Launch and/or recovery for unmanned aircraft and/or other payloads, including via parachute-assist, and associated systems and methods are disclosed. A representative method for lofting a payload includes directing a lifting device upward, releasing a parachute from the lifting device, with the parachute carrying a pulley and having a flexible line passing around the pulley. The flexible line is connected between a tension device (e.g., a winch) and the payload. The method further includes activating the tension device to reel in the flexible line and accelerate the payload upwardly.

A system performs a control method to launch an unmanned aerial vehicle, UAV. The control method includes calculating a selected altitude, relative to a reference level, for launching the UAV, operating a lifting arrangement to vertically elevate the UAV to the selected altitude, and causing the UAV to be launched from the selected altitude. Elevating the UAV may improve the performance of the UAV in terms of range, power consumption, ability to carry payload, transit time to destination, etc. The selected altitude may be calculated as a function of parameter data representing any of the UAV, the lifting arrangement, or surrounding conditions. An apparatus is further provided to determine an optimal location of the system in relation to a plurality of destinations of UAVs to be elevated by the system.

A system performs a control method to launch an unmanned aerial vehicle, UAV. The control method includes calculating a selected altitude, relative to a reference level, for launching the UAV, operating a lifting arrangement to vertically elevate the UAV to the selected altitude, and causing the UAV to be launched from the selected altitude. Elevating the UAV may improve the performance of the UAV in terms of range, power consumption, ability to carry payload, transit time to destination, etc. The selected altitude may be calculated as a function of parameter data representing any of the UAV, the lifting arrangement, or surrounding conditions. An apparatus is further provided to determine an optimal location of the system in relation to a plurality of destinations of UAVs to be elevated by the system.

One variation of a tram system includes: a chassis; a latch configured to selectively engage a latch receiver mounted to an aircraft; an alignment feature adjacent the latch and configured to engage an alignment receiver mounted to the aircraft and to communicate acceleration and braking forces from the chassis into the aircraft; an optical sensor facing upwardly from the chassis; a drivetrain configured to accelerate and decelerate the chassis along a runway; and a controller configured to detect an optical fiducial arranged on the aircraft in optical images recorded by the optical sensor adjust a speed of the drivetrain to longitudinally align the alignment feature with the alignment receiver based on positions of the optical fiducial detected in the optical images, trigger the latch to engage the latch receiver once the aircraft has descended onto the chassis, and trigger the drivetrain to actively decelerate the chassis during a landing routine.

One variation of a tram system includes: a chassis; a latch configured to selectively engage a latch receiver mounted to an aircraft; an alignment feature adjacent the latch and configured to engage an alignment receiver mounted to the aircraft and to communicate acceleration and braking forces from the chassis into the aircraft; an optical sensor facing upwardly from the chassis; a drivetrain configured to accelerate and decelerate the chassis along a runway; and a controller configured to detect an optical fiducial arranged on the aircraft in optical images recorded by the optical sensor adjust a speed of the drivetrain to longitudinally align the alignment feature with the alignment receiver based on positions of the optical fiducial detected in the optical images, trigger the latch to engage the latch receiver once the aircraft has descended onto the chassis, and trigger the drivetrain to actively decelerate the chassis during a landing routine.

An unmanned aerial vehicle (UAV) adapted for transit in and deployment from a projectile casing is provided. The UAV includes a wing assembly coupled to the projectile casing and the wing assembly moveable between a closed position and a deployed position. The UAV further includes a propulsion system including at least one rotor disposed on the wing assembly to generate lift, wherein in the closed position, the wing assembly is substantially integral with the projectile casing and in the deployed position, the wing assembly is extended outwards from the projectile casing.

An unmanned aerial vehicle (UAV) adapted for transit in and deployment from a projectile casing is provided. The UAV includes a wing assembly coupled to the projectile casing and the wing assembly moveable between a closed position and a deployed position. The UAV further includes a propulsion system including at least one rotor disposed on the wing assembly to generate lift, wherein in the closed position, the wing assembly is substantially integral with the projectile casing and in the deployed position, the wing assembly is extended outwards from the projectile casing.

An aircraft tow vehicle and methods of towing an aircraft are disclosed. An aircraft tow vehicle comprises an aircraft structural interface configured to couple to a wheel assembly of a main landing gear of an aircraft; and an aircraft towing propulsive force system configured to propel the aircraft forward when the aircraft structural interface is coupled to the wheel assembly.

An aircraft tow vehicle and methods of towing an aircraft are disclosed. An aircraft tow vehicle comprises an aircraft structural interface configured to couple to a wheel assembly of a main landing gear of an aircraft; and an aircraft towing propulsive force system configured to propel the aircraft forward when the aircraft structural interface is coupled to the wheel assembly.

One variation of a tram system includes: a chassis; a latch configured to selectively engage a latch receiver mounted to an aircraft; an alignment feature adjacent the latch and configured to engage an alignment receiver mounted to the aircraft and to communicate acceleration and braking forces from the chassis into the aircraft; an optical sensor facing upwardly from the chassis; a drivetrain configured to accelerate and decelerate the chassis along a runway; and a controller configured to detect an optical fiducial arranged on the aircraft in optical images recorded by the optical sensor adjust a speed of the drivetrain to longitudinally align the alignment feature with the alignment receiver based on positions of the optical fiducial detected in the optical images, trigger the latch to engage the latch receiver once the aircraft has descended onto the chassis, and trigger the drivetrain to actively decelerate the chassis during a landing routine.