理論火箭 的英文怎麼說

中文拼音 [lǐlúnhuǒjiàn]
理論火箭 英文
theoretical rocket
  • 理 : Ⅰ名詞1 （物質組織的條紋） texture; grain （in wood skin etc ） 2 （道理;事理） reason; logic; tru...
  • 論 : 論名詞（記錄孔子及其門徒的言行的「論語」） the analects of confucius
  • 火 : fire
  • 箭 : 名詞（古代兵器） arrow
  • 理論 : theory
  • 火箭 : [航空] rocket; fire arrow; bird
  1. T crowe, et al. effect of spin on the internal ballistics of a solid - propellant motor r. aiaa 66 523

    曹泰岳，常顯奇，等.固體火箭發動機燃燒過程理論基礎m .長沙：國防科技大學出版社
  2. C t crowe, et al. effect of spin on the internal ballistics of a solid - propellant motor r. aiaa 66 523

    曹泰岳，常顯奇，等.固體火箭發動機燃燒過程理論基礎m .長沙：國防科技大學出版社
  3. D r greatrix. acceleration - base combustion augmentation modelling for non - cylindrical grain solid rocket motors r. aiaa 95 2876

    曹泰岳，常顯奇，等.固體火箭發動機燃燒過程理論基礎m .長沙：國防科技大學出版社
  4. 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。
  5. 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
  6. According to the " solid - particle " theoretical model, a theory model of the dynamic burning - velocity of a rocket - portfire in its igniting delay - time cannulation is established, a theory model of the dynamic delay - time is educed. the factors are analyzed, setting position and shape of a igniting delay - time cannulation that affect its igniting delay - time, the theoretical basis is offered to develop the high - level precision rocket - portfire in the air

    本文根據「固體粒子」效應理論，建立了點火延期管動態燃速數學模型，導出了點火延期管動態延時控制的理論計算模型，分析了火箭空中點火延期管的安裝位置及其形態對其延期時間的影響，為高精度火箭空中點火具的工程研製提供了理論依據。
  7. On the part of the theory of the automatic test technology used in the rocket engine ground test, on the basis of the architectures and standards of some typical automatic test systems ( ats ), the test action model, ats data model, database model and the universal instrument - driving model are established

    在火箭發動機地面試驗自動測試技術理論方面，在典型自動測試系統（ ats ）的體系結構和相關標準的基礎上，建立了火箭發動機地面試驗測試行為模型、 ats數據模型、數據庫模型和通用儀器驅動模型，然後，建立了面向火箭發動機地面試驗的開放式柔性ats體系結構軟硬體模型。
  8. It can be used not only to change the fire precision of the base bleed projectile, but also to improve the effect of reduction drag and expansion range. the calculating model of the secondary expansive pressure of the burning gas is constructed by means of analysis of the experimental resuits, it has been confirmed that the new base bleed unit can be designed, with the secondary expansive principle of the burning gas pressure. the engineering project of a hybrid base - bleed - rocket high - level efficient extended - range projectile is designed, with the secondary expansive principle of the burning gas pressure, the feasibility and the true worth of its engineering applications is validated in theory

    本文提出了底排燃氣壓力不隨外部壓力變化，既可改善底部彈射擊精度又可提高減阻效果的二次擴張原理，建立了底排燃氣二次擴張壓力的計算模型，並通過採用二次擴張原理的新型底排裝置與傳統底排裝置的對比試驗，驗證了新型底排裝置結構實現的可行性；完成了基於底排燃氣二次擴張高效增程原理的底排?火箭復合高效增程彈方案設計及其有關計算，從理論上驗證了其工程應用的可行性和實際價值。
  9. Abstract : this paper introduces the principles of doppler radar signal processing method in the modulation. it provides the processing method for projectile tracer time, the burst time, rocket engine working time, projectile spin and flight attitude from signal of doppler radar

    文摘:介紹了測速雷達調制域彈道信息處理方法的工作原理，詳細論述了從測速雷達信號中處理彈丸曳光時間、底排燃燒工作時間、火箭發動機工作時間、彈丸旋轉速度、飛行姿態角和擺動周期等彈道信息的方法。
  10. It has been maked for immediate and statistical analysis that the calculation about the work order parameter of the base - bleed - rocket is calculated in the taguchi method, its influencing trend is bring out in the open, the theoretical base is settled for confirming the greatest combination about the work order parameter of the base - bleed - rocket. the multi - objectile optimal design model is established that the indexes have been taked into account first and synthetically, such as physical parameter range lethality power strength and flight stability and so on, the program is compiled and the example is calculated. the true worth of the theoretical work in this paper is validated by flight experimentation of 130mm hybrid base - bleed - rocket extended - range principium projectile

    本文進行了底排?火箭復合增程彈工作時序參數正交試驗設計的直觀分析與方差分析，揭示了每個參數對射程計算的影響趨勢，為進一步確定底排?火箭工作時序參數值的最佳匹配組合奠定了理論基礎；建立了底排?火箭復合增程彈多目標優化設計模型，該模型首次綜合考慮了底排?火箭復合增程彈的結構特徵參量、結構強度性能、飛行穩定性、威力性能和射程指標，編制了相應的分析程序，進行了算例計算；完成了130mm底排?火箭復合增程原理樣彈的結構設計與飛行試驗，其試驗結果驗證了本文理論研究工作的實際應用價值。
  11. This paper discusses the design principles of rocket designing, engineering database and planar, three - dimensional accessory and constructional drawing in detail, including the dynamic assemble process. in the same time, the correlative result is given

    文中對火箭彈設計理論、工程數據庫的設計和二、三維零件圖、裝配圖的設計開發過程進行了詳細的闡述，給出了相應部分的設計結果。
  12. 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。
  13. A. ciucci, et al. numerical analysis of ignition transients in solid rocket motors

    余貞勇，固體火箭發動機翼槽內火焰傳播機理研究，西北工業大學博士論文， 2000 . 3 。
  14. 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。
  15. In the theoretical aspect, performance analytical model of was proposed, in which allowances were made to allow for variable cross - sectional area, include the heat release of chemical reaction, and allow for mass addition. software was generated, and performance of rocket ejector was analyzed accounting for heat release location, flow parameters and structural configuration

    在理論方面，建立了引射火箭模態的性能分析模型，該模型考慮了化學反應放熱、加質和變幾何截面的影響；編寫了相應的軟體，並結合放熱位置、流動參數和發動機結構進行了引射火箭的概念設計。
  16. The paradoxical result of a ball of negative matter chasing a rocket ship off into space at a constantly increasing speed is so bizarre that there must be some logical reason why negative matter cannot exist

    負物質球體以恆定的速率追逐火箭飛船這一似是而非的結論是如此的奇異古怪，一定要有符合邏輯的理由說明為什麼不存在負物質。
  17. In view of the fact that there are three types of a hybrid base - bleed - rocket extended - range projectile and they are different from each other in the general structural layout, their structural characteristics and the work performance of the two propellant units is analyzed in this paper

    本文針對三種總體結構布局形式不同的底排?火箭復合增程彈，分析了它們的結構特點和底排裝置、火箭裝置的工作特性，詳細討論了復合增程彈底排?火箭工作時序選擇對彈道特性的影響以及實現理論上最佳彈道的匹配條件。
  18. 6. using simulation data of cz - 2f launch vehicle fault simulation system, the result of simulation based on cz - 2f launch vehicle pitch direction indicate that hm filtering fault detect can assure whether fault occurs, and this method achieves a better robustness and improves detect accuracy

    以cz ? zf大型運載火箭作為研究對象，利用c2 ? 2f運載火箭故障模擬系統的模擬數據，使用h _濾波故障檢測方法對cz ? 2f運載火箭的俯仰通道進行了故障檢測模擬，通過對余量曲線的分析表明這種方法能較好的判斷故障是否發生，由此說明了利用h _濾波理論進行魯棒故障檢測的可行性。
  19. Criteria for the nonlinear dynamic stability of rotative vehicles are derived by the liapunov ' s first method and the routh - hurwitz stability criterion, this criteria can be applied to the dynamic stability analysis of controlled rotative missiles, projectiles and rockets

    應用李亞普諾夫第一近似理論和勞斯霍爾維茨方法導出了旋轉飛行器的非線性運動穩定性判據，這個判據可應用於有控旋轉導彈的運動穩定性分析，也可應用到炮彈和火箭彈上。
  20. On the other hand, quite a number of practical systems with numerous dimensions may have some fast variables taking on singular impulse characteristic, such as electric power system, control system of rolling mill assembly, biochemical process, nuclear reactor, control system of airplane and rocket, and chemical diffused reaction, etc. so, it is important to study the problem of robust control of singular system i n the domain of control theory

    一般這些不確定性並非不可度量的，通常能給出這些不確定性大小的某種約束，魯棒控制理論正是處理系統模型具有不確定性的有效方法。另一方面，在大多數維數很大的實際系統中，都有呈現奇異攝動特性的快變變量，如電力系統，冷軋機的工業控制系統，生物化學過程，核反應堆，飛機和火箭系統，以及化學擴散反應等。
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