missile body 中文意思是什麼
missile body
解釋
導彈彈體-
The 3 - d complex flowfield of rocket - missile with wings and empennages induced by the interaction between by base jet and the flow around the body has been numerically simulated. the main work is as follows : first, the gordon - mcbride program was developed to make it more friendly and efficient to the users
本文對帶彈翼/尾翼彈箭的三維噴流繞流復雜流場進行了數值模擬，其主要研究內容有：首先，對gordon - mcbride火箭程序作了改進，使改進后的軟體具有了非常友好的人機交互界面。 -
Fluent was used to simulate the flowfield of 3 - d complex flowfield of rocket - missile with wings and empennages induced by the interaction by base jet and the flow around the body. in order to study the complex flow problem above, numerical simulations were performed under the following kinds of flow conditions : ( l ) flow of rocket - missile with wings disturbed by supersonic upstream flow. ( 2 ) flow of rocket - missile with wings disturbed by supersonic upstream flow with attack angle
為了研究以上復雜流場考慮了如下幾種情況： （ 1 ）帶彈翼彈箭超音速無攻角繞流； （ 2 ）帶彈翼彈箭超音速有攻角繞流； （ 3 ）帶彈翼彈箭亞音速有攻角繞流； （ 4 ）帶彈翼彈箭超音速有攻角繞流噴流干擾； （ 5 ）帶彈翼尾翼彈箭超音速有攻角繞流； （ 6 ）帶彈翼尾翼彈箭超音速有攻角繞流噴流干擾。 -
This paper analyzes the structural reliability of surfa ce ( ship ) to air missile body, introduced the method of engineering calculation f or structural reliability of missile body and presents a technical way of impro ving structural reliability of missile body
對地（艦）空導彈彈體結構可靠性進行了分析，介紹了彈體結構可靠性的工程計算方法，提出了改進彈體結構可靠性的技術途徑。 -
Abstract : this paper analyzes the structural reliability of surfa ce ( ship ) to air missile body, introduced the method of engineering calculation f or structural reliability of missile body and presents a technical way of impro ving structural reliability of missile body
文摘:對地（艦）空導彈彈體結構可靠性進行了分析，介紹了彈體結構可靠性的工程計算方法，提出了改進彈體結構可靠性的技術途徑。 -
In this thesis, based on pershing ii surface to surface missile, a new kind of ballistic missile was designed with an additional rocket engine, which can be ignited twice. firstly, aerodynamic computational models of missile body and warhead which reentry with supersonic are built according to the task requirements ; secondly, the propulsion system model of missile is built whose first two stages are solid rocket engines and the third stage is liquid - solid combined rocket engine. the nozzle and the shape of the engine are designed to meet the needs of the populsion project ; thirdly, the trajectory model of the mass point is built and a wavy trajectory is designed & optimized ; finally, the ability of a missile ' s breaking through defence is analyzed
以美國潘興導彈為原型，增加可兩次點火的末級發動機，改裝成具有跳躍能力的地地彈道導彈；首先，根據任務需求，建立了導彈的氣動模型，並建立了彈頭再入時高超聲速氣動模型；其次，建立了導彈推進系統模型，前兩級採用了固體火箭發動機，第三級採用了固?液組合火箭發動機，並在總體方案要求下，對發動機噴管和外形進行了設計；第三部分，建立了導彈質點彈道模型，設計了一條跳躍式彈道，並對跳躍式彈道進行了優化設計；最後，對導彈進行了突防能力分析，從分析的結果可以看出，跳躍式彈道的突防能力比常規的拋物線彈道要強。 -
Many test cases are calculated to verify the above study. the cases are either real or standard testing models, including multi - element airfoil, wing - body configuration, cone / cylinder missile model and 3 - d high - lift systems, etc. the results of present calculation are in good agreement with experiment data, and show flexibility and accuracy of the approaches. base on the cartesian grids, this thesis has targeted the development and integration of many algorithms and techniques such as adaptive refinement, omni - tree data structure, hybrid grid method, etc. an analysis software and research methods are designed and developed for the steady - unsteady and viscous - inviscid flow complex systems and configuration
7 .運用上述研究成果和結論，進行了大量算例的實驗驗證，外形范圍包括多種標模與型號，涉及多段翼型、 m6機翼、細長體模型、翼身組合體、兩段機翼增升標模、帶縫翼和襟翼的三段增升翼身組合體等復雜外形，計算結果均與實驗吻合良好，充分說明了本文發展的各種演算法、流場求解、網格生成方法的正確性和魯棒性。 -
Then according to system simulation technology, the overall air - to - ground attack simulation plan is made with the thought of models and layers. after that, the mathematical models of main parts in the simulation are made such as aircraft body, propulsive system, flight control system, fire control system, bomb and air - to - ground missile. on the basis of these mathematical models, using the object - oriented design methodology, a set of air - to - ground attack real - time visual simulation software is developed. this software can be used to aid aircraft design, research of air - to - ground attack tactics and flight training
本文首先介紹了現代戰爭中空對地攻擊的技術裝備及其特點，計算機模擬技術的發展以及面向對象的軟體設計思想；而後使用系統模擬技術，依據分層、模塊化設計思想，制定了空對地攻擊模擬系統總體設計方案；之後根據目前技術狀況，建立了戰斗機機體、推進系統、飛控系統、火控系統、航空炸彈、空地導彈等子系統數學模型；在此基礎上，利用面向對象的軟體設計思想，在基於pc的平臺上開發了一套對地攻擊視景模擬軟體，實現了戰斗機對地攻擊實時視景模擬。 -
This thesis first states the characteristics of the equipments that have been adopted by the modern fighter and their basic technical performance. then an overall layered modular design for air combat simulation system is made utilizing system simulation technology and critical sub - systems have been mathematically modeled known as fighter body, propulsive system, flight control system, radar, fire control system, gun, air - air missile and avionics. after that a set of distributed air combat simulation system software is developed based on the scene graphics pc platform
本文首先介紹了現代戰斗機空戰技術裝備及其基本技術性能特點；而後使用系統模擬技術，依據分層模塊化設計思想，制定了空戰模擬系統總體設計方案；之後根據目前技術狀況，建立了戰斗機機體、推進系統、飛控系統、雷達、火控系統、航炮、空空導彈、航電設備等戰斗機關鍵子系統數學模型；在此基礎上，根據總體設計方案，在基於pc的分佈互動式視景模擬平臺上開發了一套分散式空戰模擬系統軟體，實現了戰斗機互動式飛行模擬和分散式空戰模擬。 -
According to flight dynamics, a particle model and an attitude model in launching coordinate system and in quasi missile body coordinate system are established, the influence imposed by constant wind, thrust bias of the motor and connection bias are analyzed
應用飛行動力學理論，建立了發射坐標系與準彈體系下助推段和分離過程質點運動和姿態動力學模型，分析常風干擾、發動機推力偏差和裝配誤差影響等。 -
It can be seen from the deformation courses of the tubes that the local dents firstly occur at the beginning of impact. with the growth of the dents, the stiffness decreases, and the rigid - body translations and the whole deformations take place. the initial kinetic energy of the missile decreases rapidly to approximate zero during the course of impact, and the energy is transferred to internal energy and kinetic energy of the tube
同時，也得到了一些實驗中沒有觀察到的現象：從模擬的管梁的變形歷程可以看出，在沖擊瞬時，管梁先發生局部凹陷，隨著局部凹陷的加大，管梁的抗彎剛度減小，然後太原理工大學碩士學位論文剛體平動和整體變形發生，而且速度越大，這種現象越明顯;子彈的入射動能在撞擊過程中急劇減小，撞擊結束后減小到可以忽略不計。 -
We generated its grid surface on the fuselage or missile body according to the geometry projection relation between aerodynamic components and the bilinear interpolation approach. finally, we successfully developed a new algebra grid generation technique in virtue of the improved four - boundary interpolation. in this thesis, we put emphasis on the researches of aerodynamic inverse design and drag reduction questions for airfoil and wing using euler equations and control theory proposed by jameson
（ 2 ）進行了應用控制理論和二維歐拉方程的翼型氣動反設計，以及有升力約束情形下翼型跨音速減阻問題研究，分別推導了相應的共軛方程及邊界條件的數學形式，並給出了相應的梯度求解公式形式，研究發展了共軛方程及梯度的數值求解方法，成功進行了多個翼型的反設計和減阻問題研究。 -
The directivity coefficient of the phased array antenna has been generalized and discussed. according to the formulations of microstrip antenna design theory, planar and cylindrical microstrip patch cell has been analyzed. we can conclude that the cylindrical microstrip patch cell has the performance of high gain, low thickness, high resonant frequency, uniform directivity diagram, and easy fabrication on missile body, so it is a good choice
本文根據微帶天線設計理論，分析了平面和柱面兩種微帶貼片單元，其中柱面微帶貼片單元增益高、厚度小、諧振頻率高、方向圖均勻，且較易加工製作在彈體上，適合在相控陣天線中做共形輻射單元。 -
Ours was the only missile with an undetectable body
我們的導彈是唯一可以隱形的導彈 -
The separation flows of the onera m6 wing, slender body of missile and delta wing are simulated, the simulation capability of b - l model on large eddy is tested, the computational results agree well with experimental data
對oneram6機翼、細長旋成導彈體和大后掠三角翼的分離流進行了模擬。檢驗b - l模型對大迎角分離流動的模擬能力，取得了較好的計算結果。 -
Analysis on strength of the orbit and attitude control section body for missile
導彈軌姿控艙體的強度分析 -
Thirdly, this dissertation briefly introduces the engineering estimation method of the aerodynamic heat and supplies the simplified formulas. not considering the rejection, the ablation and some other factors, the author calculates the stagnation heat flux and the non - stagnation field heat flux distribution of some fly situation as the example aerodynamic heat environment. finally, by using the ansys program, the thermal vibration characters of the plate and missile body structures with different materials is analyzed
這一方法提高了熱振動的分析效率；第三，簡要的介紹了工程上計算氣動熟的估算方法及熱流密度計算的簡化公式，在不考慮燒蝕以及質量引射等影響下，本文計算了幾種飛行條件下駐點和非駐點區的熱流密度分佈，作為本論文算例的氣動加熱環境。
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