Abstract: The present invention provides a landing gear. The landing gear includes a trunnion having at least one principal pivot point. The principal pivot point is adapted to be pivotably coupled to an airframe to allow the trunnion to pivot about a principal trunnion pivot axis; the trunnion is operable to move between a deployed position and a stowed position by pivoting about the principal trunnion pivot axis. The trunnion further includes at least one secondary pivot point. The landing gear also includes a subframe having at least one principal pivot point. The principal pivot point of the subframe is pivotably coupled to the secondary pivot point of the trunnion to allow the subframe to pivot about a principal subframe pivot axis; the subframe is operable to move between a deployed position and a stowed position by pivoting about the principal subframe pivot axis. The landing gear further includes a wheel rotatably coupled to the subframe.

Abstract: The present invention provides a landing gear. The landing gear includes a trunnion having at least one principal pivot point. The principal pivot point is adapted to be pivotably coupled to an airframe to allow the trunnion to pivot about a principal trunnion pivot axis; the trunnion is operable to move between a deployed position and a stowed position by pivoting about the principal trunnion pivot axis. The trunnion further includes at least one secondary pivot point. The landing gear also includes a subframe having at least one principal pivot point. The principal pivot point of the subframe is pivotably coupled to the secondary pivot point of the trunnion to allow the subframe to pivot about a principal subframe pivot axis; the subframe is operable to move between a deployed position and a stowed position by pivoting about the principal subframe pivot axis. The landing gear further includes a wheel rotatably coupled to the subframe.

Abstract: The present invention provides a landing gear. The landing gear includes a trunnion having at least one principal pivot point. The principal pivot point is adapted to be pivotably coupled to an airframe to allow the trunnion to pivot about a principal trunnion pivot axis; the trunnion is operable to move between a deployed position and a stowed position by pivoting about the principal trunnion pivot axis. The trunnion further includes at least one secondary pivot point. The landing gear also includes a subframe having at least one principal pivot point. The principal pivot point of the subframe is pivotably coupled to the secondary pivot point of the trunnion to allow the subframe to pivot about a principal subframe pivot axis; the subframe is operable to move between a deployed position and a stowed position by pivoting about the principal subframe pivot axis. The landing gear further includes a wheel rotatably coupled to the subframe.

Abstract: A landing gear (30) includes a trunnion (40) that has at least one principal pivot point (42). The principal pivot point (42) is adapted to be pivotably coupled to an airframe (12) to allow the trunnion (40) to pivot about a principal trunnion pivot axis (45). The trunnion (40) is operable to move between a deployed position and a stowed position by pivoting about the principal trunnion pivot axis (45). The landing gear (30) also includes a wheel (60) rotatably coupled to the trunnion (40). The wheel (60) has a rolling axis (68) and a center, which is located forward of the principal pivot point (42) when the trunnion (40) is in the deployed position.

Abstract: Method and apparatus for making a fiber reinforced composite wherein fiber reinforcement material is disposed in a molding cavity formed between a substantially rigid molding tool and a compliant molding tool in a pressurizable chamber of a pressure vessel, such as an autoclave. Uncured polymer resin is introduced under pressure to the molding cavity by a resin pump disposed in the chamber or external thereof so as to initially infiltrate the fiber reinforcement material with the resin. The chamber is gas pressurized to provide isostatic pressure on the rigid and compliant tools during resin infiltration of the fiber reinforcement material. The resin-infiltrated fiber reinforcement material then is heated in the chamber to cure the resin matrix. Large surface area composites of the aerospace skin structure type can be made using the present invention.

Abstract: A missile engine inlet cover has an elongate air scoop having a rigid forward shell and a rearward attached flexible molded end piece. The missile engine inlet cover is held in place by the launch rail with the flexible molded end piece releasably inserted into or over the missile engine inlet. During missile launch, flow of air into the open end of the air scoop forces the air scoop to rotate rearward and dislodges the flexible molded end piece from the missile engine inlet to allow operation of the missile engine.