翼型系數 的英文怎麼說
中文拼音 [yìxíngxìshǔ]
翼型系數
英文
profile coefficient-
Some typical schemes are implemented via this data structure ( loop subdivision, catmull - clark subdivision, do - sabin subdivision, hybrid subdivision, adaptive subdivision ). the technique of opengl is utilized to accomplish some basic operations, such as rotation, zoom, pan, pick and so on. finally the algorithms studied by our research group are integrated, and a prototype system based on subdivision surface is developed
（ 4 ）改進了適合於曲面細分的的翼邊數據結構，並實現了典型的細分演算法（ loop細分、 catmullclark細分、 doo - sabin細分、混合細分、自適應細分） ；採用opengl技術實現了旋轉、縮放、平移、拾取等圖形的基本幾何操作；最後將本課題組研究成果加以集成，開發了一個基於細分曲面的原型系統。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。The paper introduces the structure of helicopter airscrew loading system and constructs the mathematical model of single channel loading system and analyses its dynamic performance
論文介紹了直升機旋翼加載系統的結構，在建立了單通道加載系統的數學模型的基礎上，分析了加載系統的動態性能。Based on the aerodynamics, control, structural dynamics model of smart rotor in frequency domain deduced and the determination for the number of neurons in hidden layer, the neuro - emulator using multiple independent miso neural networks with its deduced matrix expression for the smart rotor is set up. the rate of training is improved by introducing the orthogonal selection applying for smart rotor to the selection of training cases in neural modeling
試驗結果驗證了該方法的可行性，在建立了帶有主動控制后緣附翼的智能旋翼系統氣動-控制-結構動力學數學模型的基礎上，提出了適用於智能旋翼建模的多神經網路並聯型式的頻域模型，並推導出其矩陣表達式，探討了隱含層神經元數的確定方法。At the end of the experiment, we reconstructed the subsystem of second air measuring, i. e. we used airfoil measuring equipment as a replacement of original equipment of flute pipe. we also demarcated the velocities of spouts of burner which can deal with correlative data, and which can provide some help for operation
最後又對監測系統二次風測量子系統進行改造，將原笛型管裝置修復為機翼測風裝置，對傳感器進行差壓標定;在爐內噴口處標定速度，將數據進行處理，提供給熱工控制顯示用，對運行調整提供了幫助。Gabled frames are widely used in industry and civil engineering, it ' s web plates " local buckling calculated formula in the technical specification for steel - structure of one - storey light - weight buildings with gabled frames ( cecs102 : 98 ) are based on the rectangular plates " and did n ' t consider the interaction of the fringe plate. so, there are some different between the actual members and the prescript of the specification, and the post - buckling strength ' s calculated formula is based on the local buckling ' s, it must have some unreasonable
楔形門式剛架廣泛地應用於工業與民用建築中， 《門式剛架輕型房屋鋼結構技術規程》 （ cecs102 ： 98 ）中楔形腹板局部屈曲的計算公式來自矩形板，並且沒有考慮翼緣的相關作用，因此，規程中的規定與構件的實際工作狀況有一定的差異，且屈曲后強度的計算公式也是以局部屈曲系數為基礎的，勢必有其不合理性。Abstract : a new method, collaborative allocation ( ca ), is proposed to solve the large - scale optimum allocation problem in aircraft conceptual design. according to the characteristics of optimum allocation in aircraft conceptual design. the principle and mathematical model of ca are established. the optimum allocation problem is decomposed into one main optimization problem and several sub - optimization problems. a group of design requirements for subsystems are provided by the main system respectively, and the subsystems execute their own optimizations or further provide the detailed design requirements to the bottom components of aircraft, such as spars, ribs and skins, etc. the subsystems minimize the discrepancy between their own local variables and the corresponding allocated values, and then return the optimization results to main optimization. the main optimization is performed to reallocate the design requirements for improving the integration performance and progressing toward the compatibilities among subsystems. ca provides the general optimum allocation architecture and is easy to be carried out. furthermore, the concurrent computation can also be realized. two examples of optimum reliability allocation are used to describe the implementation procedure of ca for two - level allocation and three - level allocation respectively, and to validate preliminarily its correctness and effectiveness. it is shown that the developed method can be successfully used in optimum allocation of design requirements. then taking weight requirement allocation as example, the mathematical model and solution procedure for collaborative allocation of design requirements in aircraft conceptual design are briefly depicted
文摘:探討了一種新的設計指標最優分配方法- -協同分配法，用於處理飛機頂層設計中的大規模設計指標最優分配問題.分析了飛機頂層設計中的設計指標最優分配特徵，據此給出了協同法的原理並建立了數學模型.協同法按設計指標分配關系將最優分配問題分解為主系統優化和子系統優化，主優化對子系統設計指標進行最優分配，子優化以最小化分配設計指標值與期望設計指標值之間的差異為目標，進行子系統最優設計，或對底層元件（如飛機翼梁、翼肋和翼盒等）進行設計指標最優分配，並把最優解信息反饋給主優化.主優化通過子優化最優解信息構成的一致性約束協調分配量，提高系統整體性能，並重新給出分配方案.主系統與子系統反復協調，直到得到設計指標最優分配方案.兩層可靠度指標分配算例初步驗證了本文方法的正確性與可行性，三層可靠度指標分配算例證明了本文方法的有效性.最後，以重量指標分配為例，簡要敘述了針對飛機頂層設計中設計指標協同分配的數學模型和求解思路A new method, collaborative allocation ( ca ), is proposed to solve the large - scale optimum allocation problem in aircraft conceptual design. according to the characteristics of optimum allocation in aircraft conceptual design. the principle and mathematical model of ca are established. the optimum allocation problem is decomposed into one main optimization problem and several sub - optimization problems. a group of design requirements for subsystems are provided by the main system respectively, and the subsystems execute their own optimizations or further provide the detailed design requirements to the bottom components of aircraft, such as spars, ribs and skins, etc. the subsystems minimize the discrepancy between their own local variables and the corresponding allocated values, and then return the optimization results to main optimization. the main optimization is performed to reallocate the design requirements for improving the integration performance and progressing toward the compatibilities among subsystems. ca provides the general optimum allocation architecture and is easy to be carried out. furthermore, the concurrent computation can also be realized. two examples of optimum reliability allocation are used to describe the implementation procedure of ca for two - level allocation and three - level allocation respectively, and to validate preliminarily its correctness and effectiveness. it is shown that the developed method can be successfully used in optimum allocation of design requirements. then taking weight requirement allocation as example, the mathematical model and solution procedure for collaborative allocation of design requirements in aircraft conceptual design are briefly depicted
探討了一種新的設計指標最優分配方法- -協同分配法，用於處理飛機頂層設計中的大規模設計指標最優分配問題.分析了飛機頂層設計中的設計指標最優分配特徵，據此給出了協同法的原理並建立了數學模型.協同法按設計指標分配關系將最優分配問題分解為主系統優化和子系統優化，主優化對子系統設計指標進行最優分配，子優化以最小化分配設計指標值與期望設計指標值之間的差異為目標，進行子系統最優設計，或對底層元件（如飛機翼梁、翼肋和翼盒等）進行設計指標最優分配，並把最優解信息反饋給主優化.主優化通過子優化最優解信息構成的一致性約束協調分配量，提高系統整體性能，並重新給出分配方案.主系統與子系統反復協調，直到得到設計指標最優分配方案.兩層可靠度指標分配算例初步驗證了本文方法的正確性與可行性，三層可靠度指標分配算例證明了本文方法的有效性.最後，以重量指標分配為例，簡要敘述了針對飛機頂層設計中設計指標協同分配的數學模型和求解思路The three basic steps are as follows : firstly, the flow field is computed. secondly, the droplet trajectory equation is solved in order to determinate the limiting droplet trajectories and local collection coefficient. thirdly, a new iced shape is defined according to ice accretion model
其基本步驟一般分三步：計算物體的繞流流場；求解水滴軌跡方程以確定極限水滴軌跡和收集系數；根據冰增長模型來確定新的結冰翼型形狀。The integral seismic behaviors of other three kinds of connection, namely bfp, dst, and sep connections are better than that of normal wfp connection. by the way, finite - element ( fe ) analyses were conducted to predict the influence on cfst structure under different kinds of elements, mesh density, load manners and boundary conditions. after that, a special program was designed to define the constitutive relationship of concrete material in cfst structures based on apdl in ansys program
此外，本文探討了不同的單元類型、不同的網格劃分密度、加載方式與邊界條件對鋼管混凝土組合結構數值計算的影響，運用ansys中的apdl語言，編寫了適合鋼管混凝土結構分析的混凝土材料本構關系程序，並運用該程序結合ansys對常規栓焊節點與翼緣全螺栓連接節點的滯回性能進行了初步計算，為進一步地數值分析打下了基礎。The principal contributions of this dissertation are : 1. a high fidelity and real - time rotor wake inflow model was built up. based on peters - he finite states wake theory, a new influence coefficient matrix for high speed flight was derived, the modified wake model is better suitable for the flight state with a large wake skew angle
本模型以peters - he有限狀態尾跡理論為基礎，修正了大尾跡傾斜角時的誘導速度影響系數矩陣，並結合了王氏渦流理論，導出了旋翼誘導速度垂向分量和旋轉分量的表達式，可計算平尾、尾槳和垂尾氣動中心處誘導速度各分量。A distributed computer control system which is used in an helicopter airscrew multi - channel harmony loading test project is introduced in this paper. the paper analyses the construct and the model of the system
論文結合實際的工程項目，以某型號直升機旋翼氣動載荷模擬為研究內容，對加載計算機控制系統的組成、系統數學模型進行分析和研究。分享友人