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实用新型
CN204184580U 一种飞行器桨叶力效测试装置 失效 - 放弃

一种飞行器桨叶力效测试装置
摘要：
本实用新型涉及一种飞行器桨叶力效测试装置，由桨叶（1）、风箱（9）、风扇（10）、电池（7）、支架（8）构成，风箱（9）正面与顶端均安装有风扇（10），风箱（9）内安装一支架（8），支架（8）左端连接一电池（7），支架（8）顶端安装一原位测试装置（a），其原位测试装置（a）右端连接一桨叶（1）；本实用新型的有益效果为：可以准确测量由桨叶产生的推力值；直接计算出电池、电机和桨叶之间的力效值；通过设计的滑轨，可以实现升力值的等效传递。
摘要（英）：

The utility model relates to an aircraft blade effort testing device which is formed by a blade (1), an air bellow (9), fans (10), a battery (7) and a support (8). The fans (10) are arranged on the front face and the top end of the air bellow (9), the support (8) is arranged in the air bellow (9), the left end of the support (8) is connected with the battery (7), an in-situ test device (a) is arranged at the top end of the support (8), and the right end of the in-situ test device (a) is connected with the blade (1). The aircraft blade effort testing device has the advantages that the value of thrust generated by the blade can be accurately measured; the effort value among the battery, a motor and the blade can be directly calculated; a sliding rail is designed, and therefore the equivalent transmission of a lift force value can be achieved.

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