小型巡飞弹电动推进系统设计及试验验证

为快速获得满足工程需要的小型巡飞弹电动推进系统,采用螺旋桨涡流理论和一阶电动机模型建立了电动推进系统效率计算模型。以巡飞弹巡航阶段电动推进系统效率最高为目标,将爬升阶段巡飞弹所需推力及对应的反扭矩作为约束对桨机参数进行了快速优化设计,得到了电动机与螺旋桨的设计指标。根据该设计指标开展了电动机测功试验,完成了电动机选型;利用Kriging代理模型对螺旋桨进行了详细优化设计,并计算了完整的气动参数。针对设计得到的巡飞弹电动推进系统开展了风洞吹风试验,结果显示螺旋桨理论计算与试验测试误差在85%以内,巡航阶段电动推进系统效率设计结果与测试结果误差在27%以内,表明所提出的电动推进系统设计方法合理有效,能够为此类巡飞弹设计提供一定程度理论指导。 

Design and test verification of small loitering munition electric-powered propulsion system

To obtain an electric-powered propulsion system meeting the engineering requirement of small loitering munition, the vortex theory and the first-order motor model were used to establish the efficiency calculation model of the electric-powered propulsion system. The parameters of the propeller and motor were quickly designed by taking the efficiency of the electric-powered propulsion system at cruise as the objective, and the thrust and maximum counter torque in climb as constraints. According to the indicators of motor and propeller, the motor dynamometer test was carried out and the motor selection was completed, the propeller parameters were optimally designed in detail by using the Kriging agent model, and complete aerodynamic parameters were calculated. The wind tunnel test was carried out for the electric-powered propulsion system of the small loitering munition. The results showed that the deviation between the theoretical calculation and the test of propeller was within 85%, the deviation between the design and test results for the efficiency of the electric-powered propulsion system at cruise was within 27%, showing that the design method of the electric-powered propulsion system is reasonable and effective, thus providing a reference for the design of small loitering munition.