flight condition 中文意思是什麼
flight condition
解釋
飛行狀態-
A condition affecting the body ' s circadian clock, similar to jet lag, but instead stemming from altering one ' s sleep hours over a weekend of hard partying and drinking rather than from a long flight
一種影響生物鐘的狀態，類似與"時差" ，卻與"時差"概念相去甚遠，特指在周末一夜狂歡后， "大補"瞌睡以後以調整工作日不打瞌睡的狀態 -
Based on the description on the construction technology of the continuous flight auger ( cfa ) pile, the quality advantage, material requirement, construction condition of the pile is introduced, and then the causation of the quality defect and its control measure are presented herein ; from which the processes of both the construction and the quality control are analyzed as well
摘要基於對長螺旋鉆孔混凝土壓注樁施工工藝的論述，介紹了該類型樁的質量優點、材料要求、作業條件以及常見質量缺陷的原因及控制措施，對其施工及質量控制過程進行了分析。 -
The modern unmanned helicopter flight control system is generally composed of the flight control computer, the servo driving mechanism, the sensor, and the ground monitor control system etc. in this thesis the research to the helicopter flight characteristics was conducted at first, and its flight dynamic model was preliminary discussed, especially the mathematic model under hung - stop condition was formulated and the algorithm of the controller was designed in detail
現代無人直升機飛行控制系統一般由飛行控制計算機、伺服驅動機構、傳感器、地面監測控制等分系統組成。本文首先對直升機的飛行特性進行了研究，並且對飛行動力數學模型做了初步探討，尤其對在懸停狀態下的數學模型做了較為詳盡的公式推導和控制器的演算法設計。 -
What is your flight condition
飛行情況如何？ -
A new method to estimate doppler centroid and doppler rate applicable to real flight condition is proposed
該方法設置飛機速率和脈沖重復頻率比為常數，保證方位向接收信號均勻空間取樣，使用實時最小二乘擬合演算法。 -
As the air - breathing engine, the performance of solid rocket ramjet is determined not only by structure of engine and the performance of propellant, but also by flight condition
作為吸氣式發動機，其性能不僅取決于發動機本身結構和推進劑性能，與飛行狀態也有密切的聯系。 -
( 2 ) to evaluate the effects of a reaction control jet on the aerodynamic performance of a missile operating at supersonic / hypersonic flight condition, the single and two attitude jet - interaction flow between a lateral jet and the external flow has been analyzed by detailed numerical simulation
（ 2 ）分別計算了單噴流和雙噴流干擾流場。詳細分析了流場結構和彈體表面壓力分佈特性，獲得了一些有實用價值的結果。 -
A integrated flight / propulsion control ( ifpc ) theoretical schema was designed based on this concept and a engineering schema was developed after take consideration of currently engineering condition and the requirements of in - service aircraft upgrade. a auto - flight system was designed which can achieve accurate flight movement control and increase performance of flight task such as ascend, cruise, te
基於該概念設計了飛推綜合原理方案，並在考慮工程實現條件及現役飛機改進、改型要求后建立了工程實現方案，設計了軌跡跟蹤方式的自動飛行系統，解決了軌跡生成、表示、管理、跟蹤等問題，能夠實現運動狀態的精確控制，提高爬升、巡航等任務的性能。 -
To simulate the real running condition of the program on board, the flight simulation software simulates space environment and sends date to the program
飛行模擬程序模擬飛行環境，向星上程序發送模擬數據，測試星上程序的運行情況。 -
In many performance check, artillery control systematic dynamic trail aimed error is one of relatively important parameter, dynamic trail aimed error denote : when high cannon system is dynamic trailing, set bullet pellet flight time is 0, in the condition of not considering advance quantity ( 0 fly working ), the axis of artillery pipe should direct goal
在諸多的性能考核中，火控系統的動態跟蹤瞄準誤差是較為重要的參數之一。所謂動態跟蹤瞄準誤差是指：當高炮系統在進行動態跟蹤時，設定彈丸飛行時間為零，即在不帶提前量的條件下（即零飛工作方式下） ，火炮身管的軸線應直接指向目標。 -
In the condition of non - axisymmetrical stage separation in hypersonic flight, the problems of dynamics and kinematics of the validating vechicle and the launch vechicle are primarily analysised. it includes the movement of the center of mass and the rigid body of the vechicles, the relative movement of the different vechicles, the relative movement of the special parts of the different vechicles, the load analysis and the probable collision in the process of stage separation
研究了在高超聲速狀態下非對稱級間分離過程中，驗證飛行器與運載火箭分離時的相關運動學和動力學問題。包括:飛行體質心運動和剛體運動;不同飛行體之間的相對運動;不同飛行體上特殊部位之間的相對運動;分離過程中各相關飛行體上的載荷分析和分離過程中可能發生的碰撞問題。 -
Firstly, the study about flight icing is reviewed at the beginning. the condition of icing accretion, the style of icing accretion, the parameters of icing accretion in flight, and the influence of icing accretion on the aerodynamic characteristics of an airplane are analyzed
首先，回顧了國內外在飛機結冰方面的研究情況，對飛機在飛行中的結冰條件、結冰類型、結冰參數以及結冰對氣動特性的影響進行了分析討論。 -
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。 -
As an effective method for flight training, it has been widely used in today ’ s international aviation industry while the aircraft instrument system which is used to display the airplane data condition and flight parameter is an important component of the flight simulator
飛行模擬器是典型的人在迴路的模擬系統，是採用地面模擬設備模擬飛機在空中飛行的重要裝置，它已經成為當今國際航空界普遍採用的訓練飛行員的最有效的手段。 -
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。 -
Article 61 in accordance with the relevant regulations of the state, movement obstacle lights and marks shall be installed on high buildings or facilities, outside the civil airport and its obstacle clearance protection zone defined according to state regulations, that will possibly affect flight safety, and shall be kept in normal condition
第六十一條在民用機場及其按照國家規定劃定的凈空保護區域以外，對可能影響飛行安全的高大建築物或者設施，應當按照國家有關規定設置飛行障礙燈和標志，並使其保持正常狀態。 -
Cathay pacific will try to take reasonable measures to accommodate passengers with this condition by allocating a seat away from other passengers if the flight is not full and provided that advance notice is given to the carrier
有需要而持有醫生證明書的人士可以預先通知訂位組。在可能的情況下，國泰會盡量安排患者與其它乘客隔離，以減低風險。 -
Abstract : a method named multi - times optimization is presented to solve the multi - specification optimization problem, which is difficult to solve using the variational optimal theory. in the method several demands are reduced to some sub - tasks. in every subtask a demand that can not be transformed into bound condition is taken as performance specification for optimazation, and the other demands are taken as bound conditions. by means of the method, the arrival time, number of turn, turn angle of the aircraft in the terminal area are selected as performance specification separately, and the general character of optimal flight route in the terminal area is given
文摘:為了給飛機提供一條能滿足多種指標要求的最優飛行軌跡，針對變分最優理論難以求解多指標優化問題，提出了命名為多次優化的方法，即將多要求的優化任務分成先後相繼的多次任務，每次任務中選取一種不能邊界轉化的要求作為最優性能指標，而其餘要求轉化為邊界條件.利用這一方法以時間、轉彎次數、轉彎角度為最優性能指標給出了終端區最優飛行軌跡的一般特徵 -
In this paper, maccormack explicit time - split scheme, baldwin - lomax algebraic turbulent model and two - steps hydrogen - air nonequilibrium chemical kinetics model are employed to simulate the 2 - d flow fields in a fixed geometry scramjet combustor in different injecting way of fuel in different flight conditions. the results show, in the same entrance condition, the operating mode of scramjet combustor is influenced by the control of fuel
本文採用maccormack顯式時間分裂法、 b - l代數渦粘性湍流模型及氫-空氣兩步非平衡化學動力學反應模型，模擬了在不同的飛行馬赫數條件下，固定幾何的雙模態燃燒室在不同供油規律下的二維燃燒流場。 -
This model is formulated as a non - linear state - space representation of helicopter flight dynamics, incorporating with blade element unsteady aerodynamics, a finite state dynamic inflow wake model, and flapping / lead - lag blade dynamic model. the formulation of the coupled rotor and fuselage equations enables the use of common solution techniques for trim and linearization in arbitrary steady flight condition as well as control response calculations
本項研究針對新機研製過程必須解決的品質評定、飛控系統設計等問題，按照ads - 33軍用品質規范的要求，建立了一個較完整的直升機非線性的、具有狀態空間表達形式的飛行動力學模型，進行了模型驗證工作，並以某樣例直升機為例，計算了ads - 33品質規范（ 3
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