propellant combustion 中文意思是什麼

propellant combustion 解釋
推進劑燃燒
  • 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。
  • combustion : n. 1. 燃燒，發火，點火。2. （有機體內營養料的）氧化。3. 騷動。
  1. 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。
  2. The experimental study on the thermal aging combustion property of the composite modified double base propellant and its life - time calculation

    改性雙基推進劑熱老化燃燒性能試驗研究與壽命預估
  3. 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。
  4. The coating processes and quality checking methods for low temperature coefficient coated high - energy nitroamine propellant have been studied based on the experiment data treatment and comparison of ltsc propellant combustion properties in closed vessel with that in gun, we found that there are some combustion functions in closed vess el are similar to that in gun

    通過對低溫感硝胺火藥在密閉爆發器和火炮膛內實驗數據的處理與比較，找出了其在爆發器和火炮膛內燃燒特徵相似的一些函數關系式，為利用密閉爆發器試驗模擬火炮彈道性能提供了基礎。
  5. As to the experimental study, a test system was designed firstly, which include propellant feed system, cooling system, controlling system and measure system. secondly, a test engine was designed according to the experimental requirement. on this basis, experiments under different working conditions were done, and the results of them were analyzed, which showed the combustion efficiency and stability

    實驗方面，首先設計了針對三組元發動機推力室工作過程進行試驗的試驗系統，包括推進劑供應系統與冷卻水供應系統、控制系統以及壓力、溫度、流量的測量採集系統；其次，設計出符合試驗要求的縮尺發動機；最後針對所設計的試驗系統和發動機，進行了不同工況的試驗，對所得數據進行了分析處理，得到了不同工況下燃燒效率和燃燒穩定性特性。
  6. In this paper, simple reacting flow model in solid - propellant ducted rocket combustor based on eddy break - up model is established. the model is used to simulate the three - dimensional combustion flowfields in an experimental motor. some factors how to affect the combustion efficiency are discussed in the paper, including air intake and gas generator nozzle

    本文基於簡單反應的旋渦分裂模型，建立了固體火箭沖壓發動機補燃室內的湍流燃燒模型，並在該模型下對某實驗發動機進行了三維數值模擬，研究了補燃室設計參數包括進氣道出口設計參數和燃氣發生器噴管設計參數對燃燒效率的影響。
  7. 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。
  8. The results show that the thermodynamic properties of propellant combustion gas products have an important effect on its expanding power, and the correlation between conventional energy parameters such as impetus, potential energy and its power capability is not identical

    結果表明，發射藥燃氣產物的熱力學性質對其膨脹做功具有較大的影響，傳統的火藥力或潛能能量參數與做功能力之間的關系並非完全一致。
  9. In order to study the combustion process and the movement of propellant in the barrel, a multi - photo x - ray experiment system was designed. four groups of photos under different ignition systems were obtained, and these photos were manipulated with digital image manipulation technology. the gray degree of the photos was averaged, and the information, such as density, velocity of the projectile and the trace - indicating grains and confliction velocity of the propellant against the projectile under the consideration of the velocity of the projectile, was extracted and analyzed quantitatively

    本文就利用由多幅脈沖x光攝影技術所獲得的四種不同點火條件下的火炮膛內火藥顆粒群運動狀況的陰影照片，進一步利用數字圖像處理的技術及相關演算法，編制軟體對照片進行了處理，統一了照片的灰度，最終在定量上獲得了不同點火條件下的火藥顆粒的密度分佈規律、彈丸和示蹤藥粒的運動速度以及在考慮到彈丸運動的前提下的火藥顆粒與彈丸的撞擊速度。
  10. Measurement of small - signal gain on solid propellant combustion driven co2 gasdynamic laser

    2氣動激光小信號增益測量
  11. In order to investigate the effect of 2, 4 - dihydroxylbenzoate ( - bi ) on the combustion of double - base propellant, the combustion law of the propellants containing - bi was studied by means of the single frame amplification photography fl miniature thermocouple, the scanning electron microscopy ( sem ) and the link isis energy spectrum

    摘要為了探索2 ， 4 -二羥基苯甲酸鉍對雙基推進劑燃燒的催化作用，採用單幅放大彩色攝影法、型微熱電偶技術、掃描電鏡和電子能譜研究了含2 ， 4 -二羥基苯甲酸鉍雙基推進劑的燃燒規律。
  12. The composite propellant with mini al content is studied for the special motor propellant grain, which is required to be constant in energy while the internal ballistic property and combustion products change instantly

    為滿足瞬間變換內彈道和燃燒產物而能量不變的特殊發動機裝藥要求，設計了微鋁含量復合推進劑配方。
  13. Abstract : the composite propellant with mini al content is studied for the special motor propellant grain, which is required to be constant in energy while the internal ballistic property and combustion products change instantly

    文摘:為滿足瞬間變換內彈道和燃燒產物而能量不變的特殊發動機裝藥要求，設計了微鋁含量復合推進劑配方。
  14. The physical and chemical processes of nozzle atomization and the evaporation, mixing and combustion of propellant drop flow are very complex. for the reason, the researches on nozzle are still based on the experimental research now in or abroad

    由於噴嘴霧化及其噴霧流的蒸發、混和和燃燒是一個非常復雜的物理化學過程，目前國內外對噴嘴的研究仍以模型實驗研究為主。
  15. This deduction forms the basis of the two-temperature postulate for composite propellant combustion.

    這種推理就是構成復合推進劑燃燒中兩溫概念的基礎。
  16. Liquid propellant combustion processes are quite complicated and defy precise analytical description.

    液體推進劑燃燒過程是相當復雜的，很難對其進行嚴謹的分析描述。
  17. In order to evaluate energy parameters of propellant accurately and impersonally, thermodynamic parameters of different propellant formulations were computed by potential energy method, and the correlations between the thermodynamic parameters and expanding power capability of propellant combustion gas in barrel weapon were researched

    摘要為了更加準確和客觀地評價發射藥的能量參數，採用內能法計算了不同組分發射藥配方的熱力學參數，研究了發射藥燃燒氣體在身管武器中的膨脹做功能力與熱力學參數的相互關系。
  18. The dynamic aspects of the combustion process are determined primarily by the injection pattern, the propellant combination, and the operating conditions.

    燃燒過程的動力特性主要由噴射型式，推進劑組合及工作條件來確定。
  19. As to the simulation, the inner flow field of thrust chamber was simulated. here the thrust chamber was treated as a two - dimension problem. the simulation model involved injection, mixing and combustion of gaseous propellant

    模擬方面，對三組元發動機推力室的穩態燃燒過程進行了數值模擬，分析了推進劑各組元和各燃燒產物組分在推力室內的分佈。
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