A submersion system for a rotorcraft is described and includes a control module for controlling a depth to which the rotorcraft is submerged in a body of water; a compressed air chamber associated with the control module; and at least one flotation pod including a sealable opening on a top surface thereof and an opening on a bottom surface thereof. The control module selectively causes water to be taken into the at least one flotation pod to cause the submersion system to submerge in the body of water and selectively causes water to be evacuated from the at least one flotation pod to cause the submersion system to float in the body of water.

An underwater rescue device, including a cabin provided with a hatch is provided, wherein the hatch is capable to open or close the cabin to form a confined space inside the cabin; a salvage device arranged inside the cabin, comprising a rescue platform and a gripper mechanism arranged on the rescue platform, wherein the rescue platform is movable, the rescue platform is capable to rotate relative to the cabin along at least one rotational axis and is capable to lift and lower to remove the cabin, and the gripper mechanism is configured to grab a drowning person and fix the drowning person on the rescue platform; a cardiopulmonary resuscitation device arranged inside the cabin; a drainage device arranged on the cabin; and a power device arranged on an outer side of the cabin. It has a high degree of automation and can provide immediate rescue for drowning personnel.

An underwater rescue device, including a cabin provided with a hatch is provided, wherein the hatch is capable to open or close the cabin to form a confined space inside the cabin; a salvage device arranged inside the cabin, comprising a rescue platform and a gripper mechanism arranged on the rescue platform, wherein the rescue platform is movable, the rescue platform is capable to rotate relative to the cabin along at least one rotational axis and is capable to lift and lower to remove the cabin, and the gripper mechanism is configured to grab a drowning person and fix the drowning person on the rescue platform; a cardiopulmonary resuscitation device arranged inside the cabin; a drainage device arranged on the cabin; and a power device arranged on an outer side of the cabin. It has a high degree of automation and can provide immediate rescue for drowning personnel.

Unmanned Aerial Vehicles also known as UAVs or Drones, either autonomous or remotely piloted, are classified as drones by the US Federal Aviation Administration (FAA) as weighing under 212 pounds. The system described herein details Autonomous Flight Vehicles (AFV) which weigh over 212 pounds but less than 1,320 pounds which may require either a new classification or a classification such as Sport Light Aircraft, but without the requirement of a pilot due to the safe autonomous flight system such as the Safe Temporal Vector Integration Engine or STeVIE. Safe Autonomous Light Aircraft (SALA) are useful as drone carriers, large scale air package or cargo transport, and even human transport depending on the total lift capability of the platform.

Unmanned Aerial Vehicles also known as UAVs or Drones, either autonomous or remotely piloted, are classified as drones by the US Federal Aviation Administration (FAA) as weighing under 212 pounds. The system described herein details Autonomous Flight Vehicles (AFV) which weigh over 212 pounds but less than 1,320 pounds which may require either a new classification or a classification such as Sport Light Aircraft, but without the requirement of a pilot due to the safe autonomous flight system such as the Safe Temporal Vector Integration Engine or STeVIE. Safe Autonomous Light Aircraft (SALA) are useful as drone carriers, large scale air package or cargo transport, and even human transport depending on the total lift capability of the platform.

An actuation system and method are actuated to control magnetic adhesion of a wheel to a surface. The actuation system is coupled to the wheel having inner and outer annular discs and the wheel is configured to adhere magnetically to a surface. The actuation system has a motor configured to rotate a first disc and to not rotate a second disc. In a first configuration, the motor rotates the first disc relative to the second disc in a first rotational direction, thereby generating a first magnetic flux to increase the adhesion of the wheel to the metallic surface. In a second configuration, the motor rotates the first disc relative to the second disc in a second rotational direction opposite the first rotational direction, thereby generating a second magnetic flux to decrease the adhesion of the wheel to the metallic surface. A method is also disclosed.

A land-and-air vehicle configured to switch between a ground traveling mode and an aerial flight mode incudes a body, a wing, a wheel, a suspension, and a lock mechanism. The wing is attached to the body. The wheel is provided on a lower side of the body. The suspension is configured to support the body via the wheel on ground, and to contract due to self-weight of the land-and-air vehicle. The lock mechanism is configured to limit expansion of the suspension from a state in which the suspension has contracted due to the self-weight.

A land-and-air vehicle configured to switch between a ground traveling mode and an aerial flight mode incudes a body, a wing, a wheel, a suspension, and a lock mechanism. The wing is attached to the body. The wheel is provided on a lower side of the body. The suspension is configured to support the body via the wheel on ground, and to contract due to self-weight of the land-and-air vehicle. The lock mechanism is configured to limit expansion of the suspension from a state in which the suspension has contracted due to the self-weight.

An aircraft has an empennage and a folding system. The folding system has aerofoils and node bodies which are connected to one another. The aerofoils have at least two nose-side aerofoils and at least two tail-side aerofoils, of which one of the nose-side aerofoils and one of the tail-side aerofoils are port-side aerofoils and one of the nose-side aerofoils and one of the tail-side aerofoils are starboard-side aerofoils. The node bodies have fuselage-side node bodies and outer node bodies. The nose-side aerofoils and tail-side aerofoils are each articulated at a first end to an associated fuselage-side node body, and the nose-side aerofoils and tail-side aerofoils are each articulated at a second end to an outer node body. The tail-side node bodies are displaceable at least partially along an associated translation axis. The folding system functions as the empennage during flight.

An aircraft has an empennage and a folding system. The folding system has aerofoils and node bodies which are connected to one another. The aerofoils have at least two nose-side aerofoils and at least two tail-side aerofoils, of which one of the nose-side aerofoils and one of the tail-side aerofoils are port-side aerofoils and one of the nose-side aerofoils and one of the tail-side aerofoils are starboard-side aerofoils. The node bodies have fuselage-side node bodies and outer node bodies. The nose-side aerofoils and tail-side aerofoils are each articulated at a first end to an associated fuselage-side node body, and the nose-side aerofoils and tail-side aerofoils are each articulated at a second end to an outer node body. The tail-side node bodies are displaceable at least partially along an associated translation axis. The folding system functions as the empennage during flight.