An aircraft includes a boundary layer ingestion fan defining a centerline and including a plurality of fan blades rotatable about the centerline. The aircraft also includes a fuselage extending between a forward end and an aft end along a longitudinal direction, the boundary layer ingestion fan positioned within the fuselage at the aft end of the fuselage, the fuselage defining an inlet upstream of the boundary layer ingestion fan extending at least about 180 degrees around the centerline of the boundary layer ingestion fan, the fuselage further defining an exhaust downstream of the boundary layer ingestion fan.

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 improved aircraft system is provided. The improved aircraft system comprises an adjustable vortices device that may be attached to an aircraft to create various vortices effects, which increase take-off weight and improve low-speed handling of the aircraft. The adjustable vortices device comprises a linear actuator, a pivot mechanism, and a vortex generator. The pivot mechanism is operably connected to the linear actuator in a way such that the translational energy of the linear actuator causes the pivot mechanism to rotate about a central axis. The vortex generator is moveably attached to a surface of the aircraft and coupled to the pivot mechanism in a way such that rotating the pivot mechanism causes the vortex generator to rotate about a central axis, which alters the angle the vortex generators move through the air.

An apparatus for launching a payload includes a primary barrel, a primary projectile including a secondary barrel, and a secondary projectile including the payload. Prior to firing the apparatus to launch the payload, the primary projectile is contained within the primary barrel, and the secondary projectile is contained within the secondary barrel. Ignition, detonation, or expansion of a primary propellant within the primary barrel launches the primary projectile from the primary barrel. Ignition, detonation, or expansion of a secondary propellant within the secondary barrel launches the secondary projectile from the secondary barrel. The secondary projectile can further include a volume of a secondary explosive material; detonation of the secondary explosive material propels at least a portion of the payload away from a remainder of the secondary projectile. The payload can include cremation remains, DNA, or text, images, or other information.

An apparatus for launching a payload includes a primary barrel, a primary projectile including a secondary barrel, and a secondary projectile including the payload. Prior to firing the apparatus to launch the payload, the primary projectile is contained within the primary barrel, and the secondary projectile is contained within the secondary barrel. Ignition, detonation, or expansion of a primary propellant within the primary barrel launches the primary projectile from the primary barrel. Ignition, detonation, or expansion of a secondary propellant within the secondary barrel launches the secondary projectile from the secondary barrel. The secondary projectile can further include a volume of a secondary explosive material; detonation of the secondary explosive material propels at least a portion of the payload away from a remainder of the secondary projectile. The payload can include cremation remains, DNA, or text, images, or other information.

An improved aircraft system is provided. The improved aircraft system comprises an adjustable vortices device that may be attached to an aircraft to create various vortices effects, which increase take-off weight and improve low-speed handling of the aircraft. The adjustable vortices device comprises a linear actuator, a pivot mechanism, and a vortex generator. The pivot mechanism is operably connected to the linear actuator in a way such that the translational energy of the linear actuator causes the pivot mechanism to rotate about a central axis. The vortex generator is moveably attached to a surface of the aircraft and coupled to the pivot mechanism in a way such that rotating the pivot mechanism causes the vortex generator to rotate about a central axis, which alters the angle the vortex generators move through the air.

A takeoff and landing platform, a UAV, a takeoff and landing system, a storage device and a takeoff and landing control method are provided. The takeoff and landing platform includes: a bracket, one end of the bracket is fixed on a base, and another end thereof extends in a direction away from the base, and the bracket is provided with a vertical guide rail. Multiple UAVs may be vertically stacked on the bracket along the guide rail and take off from the bracket. Hence, the manpower investment and site investment are reduced for multiple UAVs to perform collaborative operations. It can not only reduce the cost of multiple UAV collaborative operations, but also improve the efficiency of multiple UAV collaborative operations.

An aircraft includes a boundary layer ingestion fan defining a centerline and including a plurality of fan blades rotatable about the centerline. The aircraft also includes a fuselage extending between a forward end and an aft end along a longitudinal direction, the boundary layer ingestion fan positioned within the fuselage at the aft end of the fuselage, the fuselage defining an inlet upstream of the boundary layer ingestion fan extending at least about 180 degrees around the centerline of the boundary layer ingestion fan, the fuselage further defining an exhaust downstream of the boundary layer ingestion fan.

An aircraft includes a boundary layer ingestion fan defining a centerline and including a plurality of fan blades rotatable about the centerline. The aircraft also includes a fuselage extending between a forward end and an aft end along a longitudinal direction, the boundary layer ingestion fan positioned within the fuselage at the aft end of the fuselage, the fuselage defining an inlet upstream of the boundary layer ingestion fan extending at least about 180 degrees around the centerline of the boundary layer ingestion fan, the fuselage further defining an exhaust downstream of the boundary layer ingestion fan.

A heavy payload, autonomous UAV able to deliver supply by way of airdrop with more precision and at a lower cost. The UAV can be equipped with a movable wing system. The UAV can include a removable storage box. The UAV can be equipped with a drogue parachute for deploying the wings upon jettison of the UAV from a mothership. The UAV can be controlled remotely or it can operate autonomously. The UAV can include canard wings. The canard wings and the movable wings can include ailerons to effectuate flight control of the UAV. The UAV can be reusable or can be an expandable UAV. The UAV's wings can be configured to automatically separate from the UAV during the landing sequence.