面對面火箭 的英文怎麼說

中文拼音 [miànduìmiànhuǒjiàn]
面對面火箭 英文
surface to surface rocket
  • 面 : Ⅰ名詞1 （頭的前部; 臉） face 2 （物體的表面） surface; top 3 （外露的一層或正面） outside; the ri...
  • 對 : Ⅰ動詞1 （回答） answer; reply 2 （對待; 對付） treat; cope with; counter 3 （朝; 向; 面對） be tr...
  • 火 : fire
  • 箭 : 名詞（古代兵器） arrow
  • 面對面 : facing each other; face-to-face; front to front; vis-à-vis
  • 面對 : face; confront
  • 火箭 : [航空] rocket; fire arrow; bird
  1. A lot of engineering applications are carried out using our proposed method in this paper, such as thermal deformation measurement of a car lamp, analysis of the super low frequency harmonic vibration of a piezoelectric ceramic, dynamic mechanical behavior analysis of the ballistite material and so on

    在前面所提出的理論基礎之上，本文對該方法在實際工程中的應用做出了大量的工作。本文利用時間序列法實現了汽車前燈配光鏡的熱變形檢測、壓電陶瓷片的超低頻振動分析以及火箭固體燃料的動態力學特性研究。
  2. 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。
  3. Disigning coolant channel on the firebox of liquid rocket engine to loxodrome ( equal - angle helix ) groove can improve firebox coolant capability greatly. because the width dimension of loxodrome groove is narrow and the depth is deep, some machining methods are incapable, such as end - milling or electrochemistry. according to the peculiarities, a cnc disk - cutter - milling method which is composed of five motion axes with four simultaneously interpolated ones is researched. because most firebox generatrix is composed of complex curves, it is very difficult to get cnc cutting program with manual means. in order to deal with the problem, the loxodrome mathematics model is studied, and an auto - programming software system is developed. the software system can generate cnc cutting program of loxodrome on many kinds of turned surface. the constriction - distension segment of firebox is the most representative workpiece. the sharp changing of its generatrix slope makes loxodrome milling difficult. with the theory analyzing and practice cutting experiment, some applied techniques, which include milling mode and direction, choosing cutter diameter and cutting start point setting, are developed. adopting the technology above, tens regular workpiece have been manufacturing. the two - year manufacture practice has confirmed the validity and feasibility of developed loxodrome coolant channel milling method. the developed technology is also worth to be referenced to other similar workpiece

    將液體火箭發動機燃燒室的冷卻通道設計為斜航線（等傾角螺旋線）槽形，可以大幅度改善燃燒室的冷卻性能.斜航線冷卻槽的槽寬尺寸較小而槽深尺寸較大，所以無法使用棒銑刀銑削、電化學等加工方式.針對這些特點，提出了五軸控制、四軸聯動的數控片銑刀銑削加工方法.由於燃燒室外表面的母線輪廓復雜，手工編制數控加工程序難度大.為了解決數控加工程序的編制問題，研究了斜航線的數學模型，開發了自動編程軟體系統.使用該系統，可以生成多種母線輪廓回轉體外表面上的斜航線數控加工程序.燃燒室收斂-擴張段的母線斜率變化大，加工難度大，是斜航線冷卻通道加工的最典型工件.經過理論分析和實際切削實驗，研究了針對該類型工件的片銑刀直徑選擇、銑削方式和方向、刀具調整和起刀點的設置等多項實際的加工方案.採用上述的一系列技術，已經成功地加工了數十個合格工件.經過兩年多的實際生產過程應用，驗證了所開發的斜航線冷卻通道加工方法的正確性和可行性.這些加工技術的研製成功，對其他相似類型零件的加工亦具有參考意義
  4. Of all the discoveries of the outer atmosphere made possible by rockets and satellites, few equal in lmportance the revelation of the high radiation belts by van allen in 1958

    譯為:在所有藉助火箭和衛星才能獲得的對外層大氣的發現中，在重要性方面很少能與范艾倫1958年發現高層輻射帶相比。
  5. Because the propellant grain is viscoelastic material, the liner and adiabatic layer are also viscoelastic one, the interface debond problem is actually interface crack about elastic - viscoelastic or bi - viscoelastic materials. research about this problem relates to the knowledge of viscoelastic mechanics and interface fracture and combustion. numerical analysis method about interface debond on solid rocket motor is researched in this paper

    由於固體火箭發動機的推進劑藥柱是一種粘彈性材料，襯層和絕熱層也具有粘彈性性質，因此其界面脫粘問題實際上是彈性-粘彈性或雙粘彈性各向同性材料界面裂紋問題，對該問題的研究涉及到粘彈性力學、界面斷裂力學和燃燒學等相關學科。
  6. Clemens began his night by recording a flyout and a groundout to the first two batters he faced, and he appeared to be back at full strength

    火箭人在第一局面對前二位打者時，以一個飛球和一個滾地球出局開啟這場球賽，而他似乎已回到了滿滿活力的時刻。
  7. The improvement to internal ballistic calculation precision of solid rocket motor ( srm ) is important to capture target of missile. and to accomplish it ' s task. calculation of burning surface of propellant grain is essential to interinal ballistic performance calculation

    提高固體火箭發動機內彈道的計算精度對導彈準確捕獲目標、完成任務有著重要的作用，而發動機工作時瞬態燃面計算是內彈道性能計算的基礎。
  8. New developments in decision theory, artificial theory and dynamic analysis method are applied to evaluation the possible projects. the main contents in this paper are included as follows : first, has improved an format reasoning method based on multiple attribute utility model and knowledgebase theory ; second, has proposed complex utility model by improving the theory of multiple attribute utility ; third, has presented a kind of weapon intelligent decision support system, based on the complex utility model and developed with com / dcom criterion ; forth, this paper also has build the dynamic simulation model for long - rang multiple tube rocket launcher system, and the tire dynamic model has applied in the rocket launcher system dynamic simulation model ; fifth, through building the rocket - launcher contact model, this paper has analyzed the dynamic forces between the rocket and launcher ; finally, this paper has build the evaluation model of the project about improving existing rocket launcher to the launcher that using canister, and get the conclusion through using the widss. the studies in this paper not only proposed scientific warrant to the choice of projects in this pre - studied national defense task about improving existing rocket launcher to the launcher that using canister, but also can give other studied tasks with decision supported

    主要內容包括：在總結決策分析與專家系統規則庫技術的基礎上，提出了融決策分析與專家系統規則庫技術於一體的形式化推理機制，該機制能有效的將定量計算和定性知識融為一體，將規范的決策分析解題過程與專家系統特有的演化推理方法有機結合起來；在多屬性效用理論的基礎上，建立了一般形式的復式效用模型，並實用化了全相關乘式效用模型，提供了較完善的通用建模、分析和解釋功能：引入了com dcom組件技術，開發了基於組件的widss系統，該系統基於形式化推理機制，易於擴展，能夠面向多種決策問題，具有較強的通用性；建立了遠程多管火箭炮全炮動力學模擬模型，將充氣輪胎動力學模型、輪胎和路面的相互作用模型運用於多管火箭炮動力學模擬計算中；利用碰撞接觸理論，對火箭彈在定向器管內的運動受力情況進行了模擬計算；建立了遠程多管火箭炮箱式發射改進方案模型，並利用動力學模擬計算結果在widss系統中進行了方案性能評估。
  9. The remote sensing refers to air to ground one, namely from different working platform far away the ground ( for example gao ta, balloon, airplane, rocket, the artificial earth satellite, spaceship, aerospace craft and so on ), through the sensor, exploring the information ( radiation ) to the earth ' s surface electromagnetic wave, and after the information transmission, processes, estimation and analysis, it can be regarded as a kind of comprehensive technology of surveying and monitoring earth ' s resources and its environment

    摘要遙感是指空對地的遙感，即從遠離地面的不同工作平臺上（如高塔、氣球、飛機、火箭、人造地球衛星、宇宙飛船、航天飛機等）通過傳感器，對地球表面的電磁波（輻射）信息進行探測，並經信息的傳輸、處理和判讀分析，對地球的資源與環境進行探測和監測的綜合性技術。
  10. The influence of double - push accelerated velocity, spin - rate regularity and unfolding fins on air rocket dispersion and the mechanism of decreasing of air rocket dispersion are also studied respectively

    分別研究了雙推力加速度，轉速規律和尾翼延時張開，對地面火箭彈和航空火箭彈散布的影響，以及減小航空火箭彈散布的機理。
  11. As far as the system observation for accuracy evaluation of carrier rocket is concerned, there may exist different types of observed data and priors. heterogeneous information means that the different information describing the different characteristics of the same object. since all of the information is relevant to the same object, the fusion is possible. it is a key problem that how to fuse the heterogeneous information to obtain the better evaluation result. therefore, the different heterogeneous information and data is thoroughly studied, moreover, the mathematical description for information fusion of different parameter priors and data is constructed in this paper. based on their relationship between different parameters, indirect prior and observation data is transformed into prior in impact point observation space, which is fused with original prior by weight determined by maximum entropy rule to obtain the mixed posterior distribution. therefore, the test results can be given by combining posterior distribution and impact error observed data. then its application on evaluating guidance systematic error is elaborated as it applies trajectory tracking data, test value of coefficients of guidance instrumentation systematic error, impact point observation data and prior. especially, the advantage of this method lies in its application in case that guidance instrumentation systematic error may not be computed precisely. finally a detailed example on evaluation of carrier rocket is given to verify the theory

    為充分利用運載火箭觀測中的不同觀測空間和過程的信息來進行精度評估，針對該背景建立了異質先驗融合的數學描述.研究了飛行試驗中不同觀測空間和過程的異質先驗信息和數據，基於不同觀測過程的解析關系，將間接過程的先驗和觀測數據算出的后驗分佈轉換成落點觀測空間上的先驗，與原落點的先驗進行了最大熵加權融合，得到混合后驗分佈，從而結合落點觀測數據給出評定結果.在無法解算出精確的制導工具誤差系數的情況下，這種方法充分利用了彈道跟蹤數據、工具誤差系數的地面測試先驗值、落點先驗及落點數據，穩健性更好，準確性更高
  12. The results of static firing test shows that the thermal erosion properties, mechanical properties, tand thermal shock resistance of the c / sic composites can meet a demand for thermal - structure application in the area of aerospace such as liquid rocket thruster

    試驗發動機地面熱試車結果表明，該c / sic復合材料的力學性能、燒蝕性能和熱震性能優良，可滿足宇航工程中諸如液體火箭發動機推力室等對熱結構材料的使用性能要求。
  13. For the research requirement of the high g - load mobile missile srm, the work process of solid rocket motor under lateral overload is investigated by the use of theoretical analysis and numerical simulation methods involving the calculation of internal ballistics, the simulation of flow field and the analysis of structural integrity

    本文以高速機動防空導彈固體發動機研製需求為背景，採用理論分析和數值模擬方法，從內彈道計算、內流場模擬、結構完整性分析等幾個方面對橫向過載作用下固體火箭發動機工作過程進行了研究。
  14. Abstract : from engineering point of view, this paper presents several issues of interest and consideration strategy on failure mode analysis 、 monitoring control parameter selection of fault monitoring and detecting and hardware possibility assurance for monitoring control study of liquid propellant rocket engine for launchers

    文摘:本文從工程觀點出發，對開展運載火箭液體發動機故障監控研究所涉及到的失效模式分析、監控參數選取、故障監控方法和硬體可靠性保證措施等方面提出了若干值得注意的問題和考慮策略。
  15. The conclusion that the optimal secondary nozzle exit area generating the maximum thrust agrees well with the numerical simulation, indicating that the exit area of secondary nozzle should be optimized according to structure and flow parameters during design

    表明在引射火箭設計時，應結合引射火箭的結構和流動參數對二次噴管出口面積進行優化設計，以達到最佳推力性能。
  16. The experimental results indicates that the secondary mass flow increases with increasing of primary mass flow rate, but the bypass decrease because the primary mass flow rate increase more rapidly than secondary mass flow. the expansion configuration shows low thrust property due to low pressure in flow path. the secondary nozzle changes the pressure distribution in ejector combustor, and decreases bypass ratio, but obtain more completely mixing

    結果表明：二次流流量隨著一次流流量的增加而增加，由於二次流流量的增加速度低於一次流，引射系數減小；在純擴張式結構實驗中，引射燃燒室壓強很低，難以實驗推力增強；二次噴管改變了引射燃燒室的壓強分佈，降低了引射系數，改善了混合狀況能；對于本文的實驗結構，存在一個最優的二次噴管出口面積，使引射火箭推力最大，同數值模擬結果相吻合。
  17. Using the ipga and setting the terminal speed increment of the upper stage and the manufacture cost of cpkm as objective functions, the rocket motor are processed dual - objective optimization design that has six design parameters

    採用ipga演算法，以該運載火箭上面級末速度增量最大及cpkm發動機的製造成本最低作為目標函數，對該發動機進行了雙目標優化設計。
  18. Based on widely assimilating the internal and overseas researches, the theory and methods of solid rocket motor ( srm ) thrust vector measurement and the automatic test technology are studied detailedly and comprehensively by means of theoretical analysis, engineering implement and experimental validation. the results attained are as follows

    論文在廣泛吸收國內外研究成果的基礎上，藉助理論分析、工程實現和試驗驗證等手段，對火箭發動機地面試驗中的推力矢量測量理論與方法以及自動測試技術進行了系統深入的研究，取得了一系列研究成果。
  19. According to the definition and expression of the thrust, as well as the condition derived from them, a method of solid rocket ramjet thrust determination and its program are provided on the basis of engine ground simulation test

    本文以西北工業大學固體火箭沖壓發動機直連式試車臺為研究對象，探討固體火箭沖壓發動機地面試驗技術。首先，從推力的定義出發，建立了試驗中來流空氣流量、燃料流量與固體火箭沖壓發動機推力之關系。
  20. In the theoretical aspect, secondary combustion in ejectorjet and thermal throat was researched. theory of duct flow was conducted, the difference and homology between heat added flow and entropy fixed flow was described

    在理論研究方面，本文對引射火箭二次加熱及熱力喉道進行了研究，推導並分析了一般的管流理論，闡述了加熱管流與變截面等熵管流之間的異同。
分享友人
分享到 Line

分享到臉書