DEVICE FOR THE AIRCRAFT MODELS TESTING IN WIND TUNNELS Russian patent published in 2019 - IPC G01M9/00 

FIELD: aerodynamics.

SUBSTANCE: invention relates to the experimental aerodynamics, in particular to devices for the aircraft models testing in wind tunnels, and can be used to determine the aircraft stationary and non-stationary aerodynamic parameters system. Device contains adapter with the tested model mounting unit, installed by means of a hinge with the possibility of free rotation relative to the transverse axis in the prescribed limits on the bottom holder, placed in the wind tunnel working part, adapter angular position sensor with a sensitive element and an anchor, a force-measuring element located on the holder front part behind the hinge, and the model installation and starting mechanism from the given initial angle in the form of located in the holder body pneumatic cylinder, which rod interacts with the retainer and is connected to the catcher in the form of facing the adapter flaring with inclined and longitudinal with respect to the holder axis contact surfaces, interacting with attached to the adapter cam central part, retainer is made in the form of movable along the holder bushing, interacting with the cam peripheral parts. Device also contains an additional hinge providing the adapter free rotation in the specified limits around the transverse axis, perpendicular to the main hinge axis, and the adapter angular position sensor in the additional hinge with an anchor and sensitive element rotation plane. Sensing element is mounted on the holder along the main hinge axis, and fixed on the adapter anchor surface, facing the sensitive element, is made in the form of a cylinder, which axis is parallel to the additional hinge axis and is offset relative to the main one axis, and interchangeable wedge spacers between the tested model mount and the adapter body provide the intersection of the mount longitudinal axis and these hinges axes intersection point. At that, the model installation and start-up mechanism catcher flaring is made in the form of a funnel with a conical and cylindrical surfaces, coaxial with the said mechanism pneumatic cylinder rod, and the cam central part is made in the form of cylindrical pin with a spherical tip corresponding to the catcher cylindrical surface.

EFFECT: technical result consists in expansion of the AC aerodynamic characteristics range and the test conditions approximation to their full-scale flight conditions, in which the AC angular oscillations are spatial in nature.

1 cl, 13 dwg