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根据摆振简化理论推导了一种直升机的支柱式前起落架摆振动力方程。从摆振特性分析中可以看出,在某些状态下,起落架不需要提供阻尼也能保证摆振系统的稳定性。但随滑跑速度的提高,临界当量阻尼有增大的过程。随地面载荷的增加,临界当量阻尼也有增大。在所有状态下,安装在起落架上的减摆器都需要提供足够的阻尼,以保证摆振系统的稳定性。从摆振响应分析中可以看出,响应曲线跟摆振特性分析结果吻合,反证了分析求解过程的合理性。
According to the simplified theory of shimmy, a helicopter pedestal nose gear vibration equation is derived. From the analysis of shimmy characteristics, it can be seen that under certain conditions, the landing gear does not need to provide damping and can ensure the stability of the shimmy system. However, with the increase of running speed, the critical equivalent damping has an increasing process. As the ground load increases, the critical equivalent damping also increases. In all conditions, the landing gear mounted dampeners need to provide sufficient damping to ensure the stability of the shimmy system. From the analysis of shimmy response, it can be seen that the response curve is consistent with the shimmy analysis, which proves the rationality of the analysis and solution process.