flight stability 中文意思是什麼
flight stability
解釋
飛行穩定性-
To determine which exchange-rate system offers the most stability in the face of such capital flow shocks, let us take the case of sudden capital flight from the country.
為了確定哪一種匯率制度在面臨這種資本流動沖擊時具有最大的穩定性，讓我們以資本突然從這個國家外逃為例。 -
Some flight course switch rules are researched. uav ’ s launch stability and flight course precision are influenced by wind. through the research of flight control, some way are found to lower the wind influence
研究了風速對無人機的發射穩定性影響，通過風速對無人機導航控制影響的分析，提出了減小側風影響的控制策略，並推出一種計算平均水平風速的方法。 -
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。 -
Long before wilbur and orville wright started building glider models, those determined bicycle mechanics realized that achieving controlled flight depended largely on finding means to regulate lateral ( side - to - side ) stability in the air
早在魏爾柏?萊特和奧維爾?萊特兩兄弟開始製造滑翔機模型之前，熱血的自行車技工就知道，要能隨心所欲地飛行，必須找出在空中維持側向穩定的方法。 -
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。 -
To study the influence of this damper configuration to aeromechanical stability, some work has been done in this thesis. first, dynamic equation of the rotor - hub system was modeled with the generalized hamilton principle, which can be used to analyze the stability problem in different conditions like on - ground, hovering and flight. when fastening the fuselage, the model can also be used to analyze the stability problem of isolated rotor system
為了研究這種新型布置減擺器對直升機穩定性的影響，本文所作研究工作如下:首先，本文利用廣義的hamilton原理建立了適用於不同狀態（地面、懸停和前飛）的旋翼/機體耦合系統的動力學模型，該模型中將機體固定可以用來分析孤立旋翼的穩定性問題。 -
Several icing parameters were imported to calculate the change of drag coefficient and typical derivatives between clean aircraft and iced aircraft, and the aircraft flight envelope change of iced and un - iced situation was computed, and the small disturbance flight dynamics model was modified to study the effect of the ice accretion on the aircraft dynamics by importing the ice parameter to it, and the longitudinal and lateral stability and the elevator, aileron and rudder step response were also studied and simulated
根據這些參數計算了飛機結冰后阻力系數以及典型氣動導數的變化，並計算了結冰前後飛機的飛行包線；同時對結冰前後飛機的縱向、橫側動穩定性以及升降舵、副翼和方向舵階躍操縱響應進行模擬計算。 -
During helicopter slung - load flight, the main flight quality modes include : phugoid, dutch roll, longitude and latitude slung - load oscillation. according to the ads - 33e - prf specifications, the flight stability qualities had been evaluated
直升機機外吊掛飛行過程中，體現飛行品質的運動模態主要為荷蘭滾模態、縱向浮沉振蕩模態，以及吊掛物橫向、縱向振蕩模態。 -
Through calculating and analyzing basic performance, the flight characteristic of the towed system is researched. stability and control issue of carrier rocket is discussed primarily. the net result of the thesis will prove the feasibility of the scheme of towed launch
論文通過牽引系統基本性能的計算和分析，完成牽引飛行特性的研究，同時對運載器的穩定性和控制問題進行初步的探討，最終結果將驗證牽引發射方案的可行性。 -
Flight stability characteristic for triangle cross - sectional projectile
三角形截面彈芯的飛行穩定特性 -
During the procedure of long - distance high - speed flight of flying objects, the measuring precision of the mass characteristic parameters is vital to the flight stability, controllability, maneuverability, hit rate of flying objects
在高速遠程飛行物體的飛行及命中目標過程中，質量特性參數測量的精確與否對高速遠程飛行物體飛行的穩定性、可操控性、機動性及命中率有著舉足輕重的作用。 -
It has been maked for immediate and statistical analysis that the calculation about the work order parameter of the base - bleed - rocket is calculated in the taguchi method, its influencing trend is bring out in the open, the theoretical base is settled for confirming the greatest combination about the work order parameter of the base - bleed - rocket. the multi - objectile optimal design model is established that the indexes have been taked into account first and synthetically, such as physical parameter range lethality power strength and flight stability and so on, the program is compiled and the example is calculated. the true worth of the theoretical work in this paper is validated by flight experimentation of 130mm hybrid base - bleed - rocket extended - range principium projectile
本文進行了底排?火箭復合增程彈工作時序參數正交試驗設計的直觀分析與方差分析，揭示了每個參數對射程計算的影響趨勢，為進一步確定底排?火箭工作時序參數值的最佳匹配組合奠定了理論基礎；建立了底排?火箭復合增程彈多目標優化設計模型，該模型首次綜合考慮了底排?火箭復合增程彈的結構特徵參量、結構強度性能、飛行穩定性、威力性能和射程指標，編制了相應的分析程序，進行了算例計算；完成了130mm底排?火箭復合增程原理樣彈的結構設計與飛行試驗，其試驗結果驗證了本文理論研究工作的實際應用價值。 -
According to the measuremental data of the two ammunications, the anti - designed computation and analysis of aerodynamic characteristic, flight stability, exterior ballistic characteristic for the two ammunications are studied with the advanced methods of the exterior ballistics. using the monte calo algorithm, the statistic mathematical model about ammunication ' s intensity is established and the 1000 miter vertical target intensity and the fall intensity are discussed in detail for the two ammunications. the improval potential and the main technical approachs of these ammunication ' s exterior ballistic performances are presented by compositive optimal algorithm
根據工廠對俄ak130艦炮彈藥的測繪數據，利用先進的外彈道數值分析方法對兩種彈藥的空氣動力特性、飛行穩定性特性、外彈道特徵量等進行了反設計計算分析；採用montecarlo方法，建立了艦炮彈藥密集度性能統計分析數學模型，對兩種彈藥的立靶密集度和地面密集度進行了詳細的計算分析；利用外彈道性能綜合優化設計方法對兩種彈藥的外彈道性能指標的改進潛力和主要技術途徑進行了分析。 -
Appropriate evaluation indexes are established based on the considerations for the missile impact, the target tracking stability and the flight stability of the missile. a simulation program is designed to simulate the missile - ship engagement scenario, and also evaluate the electronic protection capability of the active - passive multimode seeker
分別從反艦導彈彈著點、導引頭目標跟蹤穩定性和反艦導彈飛行穩定性三個方面考慮，研究了評估復合制導反艦導彈主被動復合導引頭抗干擾性能的基本理論和方法，建立了評估指標。 -
The main factors which affected the flight stability quality included : forward flight speed, slung - load and helicopter mass ration, slung - load aerodynamic forces and cable length, etc. through adjusting the above structure and performance parameters, rational flight parameters can be decided, which can ensure the safe helicopter mission operations of the slung - load flight
影響飛行品質穩定性要求的主要因素為:直升機飛行速度、吊掛物/直升機質量比、吊掛物氣動特性、吊掛鋼索長度等。通過對上述結構參數、性能參數的調節，可確定合理、經濟的飛行參數，保證安全、高效的完成直升機機外吊掛飛行運輸任務。 -
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。 -
The design of configuration and other primary structures of the helicopter have been finished. in order to analysis the stability and control of the helicopter, a flight mechanical modeling has been founded based on a single - rotor helicopter
本文以常規單旋翼帶尾槳的直升機配平和操穩計算方法為基礎，建立了帶涵道共軸式直升機飛行動力學模型，對碟形無人直升機進行了配平和操縱性和穩定性分析計算。 -
Flight mechanics. concepts, quantities and symbols stability and control of aircraft
飛行力學概念量和符號飛機穩定性和操縱性 -
Fuzzy controller design and stability analysis for flight control systems
飛控系統模糊控制器設計及穩定性分析 -
The lamv features redundant ， independent computer systems for flight management ， stability ， and control
Lamv的特色是用獨立的咒余計算機系統分別進行飛行管理、穩定性調整和控制。
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