彈翼 的英文怎麼說

中文拼音 [dànyì]
彈翼 英文
missile wing
  • 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
  • 翼 : Ⅰ名詞1 （翅膀） the wing of a bird 2 （像翅膀的東西） the wing of an aeroplane etc : 鼻翼 wing of...
  1. In contrast to the aerodynamic winged vehicle, a true ballistic missile is controlled for only a few minutes at the start of its flight.

    與空氣動力有翼導彈大不相同，一枚真正的彈道導彈只在起飛的幾分鐘內受人們控制。
  2. At last, the effect on the outer ballistic trajectory characteristic after the ablation of hypersonic projectile wing has been analyzed

    最後，初步分析了高超聲速彈翼表面發生燒蝕后對其外彈道特性的影響。
  3. The soldiers marched in a half circle round something in the place where the ball had fallen, and an old cavalryman, an under officer, lingered behind near the dead, and overtaking his line, changed feet with a hop, got into step, and looked angrily about him

    士兵們從炮彈落下的地方呈弧形繞過去，年老的騎兵，側翼的士官，在陣亡的人員附近掉隊了，后來又趕上自己的隊伍，跳一跳，換一下腳步，合著隊伍行進的腳步，他很氣忿地回顧一下。
  4. If this load centroid is behind the elastic axis of the wing structure, then a nose-down twist of the main wing surface results.

    如果該載荷重心在機翼結構彈性軸之後，則引起主機翼表面前端向下的扭轉。
  5. With circumspection, as invariably when entering an abode his own or not his own : with solicitude, the snakespiral springs of the mattress being old, the brass quoits and pendent viper radii loose and tremulous under stress and strain : prudently, as entering a lair or ambush of lust or adder : lightly, the less to disturb : reverently, the bed of conception and of birth, of consummation of marriage and of breach of marriage, of sleep and of death

    謹慎地，就像每一次進入一座房子他自己的或並非他自己的的時候那樣，小心翼翼地，因為床墊子那蛇狀螺旋彈簧已經陳舊了，黃銅環和蝰蛇狀拱形擋頭也鬆鬆垮垮的，一用力過頭就顫悠顧慮周到地，就好像進入肉慾或毒蛇的巢穴或隱身之處似的輕輕地，省得驚動她虔誠地，因為那是妊娠與分娩之床，合巹與失貞之床，睡眠與死亡之床。
  6. The stability of the tiltrotor in the heli copter mode is analyzed aiming t a semi span soft - inplane tiltrotor model with an elastic wing

    集成了非定常動態人流方程與傾轉過渡狀態的多體動力學力程，建立了傾轉旋翼機時域非定常氣彈耦合分析模型。
  7. Finite element analysis of empennage of a special bullet

    某型特種彈尾翼片的有限元分析
  8. 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。
  9. 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。
  10. Creative design of folding fin mechanisms of missile based on yan ' s mechanical creative design procedure

    基於顏氏機構創造法的導彈翼面折疊機構方案創新設計
  11. The software designed for the system is validated by experiments and proved correct. the system can s imulate the real air - stream and put it on missile ' s wings to make them work under the same force environment as the real spread process, so the relationship of explosive stuff and attack angle can be calculated

    本文所設計的監控軟體已通過實際系統的驗證，說明整個系統的設計是合理正確的，能夠真實的模擬力矩，產生一種類似真實氣流阻力的載荷，並將其正確施加於彈翼（尾翼）上，使彈翼（尾翼）能在與展開過程中實際受力相同的狀態下工作。
  12. The interior temperature distribution and ablation model of projectile wing is established from general transmitting heat differential equation ; at the same time, the heat flow density and pressure distribution model of projectile wing is also established

    從一般形式的導熱微分方程出發，逐步建立了彈翼內部溫度分佈和燒蝕的數學計算模型；與此同時，建立了彈翼表面的熱流密度和壓力分佈的數學模型。
  13. The paper simulate the transient thermal response of projectile wing according to the simulation software, and discuss the ablation characteristic when the projectile wing is in different initial velocity, in different wing shape, in different atmosphere condition and in different material condition

    本文通過模擬軟體模擬了彈翼的瞬時燒蝕外形，並詳細討論了不同初速、不同翼形、不同氣象條件及不同材料條件下的燒蝕特性。
  14. Because these projectiles attain hypervelocity within the atmosphere and are subjected to enormous heating as well as aerodynamic loads, the survivability of the front region of projectile wing is very important for designer to consider

    由於這類彈丸在大氣中高速飛行，並受到劇烈的氣動加熱及空氣動力負荷的作用，因此，彈翼前緣部的生存能力就成為彈丸設計中必須要考慮的問題。
  15. The model is solved with the finite difference method, the simulation software is organized to simulate the transient thermal response of the front region of projectile wing such as those launched by electrothermal chemical guns

    採用有限差分法進行數值求解，並編制了較為通用的模擬軟體，用於模擬諸如由電熱化學炮發射的高超聲速穿甲彈彈翼前緣的瞬時熱效應。
  16. The load control system has already passed the test ' s validate. it shows that the design of whole system is correct. the system can truly simulate the real air - stream and put it on missile ' s wings to make them work on the same force situation as in the real spread process, so the relationship of explosive stuff and attack angle can be confirmed

    本文所設計的加載控制系統已通過實際系統的驗證，說明整個系統的設計是合理正確的，它能夠真實地模擬類似真實氣流阻力的載荷，並施加於彈翼或尾翼，模擬其在真實工作環境下的受力狀態，可以測算導彈攻角與火工品填藥量的關系。
  17. The first part improves the rigid of the structure and second part decreases the weight. a composite wing - cabin structure is analyzed and optimized in this paper. the result shows that the rigid and the weight of the structure are improved obviously

    本文通過對一個全復合材料的彈翼、艙段組合結構按上述方法進行了優化設計，計算結果表明，結構在剛度、重量方面均可得到明顯的改善。
  18. Numerical results are in good agreement with some data and the method and procedure presented in this paper are verified. and then the wing ? flutter characters of a missile wing are numerical simulated with the examples of a missile wing

    以某導彈翼面為算例，對彈翼的亞、跨、超音速的顫振臨界速度進行了數值計算，部分計算結果與風洞計算結果相比較，一致性很好。
  19. To overcome the shortcomings of low efficiency and high uncertainty in the measurment of wings ' cross section shape by using a templet, a nc non - contact measuring system is designed

    摘要為解決使用專用樣板進行彈翼測量效率低、誤檢率高的缺點，設計了一種數控非接觸測量系統。
  20. An profile evaluating method based on least square principle is described

    在該系統中給出了一種基於最小二乘原理的彈翼輪廓誤差評價方法。
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