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基于自由尾迹/面元法的耦合方法,建立了一种旋翼气动干扰模型和直升机配平计算模型.采用自由尾迹方法和升力面理论计算旋翼尾流带来的气动干扰,使用三维面元模型代替机身,采用涡镜像法模拟机身对尾迹的诱导和堵塞.以UH-60A直升机为算例,基于耦合方法,分别计算了旋翼尾迹形状以及尾迹对机身、平尾和尾桨的下洗速度,并与风洞试验结果对比.最后将自由尾迹/面元耦合法与直升机飞行力学模型嵌套,完成了配平计算,并与试飞结果和涡粒子模型计算结果进行了对比,结果的一致性证明了本方法的有效性.
Based on the free wake / face method coupling method, a rotor aerodynamic interference model and a helicopter trim calculation model are established. The aerodynamic interference caused by the rotor wake is calculated by using the free wake method and the lift plane theory. The 3D plane model is used instead of the machine Body, using the vortex mirror method to simulate the fuselage induced wake and blockage.U-60A helicopter as an example, based on the coupling method, respectively, calculated the shape of the wake of the rotor and wake on the fuselage, tail and tail rotor wash rate, And compared with the wind tunnel test results.Finally, the free wake / face-element coupled method is nested with the helicopter flight mechanics model, and the balance calculation is completed and compared with the results of the test flight and the eddy particle model. The consistency of the results proves The effectiveness of this method.