Abstract: In certain embodiments, a structural mount in an aircraft includes a bottom assembly including a plurality of rigid trusses disposed within an aircraft structure. The bottom assembly is configured to pivot relative to the aircraft structure via a pivot mount. A plurality of adjustable mounts are disposed on top of the bottom assembly. A top assembly is mounted to the plurality of adjustable mounts. The adjustable mounts are used to adjust a position of the top assembly. A mechanical linkage is mounted to the bottom assembly. The mechanical linkage may be configured to adjust a control surface external to the bottom assembly.

Abstract: A wing fuselage joint for an aircraft having joining members which include a first configuration and a second configuration. The joining members of the first configuration include a platform and bracket configured to pivot in a lateral plane and translate in a longitudinal direction. The joining members of the second configuration include a platform and bracket configured to pivot in a longitudinal plane and translate in a lateral direction. The joining members of either configuration join the fuselage structure and the spar of an aircraft together.

Abstract: In an embodiment a weight on wheels (WOW) system for a landing gear system includes a sensor assembly with a switch and configured to be mounted to a shock absorber, and a landing disc assembly connected to the sensor assembly, the landing disc assembly configured to contact a ground surface and to be mounted to the shock absorber, wherein the switch is configured to indicate a landing or a taking-off of an aerial vehicle from the ground surface.

Abstract: A wing-fuselage truss joint assembly for an aircraft includes joining members secured to the aircraft's wing and fuselage structures. The joining members each include forward and aft wing joints and forward and aft fuselage joints connected by an upright member. The forward joining members are pivotally connected using interconnecting members and the aft joining members are connected using aft truss members. The forward-right and aft-right joining members and the forward-left and aft-left joining members are connected by truss link members and diagonal truss link members. The wing-fuselage truss joint assembly is configured to reduce forces experienced by the wing from being transferred to the aircraft fuselage.

Abstract: A wing fuselage joint for an aircraft having joining members which include a first configuration and a second configuration. The joining members of the first configuration include a platform and bracket configured to pivot in a lateral plane and translate in a longitudinal direction. The joining members of the second configuration include a platform and bracket configured to pivot in a longitudinal plane and translate in a lateral direction. The joining members of either configuration join the fuselage structure and the spar of an aircraft together.

Abstract: A vertical takeoff and landing (VTOL) aircraft includes a maximum takeoff weight (MTOW) of about 1700-kg, a cruising speed of about 80-knots equivalent airspeed (EAS) to about 100-knots EAS, a nominal range of about 300-km, a nominal flight time of about 4-hours, and at least one pair of rotors configured to provide vertical thrust. Each rotor of the at least one pair includes an about 2-meter propeller diameter, a disk loading of about 67-kg/m2 to about 110-kg/m2, and an operating speed of about 1800 rotations-per-minute (RPM) to about 2700-RPM.

Abstract: An embodiment aircraft boom includes a boom member, a vertical stabilizer, a rear landing gear, and a front landing gear. The boom member may extend in a first direction and have a front internal structural member disposed therein, where a portion of the front internal structural member is a first attachment point for a first wing. The vertical stabilizer may extend from the boom member, where the vertical stabilizer has a rear internal structural member disposed therein and extends from the boom member and through an interior of the vertical stabilizer, and where a portion of the rear internal structural member is a second attachment point for a second wing. The rear landing gear may be coupled to the rear internal structural member. The front landing gear may be coupled to the front internal structural member of the boom member.

Abstract: An embodiment aircraft boom includes a boom member, a vertical stabilizer, a rear landing gear, and a front landing gear. The boom member may extend in a first direction and have a front internal structural member disposed therein, where a portion of the front internal structural member is a first attachment point for a first wing. The vertical stabilizer may extend from the boom member, where the vertical stabilizer has a rear internal structural member disposed therein and extends from the boom member and through an interior of the vertical stabilizer, and where a portion of the rear internal structural member is a second attachment point for a second wing. The rear landing gear may be coupled to the rear internal structural member. The front landing gear may be coupled to the front internal structural member of the boom member.