火箭結構 的英文怎麼說

中文拼音 [huǒjiànjiēgòu]
火箭結構 英文
rocket structure
  • 火 : fire
  • 箭 : 名詞（古代兵器） arrow
  • 結 : 結動詞（長出果實或種子） bear （fruit）; form （seed）
  • 構 : Ⅰ動詞1 （構造; 組合） construct; form; compose 2 （結成） fabricate; make up 3 （建造; 架屋） bui...
  • 火箭 : [航空] rocket; fire arrow; bird
  • 結構 : 1 （各組成部分的搭配形式） structure; composition; construction; formation; constitution; fabric;...
  1. Impulsive loads for structural tests have been generated by explosive cartridges or by small rockets.

    人們曾用過彈藥筒的爆炸或用小型火箭來產生結構試驗所需的脈沖荷載。
  2. At the same time, we colligated general math models and solving methods of reliability which are on using now. all of the models and methods have been compared and analysed

    結構可靠性設計是固體火箭發動機研究工作中的重要內容。採用可靠性設計方法，可以確保發動機實現預定的質量指標。
  3. Abstract : solid propellant rocket motors are preferred for most ballistic missiles because they need simple maintenance and can be launched quickly. but the conventional thrust termination devices limit the depletion of every stage ' s grain and increase some extra - weight. an improved method for designing a multi - stage solid rocket based depleted shutdown was provided. in order to solve the problem of lack of thrust termination devices, a device to adjust the burnout angle will match the final burnout velocity and satisfy the desired range. the method can also limit the detection from anti - ballistic missile system

    文摘:由於維護簡單和發射快速，彈道導彈多用固體火箭發動機，但繁雜的推力終止裝置使各級裝藥不能耗盡並讓結構增重.提出了一種對基於耗盡關機多級固體火箭概念設計的改進方法，此方法滿足導彈系統主要的戰技要求.為解決無推力終止裝置的末速不準問題，可在末級發動機採用姿態調整裝置，對射角進行調整，配合末速以滿足射程要求.本方法還可抑制敵方反導探測
  4. The solid rocket ramjet, which combines the techniques of ramjet propulsion and solid rocket propulsion, offers the following advantages for missile propulsion : high specific impulse, simple configuration, high credibility, convenient using and high maneuverability

    固體火箭沖壓發動機結合了沖壓技術和固體火箭技術，具有比沖高、結構緊湊、工作可靠、使用方便、機動性好等優點，是新一代超聲速戰術導彈的優選動力裝置。
  5. 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。
  6. 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。
  7. Hence, it is very significant to analyze the mechanism and extend law of interface debond of solid rocket motor

    因此，研究固體火箭發動機界面脫粘的機理和擴展規律，是固體火箭發動機結構完整性分析的重要課題。
  8. Interface debond between propellant and liner is a key form of failure of the structure integrity in the analysis of solid rocket motor

    在固體火箭發動機結構完整性分析中，襯層/推進劑藥柱粘接界面的脫粘是完整性被破壞的關鍵形式之一。
  9. 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。
  10. Added a security measure to prevent an occasional bug where your smaw rocket continuously fires

    增加了一個安全測量數據結構以防止一個偶然出現的smaw火箭發射器不斷的發射的錯誤。
  11. The solid - propullant ducted rocket, which combines the advantages of solid propullant rocket and ramjet propulsion, is a new kind of combined propulsion system. it offers considerable advantages for missile propulsion, such as high specific impulse, high speed, light weight, long range, high maneuver and simple structure. as the major direction of the propulsion system for supersonic missile, the ducted rocket has good prospects

    它將固體火箭技術和沖壓技術有機結合在一起，具有比沖高、速度快、重量輕、射程遠、機動性能好和結構簡單等諸多優點，最大限度地滿足了新一代導彈對其動力裝置提出的要求，是超聲速導彈動力裝置的一個主要發展方向，有著廣闊的研究前景。
  12. Reliability analysis of solid rocket motor grains with response surface methodology

    固體火箭發動機藥柱點火過程結構可靠性的響應面法
  13. The saturn v rocket is sprouting plants and mold and its structure is home

    土星v號火箭正繁演各種植物及菌類還有結構體是溫床。
  14. The 110 - meter - long saturn v rocket is sprouting plants and mold and its corroded structure is home

    一百一十公尺高的土星v號火箭正繁演各種植物及菌類，還有它已腐蝕的結構體正是各種動植物匯集的溫床
  15. The 110 - meter - long saturn v rocket, which never got off the ground at johnson space center because nasa canceled the apollo program, is sprouting plants and mold and its corroded structure is home to an assortment of creatures, including a nesting owl

    因太空總署阿菠羅計畫的取消而未有機會從強森太空中心離開地面的一百一十公尺高的土星v號火箭，正繁演各種植物及菌類，還有它已腐蝕的結構體，正是各種動植物匯集的溫床，這包括一隻正在築巢的貓頭鷹。
  16. In other cases, civil engineers are assigned to work on a project in another field ; in the space program, for instance, civil engineers were necessary in the design and construction of such structures as launching pads and rocket storage facilities

    另外土木工程師還會被安排到另一些領域區工作，如太空開發計劃，在設計和建造一些結構如火箭發射架和儲存設施時，土木工程師就有必要參與其中的設計和建設。
  17. Gap design of solid rocket motor nozzle was analysized through thermal and structure analysis

    摘要通過熱和結構計算，對固體火箭發動機噴管縫隙設計進行了分析。
  18. 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。
  19. 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。
  20. 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。
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