in-flight stability 中文意思是什麼
in-flight stability
解釋
飛行安定性-
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。 -
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。 -
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。 -
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。 -
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。 -
In chapter 3, the non - linear equation was linearized with the jacobi matrix, and then the linearized equation was transformed into fixed frame to analyze the stability problem with eigenvalue method ( on - ground or hovering ) or floquet theory ( forward flight ). meanwhile, the equation was perturbed by sweep frequency excitation from steady state to get transit decay of lag response which was then transformed into fixed frame with a numerical fourier coordination transformation ( fct ). the fixed frame response along with the body response was analyzed via an fft to determine modal frequencies
然後，在穩態響應的基礎上利用雅各比矩陣對非線性方程進行了線化，線化后的方程利用多槳葉坐標變換轉換到固定系下后，利用直接特徵值分析（地面、懸停）或floquet理論（前飛）對系統進行了穩定性分析;同時，對系統進行了瞬態響應分析;在系統達到穩態的基礎上進行掃頻激勵，用fft變換求得系統頻率，進而用移動矩形窗方法分析得到系統的阻尼。 -
Unlike traditional differential geometrical method, the robust adaptive neural net - based control emphasizes on the theory and application of intelligence control in nonlinear system that is weighed by robust performance index. the problem of robust reliability and stability in a kind of weak nonlinear system is first proposed in the dissertation, and then it deeply analyses and discusses the problem of how to design track controller in strong nonlinear system with uncertainties and external disturbance on the premise of guaranteeing the whole system ' s robust performance index. the distributed 3d flight simulation platform is mainly used to validate real - time program and evaluate the efficiency of advanced flight control laws, therefore, some theories and techniques related to the platform are also introduced
基於神經網路的魯棒自適應控制研究和分散式三維飛行模擬平臺的構建是本論文研究的兩個主要內容，與傳統微分幾何方法不同的是，基於神經網路的魯棒自適應控制側重於智能控制方法在以魯棒性為性能指標的非線性系統中的理論和應用研究，論文以一類弱非線性系統的魯棒可靠鎮定問題為引線，逐步深入地分析和探討了在保證整個被控系統魯棒性能指標的前提下，對于幾類具有不確定性和外部擾動的強非線性系統跟蹤控制器的設計問題；分散式三維飛行模擬平臺主要用於先進飛行控制律的實時程序驗證和效能評估之用，因此關于平臺的一些開發原理和技術方法也在文中給出了介紹。 -
And then the stability and the stable error response of the dpll are analyzed. there is an obvious doppler shift frequency offset in the received signal with flight at a high speed, in the dissertation the uniform sampling second - order dpll is used to remove the frequency bias for its excellent high - pass characteristic of the error transfer function
由於高速飛行的遙測目標在接收信號中會出現較大的多普勒頻率分量，而典型均勻采樣二階數字鎖相環dpll （ digitalphase - lockedloop ）的誤差函數具有高通特性，所以本文提出一種利用其高通特性來去除多普勒頻率分量的新方法。 -
Flight dynamics - concepts, quantities and symbols - part 4 : concepts, quantities and symbols used in the study of aircraft stability and control
飛行動力學.概念量及符號.第4部分:研究飛行器穩定性及操縱性用的概念量和符號
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