pitch flight 中文意思是什麼
pitch flight
解釋
俯仰機動飛行-
Using coordinate transformation method, the formula of imv on every point of image plane was deduced, and it included almost all motorial factors : the flight velocity of aircraft, roll, pitch, yaw, camera ' s scan and so on. thus, it is a precise formula, and it is also applied to frame cameras and push _ room cameras with array ccd
利用坐標系變換的方法可推出像面上各點的像移速度公式，該公式包含了幾乎所有的運動因素：飛機的前向飛行、飛機的姿態角變化、相機自身的擺掃運動等等，是精確的像移速度公式。本公式同樣適用於畫幅式航空相機和線陣ccd推掃型航空相機。 -
According to purpose of the towed flight, a new trajectory consisting of taking off, climbing phase, level flight phase is presented with. trajectory pitch angle of the towing plane is optimized. according to the flight law of the towing plane, the fin deflection angle and amplification coefficient of particle - system trajectory of carrier rocket are designed, in order to realizing flight steadily of the carrier rocker
根據牽引飛行的目的，對載機應用了「起飛?爬升?平飛」的變軌道飛行方案，同時對載機軌道的傾角、傾角變化規律進行優選設計；再根據載機的飛行規律，對運載器質點系軌道的舵偏規律及其放大系數進行了設計計算，實現運載器穩定牽引飛行。 -
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。 -
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。
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