空氣彈性力學 的英文怎麼說

中文拼音 [kōngqìdànxìnglìxué]
空氣彈性力學 英文
aeroelasticity
  • 空 : 空Ⅰ形容詞（不包含什麼; 裏面沒有東西或沒有內容; 不切實際的） empty; hollow; void Ⅱ名詞1 （天空） s...
  • 氣 : Ⅰ名詞1 （氣體） gas 2 （空氣） air 3 （氣息） breath 4 （自然界冷熱陰晴等現象） weather 5 （氣味...
  • 彈 : 彈名詞1. （彈子; 小球形的東西） ball; pellet 2. （內裝爆炸物, 具有破壞和殺傷能力的東西） bullet; bomb
  • 性 : Ⅰ名詞1 （性格） nature; character; disposition 2 （性能; 性質） property; quality 3 （性別） sex ...
  • 力 : Ⅰ名1 （力量; 能力） power; strength; ability; capacity 2 [物理學] （改變物體運動狀態的作用） forc...
  • 學 : Ⅰ動詞1 （學習） study; learn 2 （模仿） imitate; mimic Ⅱ名詞1 （學問） learning; knowledge 2 （學...
  • 空氣 : 1 （大氣） air; atmosphere 2 （氣氛） atmosphere 3 （氣閘） air brake4 pneum ; pneumo ; pneumat ;...
  1. The dr. wu lumbar tractor has modern design with two jars which utilize the condensability of air and the hydromechanical theory to realize the auto balance of the air pressure in the two jars, thus guaranteeing the elastic pulling of lumbar, the only one that conforms to the “ human bio - elastic mechanics ”

    伍醫生腰椎牽引器設計新穎，採用雙氣缸連通，利用空氣的可壓縮性與流體力學的原理實現了兩氣缸壓力自動平衡，達到腰椎彈性牽引之目的，是目前國內唯一符合「人體彈性生物力學」的腰椎牽引器。
  2. Tzong - shyng leu, pong - jeu lu, and jeng - ren chang, " application of flexible micro balloon actuators for forebody aerodynamic control, " international symposium on experimental mechanics, december 2002

    呂宗行，陸鵬舉，張政仁， "可橈性微泡致動器在前彈體氣動力控制之應用， "中國航空航太學會，高雄， 2002
  3. Three dimensional interaction flowfield over high - speed spinning projectile with lateral jets is numerically simulated in this dissertation firstly. complicated shocks wave patterns is analyzed. several factors concerned such as high - speed spinning, attack angle, base bleed and so on, are studied

    本文首次完成了高速旋轉彈丸側噴三維干擾湍流流場的數值模擬，分析了彈丸側噴流場復雜的波系結構，研究了高速旋轉、攻角、底噴等因素對彈丸側噴流場的影響規律，深入分析了旋轉側噴彈丸的空氣動力學特性。
  4. 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。
  5. Abstract : this paper introduces briefly the control principle of trajactory correction technique and analyzes the structures and application areas of several typical trajectory correction mechanisms such as paddle type ring and d - ring etc. moreover, it makes the aerodynamics simulation and dynamics simulation of trajectory correction mechanism as paddle type damping ring. the simulation result proves the correctness and feasibility of the design

    文摘:簡要介紹了彈道修正技術的控制原理；分析了槳式、 d型環等幾種典型彈道修正裝置的結構特點和應用范圍；並對其中的槳式阻尼環彈道修正裝置分別進行了空氣動力學模擬和運動學模擬，驗證了設計的可行性和正確性。
  6. The complicated aerodynamics characteristic of spinning projectile with lateral jets and with attack angle is studied detailedly. the formation and changes are analyzed including magnus force, normal force, yawing moment, pitching moment and pressure center

    系統分析了旋轉側噴彈丸復雜的空氣動力學特性，分析了馬格努斯力系數、法向力系數、偏航力矩系數、俯仰力矩系數和壓力中心等參數的產生機理和變化規律。
  7. 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。
  8. This group focus on the research of missile and launch vehicle, which contain the guidance law and the controller design. there are two researchers in this group now, including one m. d

    本研究群的宗旨乃進行攔截飛彈及運載火箭之研究，主要包含導引法則及自動駕駛儀控制器設計等項目，並利用各式各樣的模擬（其中也包含空氣動力學模型） ，驗證其系統可行性。
  9. Based on aerodynamic theory and the characteristics of the shockwave around a supersonic projectile, the article constructs a mathematical modeling of a l - shaped vertical target for projectiles shooting with forward direction and any direction, and analyzes the error sources and provides correcting ways to lower the error

    摘要本文根據空氣動力學理論和超音速彈丸的激波特性，建立了在使用l型立靶基礎上正向射擊和任意角度射擊時的數學模型，並進行了誤差分析，提出了減小誤差的修正方法。
  10. The single point suspending system kinetic model including secondary suspending structure is built at the beginning of the paper, then this paper gives the relation between the stiffness and damping of air spring and dynamic characteristic of single point suspending system

    因此，本文首先建立了二級結構單點懸浮系統的動力學模型，研究了二級結構中空氣彈簧剛度和阻尼對系統動態特性的影響。
  11. At last the dynamics of trailer is analysed when trouble is take place including the lateral stability when the anti yaw dampers become ineffective, the ride index when airsprings have no air and the negotiation when the trailer runs on the curve the tilting actuator does n ' t work or work in the contrary direction

    最後，論文分析了拖車在幾種故障工況下的動力學性能，包括抗蛇行減振器失效工況的橫向穩定性；空氣彈簧無氣工況的運行平穩性；曲線通過時傾擺作動器不動作和傾擺作動器反向動作工況拖車的動態曲線通過性能。
  12. First, being based upon kalman filter, extended kalman filter formulas was established ; second, with using extended kalman filter in non - linear dynamics system maximum likelihood identification method, the self - contained formulas of estimating parameter was established ; third, according to the air layout of the missle, the aerodynamic parameters identification calculating model was gained, with applying to the non - linear dynamics system maximum likelihood identification method ; finally, with using the calculating model, the aerodynamic parameters were gained. the results which were gained from the calulating model were almost consistent with which were gained from the wind tunnel experiment. thus, it was viable to use the method to estimate the aerodynamic parameters

    首先，以卡爾曼濾波為基礎，將其推廣于非線性動力學系統，建立了廣義卡爾曼濾波算式；其次，把廣義卡爾曼濾波算式應用於非線性動力學系統最大似然演算法和非線性動力學系統最大似然遞推演算法中，建立了各自的參數估計完備算式；再其次，以所建立的傾斜穩定導彈空間運動數學模型為基礎，根據該導彈的氣動布局，推導並建立了該導彈空間運動數學模型，將最大似然遞推演算法應用其中，建立了導彈氣動力參數辨識的數學模型；最後，利用該模型，估算出了氣動力參數，所得結果與風洞實驗數據基本吻合，從而認為採用此方法是可行的。
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