years afterward ( especially on early monoplanes such as the bleriot xi ), ever faster flight speeds eventually led them to beef up wing structures to resist the resulting stresses

    雖然其後許多年間，飛機設計師和工程師仍繼續採用翹曲機翼設計（尤其是布雷修xi型等早期單翼機） ，但由於飛行速度不斷提升，終于迫使他們加強機翼結構，以承擔所增加的應力。
  3. In this paper, firstly the macro parameter of the series connection app was comprehensively analyzed, among which the trajectory location of the bullet emission and the terminal velocity of the bullet were mainly analyzed, and the feasibility of the series connection app to cope with explosive reactive armor was demonstrated. and then the macro design about the head of the series connection app was made, among which a particular analyse about the bullet " s launching process was made, from which we concluded the relation between the thickness of the airproof loop and the velocity of the bullet detached from the carrier and the relation between the length of the bullet and the velocity of the bullet detached from the carrier and the relation between the length of the bullet and the burning rate of the powder and the relation between the length of the bullet and the maximum pressure of the emission hole and the relation between the length of the bullet and the emitting time of the bullet, and the reasonable str ucture of the head of the carrier and bullet were designed, then the intensity of the head of the carrier was checked out using of the software of ansys

    本文首先對子母式穿甲彈總體參量作了全面的計算分析，其中主要分析了子彈射出的彈道位置和必要的子彈著靶速度，論證了子母式穿甲彈對付爆炸式反應裝甲的可行性，然後對子母式穿甲彈彈頭部進行了總體設計，其中主要對子彈的發射過程進行了詳細的分析，得出了母彈彈頭部發射孔內閉鎖環厚度與子彈飛離母彈速度的關系、子彈長度與子彈飛離母彈速度的關系、子彈長度與火藥燃燒率的關系、子彈長度與母彈彈頭部發射孔內最大壓力的關系以及子彈的長度與子彈發射所需時間的關系，設計出了合理的母彈彈頭部結構和子彈的結構，並利用ansys有限元分析軟體對母彈彈頭部的強度進行了校核。
  4. One ornithologist had devised a formula to compute the ratio of domestic to pure - strain wild turkey in an individual bird by comparing the angle of flight at takeoff and the rate of acceleration

    有個鳥類學家設計了一種計算公式，對家養火雞和純種野火雞進行起飛角度和加速度的比較。
  5. This paper presents a wider research field - risk analysis. through the study of the effects that threat factors and error factors impact on the flight risk and adjusting performance rules, the horizontal safe corridor, threat avoidance, vertical altitude real - time modification and the fastest trajectory programming are progressed

    總結前人在該方面的研究成果，提出一個更加廣義的研究角度? ?風險分析。通過對威脅因素、誤差因素對飛行風險的作用，調整性能準則而進行了水平安全走廊設計、威脅迴避、垂直離地高度實時修正以及最快速航跡規劃。
  6. The control laws of longitudinal and lateral - directional autopilot modes are designed based on root locus theory. the control laws of altitude holding mode, heading holding mode, auto - throttle control and air speed holding mode are designed as well

    研究了無人機的飛行控制技術，利用根軌跡法設計了無人機的縱向與側向姿態保持控制律，設計了高度保持、航向保持、自動油門及速度保持控制律。
  7. The main research work of the thesis is summarized as follows : 1. the improved fuzzy logic control method the phenomenon of steady - state errors and flutter exists in the traditional fuzzy controller. an improved fuzzy controller without quantilizing is presented

    地形跟隨飛行控制律設計針對某型飛機應用控制航跡角法和控製法向加速度法對不同的反饋信號分別設計了pi控制器和模糊控制器，並做了模擬比較與魯棒性驗證。
  8. 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。
  9. The design of the rocket nozzle also has much to do with the behavior of the exhaust and the resulting velocity of the vehicle itself.

    火箭噴管的設計與排氣的性能及飛行器本身的有效速度也有很大關系。
  10. To solve the problems caused by the varieties of the missile dynamics with the difference of flight height, velocity and attitude angle in modeling the missile, in this thesis, the theory of variable structure model reference adaptive control is used to design a pitch channel autopilot based on a longitudinal missile model, the status equation using the measurable parameters of load and angular rate is established, and the methodology to choosing the reference model is discussed also, and the performance of the controller is analyzed by means of simulation

    為了解決攔截彈氣動參數隨飛行高度、速度、姿態的不同，變化范圍大，控制系統難以準確建模的困難，基於縱向平面攔截彈模型，採用模型參考變結構控制理論設計了俯仰通道姿控復合控制系統，以可測量變量過載和角速度作為狀態量建立了系統的狀態方程，討論了參考模型的選擇方法，並對系統的性能作了模擬分析。
  11. Finally, one trajectory meeting the height and the speed of towing flight is designed

    最終設計出一條滿足牽引飛行高度和速度的軌道。
  12. With the high development of the quantum circuits, the testability of the circuits will become a very serious problem. the method of testability design for rt circuits is proposed in the end of this paper, which has high testability and low hardware cost. only adding one extra mos transistor and two control ports, it can detect all open and short faults in rt circuits

    隨著量子電路的飛速發展，由於其本身所特有的高集成度特點，電路的測試必然會成為越來越嚴重的問題，因此論文在最後就電路中常見的開路、短路故障提出了rt電路的可測試性設計方法，並針對具體的mobile電路進行了可測試性設計， pspice模擬結果表明達到了可測試的目的。
  13. The electro - hydraulic proportional control law is given. the laws of tracking control of displacement and speed of aircraft as well as tracking control of angle and angular speed of belt wheel are designed by means of state feedback linearization and quadratic performance index linear optimal control method. the robustness of the designed systems is analyzed, and arresting processes are simulated

    給出了電液比例控制規律；利用狀態反饋線性化及二次型性能指標線性最優控制方法分別設計了系統跟蹤控制飛機位移與速度以及跟蹤控制帶輪轉角與角速度的非線性控制規律；對所設計的攔阻系統進行了魯棒性分析及攔阻過程模擬，模擬結果表明，通過選取適當比例系數或控制權系數，兩種控制系統的控制效果及魯棒特性均優于新型飛機攔阻系統。
  14. In this paper, a new way of real - time damage detection method was proposed according to the high speed working situation of the composite flywheels for energy storage, and a suit of equipment was developed to test the composite samples with piezoelectric disc built - in, the response waves before and after the damage occurred were recorded to the computer. on the base of traditional spectrum analysis of signal recorded, the wavelet analysis was introduced and the program in matlab language was made. with the wavelet packet decomposition of the signal, the relations between the change of response signals and damage characters were gotten, a database for damage recognition was created

    本文結合儲能復合材料飛輪高速旋轉的工作特點，提出了一種在線檢測飛輪轉子損傷的方法，自主設計一套實驗裝置對模擬各種損傷的的試樣進行了測試，試樣損傷前後的響應信號被採集后存入計算機中；在對採集信號進行傳統的頻譜分析的基礎上，引入了先進的小波分析理論，利用matlab語言編寫程序，對信號進行小波分解，得到了信號變化和損傷特徵之間的關系，建立了一個識別飛輪損傷的數據庫；小波包分解得到信號對比圖和特徵向量，可以有效判定材料內部有無損傷和損傷的程度，結合頻譜分析等，可一定程度上判定損傷的類型，為儲能飛輪的安全運轉和智能化運作提供了決策依據。
  15. The application of control law developed above to the problem of reconflgurable flight control is described. based on the simulation results, the effects of learning rate ( or adaptation gain ) and slide model terms on the control system are discussed. comparing with adaptive control, the control law is helpful to improve system ' s transition response and reduce undesirable oscillations, provides nearly perfect tracking in the case of undetected failure

    4 、探討了所設計的控制律在重構飛行控制中的應用，討論了自適應調整率對自適應控制性能的影響、滑模魯棒控制補償項對控制性能的影響；對幾種舵面損傷的模擬結果表明，本文的控制律較自適應控制具有響應改善速度快、響應振蕩小的優點，具有較好的重構功能。
  16. Firstly, i present a new structure of torque measurement ? rating torque sensor. secondly, introduce the fundamental principle of the dynamic torque. and then bring forward new methods of measuring flywheel moment and acceleration, which has been proved not only by theory, but also by experiment

    本文首先提出了轉矩測量的一種新結構? ?光柵靜態（平均）轉矩測量傳感器；然後闡述了動態轉矩測量的基本原理；接著提出了新的飛輪矩與加速度測量方法，並對其進行了理論推導及實驗證明；最後對提出的通用轉矩測量系統進行了硬體、軟體上的設計。
  17. Because of the complicated flight state of the aircrafts, there rests a critical demand for high speed operation of flight data in the synthetical graphical display system : we must finish all computations of the flight data and send them into the display panel in a very short time which is critically specified by the display instruments

    在機載綜合顯示系統中，由於飛行狀態復雜，對飛行數據的處理和顯示都提出了比較嚴格的時間要求：需要在顯示器的一幀時間內完全計算數據並完成顯示任務。因而在工程中，硬體設計的運算速度成為至關重要的因素之一。
  18. The table is a important device in the hardware - in - the - loop simulation system, and it simulates the flight of unmanned aerial vehicle so as to achieve flying parameters from those sensors. the signals of sensors in the table are transmitted by many cables previously, thus it confines the movement range of the three - axis frameworks. as the perfomance of uav become complicated, the signals cables are replaced by wire rings in some tables, but it brings many difficulties and unreliable factors for the simulation table ’ s design also. bluetooth, as a new short - range wireless communication technology, is a reasonable and feasible scheme in this condition

    三軸模擬轉臺是無人機地面半實物模擬系統中的重要設備，用來模擬飛機在空中的姿態和角運動，以驅動傳感器產生飛行姿態、角速度及角加速度信號。早期轉臺上傳感器信號通過穿在框架中的電纜進行傳輸，這就限制了框架的運動范圍。隨著無人機任務的復雜程度不斷提高，出現了採用導電滑環傳遞信號的模擬轉臺，但這也給轉臺設計帶來了困難，且存在不可靠因素。
  19. The controller for longitudinal short period model of aircraft has been designed and simulated by using those schemes. simulation results are demonstrated to show that the scheme is not only simpleness and easy accomplish, but also enhance the performance of flight and the effectiveness and applicability of the proposed method

    模擬結果表明，用此方法，不但使設計過程簡單且易於實現，而且用該方法設計出控制器可以有效地改進飛機的飛行性能，提高失速迎角，加快起恢復速度，閉環跟蹤效果也令人滿意。
  20. The fast development of computer science and electron technology make the appearance of virtual aircraft instrument system that highly integrates the digital information from airborne devices possible and the cockpit layout could be easily changed while the pilot can get flight information more quickly and control the aircraft more efficiently

    計算機技術以及相應電子技術的高速發展，以及高度集成機載電子設備信息的多功能虛擬儀表系統出現，改變了以往飛機座艙中儀器儀表紛繁復雜的布局，使得飛行員能快速獲得飛行信息，從而更加有效地操縱和管理整個飛行系統。
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