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 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 self-contained, compact camera wash system 1000 for a drone 800 or as an automotive aftermarket kit 1101 uses a pressurized container 1002 similar to a common aerosol can to supply washer fluid to a washer nozzle 1020 via actuable valving. The fluid supply container is small for use with drone cameras (e.g., ˜15 ml in volume) and is readily packaged in a compact assembly. For the automotive aftermarket kit 1101 a larger volume container volume is provided and configured to be easily replaced as needed.

A voltage controlled aircraft electric propulsion system includes an electric propulsion system. The voltage controlled aircraft electric propulsion system may include electric propulsors providing thrust for the aircraft. In hybrid systems, a gas turbine engine may also be included. The electric propulsion system may include at least one electric generator power source, at least one propulsor motor load, and at least one stored energy power source, such as a battery. The propulsor motor load may be supplied power from a power supply bus. The voltage of the power supply bus may be adjusted according to an altitude of the aircraft while maintaining a substantially constant current flow to the propulsor motor load. Due to the adjustment to lower voltages at increased altitude, insulations levels may be lower.

A removable step assembly for a helicopter includes a main tube, which supports a forward step and a rear step, as well as a bushing housing. The main tube is mounted to a helicopter by the bushing housing, an associated bushing, and by an adapter assembly that is secured to the cabin of the helicopter.

The invention relates to a device for the rapid reactivation of a helicopter turbine engine (6), characterised in that it comprises a pneumatic turbine (7) mechanically connected to said turbine engine (6) so as to be able to rotate it and ensure reactivation thereof; a pneumatic storage (9) connected to said pneumatic turbine (7) by means of a pneumatic circuit (10) for supplying pressurised gas to said pneumatic turbine (7); a controlled fast-opening pneumatic valve (11) arranged on the pneumatic circuit (10) between said storage (9) and said pneumatic turbine (7) and suitable for being on demand placed at least in an open position in which the gas can supply said pneumatic turbine (7), or in a closed position in which said pneumatic turbine (7) is no longer supplied with pressurised gas.

An autogyro includes an autorotation rotor and an instrument panel that includes comprising one or both of a display unit and a control unit. The instrument panel has a viewing window formed by a recess in the instrument panel located to expand a field of view for an autogyro pilot. A pilot seat is arranged in front of the instrument panel and is positioned centrally in a transverse direction of the autogyro in front of the instrument panel.

Systems and methods for moving an illumination spot of a searchlight beam at a constant groundspeed. The method includes receiving state data comprising an attitude for the mobile platform. The method computes an elevation angle, theta, of the beam as a function of the attitude, an elevation actuator angle and a known mounting orientation for the searchlight. Responsive to receiving a searchlight control command from a user input device, the method determines a respective rate of change of theta, dtheta/dt, and rate of change of Psi, dPsi/dt, required to maintain the constant groundspeed of the illumination spot, as a function of the state data. The method updates theta responsive to the determined dtheta/dt and generates actuator control commands for an elevation actuator based thereon. The method updates Psi responsive to the determined dPsi/dt, and generates actuator control commands for an azimuth actuator based thereon.

A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.