Testing apparatus, systems and methods for statically determining free play of aircraft control surfaces

摘要

Testing apparatus, systems and methods are provided to obtain measurements pertaining to aircraft control surfaces mounted to stationary aircraft structures for displacements about a hinge axis. A support structure and an actuator carried by the support structure may be provided, the support structure including attachment assemblies for positionally fixing the testing apparatus to the stationary aircraft structure. The actuator carried by the support structure includes a rectilinearly movable actuator shaft which contacts the aircraft control surface when the support structure is positionally mounted to the stationary aircraft structure. Actuation of the actuator will thereby cause the actuator shaft to apply a load to the movable aircraft control surface to cause deflection thereof about the hinge axis.

主权项

1. A static free play testing apparatus for determining free play of a moveable aircraft control surface which is mounted to a stationary aircraft structure for displacements about a hinge axis, wherein the testing apparatus comprises:
an elongate support structure having opposed first and second ends; first and second attachment assemblies operatively associated with the support structure for removably positionally fixing the support structure to the stationary aircraft structure, wherein
(i)the first attachment assembly is positioned at the first end of the elongate support structure for positional fixation to the stationary aircraft structure, and the second attachment assembly is spaced from the first attachment assembly toward the second end of the support structure for positional fixation to the stationary aircraft structure adjacent to the moveable aircraft control surface, and wherein(ii) each of the first and second attachment assemblies comprise an adjustable stem connected to the support structure for allowing linear adjustments of the stem, and a suction CUP attached to a terminal end of the stem for placement against a surface of the stationary aircraft structure; an actuator carried by the second end of the support structure, the actuator having a rectilinearly moveable actuator shaft which extends from the actuator at the second end of the support structure and contacts the moveable aircraft control surface when the support structure is removably positionally fixed to the stationary aircraft structure by the first and second attachment assemblies, wherein actuation of the actuator causes the actuator shaft to sequentially apply compression and tension loads the moveable aircraft control surface to cause respective deflections thereof about the hinge axis; a load cell operatively connected to the actuator shaft for sensing the sequentially applied compression and tension loads to the aircraft control surface and outputting a signal indicative of resistance forces thereto, and a displacement transducer having a transducer support that is capable of being removably fixed to the stationary aircraft structure, the displacement transducer being positioned in operative contact with the moveable aircraft control surface to output a deflection measurement signal indicative of the moveable aircraft control surface in response to movement of the moveable aircraft control surface by the sequential application of the compression and tension loads.