Abstract: A photographic mirror assembly includes a mirror which comprises a plurality of panels that are movably coupled together thereby facilitating a user to see themselves from a plurality of angles. An image capturing unit is integrated into the mirror to capture images of the user. The image capturing unit can overlay various eyeglasses onto the user to facilitate the user to view themselves wearing various eyeglasses prior to purchasing eyeglasses. An actuator is coupled to the mirror spacing the mirror an adjustable distance from the vertical support surface. A remote control is in wireless communication with the image capturing unit and the actuator to facilitate the user to remotely control operation of the image capturing unit and the actuator.

Abstract: A photographic mirror assembly includes a mirror which comprises a plurality of panels that are movably coupled together thereby facilitating a user to see themselves from a plurality of angles. An image capturing unit is integrated into the mirror to capture images of the user. The image capturing unit can overlay various eyeglasses onto the user to facilitate the user to view themselves wearing various eyeglasses prior to purchasing eyeglasses. An actuator is coupled to the mirror spacing the mirror an adjustable distance from the vertical support surface. A remote control is in wireless communication with the image capturing unit and the actuator to facilitate the user to remotely control operation of the image capturing unit and the actuator.

Abstract: Initial retraction of telescoping cylinders (22, 72) forces hydraulic fluid through an orifice area into a low pressure chamber (116). When the cylinders (22, 72) reach a predetermined position, a stop surface (120) carried by the second cylinder (72) engages a floating member (52) carried by the first cylinder (22). Further retraction causes the floating member (52) to move relative to the first cylinder (22) and compress a high pressure chamber (44). When the shock strut (20) is pivoted into a stowed position, the cylinders (22, 72) are retracted to the predetermined position without compressing the high pressure chamber (44). In a second embodiment, a linkage mechanism (298) moves the high pressure chamber (318) relative to the first cylinder (272) to allow the shock strut (220) to be shortened beyond the predetermined position without compressing the high pressure chamber 318.

Abstract: An aircraft trailing edge flap assembly including a main flap and an aft flap are repositioned by a dual arm rotary actuator. One arm of the rotary actuator repositions the main flap by driving a carriage assembly along a linear track. The other arm of the rotary actuator repositions the aft flap by driving a bell crank assembly which is operatively connected to an aft flap support member extending downward from the aft flap. The aft flap support member is operatively connected to a main flap support member which extends downwardly and rearwardly from the rear portion of the main flap to operatively connect with a mounting member extending downwardly and rearwardly from the track so that the track mounting member supports the majority of aerodynamic load forces applied to the flap assembly. Both arms of the rotary actuator rotate together through a predetermined arc so that the aft flap and main flap remain in a nested configuration.

Abstract: A four bar linkage, between a hinge carriage segment and a translating door segment, of an outward opening overhead rotation plug type aircraft door, defines the relative movement between the two segments. A door handle actuates linkages that extend between the two segments to power the relative movement. When the handle is in either the down and the door locked position, or in the up and unlocked ready for outward rotation position, the linkage is overcenter so that the handle remains in position. A safety link extends between the two segments to provide fail safe locking at either handle position.

Abstract: Apparatus to compensate for airflow blockage and attendant airflow separation, loss of lift, and flap buffeting caused by the support members connecting a flap to the stationary portion of the wing is disclosed. An airflow duct, located between the lower and upper surfaces of the flap, is dimensioned and positioned such that when the flap is extended, air flowing through the airflow duct is discharged over the blocked portion of the upper flap surface. A recessed airflow channel, formed in the upper surface of the flap to direct additional airflow over the blocked region, is included for use in situations in which the flap structure precludes an airflow duct of sufficient size to fully compensate for the airflow blockage. Duct closure doors are included to seal the airflow duct inlet opening when the flaps are retracted to thereby reduce drag during operation of the aircraft in the cruise regime.

Abstract: An aerial refueling boom utilized in the transfer of fuel from a tanker airplane to a receiver airplane and more particularly, to the boom geometry or gimballing which comprises an axis fixed with respect to structure of the tanker airplane about which the boom rotates in elevation and an inclinable axis about which the boom rotates for lateral movement. The angle of inclination of the boom lateral motion pivot axis or azimuth axis varies with respect to the longitudinal axis of the airplane axis as the boom is changed in elevation angle. A pair of aerodynamic surfaces formed into a Vee and known as ruddevators are mounted towards the trailing end of the boom for flying the boom about these axes. The ruddevators are part of a control system which includes a pantographing cable system for automatically changing the angle-of-attack of the aerodynamic surfaces and for alleviating the air loads imposed by the receiver airplane when it is imparting the movement of the boom during the refueling engagement.

Abstract: A flying refueling boom for an aerial tanker airplane, with a mechanism for moving the boom about different axes. The boom having a pair of aerodynamic surfaces formed into a Vee and known as ruddevators, for moving the boom about the following axes: a tiltable vertical axis for boom movement in a sideways direction or in azimuth; a lateral axis for boom movement in an up-and-down direction or in elevation; and a longitudinal axis for movement of the boom about a roll axis. The ruddevator control system includes a pantographing cable system for automatically changing the angle-of-attack of the aerodynamic surfaces and for alleviating air loads imposed by the receiver airplane, when it is imparting the movement of the boom during refueling engagement. The boom support system includes an articulation mechanism for combining a certain amount of boom roll motion as a function of azimuth movement of the boom; and a device for varying the ratio between the degree of roll motion change vs.