Abstract: An internal wing control surface linkage system comprising: an actuator arm configured to rotate around a first rotation axis within an airfoil body. A linking arm is mounted within the airfoil body. The linking arm comprises a linking tube and a linkage rod slideably received within the linking tube. The linking tube comprises a hinged end pivotally coupled to the actuator arm about a first pivot axis parallel to the first rotation axis to cause deflection of a control surface coupled to the airfoil body during rotation of the actuator arm. The linkage rod comprising a hinged end coupled to a clevis about a second pivot axis of the control surface. A spherical bearing swivelly coupling the linking arm and providing a fixed swivel pivot which swivels the linking arm, as the linking tube simultaneously slides within the spherical bearing and, in combination, the rod simultaneously slides within the linking tube.

Abstract: An apparatus, having: a fuselage body section (180) configured to be secured to an aircraft fuselage (16); a pivot column (310) protruding from the fuselage body section; and a center wing section (214) configured to be secured to a center wing panel of a trifold wing (200). The fuselage body section and the center wing section are configured to cooperate with each other to rotate the center wing section relative to the fuselage body section from a stowed position (250) to a deployed position (302). The pivot column comprises a column feature (240) configured to engage with tip features (236) of the trifold wing to hold the trifold wing in a folded configuration when the trifold wing is in the stowed position and to disengage from the tip features as the trifold wing rotates to the deployed position, thereby freeing the trifold wing to unfold.

Abstract: An aircraft is provided comprising: a fuselage, a first tail fin rotatably mounted to a first lateral side and a second tail fin rotatably mounted to the second lateral side. A wing body is rotatably mounted to the underside of the fuselage. A pair of independent tail fin latch and release devices are provided to independently latch the first tail fin and the second tail fin when the wing body having a first angle is in a stowed position with respect to the fuselage, to independently unlatch the first tail fin in response to a second angle of the wing body with respect to the fuselage, and to independently unlatch the second tail fin in response to a third angle of the wing body with respect to the fuselage. The first angle, second angle and third angle are different angles with respect to the longitudinal axis of the fuselage.

Abstract: A control surface assembly for an unmanned aerial vehicle (UAV) is disclosed. The control surface assembly has a fin configured to be rotatably coupled to a fuselage of the UAV, with a control surface member rotatably coupled to the fin. A control surface linkage is configured to be coupled between the control surface member and an actuator disposed in the fuselage. The fin is rotatable with respect to the fuselage between a stowed configuration and a deployed configuration. In the deployed configuration, the control surface linkage is configured to rotate the control surface member with respect to the fin, when the actuator actuates the control surface linkage. In the stowed configuration, however, the control surface linkage is configured to move with respect to the fin without rotating the control surface member, when the actuator actuates the control surface linkage.

Abstract: A set point of a pressure output of a pressure regulator (12) is adjustable without having to overcome a biasing force to selectively adjust the set point of the pressure output. The regulator includes a housing (14) having a chamber (18) and a pressure output port (24) in fluid communication with the chamber (18). A piston (38) having an interior cavity (42) is slidably disposed within the chamber (18) of the housing (14). A biasing member (88) extends between the piston (38) and the housing (14), such that a biasing force is applied to the piston (38) which increases as the piston (38) is moved in a direction away from the pressure output port (24) of the housing (14). The piston (38) has a first flow port (54) which extends through a wall of the piston (38). An operating member (56) has a second flow port (60) which is positionable within the interior cavity (42) of the piston (38) at selected distances from the ends (20, 22) of the housing (14).