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本文介绍了半实物数字仿真的模型校验技术,重点讨论仿真模型的正确性校验、仿真模型的误差分析、仿真模型的误差补偿问题,为取得正确的系统特性作为仿真试验的依据提供了基本保证。 相似文献
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本文将数字模拟方法与NASTRAN软件的非线性瞬态响应模块结合起来,用于求解在随机激励下非线性系统的随机响应问题,同时用该方法对一个典型结构(悬臂矩型板)进行了计算与实验,结果是令人满意的。 相似文献
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某海防导弹所使用的机电定时机的,存在着故障率高,指令装定精度低,精密机加件多,装配结构复杂等不足之处,影响了导弹的质量。数字化定时机构(含程序电压产生器)采用数字电路进行模拟装定,在不改变现段导弹的发控设备和弹上雷达的其他分机及测试设备的基地上,直接替换原机电式定时机构。经试验证明具有时间精度高,可靠性好,维修方便等优点。 相似文献
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由于数字计算机的时序工作方式,在数字计算机上进行连续系统仿真,要做到实时,常常在频带上受到限制。以Transputer为基础的数字仿真器,采用了并行处理技术和超大规模集成电路相结合,使仿真速度大大提高。 相似文献
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本文分析了将通用数字机作为实时数字仿真主机的可行性和需要解决的问题。在分析目前流行的几个主要操作系统性能的基础上,说明选用美国DEC公司的VAX/VMS操作系统作为仿真应用的优越性。着重论述了将DEC公司的VAX系列机应用于实时数字仿真的输入输出技术。 相似文献
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Numerical Investigation of Inlet Distortion on an Axial Flow Compressor Rotor with Circumferential Groove Casing Treatment 总被引:1,自引:0,他引:1
Huang Jian* Wu Hu School of Power Energy Northwestern Polytechnical University Xi’ an China 《中国航空学报》2008,21(6):496-505
On the base of an assumed steady inlet circumferential total pressure distortion, three-dimensional time-dependent numerical simulations are conducted on an axial flow subsonic compressor rotor. The performances and flow fields of a compressor rotor, either casing treated or untreated, are investigated in detail either with or without inlet pressure distortion. Results show that the circumferential groove casing treatment can expand the operating range of the compressor rotor either with or without inlet pressure distortion at the expense of a drop in peak isentropic efficiency. The casing treatment is capable of weakening or even removing the tip leakage vortex effectively either with or without inlet distortion. In clean inlet circumstances, the enhancement and forward movement of tip leakage vortex cause the untreated compressor rotor to stall. By contrast, with circumferential groove casing, the serious flow separation on the suction surface leads to aerodynamic stalling eventually. In the presence of inlet pressure distortion, the blade loading changes from passage to passage as the distorted inflow sector is traversed. Similar to the clean inlet circumstances, with a smooth wall casing, the enhancement and forward movement of tip leakage vortex are still the main factors which lead to the compressor rotor stalling eventually. When the rotor works trader near stall conditions, the blockage resulting from the tip leakage vortex in all the passages is very serious. Especially in several passages, flow-spillage is observed. Compared to the clean inlet circumstances, circumferential groove casing treatment can also eliminate the low energy zone in the outer end wall region effectively. 相似文献
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文提出一种关于再入飞行器程序机动飞行的制导方案。该方案利用辐射传感装置,精确地确定再入飞行器机动起点的位置。再利用捷联式惯导系统控制飞行器的落点。 相似文献