An air delivery barrel system is described, the air delivery barrel system includes a strap system that provides line stretch of the strap system when a force is exerted on the strap system, the strap system including a continuous strap, a first barrel, the first barrel being formed out of a cylindrically shaped wall and the cylindrically shaped wall including a channel that the strap system passes through, an end cap, the end cap being detachably connectable to a bottom end of the first barrel, the end cap protecting a bottom portion of the strap system, a lid, the lid being detachably connectable to a top end of the first barrel, the lid including a recess through which the strap system passes through, and a second barrel that can be situated within the first barrel and the cylindrically shaped wall of the first barrel protects the second barrel.

An air delivery barrel system is described, the air delivery barrel system includes a strap system that provides line stretch of the strap system when a force is exerted on the strap system, the strap system including a continuous strap, a first barrel, the first barrel being formed out of a cylindrically shaped wall and the cylindrically shaped wall including a channel that the strap system passes through, an end cap, the end cap being detachably connectable to a bottom end of the first barrel, the end cap protecting a bottom portion of the strap system, a lid, the lid being detachably connectable to a top end of the first barrel, the lid including a recess through which the strap system passes through, and a second barrel that can be situated within the first barrel and the cylindrically shaped wall of the first barrel protects the second barrel.

The present disclosure provides an aircraft comprising: a fuselage; and a payload module coupled to the fuselage, the payload module comprising one or more data storage devices. The payload module is configured to be decoupled from the fuselage during flight upon receipt of a de-coupling input.

Methods of reducing wing type parachute opening shock during a parachute drop, and parachute systems with reduced opening shocks are disclosed, the opening force reduction is achieved by dynamic braking, i.e. dynamically adjusting the canopy control lines during the inflation stage of the canopy. Typically, the control lines are set to zero brake length when the parachute canopy is released from the deployment bag, and are at least shortened during the inflation stage, optionally all the way to full brake. Optionally the control lines are also lengthened prior to completion of the canopy inflation. Other features and parachute systems are also disclosed.

Described is a method of delivery for cargo or goods from an aerial vehicle (mothership) to a designated ground delivery location via the use of a direct air shipping package. For example, an aerial vehicle may be an airplane or helicopter that remains at altitude with a package stowed for deployment. As the mothership travels in the vicinity of the designated location the package flight control computer (flight controller) calculates a preferred travel trajectory based upon the aerodynamic properties of the package and location relative to the designated delivery location such as a small delivery pad located on a patio of a home. When the mothership transits through a calculated release point the package disengages the mothership. As the package descends it may increase accuracy relative to the designated delivery location by altering aerodynamic properties to maintain the preferred travel trajectory and decreasing landing zone size requirements and increasing precision of delivery. To reduce the impact force at landing the designated delivery location and/or the package may contain a net, airbag, parachute or similar device to provide a suitably soft landing suitable for commercial home delivery.

Embodiments relate to a client-facing application for interacting with a transport service that transports items via unmanned aerial vehicles (UAVs). An example graphic interface may allow a user to order items to specific delivery areas associated with their larger delivery location, and may dynamically provide status updates and other functionality during the process of fulfilling a UAV transport request.

Embodiments relate to a client-facing application for interacting with a transport service that transports items via unmanned aerial vehicles (UAVs). An example graphic interface may allow a user to order items to specific delivery areas associated with their larger delivery location, and may dynamically provide status updates and other functionality during the process of fulfilling a UAV transport request.

Embodiments described herein may help to provide support via a fleet of unmanned aerial vehicles (UAVs). An illustrative medical-support system may include multiple UAVs, which are configured to provide support for a number of different situations. Further, the medical-support system may be configured to: (a) identify a remote situation, (b) determine a target location corresponding to the situation, (c) select a UAV from the fleet of UAVs, where the selection of the UAV is based on a determination that the selected UAV is configured for the identified situation, and (d) cause the selected UAV to travel to the target location to provide support.

Embodiments described herein may help to provide support via a fleet of unmanned aerial vehicles (UAVs). An illustrative medical-support system may include multiple UAVs, which are configured to provide support for a number of different situations. Further, the medical-support system may be configured to: (a) identify a remote situation, (b) determine a target location corresponding to the situation, (c) select a UAV from the fleet of UAVs, where the selection of the UAV is based on a determination that the selected UAV is configured for the identified situation, and (d) cause the selected UAV to travel to the target location to provide support.

An aircraft includes an airframe having at least one wing. A distributed propulsion system is attached to the airframe and includes first and second pluralities of propulsion assemblies. In a vertical takeoff and landing flight mode, each of the propulsion assemblies generates vertical thrust with rotor assemblies of the first plurality of propulsion assemblies rotating in a horizontal plane and rotor assemblies of the second plurality of propulsion assemblies rotating in a parallel horizontal plane. In a forward flight mode, each of the propulsion assemblies generates forward thrust with the rotor assemblies of the first plurality of propulsion assemblies rotating in a vertical plane and the rotor assemblies of the second plurality of propulsion assemblies rotating in a parallel vertical plane. In both the vertical takeoff and landing flight mode and the forward flight mode, a pod assembly coupled to the airframe remains in a generally horizontal attitude.