推進劑結構 的英文怎麼說

中文拼音 [tuījìnjìjiēgòu]
推進劑結構 英文
propellant structure
  • 推 : 動詞1 （向外用力使物體移動） push; shove 2 （磨或碾） turn a mill or grindstone; grind 3 （剪或削...
  • 進 : 進構詞成分。
  • 劑 : Ⅰ名詞1 （藥劑; 制劑） a pharmaceutical or other chemical preparation 2 （某些有化學作用的物品） a...
  • 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...
  • 推進 : 1 （推動工作 使前進） push on; carry forward; advance; give impetus to 2 [軍事] move forward; dri...
  • 結構 : 1 （各組成部分的搭配形式） structure; composition; construction; formation; constitution; fabric;...
  1. This includes both the fundamental bending characteristics of the airframes and the propellant dynamics.

    這包括飛行器結構的基本彎曲特性和推進劑動力學。
  2. 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。
  3. As the air - breathing engine, the performance of solid rocket ramjet is determined not only by structure of engine and the performance of propellant, but also by flight condition

    作為吸氣式發動機，其性能不僅取決于發動機本身結構和推進劑性能，與飛行狀態也有密切的聯系。
  4. Different equations to corresponding components are presented by analysing and transformating the general equations of fluid routes, then static characteristics mathematical model of liquid propellant space propulsion system is presented. based on the data of static characteristics calculation, mass model of thruster, propellant, propellant tank, gas, gas bottle, pipe and valve is presented using both the method of statistical regression and the method of stress analysis, then corresponding mass model is presented. based on the characteristics of liquid propellant space propulsion systems, analyse the five phases ( concept and definition, design and improvement, manufactureing and arrangement, operation and ma intenance, disposal ) in which life cycle cost of liquid propellant space propulsion systems is cost separately, then discompsed structure of life cycle cost and model of life cycle cost are presented

    將組件分成氣路組件和液路組件，再對氣路組件和液路組件進行相應的分類，然後通過對通用流路方程進行分析和變換對不同類型的組件分別建立不同的方程，從而建立了一個適用於液體推進劑空間推進系統的靜態數學模型；根據靜態計算所得到的數據，應用統計回歸法和應力分析法分別建立推力室、推進劑、推進劑貯箱、氣體、氣瓶以及導管和活門等的質量模型，從而建立相應的質量模型；結合液體推進劑空間推進系統特點，對液體推進劑空間推進系統全壽命周期費用發生的五個階段（概念和定義、設計和改進、製造和安裝、運行和維修、處理）分別進行分析，建立了液體推進劑空間推進系統全壽命周期費用分解結構和全壽命周期費用模型。
  5. Second, the concept of unified modeling language is describled, and its " 4 + 1 " views ( use case view. logical view, implementation view, process view, deployment view ) are describled based on the characteristics of liquid propellant space propulsion systems. software process model, the concept of iteration and increment, the concept of software development based on risks, sysnerty software process model are describled ; software model of the study of the software of configuration analysis of liquid propellant space propulsion systems is presented in this paper using unified modeling language and synergy software process model

    然後本文闡述了統一建模語言的概念，並結合空間推進系統特點分別對統一建模語言的「 4 + 1 」結構視圖（用例視圖、過程視圖、邏輯視圖、實現視圖、部署視圖）進行了闡述；闡述了軟體過程模型和迭代、增量及基於風險的軟體開發的概念以及synergy軟體過程模型；應用統一建模語言和synergy軟體過程模型建立了液體推進劑空間推進系統構型分析軟體的軟體模型。
  6. The antiablation of silicone rubber liner can be improved both by changing the structure of unvulcanized rubber and adding antiablative fillers, and the bond strength between propellant charge and the liner would be increased largely by coating the primer liquid on the charge surface

    硅橡膠包覆層中填料的粒徑對硅橡膠的補強效果十分重要；可從改變生膠結構、添加耐燒蝕填料兩方面來改善硅橡膠包覆層的耐燒蝕性；在推進劑藥柱表面上塗覆底塗液可以大幅提高硅橡膠包覆層與推進劑的粘接強度。
  7. Especially, when - bi together with a little carbon black ( cb ) or copper salt is used, the catalytic effect is better ; the flame structures of the double - base propellants containing - bi are similar to the typical plateau double - base propellant, but the combustion temperature distribution has been changed because of adding the - bi ; and the active components of catalysts deposit on the burning surface of propellants and the quenched surfaces of propellants with various catalysts possess different structure

    它與銅鹽和少量炭黑（ cb ）復合后，催化效果更優； 2 ， 4 -二羥基苯甲酸鉍加入后，推進劑的火焰結構保持了典型平臺雙基推進劑的結構特徵，但改變了雙基推進劑燃燒波溫度分佈，炭黑和銅鹽的加入對2 ， 4 -二羥基苯甲酸鉍的催化作用有很大影響；催化劑分解的活性組分富集在燃燒表面，不同催化劑使推進劑熄火表面形成不同的結構。
  8. Much works has been distributed to the development of a vacuum system to simulate the outer space and a measurement system to test the arcjet performance. ignition experiments in various operational modes have been done with argon as propellant. macroscopical working parameters including thrust, mass flow rate, voltage, current, inlet pressure and vacuity are obtained by the test measurement system and actual performance parameters including specific impulse, thrust efficiency, ratio of thrust and power and ratio of power and mass flow are calculated

    以氬氣作為推進劑，在不同工況下進行點火實驗，測量獲得了其工作推力、電弧電壓和電流、推進劑流率和弧室壓力等宏觀參數，得到了不同實驗條件下其工作的實際比沖、推力效率、推力/功率比以及比功率等性能參數，分析了推進劑質量流率、電弧功率、電弧加熱發動機電弧室結構尺寸等因素對其性能的影響，為數值模擬研究和實際的低功率電弧加熱發動機優化設計及研製提供了實驗基礎。
  9. 4. in order to further improve and raise storage, energy and combustion properties of boron - based fuel - rich solid propellant, while the present slurries of boron - based fuel - rich solid propellant can be cast and cured to form defect - free propellant grain, ap grading and metal fuels changing including variety and addition amount have been adjusted and investigated. the result shows that, after the adjustment, all the slurries can be cast to obtain structural perfect propellant grain which may be used to test various propellant properties

    4 、為了使現有含硼推進劑的燃燒等性能進一步提高和改善，同時為了能使現有含硼推進劑藥漿澆鑄后得到結構完整性和均勻性更好的藥柱，在2 、 3研究的基礎上，對ap的級配、低燃點金屬燃燒劑的品種和加入量等進行了較深入的研究，結果表明：這些組分進行調節后的各藥漿的流平性變化均能滿足澆鑄要求，並製成能進行推進劑其它性能測試的小方坯。
  10. The simulations results show that the spoiler is available to make the fuel and the oxidizer coming from the former to stay in the cavity for a long time, to let the fuel and oxidizer mix and burn completely. since there is a high temperature zone forming by vortex in the middle of the motor, it required a restricted thermal protection. the plate with holes decreased the vortex function in the cavity, which could not promote the combustion efficiency, but to decrease temperature in the cavity and be benefit to thermal protection of the wall

    計算結果分析表明:擾流板可以使燃料和氧化劑在擾流腔內的滯留時間加長，促進燃料與氧化劑的摻混燃燒，提高燃燒效率，但由於渦流在發動機的中間部位形成了高溫燃燒區域，致使局部燃料和絕熱層燒蝕速率增大，加大了熱防護的難度;孔板結構減弱了擾流腔內迴流區的漩流作用，不能增加推進劑燃燒效率，但可以使擾流腔內的溫度降低，給壁面熱防護帶來好處。
  11. According to the meso - scale structural characteristics of composite solid propellants ( csp ), the damage modes in csp induced by mechanical impacts, and the conclusions of former research, crack friction is considered to be the key factor for csp hot - spots

    本文根據固體推進劑細觀結構特徵及撞擊載荷作用下的損傷破壞模式，結合相關理論分析結果，將裂紋摩擦作為推進劑熱點形成的關鍵因素。
  12. Level set method was used in this paper to attain burning surface variety regulation of arbitrary configuration grain by tracing interface of grain surface burnback. the work of this thesis can be summaried as follow : 1

    本文運用等值面函數法（ levelset ） ，追蹤固體推進劑燃燒界面的變化，從而獲得了任意結構型面裝藥的燃面變化規律，本文的主要工作及創新點概括如下： 1
  13. The method of getting data from accounting system is easy, rapid, correct, so discompose the cost using the principals of accouting when building the discomposed structure of life cycle cost

    由於從會計信息系統得到費用數據這一獲取費用數據的方法具有方便、快捷、準確的特點，所以在建立液體推進劑空間推進系統全壽命周期費用分解結構時用會計的原則進行費用分解。
  14. One approach consists of varying only the total flow thereby maintaining the same thrust chamber hardware.

    有一種方法是僅改變推進劑總流量，而推力室結構保持不變。
  15. Changzheng long march 2f consists of ten subsystems : rocket body, control system, propulsion system, malfunctioning detection and management system, escape system, remote monitoring system, telemetry safety system, propellant utilization system, additional system and ground facilities

    運載火箭有箭體結構控制系統動力裝置故障檢測處理系統逃逸系統遙測系統外測安全系統推進劑利用系統附加系統地面設備等十個分系統。
  16. It is difficult to separate the inherent stability of the element configuration from that of the propellant inlet state.

    很難把單元結構的固有穩定性與推進劑進口狀態分開。
  17. Laws are drawn, disadvantages are explained and solve is suggested. according to the conclusion of tests, changes are made toward the structure. lot ' s of tests are carried out under different conditions

    針對改進后的結構，本文在各不同推進劑質量流量、不同弧電流的工況之下進行了系統的性能測試，並將所得到的結果與改進前的結論進行了比較。
  18. According to the change of the chemical properties and the mechanical properties obtained from the tests, the simulation of interior ballistic and the structural integrity analysis for these motors were conducted

    根據試驗測得的推進劑化學性能和力學性能的變化，對不同貯存期的發動機進行了內彈道和結構完整性計算。
  19. Last, the result is compared with the result of analytic method. this paper provides a new method to analyze the grain structural integrality. the result provides the gist of grain figure in optimize design

    通過這些計算和分析，為底排?火箭彈助推火箭推進劑藥柱結構完整性分析的有限元法提供參考，為藥柱藥形的優化設計提供依據。
  20. Solid rocket motor ( srm ) grain is casted integrally from solid propellants. it is one of the important structural components and also provides fuels for srm. the reliability of srm grain should be paid great attention

    固體火箭發動機藥柱是由固體推進劑整體澆鑄而成的，既為發動機提供燃料，又是重要的結構組成部分，其安全性不容忽視。
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