performance of propellant 中文意思是什麼

performance of propellant 解釋
推進劑性能
  • performance : n. 1. 執行，實行，履行；完成；實現；償還。2. 行為，動作，行動；工作。3. 性能；特性。4. 功績；成績。5. 演奏；彈奏；演出；（馴獸等的）表演；把戲。6. 【物理學】演績。
  • of : OF ＝Old French 古法語。
  • propellant : n. 推進物，推進劑；（槍炮的）發射火藥；噴氣燃料。 high-energy propellant 高能燃料。 work horse propellant 【火箭】通用燃料。
  1. Abstract : in the paper the deterrent content and the concentration of diphenylamine dibuty l phthalate and centralite in finished product manufactured by two different methods were analyzed by high performance liquid chromatography, which can provi dereference for adjusting the technology of the propellant manufacture

    文摘:利用高效液相色譜儀分別測定了發射藥在兩種制備工藝中的鈍感劑鄰苯二甲酸二丁酯和二號中定劑的含量及鄰苯二甲酸二丁酸在其中的濃度梯度分佈，為調整發射藥制備工藝提供了參考。
  2. Analysis of nozzleless solid propellant rocket motor performance

    無噴管固體火箭發動機內彈道計算
  3. The reason of these improvements are discussed as a base of lower down the power level without the debasement of performance and the alter of propellant by hydrogen or hydrazine

    為今後進一步在確保性能的前提下降低發動機功率以及以氫氣、氮氣混合或者肼作為推進劑的電弧加熱發動機的探索和研製奠定了基礎。
  4. 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。
  5. 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。
  6. What the study of the software of configuration analysis of liquid propellant space propulsion systems solved is how to develop the software of configuration analysis of liquid propellant space propulsion systems using scientific software model based on the characteristics of liquid propellant space propulsion systems in order to improve the performance and reduce the mass etc. it ' s important that can save fees and improve corporation ' s ability of participating competition

    液體推進劑空間推進系統構型分析軟體研究所要解決的問題是如何根據液體推進劑空間推進系統的特點，通過運用科學的軟體模型開發液體推進劑空間推進系統構型分析軟體。其目的是為了提高推進系統性能、減少推進系統質量等。進行液體推進劑空間推進系統構型分析軟體研究對于節約國家經費、提高企業競爭力有著重要的意義。
  7. According to the experimental parameters of mpt, the main performance parameters of different propellants have been given by engineering performance computation under designed and working states, which has great importance for the experimental research and the future work. 2. for helium and argon, the factors which influence on mpt ' s vacuum steady work have been discussed such as the material of microwave tie - in, the distance between the probe and inner - conductor, the position of the inner - conductor, the input power of microwave, the mass flowrate of propellant and the vacuum pressure of environment, and the influence has been discussed of the microwave power and the mass flowrate of propellant on the pressure of the resonance cavity, thrust, reflected power and the temperature of the resonance cavity

    論文的工作和新見解主要包括： 1在設計狀態和工作狀態下，根據mpt的實驗參數，對mpt使用不同工質時的性能進行了工程估算，這對mpt現階段的實驗研究和今後的研究有重要的指導意義； 2對于he 、 ar推進工質，討論微波的接頭材料、探針與內導體的間隙、內導體的位置、微波的輸入功率、工質的質量流量以及環境真空度對mpt真空啟動和穩定工作的影響，並探討微波的輸入功率、工質的質量流量對諧振腔壓強、推力、反射功率以及諧振腔溫度的影響； 3對于n _ 2 、 h _ 2 、 nh _ 3 、 h _ 2o推進工質，主要討論與he 、 ar工質不同的特性，並從長遠的眼光和工程應用的角度，認為其可行性不容置疑，潛在優勢不可忽略，是未來mpt應用的主流推進工質。
  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. This is the theoretical foundation for simulating the gun interior ballistic performance using the closed vessel experiment. based on the functions from closed vessel experiments, the ballistic simulation results of maximum chamber pressure, muzzle velocity and p - t curves of a 105mm gun charged with ltsc nitroamine propellant at + 50c, + 15c and - 40 environmental temperature were in good agreement with experimental data

    在密閉爆發器實驗的基礎上，應用可視化程序對某105mm火炮採用低溫感硝胺火藥在+ 50 、 + 15和- 40環境溫度下的最大膛壓、初速以及膛壓?時間曲線進行了彈道模擬，模擬與實驗結果具有較好的一致性。
  10. 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。
  11. The research of propellant energy performance indicates that the special impulse and characteristic velocity are significantly depended on o / f ratio and weakly depended on chamber pressure

    過氧化氫和pe燃料組合的能量研究表明：發動機的比沖和特徵速度與配比密切相關，與燃燒室壓強關系不大。
  12. And the effect of the work order of the two propellant units to the performance of the trajectory and the matching conditions to obtain the theoretical optimum trajectory is discussed too. according to the ballistic speciality of a hybrid base - bleed - rocket extended - range projectile during base - bleed and rocket work, its physical parameter is non - constant, such as its mass position of mass centre polar and equatorial moment of inertia. after a mulriple ballistic model of constant physical parameter is established, a mulriple ballistic model of continuous and non - continuous physical parameter is educed and the program is compiled, the theoretical tool is constructed to study othe other pivotal technology of a hybrid base - bleed - rocket extended - range projectile

    本文根據底排?火箭復合增程彈其底排燃減阻和火箭助推階段的質量、質心位置、轉動慣量等結構特徵參量變化的彈道特徵，在建立底排?火箭復合增程彈結構特徵參量為不變常量的多元彈道計算模型基礎上，導出了結構特徵參量為連續變化量和非連續變化量的底排?火箭復合增程彈多元彈道計算模型，編制了相應的計算機數值分析程序，構建了研究底排?火箭復合增程彈其它關鍵技術的理論工具。
  13. The result shows that the movement of the propellant grains is complex and relative to the ignition system very much. guns with center tube ignition and flame - spreading system can alleviate the accumulation of the propellant effectively, and will have better performance

    結果分析表明：火炮點火後膛內火藥顆粒的運動情況十分復雜，其運動規律與點傳火的方式密切相關，點火孔均勻分佈的中心傳火管點火方式可以有效的改善發射過程中火藥顆粒在彈丸底部堆積的現象，獲得更佳的發射效果。
  14. Series chamber is a new technology on the basis of the mature technology of solid propellant. it can improve the propeller ' s kinetic energy through rebuilding the existed guns. it is important to the weapons " performance improvement in our country

    它以相當成熟的固體發射藥技術為基礎，通過對現有的火炮進行改造達到提高彈丸動能的目的，這對于改進和提高我國的武器性能具有重要的意義。
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