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气动布局参数对直升机飞行品质的影响

, PP. 54-58

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Abstract:

以UH-60A直升机为例,建立了适合于飞行品质评价的直升机非线性飞行动力学模型,对算例机模型进行配平验证,并计算了稳定性、操纵性导数.计算结果与参考数据吻合较好,证明模型可用.根据军用直升机飞行品质规范(GJB902—90),选取的典型气动布局参数,计算了不同参数下的直升机的动态响应特性和操纵特性,分析了飞行品质对设计参数的敏感性.结果表明,旋翼高度对各项飞行品质指标都有明显的影响,降低尾桨高度能显著提升滚转操纵功效的品质等级,尾桨纵向位置是影响偏航操纵功效和偏航操纵灵敏度的主要因素.

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