hover-flight 中文意思是什麼

hover-flight 解釋
懸停飛行
  • hover : vi. 1. 翱翔,盤旋 (about; over)。2. 徘回 (about; near)。3. 躊躇,?徨。4. (直升飛機)停懸。vt. 伏窩孵化。n. 翱翔;徘回。
  • flight : n 1 飛行,飛翔;(鷹對獵物的)追趕。2 (候鳥等的)遷徙;飛行的一群。3 (光陰)飛逝。4 (思想等的...
  1. Helicopter is hard to hover precisely for its bad stability. ordinarily, it is improved by flight control system, such like rotorcraft unmanned aerial vehicles which use bell bar or bell - hiller stabilizer bar. bell stabilizer bar, fixed across with teetering main rotor, consists of a bar and masses at two ends

    貝爾穩定桿由一桿與兩質量塊組成,它與貝爾直升機的蹺蹺板旋翼垂直交叉放置,這種旋翼裝置有助於加大角速度阻尼,改善貝爾直升機的穩定性,但同時也降低了操作性。
  2. The model developed here is suitable for the tilt rotor aircraft during hover, transition and cruise. the longitudinal equations of motion provide a foundation for further investigation on tilt - rotor flight dynamics

    文中所建模型具有較高精度,適合於飛行包線內的所有模式,為傾轉旋翼飛機飛行動力學的進一步研究提供了基礎。
  3. 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。
  4. Frequency sweep flight technique is used to collect the flight data of a model helicopter near its hover and low speed working condition, window frequency spectrum is combined to obtain the frequency response of both lateral and longitudinal channels, then weighted fitting method is utilized to obtain the transfer functions of the two channel

    摘要利用掃頻試飛技術獲取了某無人直升機在懸停工作點附近的舵機輸入和直升機動態輸出數據,利用組合窗頻譜分析的方法獲取了直升機橫滾通道與俯仰通道動態的頻率響應特性,利用加權擬合的方法獲取了各自的傳遞函數。
  5. The acoustic noise generated by the rotate point source, uh - 1h rotor in hover and ah - l / ols in forward flight were calculated, and the computed results from several methods were compared with each other and with the experimental data

    採用旋轉點源、 uh - 1h懸停旋翼、 ah - 1 / ols前飛旋翼作為算例,對所採用的各種噪聲預測方法進行了比較。
  6. Combining cfd technology and aeroacoustic theory in time domain, the high - speed impulsive ( hsi ) noise of helicopter rotor in hover and in forward flight was predicted and investigated

    本文結合cfd (計算流體力學)技術與氣動噪聲時域理論,求解直升機旋翼懸停和前飛流場及流場氣動噪聲。
  7. For the validation of the total model, the comparison of trim results in hover / forward flight was made with the popular software of flightlab, and linearization matrixes were compared with helisim, they both show the coordination results

    本文利用所建立的模型,根據ads 33規范要求,逐條計算了( 3 3 )節的內容,並對樣例直升機進行了開環狀態下的部分品質等級的評估工作。
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