aeroelastic 中文意思是什麼
aeroelastic
解釋
變形的-
Aeroelastic analysis of flexible large aspect ratio wing
特大展弦比機翼的特性與設計 -
By numerical simulation, the servo system in this paper greatly reduces the aeroelastic stability. the structural flitter added to the system can reduce the coupling effect of servo system and structure mode and increase the flutter velocity
通過數值模擬發現，伺服系統會降低原有氣動彈性系統的穩定性，結構陷波器的引入可以減弱伺服系統和結構模態的耦合。 -
Assuming the blades conduct a planar simple harmonic motion, the flows in vibrating cascades in the case of different oscillating amplitudes, different reduced frequencies and different torsional centers are computed respectively for two blade profiles. according to comparing flow calculations at different oscillation modes, the influence of the oscillation parameters " selection on aeroelastic performances of cascades is analyzed
假定葉片做平面簡諧運動，針對兩種葉型分別計算了不同振動幅度、摺合頻率及扭心位置時的振動葉柵流場，根據各種振型下流場計算結果的比較，分析了振動參數選取對葉柵氣動彈性性能的影響。 -
The aeroelastic phenomena may be subdivided under the heading static and dynamic.
氣動彈性現象可以再分為靜態和動態兩個專題。 -
An effective transonic inverse design method for aeroelastic wing
基於控制理論方法的跨聲速彈性機翼反設計方法研究 -
Wind tunnel studies on the behaviour of aeroelastic twin cable model
串列雙索氣彈模型的風洞試驗研究 -
Structural modeling and aeroelastic analysis of high - aspect - ratio composite wings
飛翼飛機穩定性與操縱性研究 -
The different influences of temperature to two aeroelastic systems are analyzed
分析了溫度對這兩種熱結構氣動彈性系統的不同影響。 -
Mathematical model and formulations of a new tilt - rotor aircraft for aeroelastic stability analysis
新型傾轉旋翼機氣動彈性穩定性分析模型 -
The multi - body analysis of the aeroelastic stability of the tiltrotor aircraft is presented
摘要通過多體動力學方法建立了傾轉旋翼機動力學分析模型。 -
Model experiment and damping identification for aeroelastic stability of helicopter rotor with elastomeric lag damper
帶粘彈減擺器旋翼系統氣彈穩定性試驗與阻尼識別 -
Finally for all the above aeroelastic problems, distributed parallel computation is accomplished
最後對以上氣動彈性問題的數值計算進行了基於微機網路的分散式并行計算研究。 -
The research of this dissertation is focused on how to solve the 3 - dimensional compressible navier - stokes equations by the implicit finite difference algorithm and to simulate numerically the unsteady subsonic and transonic viscous flows around rigid and elastic wings. on the base of them the aeroelastic characterictics of an elastic wing have been studied
本文的主要工作是用隱式有限差分法求解三維非定常紊流n - s方程組，數值模擬剛性機翼及彈性機翼的亞、跨、超音速定常及非定常粘性繞流，並在此基礎上研究了彈性機翼的氣動彈性問題。 -
Numerical simulations demonstrate that the multi body analytical model can analyze the aeroelastic stability of the tiltrotor aircraft in the helicopter mode
數值計算表明：建立的多體動力學模型能夠快速分析直升機模式下傾轉旋翼機復雜的旋翼機翼氣彈耦合動力學特性。 -
Multi body dynamic differential equations are combined with the equations of the unsteady dynamic inflow model to establish the complete unsteadily aeroelastic coupling analytical model of the tiltrotor
結合動力人流，研究了直升機模式下傾轉旋翼機非線性非定常氣彈耦合動力學特性。 -
With the development of material technology, information technology, automation control technology, aeronautics and astronautics technology, the modern flight vehicles are required of high velocity, light structure, great flexibility and super maneuverability, which lead to the serious aeroelastic effects such as aeroservoelasticity, the coupling among the aerodynamics, structure, and control system
隨著材料技術、信息技術、控制技術以及航空航天技術本身的飛速發展，飛行器開始向高速度、輕結構、大柔性、超機動的方向發展，氣動彈性效應更加嚴重，從而引發了氣動、結構、控制系統相互耦合的氣動伺服彈性力學問題。 -
Moreover, in the application of aircraft structures design, the composite wing is still to meet the needs of aeroelastic design. through reading the aerodynamic influence coefficient matrix from the nastran file, this paper generates a static aeroelastic equilibrium equation and divergence eigen - equation, which is needed by the aeroelastic tailoring of composite wing. through this equation, the aeroelastic tailoring of composite wing and its optimization design have come into being
此外在飛機結構設計過程中，復合材料翼面結構還要滿足氣動彈性設計的需要，本文通過讀入由nastran所產生的氣動影響系數矩陣，構造出滿足復合材料氣動彈性分析所需要的靜氣動彈性平衡方程和發散特徵方程，並在此基礎上實現了復合材料氣動彈性剪裁優化設計。 -
Based on the characteristics of the membrane structures, wind - induced nonlinear coupling dynamic response analysis which can be applied to closed membrane structures is developed and the added air mass the pneumatic stiffness and the acoustical damping of the closed membrane structures are deduced. applying the method to an aeroelastic model of wind tunnel test, the displacement the velocity and the acceleration of corresponding prototype structure in time domain are obtained
本文針對封閉式薄膜結構和敞開式薄膜結構推導了全新的非線性流固耦合風振響應公式，其中耦合因素包括附加空氣質量、氣承剛度和聲致阻尼以及相對運動速度，並將此理論應用於一氣彈模型的計算，獲得了位移、速度、加速度時程以及加速度均方根。 -
Using multidisciplinary collaboration simulation, applying aeroelastic theory and method, structural modeling with fem was set up, structural dynamics and vibration mode were analyzed, and then problem of gust load alleviation for a large flexible wing was discussed
摘要利用多領域協同模擬技術，應用氣動彈性分析理論和方法，對柔性機冀進行結構有限元建模、動力學特性分析、固有振動分析，並針對垂直陣風載荷減緩進行討論。 -
The feasibility of the technique is examined by using compute simulation and flutter testing of aeroelastic models in low - speed wind tunnel
經數字模擬及氣彈模型低速風洞顫振試驗數據驗證，取得了滿意的效果。
分享友人