angle-of-attack control 中文意思是什麼

angle-of-attack control 解釋
迎角控制
  • angle : n 【英史】盎格魯人〈cf Angles〉。n 1 角,隅,角落;棱,嬗角。2 【數學】角,角位,角的度數。3 【機...
  • of : OF =Old French 古法語。
  • attack : vt 1 攻擊 (opp defend)。2 非難,抨擊。3 著手,動手,投入。4 (疾病)侵襲。5 【化學】腐蝕。n 1 ...
  • control : n 1 支配,管理,管制,統制,控制;監督。2 抑制(力);壓制,節制,拘束;【農業】防治。3 檢查;核...
  1. The shm ( single hole microblowing ) as a new perturbation active control technique has been applied to the slender body with different model noses at zero sideslip and high angle of attack

    摘要在亞臨界流動范圍內,對具有不同頭部形狀的尖拱形細長旋成體在無側滑大迎角下進行單孔位微吹氣擾動控制實驗。
  2. The dash line indicates the possibility of a direct input to the control system through an angle-of-attack indicator.

    虛線表示,通過攻角指示器,有可能直接輸入到控制系統去。
  3. Maintaining a forward ground - sole contact point improves directional control and ball flight by reducing the potential of the club to bounce or skip into the ball - especially from closely mown fairways, for players who play the ball forward in their stance or for players who sweep the ball from the turf with a shallow attack angle

    藉由降低擊球路徑的潛在負面因素,維持穩定的觸地點能改善方向控制與飛行路徑-尤其是在短草球道上想擊出漂亮直球的球友,或是得利用較淺的擊球角度自長草區擊出的情況下。
  4. In the following part, trajectory design and computation are given, including fight scheme and control & navigation laws. through the design and computation, the profile of attack angle, trajectory angle and pitch angle are designed. these works provide theoretical fundamentals for dynamics analysis and practical trajectory design

    第三部分內容是對導彈的彈道進行設計與計算,給出導彈在各段的飛行方案或導引規律。設計出導彈在整個飛行過程中的質點彈道,迎角、彈道傾角和俯仰角等參量在導彈攻擊目標過程中的變化規律,為進一步的質點系彈道和動態分析提供理論基礎。
  5. The load control system has already passed the test ' s validate. it shows that the design of whole system is correct. the system can truly simulate the real air - stream and put it on missile ' s wings to make them work on the same force situation as in the real spread process, so the relationship of explosive stuff and attack angle can be confirmed

    本文所設計的加載控制系統已通過實際系統的驗證,說明整個系統的設計是合理正確的,它能夠真實地模擬類似真實氣流阻力的載荷,並施加於彈翼或尾翼,模擬其在真實工作環境下的受力狀態,可以測算導彈攻角與火工品填藥量的關系。
  6. The angle of attack and the sideslip angle are the two important measured quantities for the aircraft navigation / control aerodynamics analysis and structure analysis. for the different kinds of disturbance influence, now the sensors ca n ' t measure it accurately, in the high angle of attack, the error will add with the angle of attack increase

    迎角和側滑角是飛機飛行導航控制、航電等方面重要的兩個測量量,由於受到各種干擾因素的影響,現代傳感器很難對其精確測量,在超大迎角飛行過程中,其測量誤差隨迎角增加而增加。
  7. Repeat of the 2002 world cup points moment, you have to attack first, picked a shooting angle, the control of good strength, shoot

    重演2002世界盃的點球時刻,先由你來攻擊,選定好射門的角度,在控制好力量,射門!
  8. Introduction : repeat of the 2002 world cup points moment, you have to attack first, picked a shooting angle, the control of good strength, shoot

    重演2002世界盃的點球時刻,先由你來攻擊,選定好射門的角度,在控制好力量,射門!
  9. According to the theory of boundary layer control and aerodynamics of delta wing at medium attack angle, the generation mechanisms of rolling, pitching, yawing moments, which are produced by coupling between the microactuator array and boundary layer near the leading edge, have been discussed

    首先,結合空氣動力學的邊界層控制原理以及三角翼在中等攻角條件下的氣動特徵,詳細討論了微致動器陣列通過與前緣邊界層的耦合產生三角翼翻滾、俯仰和偏航等力矩的機理。
  10. Then s - style high maneuver trajectory with high angles of attack is simulated by given control commands of angle of pitch

    進行了俯仰平面s型軌跡機動飛行模擬,模擬結果說明了大攻角飛行的高機動特性。
  11. 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。
  12. 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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