A detachable airplane wheel prerotation/landing brake cooling device is disclosed that comprises: an outer circular cage rim, an inner circular cage rim confronting and spaced apart from the outer circular cage rim, and a plurality of spaced apart arcuate blades spanning across and connecting the outer circular cage rim to the inner circular cage rim at a slant. Each arcuate blade includes a first section connected to the outer circular cage rim and a second section connected to inner circular cage rim. The plurality of slanted arcuate blades are, when the detachable airplane wheel prerotation/landing brake cooling device is being impinged by an airstream during the landing of the airplane, configured to (i) rotate the wheel about the axle in a forward direction, and (ii) funnel air into the plurality of annular spaces adjacent to the plurality of heat shields to thereby remove heat away from the disc brake assembly.

The display system has a three-dimensional and curved display surface made up of a single electronic display screen or several joined electronic display screens, the display surface having at least one main zone dedicated to a pilot and suitable for being located in front of said pilot, the main zone being substantially planar or concave, and at least one lateral zone associated with each main zone, each lateral zone being concave and laterally extending the associated main zone.

An air and land multimodal vehicle comprises a frame, a propeller engine attached to a first location of the frame supplying power and torque to a propeller, a ground engine attached to a second location of the frame supplying power and torque to one or more ground traction elements, and a flexible wing releasably connectable to the frame, wherein the propeller engine is vertically and horizontally spaced from the ground engine.

A propulsion system for a hybrid electric vehicle comprises a traction motor having first and second stator windings; a power source having a DC power output coupled to the first windings; a battery having a DC power output coupled to the second windings; and a controller to independently control: (i) a first power level output at the first DC power output, and (ii) a second power level of motive power output by the traction motor; wherein responsive to a signal to set the second power level less than full capacity of the traction motor, the controller provides a power difference between the first and second power levels from the second windings to the battery.

A passenger compartment which has a first connection device, by which the passenger compartment can be coupled to an aircraft, and a second connection device, by which the passenger compartment can be coupled to a land vehicle. The passenger compartment has an electrical circuit with an electrical energy storage. The electrical circuit of the passenger compartment has a coupling device by which electrical energy can be input from the electrical energy storage into an electrical circuit of the aircraft. The electrical circuit of the passenger compartment has a further coupling device by which electrical energy can be input from the electrical energy storage into an electrical circuit of the land vehicle.

An air and land multimodal vehicle comprises a frame, a propeller engine attached to a first location of the frame supplying power and torque to a propeller, a ground engine attached to a second location of the frame supplying power and torque to one or more ground traction elements, and a flexible wing releasably connectable to the frame, wherein the propeller engine is vertically and horizontally spaced from the ground engine.

A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor is configured to drive an electric motor shaft. A transmission system includes at least one gearbox. The transmission system is configured to receive rotational input power from each of the heat engine shaft and the electric motor shaft and to convert the rotation input power to output power.

A system for remote interaction with a pointing means of an aircraft cockpit display system, equipped with HMIs, includes three layers: a lower layer configured so as to receive wired electric power supply and data exchange connections; an upper layer comprising a hand-rest knob, at least one physical interaction means configured so as to interact on the pointing means for pointing at the HMIs of the cockpit, and a module with a touch-sensitive flat surface configured so as to interact on the pointing device for pointing at the HMIs of the cockpit and arranged in the extension of the hand-rest knob; and an intermediate layer configured so as to make it possible to modify the position of the upper layer.

A hybrid dump truck for surface mining, comprising a cyber-physical system including a sensing system and a control system, and a driving unit for performing autonomous driving of the dump truck along a travel path using at least the sensory data of the sensing system, wherein the closed cycle path is determined based on topographical data, wherein the control system is configured to control a cyclic energy level of the electric energy storage unit, wherein rates of change of power during autonomous or semi-autonomous driving of the hybrid dump truck from a predetermined reference point of the closed cycle path along said closed cycle path are controlled based on a desired velocity such as to reduce a difference in energy levels of the electric energy storage unit at the reference point of the closed cycle path.

A tank system for an aircraft, including a tank including an inner enclosure including a closed inner skin configured to store dihydrogen and an outer enclosure including an outer skin that surrounds the inner enclosure, a chassis including a front frame at a front end of the tank, and an attachment arrangement which attaches the outer skin of the outer enclosure to the front frame. A system of this kind makes it possible to react forces through the outer skin, thus reducing a complexity of the chassis.