A patient litter basket spin control assembly for use on a patient litter basket is provided. The assembly comprises thruster unit for discharging an air stream and is mounted on the patient litter basket. At least one sensor is associated with the thruster unit for sensing rotational movement or spin of the patient litter basket, and a power source is provided for powering the thruster unit and the sensor. A clamp member mounts on the patient litter basket and releasably receives the thruster unit. The sensors modulate the force of the air stream from the thruster unit so that the air stream counters the rotational movement of the patient litter basket to stabilize the patient litter basket by preventing the spin.

A patient litter basket spin control assembly for use on a patient litter basket is provided. The assembly comprises thruster unit for discharging an air stream and is mounted on the patient litter basket. At least one sensor is associated with the thruster unit for sensing rotational movement or spin of the patient litter basket, and a power source is provided for powering the thruster unit and the sensor. A clamp member mounts on the patient litter basket and releasably receives the thruster unit. The sensors modulate the force of the air stream from the thruster unit so that the air stream counters the rotational movement of the patient litter basket to stabilize the patient litter basket by preventing the spin.

A method for transporting a rescue device from an aerial vehicle to a person to be rescued includes launching an unmanned aerial vehicle from the aerial vehicle having an end portion releasable attached to the unmanned aerial vehicle via a first connection and a second connection. The method further includes enabling the person to be rescued to reach the end portion of the rescue device. and determining whether the end portion of the rescue device is released from the first connection. If the rescue device is released determining at the unmanned aerial vehicle whether the person to be rescued is safely attached to the rescue device. If so, the method comprises either releasing the rescue device from the second connection, or deactivating the unmanned aerial vehicle such that the unmanned aerial vehicle remains attached to the rescue device via the second connection.

A method for transporting a rescue device from an aerial vehicle to a person to be rescued includes launching an unmanned aerial vehicle from the aerial vehicle having an end portion releasable attached to the unmanned aerial vehicle via a first connection and a second connection. The method further includes enabling the person to be rescued to reach the end portion of the rescue device. and determining whether the end portion of the rescue device is released from the first connection. If the rescue device is released determining at the unmanned aerial vehicle whether the person to be rescued is safely attached to the rescue device. If so, the method comprises either releasing the rescue device from the second connection, or deactivating the unmanned aerial vehicle such that the unmanned aerial vehicle remains attached to the rescue device via the second connection.

In an aspect of the present disclosure is a system for cooling a high voltage (HV) cable on an electric aircraft, including a fuselage configured to receive the HV cable, including a first side comprising a first venting closure movable between an open position and a closed position. The fuselage may further comprise a second side opposite the first side, the second side comprising a second venting closure movable between an open position and a closed position; wherein the first and second venting closures are configured to create a cooling channel between the first and second venting closures when the first and second venting closures are in the open position, wherein the cooling channel contacts the HV cable.

There is described an aircraft configured to be able to hover, comprising a fuselage; and a support element adapted to support a load, made of elastically deformable material and constrained to said fuselage; the support element being movable in an operating position in which it is arranged at least partially outside said fuselage and supports said load; the aircraft comprises a sock surrounding the support element arranged in said operating position; the sock is configured to contain the elastic return of the support element, in case the support element arranged in said operating position is sheared off.

There is described an aircraft configured to be able to hover, comprising a fuselage; and a support element adapted to support a load, made of elastically deformable material and constrained to said fuselage; the support element being movable in an operating position in which it is arranged at least partially outside said fuselage and supports said load; the aircraft comprises a sock surrounding the support element arranged in said operating position; the sock is configured to contain the elastic return of the support element, in case the support element arranged in said operating position is sheared off.

An aircraft includes a fuselage having a former therein and a work platform system. The work platform system includes a platform that is moveable between a stowed configuration and a deployed configuration. The work platform system also has a hinge pin received by the platform. A platform stop is carried by the former and configured to inhibit rotation of the platform about the hinge pin when the platform is in the deployed configuration. The hinge pin is carried by the former.

A spectral camera control device, being installed, along with a spectral camera provided with a liquid crystal tunable filter, in an aircraft capable of stationary flight. The spectral camera control device causes the spectral camera to capture a spectral image in a snapshot mode each time a transmission wavelength of the liquid crystal tunable filter is switched while the aircraft is in stationary flight, and the spectral camera control device causes a plurality of spectral images to be captured in succession at a same transmission wavelength when an SN ratio of the captured spectral image is less than a predetermined threshold.

A spectral camera control device, being installed, along with a spectral camera provided with a liquid crystal tunable filter, in an aircraft capable of stationary flight. The spectral camera control device causes the spectral camera to capture a spectral image in a snapshot mode each time a transmission wavelength of the liquid crystal tunable filter is switched while the aircraft is in stationary flight, and the spectral camera control device causes a plurality of spectral images to be captured in succession at a same transmission wavelength when an SN ratio of the captured spectral image is less than a predetermined threshold.