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二次喷管
    Unstructured mesh was used in 3-D numerical simulation to simulate the influence of secondary nozzle on performance of rocket ejector, ejecting ability and mixing condition.
    应用非结构网格技术对引射火箭的流动进行了三维湍流数值模拟,分析了二次喷管对引射火箭总体性能、引射能力和混合状况的影响。
    It is shown that when the exit area of secondary nozzle and the fuel/oxidizer ratio is fixed, the increase of mass flow rate of secondary flow lead to the decrease of velocity of mixed flow, and increase of total mass flow rate. The synthetical result of these two phenomenon cause the increase of thrust of rocket ejector, but the increasing magnitude is relatively small, indicating that these is no necessary to claim large bypass ratio in rocket ejector design.
    结果表明:在固定二次喷管出口面积和氧/燃比的条件下,二次流(引射空气流)流量的增加引起混合气体出口速度的下降和总流量的增加,二者综合作用使发动机推力增加,但增幅不大,表明在设计发动机结构和工作参数时,不必过分追求大的引射系数;
    The results indicate that with decrease of exit area of secondary nozzle, the bypass ratio is decreasing, and the static pressure in integrated ejector combustor is increasing, and mixing condition becomes better.
    结果表明:引射能力随着二次喷管出口面积的减小而减小; 整体式引射燃烧室压强随着二次喷管出口面积的减小而上升,混合随之更为充分;
    There exists an optimal exit area of secondary nozzle to get maximum thrust of rocket ejector.
    存在一个最优的二次喷管出口面积,使发动机推力最大。
    The influence of primary flow and secondary nozzle geometry on ejector effect and thrust was investigated, and the approach to increase thrust of rocket ejector was found gradually.
    研究了一次流参数和二次喷管结构对引射效能和发动机推力的影响,找到了逐步提高推力的措施。
    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.
    表明在引射火箭设计时,应结合引射火箭的结构和流动参数对二次喷管出口面积进行优化设计,以达到最佳推力性能。
    There exists an optimal exit area of secondary nozzle to result in a maximum thrust of rocket ejector in the light of the investigated ejector chamber structure.
    在文中所研究的引射燃烧室结构条件下,存在一个最佳二次喷管出口面积,它能使引射火箭的推力达到最大。
 

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