Flight test system for flapping-wing aerial vehicle

摘要

A flight test system for a flapping-wing aerial vehicle includes a host computer platform, a measurement mechanism, and a wind tunnel. The measurement mechanism is configured to mount a to-be-tested flapping-wing aerial vehicle prototype. The measurement mechanism includes an Euler angle controller, a flow angle controller, and a tripod. The flow angle controller is mounted on the tripod. The Euler angle controller is in transmission connection with the flow angle controller. The flapping-wing aerial vehicle prototype is detachably connected to the Euler angle controller by using a first connecting member. The host computer platform is in communication connection with the measurement mechanism and the wind tunnel, and is configured to control a wind speed of the wind tunnel and display a flight status of the flapping-wing aerial vehicle prototype in real time during test.