本文设计了一种用于飞行器双机编队飞行的风洞试验模型绳系并联支撑机构，模拟在周边有障碍物的有限空间通道中的飞行运动。文中以直升机为例，根据工况参数设计了双绳牵引并联机构作为飞行器模型的支撑，建立了基于可移动的滑轮铰点与直升机模型编队协同飞行的运动学模型，对系统的静刚度进行了分析，并通过实验验证了旋翼转动对该绳系支撑系统动刚度的影响，给出了在有限空间通道中模拟双机编队飞行与着陆过程中绳与绳之间、绳与模型之间的干涉算法，并对该支撑机构的绳系结构进行了干涉分析。分析结果表明，本文设计的支撑机构能有效解决模拟飞行器模型双机编队在有限空间中飞行运动时的支撑干涉问题，而且系统刚度达到低速风洞试验的稳定性要求，是低速风洞中支撑飞行器模型进行编队飞行试验的有效解决方案。

In this paper, a wire-driven parallel suspension mechanism for two aircraft models in formation flight is designed to simulate the flight motion in a limited space channel with obstacles around it in wind tunnel test. Taking the helicop-ter as an example, based on the working condition parameters, the double wire-driven parallel mechanisms are designed as the support of the aircraft model, and the kinematic model of the helicopter for cooperative motion between the movable pulley suspension point and the helicopters in formation flight is established. Furthermore, the stiffness of the system is analyzed. Additionally, the algorithm of interference between the wire and the wire, the wire and the model in the process of two aircraft models in formation flight simulated flying and landing in the lim-ited space channel is given, and the interference analysis of the wire structure of the support mechanism is carried out. The analysis results show that the support mechanism designed in this paper can effectively solve the support interference problem for two aircraft models in formation flight in the limited space channel is given, and the sys-tem stiffness meets the stability requirements of low-speed wind tunnel test. It is an effective solution for aircraft model formation flight test in low-speed wind tunnel.