氣動力彈性 的英文怎麼說

中文拼音 [qìdònglìdànxìng]
氣動力彈性 英文
aeroelasticity
  • 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...
  • 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...
  • 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 ...
  1. 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
  2. The dynamic performance of a ram air system will vary with mach number and altitude and this tends to follow the aerodynamic characteristics of the missile.

    像導彈空氣動力特性一樣，沖壓空氣式系統的動態特性隨馬赫數和高度的變化而變化。
  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. Simulation result showed that response time of missile was reduced and guidance accuracy was accordingly increased by side jet and aerodynamic compound control manner in terminal guidance

    通過模擬研究表明：在末制導階段，採用燃氣動力氣動力復合控制方式可提高導彈的快速性，進而提高導彈的制導控制精度。
  6. 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。
  7. 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。
  8. Using above methods to solve unsteady pressure distribution, coupling structure equations, the supersonic or hypersonic aeroelasticity is simulated in time - domain

    運用上述的非定常氣動力求解方法，耦合結構動力學方程，實現超音速、高超音速氣動彈性的模擬。
  9. Integrated ase design and coupled cfd / csd simulation technology and firstly applied the reduced order model based on volterra series to the design of ase system 2

    將ase系統設計同cfd csd耦合模擬技術相結合，首次將基於volterra級數的非定常氣動力降階模型用於氣動伺服彈性系統的設計。
  10. 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。
  11. The result open out the feasibility of direct lateral force / aerodynamic control. the control style can raise the missile mobile ability in terminal trajectory

    結果揭示了直接側向力氣動力復合控制的可行性，這種控制方式可以提升導彈飛行末端的機動能力。
  12. 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。
  13. The missile with its radome is at high temperature during the entrance. due to aerodynamics heating process, the high temperature cause air ionization and ablation of the radome, so the radome is at unsymmetrical heat environment, its electrical properties vary with different parts of the radome

    導彈在再入過程中，由於空氣動力加熱效應，引起空氣電離和天線罩表面被燒蝕，因此，天線罩處于不對稱熱環境中，它各部分的介電性能不同。
  14. In this paper, the backward simulation was summarizd at home andabroad, the characteristics of shell nosing were introduced, the theory and scheme of backward simul - ation of shell nosing was constructed, the determined methods of the boundary conditions were put forward in backward simulation for the processes of shell nosing

    論述了推力矢量控制技術是提高空空導彈性能的核心技術，介紹了常用的三類推力矢量裝置，著重討論了燃氣舵式和擾流片式推矢裝置的特點、設計方法、性能及其優缺點.在此基礎上，研究了適用於氣動力/推力矢量復合控制的變結構控制系統及其開關函數的切換條件和飛行控制系統框圖.最後綜述了推力矢量裝置在第四代空空導彈上的應用情況
  15. 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。
  16. Using the engineering methods of supersonic and hypersonic flow or local piston theory developed in this paper to compute unsteady aerodynamic loads, and coupling structural equations, the supersonic or hypersonic aeroelasticity with a typical servo system under thermal environment is simulated in time - domain

    運用超音速、高超音速氣動力工程計算方法和本文發展的當地流活塞理論計算非定常氣動力，耦合結構運動方程，實現了熱環境中帶有伺服機構的氣動彈性的時域模擬。
  17. Design method of active control law based on reduced order model of unsteady aerodynamics for aeroelasticity

    基於非定常氣動力低階模型的氣動彈性主動控制律設計
  18. Flutter is the most important instable problem and it restricts the flight envelope and performance of a vehicle. aeroservoelasticity, including active flutter suppression technology, is a multidisciplinary optimization technology that studies the interaction of flexible structure, unsteady aerodynamics and flight control system

    以主動顫振抑制系統設計為代表的氣動伺服彈性力學（ ase ）是一門涉及柔性結構、飛行器運動引起的定常和非定常氣動力以及飛行控制系統相互作用的多學科技術。
  19. The software package have some functions as follows : calculating the shrapnel ' s diagnostic parameters such as the mass and the pole moment of inertia, the inner and outer ballistic characteristic, the aerodynamic force and power, and so on

    該榴彈cad軟體具有以下一些功能模塊：計算彈丸質量、極轉動慣量等構造特徵數，計算內、外彈道特性，計算氣動力，威力等。
  20. The aerodynamics characteristic of spinning projectile with lateral jets has constitutionally difference in formation from that without jet, and it waves periodically. these characteristics are very important for the study of aerodynamics of projectile with lateral jets

    與光彈體相比，旋轉側噴彈丸的空氣動力特性不僅在形成機理上發生了本質變化，而且在數值上表現出復雜的波動形式，這些特點將對旋轉側噴彈丸空氣動力研究帶來直接和深遠的影響。
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