Aircraft main landing gear drag brace backup fitting assemblies and related methods are described herein. An example aircraft wing disclosed herein includes a rear spar having a rear side and a front side opposite the rear side, a side-of-body rib coupled to the rear spar, a rib post disposed on the front side of the rear spar, where the rib post is to couple a second rib to the rear spar, a side-of-body fitting coupled to the side-of-body rib, an intercostal member coupled between the side-of-body fitting and the rib post, and a drag brace fitting disposed on the rear side of the rear spar. The drag brace fitting is coupled to the rib post and the side-of-body fitting via a first plurality of fasteners extending through the rear spar.

Aircraft main landing gear drag brace backup fitting assemblies and related methods are described herein. An example aircraft wing disclosed herein includes a rear spar having a rear side and a front side opposite the rear side, a side-of-body rib coupled to the rear spar, a rib post disposed on the front side of the rear spar, where the rib post is to couple a second rib to the rear spar, a side-of-body fitting coupled to the side-of-body rib, an intercostal member coupled between the side-of-body fitting and the rib post, and a drag brace fitting disposed on the rear side of the rear spar. The drag brace fitting is coupled to the rib post and the side-of-body fitting via a first plurality of fasteners extending through the rear spar.

Aircraft landing gear forward trunnion support assemblies and related methods are described herein. An example aircraft wing disclosed herein includes a rear spar having a rear side and a front side opposite the rear side and a forward trunnion support assembly. The forward trunnion support assembly includes first and second vertical support fittings coupled to the rear side of the rear spar, and a trunnion housing with a bearing. The trunnion housing is coupled between the first and second vertical support fittings. A central axis of the bearing is perpendicular to the rear side of the rear spar. The forward trunnion support assembly also includes a side load fitting disposed on the rear side of the rear spar. A first end of the side load fitting is coupled to the second vertical support fitting, and a second end of the side load fitting is coupled to the rear spar.

An aircraft includes a fuselage having a nose end and a tail end and a center of gravity. A primary wing is coupled to the fuselage aft of the center of gravity. A secondary wing is coupled to the fuselage forward of the center of gravity. A v-tail is coupled to the fuselage between the primary wing and the tail end of the fuselage, the v-tail comprising first and second angled stabilizers, each of the first and second stabilizers including a first end fixed to the fuselage and a second free end, distal to the fuselage.

An aircraft includes a fuselage having a nose end and a tail end and a center of gravity. A primary wing is coupled to the fuselage aft of the center of gravity. A secondary wing is coupled to the fuselage forward of the center of gravity. A v-tail is coupled to the fuselage between the primary wing and the tail end of the fuselage, the v-tail comprising first and second angled stabilizers, each of the first and second stabilizers including a first end fixed to the fuselage and a second free end, distal to the fuselage.

An aircraft having a retractable landing gear assembly configured to support some of the weight of the aircraft via one or more wheels, and another retractable non-wheeled landing gear assembly or device configured to support some of the weight of the aircraft via one or more low-friction supports such as an air cushion is disclosed. The aircraft may have a maximum take-off weight between 100 and 150 tonnes. There may be two main landing gears each carrying two wheels, a nose landing gear, and a central non-wheeled landing gear providing the low friction vertical support when the aircraft is moving on the ground/operating surface.

A leg mechanism includes an articulated leg system (100), a passive device (130) and a cable (134). The articulated leg system (100) has a leg portion (128). The passive device (130) is coupled to the articulated leg system and is configured to apply a first force to a portion thereof. The cable (134) is coupled to the articulated leg system (100) and is configured to apply a second force, in opposition to the first force, to a portion thereof. When the cable (134) is drawn away from the articulated leg system (100), the second force moves the leg portion (128) in a first direction. When tension is released from the cable (134), the passive device (130) exerts the first force so as to move the leg portion (128) a second direction that is opposite the first direction.

A leg mechanism includes an articulated leg system (100), a passive device (130) and a cable (134). The articulated leg system (100) has a leg portion (128). The passive device (130) is coupled to the articulated leg system and is configured to apply a first force to a portion thereof. The cable (134) is coupled to the articulated leg system (100) and is configured to apply a second force, in opposition to the first force, to a portion thereof. When the cable (134) is drawn away from the articulated leg system (100), the second force moves the leg portion (128) in a first direction. When tension is released from the cable (134), the passive device (130) exerts the first force so as to move the leg portion (128) a second direction that is opposite the first direction.

An unmanned aerial vehicle (UAV) includes a vehicle body and a multi-ocular imaging assembly. The multi-ocular imaging assembly includes at least two imaging devices disposed in and fixed to the vehicle body.

An unmanned aerial vehicle (UAV) includes a vehicle body and a multi-ocular imaging assembly. The multi-ocular imaging assembly includes at least two imaging devices disposed in and fixed to the vehicle body.