In this paper, 6013al / sicp / gr metal matrix composite ( mmc ) was produced by spray codeposition, by means of changing the medium of quenching, influence of five types of heat treatment system ( furnace cooling, air cooling, water quenching, dry ice quenching, liquid nitrogen quenching ) and different aging temperature on the damping was studied systematically
本文採用噴射共沉積方法制備了6013al sicp gr金屬基復合材料( mmc ) ,通過改變淬
火介質,較為系統地研究了五種熱處理制度(爐冷、空冷、水冷、乾冰冷及
液氮冷)以及不同時效溫度( 120 、 150 、 170 、 190及210 )對6013al sicp grmmc阻尼性能影響。
Droplet ignition and extinction in practical combustors are strongly influenced by forced convection and turbulence.
在實際燃燒室中,
液滴點
火和熄
火受到強迫對流和紊流的強烈影響。
Long - hole and geometrical proportion type of mixing unit is finally adapted in lpg supply system, and power and torque output of lpg engine are improved by increasing compression ratio, and ignition characteristic is tried to adjusted to satisfy engine performance. meantime emission performance and noise level of lpg engine at full - throttle and other various part - throttle operations are tested and compared with former gasoline engine. ( 3 ) it is verified by engine dyno tests that lpg engine has better synthesized performance at aspects of power and torque, fuel economy, as well as emission than former gasoline engine
選擇了等比例長孔式混合器控制空燃比;通過提高壓縮比來彌補動力性的損失;以動力性為主控目標,對最大功率點、最大扭矩點、中等轉速、最低轉速點所對應的發動機轉速做了點
火特性的調節;通過空燃比的合理控制,直接改善發動機的動力性、經濟和排放指標;作為對缸內燃燒過程的理論分析,進行了燃燒特性的實驗測試;對原汽油機和新開發的
液化石油氣發動機,進行了外特性和部分負荷特性以及怠速的排放及噪聲對比性測試。
Through malfunction of the tests of 810 research institute, the combustion performance of the hybrid motor and model about regression rate have been studied in the dissertation. the main aspects are as follows : the performance of the hno3 + n2o4 - htpb hybrid rocket motor were all discussed
本文結合航天科技集團公司810研究所正在研製的ak - 20l / htpb + al組合固
液火箭發動機,開展了固
液火箭發動機混合燃燒特性的數值模擬工作,在此基礎上給出固體燃料退移速率預示模型及預示結果。
5. the internal ballistics and the throttling performance of 85 % h2o2 - pe hybrid rocket motor loaded with tube grain are studied. the hot firing data of two test motors have been carefully analyzed
研究了管型藥柱的85 h _ 2o _ 2 - pe固
液火箭發動機的內彈道性能和節流特性,分析了兩臺發動機的試驗結果。
The pressurized 85 % h2o2 - pe hybrid rocket motor test system has been designed and built up for the research work. the hot firing tests and the shutdown - restart of the motor were successfully performed. 2
設計和建造了85 h _ 2o _ 2 ? pe固
液火箭試驗發動機和擠壓式固
液火箭發動機試驗系統,並成功地進行了點
火和再啟動。
Because of their low - cost, high safety and reliability, flexible energy management and shutdown - restart ability, hybrid rocket motors have received increasing attention from the space propulsion specialist all over the world
固
液火箭發動機因具有低成本、高安全性和可靠性、靈活的能量管理和推力可控等特性,越來越受到國內外航天推進專家的重視。
Have evolved deep under the oceans at hydrothermal vents, where volcanic fluids rich in reduced chemicals served as an energy source, or in shallow geothermally heated waters on earth s surface, where these chemicals or sunlight could have provided an energy source for
這類生物可能在深海中的熱
液火山口處演化,那裡的熔
液含有豐富還原化學物,提供了生長和復制所需的能量又或在地球表面受地溫加熱的淺水處演化,從陽光或水中的化學物中攫取能源。
Through the tests of the 85 % h2o2 - pe hybrid rocket motor, the operation process of the hybrid motor has been studied in the dissertation. the main aspects are as follows : 1
本文結合85 h _ 2o _ 2 ? pe固
液火箭發動機試驗,從以下幾個方面比較系統地研究了固
液火箭發動機的工作過程: 1
The low frequency burning oscillation of the 85 % h202 - pe hybrid rocket motor is discussed
研究了85 hzoz ? pe固液火箭發動機的低頻振蕩燃燒現象。