Provided is a seeder assembly for an aerial vehicle as shown and described. The distribution assembly includes a frame selectively attachable to an aerial vehicle and at least one distribution device attached to the frame. The distribution device having a body defining a cavity to receive a plurality of products and a barrel to discharge the plurality of products. A control device configured to communicate with the aerial vehicle and the distribution device to coordinate the timing that products are discharged and a spacing of a subsequent discharged product relative to the speed of the aerial vehicle. A system, method, and cartridge device associated with the distribution assembly are also contemplated by this disclosure.

Provided is a seeder assembly for an aerial vehicle as shown and described. The distribution assembly includes a frame selectively attachable to an aerial vehicle and at least one distribution device attached to the frame. The distribution device having a body defining a cavity to receive a plurality of products and a barrel to discharge the plurality of products. A control device configured to communicate with the aerial vehicle and the distribution device to coordinate the timing that products are discharged and a spacing of a subsequent discharged product relative to the speed of the aerial vehicle. A system, method, and cartridge device associated with the distribution assembly are also contemplated by this disclosure.

An aircraft has an airframe with first and second wings having first and second pylons extending therebetween. A distributed propulsion system attached to the airframe includes at least first, second, third and fourth propulsion assemblies that are independently controlled by a flight control system. A pod assembly is coupled to the airframe. In a VTOL flight mode, the first and second propulsion assemblies are forward of the pod assembly and the third and fourth propulsion assemblies are aft of the pod assembly. In a forward flight mode, the first and second propulsion assemblies are below the pod assembly and the third and fourth propulsion assemblies are above the pod assembly. In both the VTOL and forward flight modes, the first and fourth propulsion assemblies generate thrust having a first direction while the second and third propulsion assemblies generate thrust having a second direction that is different from the first direction.

An aircraft has an airframe with first and second wings having first and second pylons extending therebetween. A distributed propulsion system attached to the airframe includes at least first, second, third and fourth propulsion assemblies that are independently controlled by a flight control system. A pod assembly is coupled to the airframe. In a VTOL flight mode, the first and second propulsion assemblies are forward of the pod assembly and the third and fourth propulsion assemblies are aft of the pod assembly. In a forward flight mode, the first and second propulsion assemblies are below the pod assembly and the third and fourth propulsion assemblies are above the pod assembly. In both the VTOL and forward flight modes, the first and fourth propulsion assemblies generate thrust having a first direction while the second and third propulsion assemblies generate thrust having a second direction that is different from the first direction.

A spherical compartment is designed to hold a cargo or one or more individuals and absorbing impact as the spherical compartment is dropped from a height. The spherical compartment includes a frame with vertically oriented frame elements and at least one horizontally oriented frame element. The frame elements may be air beams; thus, the frame may be an air frame. The frame may carry a suspension system that suspends the payload within an interior of the spherical compartment. An outer skin affixed to the frame may impart the spherical compartment with low wind resistance. Methods of using the spherical compartment are also disclosed.

A device for the automated charging and discharging of an object on a free-flying autonomously controlled drone includes a landing platform for the drone, a storage device for storing objects, a robot where the robot is configured to remove an object from the storage apparatus in an automated manner and to provide the object on the landing platform to be picked up by the drone and is configured to pick up in an automated manner an object that is provided on the landing platform by the drone and to deposit the object in the storage apparatus, and a controller where the robot is controllable by the controller.

A device for the automated charging and discharging of an object on a free-flying autonomously controlled drone includes a landing platform for the drone, a storage device for storing objects, a robot where the robot is configured to remove an object from the storage apparatus in an automated manner and to provide the object on the landing platform to be picked up by the drone and is configured to pick up in an automated manner an object that is provided on the landing platform by the drone and to deposit the object in the storage apparatus, and a controller where the robot is controllable by the controller.

A stabilizing system for a cable has a cable deployed and suspended from a helicopter, a cargo support attached at a deployed end of the cable, an end effector attached to the cable, the end effector comprising thrusters directed in a plurality of directions orthogonal to a vertical axis of the cable, first control circuitry in the helicopter, and second control circuitry in the end effector. Thrust of individual thrusters is controlled through the first and second control circuitry maintaining the axis of the cable vertical, damping swinging of the cable.

A supply drop assembly for delivering one or more payloads via an aerial vehicle, the assembly comprising a payload body configured to receive a payload; and one or more wings attached to the payload with a connector or integral to the one or more wings; wherein when the supply drop assembly is dropped from the aerial vehicle, the one or more wings start rotating thereby generating lift and slowing the rate of descent of the payload as it falls downwards to a recipient.

A supply drop assembly for delivering one or more payloads via an aerial vehicle, the assembly comprising a payload body configured to receive a payload; and one or more wings attached to the payload with a connector or integral to the one or more wings; wherein when the supply drop assembly is dropped from the aerial vehicle, the one or more wings start rotating thereby generating lift and slowing the rate of descent of the payload as it falls downwards to a recipient.