首页> 外国专利> a study of parametric resonance in the u0430u0432u0442u043eu043au043eu043bu0435u0431u0430u043du0438u044fu0445 on u043au0440u0435u043du0443 aerodynamic models

a study of parametric resonance in the u0430u0432u0442u043eu043au043eu043bu0435u0431u0430u043du0438u044fu0445 on u043au0440u0435u043du0443 aerodynamic models

机译:在 u043a u0440 u0435 u044f u0445气动模型上对 u0430 u0432 u0442 u043e u043a u043e u043b u0435 u0435 u0431 u04330 u043d u043d

摘要

a study of parametric resonance in the u0430u0432u0442u043eu043au043eu043bu0435u0431u0430u043du0438u00a0u0445 on u043au0440u0435u043du0443 aerodynamic models, including the model in the flow of a wind pipe s, finding her at the angle of attack in which the u0432u043eu0437u0431u0443u0436u0434u0430u044eu0442u0441u00a0 u0430u0432u0442u043eu043au043eu043bu0435u0431u0430u043du0438u00a0 and changing their parameters, u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 whatin order to u043fu043eu0432u044bu0448u0435u043du0438u00a0 accuracy u043cu043eu0434u0435u043bu0438u0440u043eu0432u0430u043du0438u00a0 real flight conditions of an aircraft by u0437u0430u0434u0430u043du0438u00a0 parametric perturbations on the angle of attack, after the withdrawal of mo new delhi at the angle of attack are oscillatory u043fu0435u0440u0435u043cu0435u0449u0435u043du0438u00a0 it vertically, with a continuously u0438u0437u043cu0435u043du00a0u044eu0449u0435u0439u0441u00a0 u0438u0437u043cu0435u0440u00a0u044eu0442 frequency and frequency of these movements.
机译:在 u043a u0440 u0435 u00a0 u0445上的 u0430 u0432 u0442 u043e u043a u043e u043d u043d u00a0 u0445中的参数共振研究,包括空气动力学模型,包括风管s中的模型,以 u0432 u043e u0437 u0431 u0441 u0443 u0436 u0434 u0430 u044e u0442 u0441 u00a0 u0430 u0432 u0442 u043e u043a u043e u043b u0435 u0431 u0430 u043d u0438 u00a0并更改其参数 u043e u0442 u043b u0438 u0447 u0430 u044e u0449 u0438 u0439 u0441 u0441为了达到 u043f u043e u0432 u044b u0448 u0435 u043d u0438 u00a0精度 u043c u043e u0434 u0435 u043b u0438 u0440 u043e u043e u0432 u0430 u043d u0438 u00a0真正的航班 u0437 u0430 u0434 u0430 u043d u0438 u00a0在迎角上的参数扰动引起的飞机状况,在以迎角移开新德里之后,是振荡性 u043f u0435 u0440 u0435 u043c u0435 u0449 u0435 u043d u0438 u00a0垂直并连续y这些移动的频率和频率以及这些动作的频率。y u0438 u0437 u043c u0435 u043d u0040 u0441 u00a0 u0438 u0437 u043c u043c u0435 u0440 u0040 u00a0 u044e u0442

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