Patent ID: 7229046
Filing Date: 2007-06-12
Classification: A63H,B64C,Y02T

Abstract:
1. A system for powering an aerodynamic control member on an aircraft comprising: a first aerodynamic member; a second aerodynamic member; at least one hinge which joins said aerodynamic members to one another wherein said aerodynamic members rotate in relation to one another around a single hinge line; at least one servo having a case and a rotational output shaft, said rotational output shaft having a central axis of rotation; a first means for attaching said case to said first aerodynamic member, wherein the central axis of said rotational output shaft is located on and is axially aligned with said hinge line, wherein said first means for attaching said case to said first aerodynamic member is a servo mount comprising: a pair of rigid plates of predetermined size and shape, said plates being positioned parallel to one another at a distance apart approximating a minor dimension of said servo case wherein said case is sandwiched between said plates; a structural means securing said plates in relation to one another creating a hollow box-shaped structure with an opening of sufficient size to slidably insert said servo between said plates; a relief in said first aerodynamic member of sufficient size and shape to insert said box-shaped structure within said member; a means for securing said box-shaped structure within said first member, whereby said servo is configured for slidable insertion therein; and a second means for attaching said rotational output shaft to said second aerodynamic member, whereby said servo precisely positions said aerodynamic members in relation to one another and the same rotational motion and direction of rotation is preserved throughout the system.