Abstract: A robot including a hybrid fan-based and fluid-based propulsion system to provide thrust, such as deceleration during fall to create a smooth landing or to provide a quick reduction in velocity, and to provide actuation/controlled motion, such as to hover after quick deceleration and to control orientation or pose. The hybrid propulsion system uses discharging of pressurized fluid and exhausted gas (or fluid in some cases) from ducted fans (or propellers, impellers, and the like) to provide controlled thrust and/or lift forces. The hybrid propulsion system uses of pressurized fluid for generating larger or primary thrust and quick changes in velocity. The hybrid propulsion system includes a fan-based propulsion assembly with ducted fans that use environmental air (or fluids) to provide lower or secondary thrust. Both types of propulsion can be integrated into a robot or robotic figure to move the robot during flight (e.g., during falling or hovering).

Abstract: The invention relates to a device for propelling a passenger, comprising a body arranged to receive said passenger and cooperating with a fuel-fed thrust unit. The arrangement of such a device enables great freedom of movement in the air. More specifically, the thrust unit comprises at least one thrust sub-unit, each advantageously comprising at least two thrusters and secondary course-correction and/attitude-correction thrusters.

Abstract: Provided is a method for controlling flight of a drone and an apparatus supporting the same. More specifically, the drone according to the present invention determines whether or not a specific condition is satisfied to deploy a parachute during the flight, and in a case where the specific condition is satisfied, the drone may stop an operation of one or more propellers to deploy the parachute. Next, the drone deploys the parachute, the parachute is deployed toward an area beside the drone, and the flight of the drone may be controlled by adjusting a rotation speed of each of the one or more propellers.

Abstract: A robot including a hybrid fan-based and fluid-based propulsion system to provide thrust, such as deceleration during fall to create a smooth landing or to provide a quick reduction in velocity, and to provide actuation/controlled motion, such as to hover after quick deceleration and to control orientation or pose. The hybrid propulsion system uses discharging of pressurized fluid and exhausted gas (or fluid in some cases) from ducted fans (or propellers, impellers, and the like) to provide controlled thrust and/or lift forces. The hybrid propulsion system uses of pressurized fluid for generating larger or primary thrust and quick changes in velocity. The hybrid propulsion system includes a fan-based propulsion assembly with ducted fans that use environmental air (or fluids) to provide lower or secondary thrust. Both types of propulsion can be integrated into a robot or robotic figure to move the robot during flight (e.g., during falling or hovering).

Abstract: An unmanned aerial vehicle (UAV) includes a body that supports breakaway components. One component is a battery pack which powers the vehicle. Two other components are pod assemblies, which each include at least one motor and one propeller. Each motor is supported within a support ring using spokes or filament. The spokes keep the motor firmly stable during operation and also effectively encage the otherwise dangerous spinning propeller. This allows the vehicle to operate with a higher level of safety than conventional UAVs. The breakaway feature can be established using magnets.

Abstract: A braking system for a rotorcraft having a rotor hub assembly includes a generator having an armature mechanically coupled to the rotor hub assembly such that the armature is rotatable in response to rotation of the rotor hub assembly and a braking unit in selective electrical communication with the generator. The braking unit is adapted to apply an electrical resistance to rotation of the armature, thereby reducing a rotational speed of the rotor hub assembly.

Abstract: A personal flight vehicle including a platform base assembly that provides a surface upon which the feet of an otherwise free-standing person are positionable, and including a plurality of axial flow propulsion systems positioned about a periphery of the platform base assembly. The propulsion systems generate a thrust flow in a direction substantially perpendicular to the surface of the platform base assembly, where the thrust flow is unobstructed by the platform base assembly. The thrust flow has a sufficient intensity to provide vertical takeoff and landing, flight, hovering and locomotion maneuvers. The vehicle allows the pilot to control the spatial orientation of the platform base assembly by the movement, preferably direct, of at least part of his or her body, and the spatial movement of the vehicle is thus controlled.

Abstract: A multi-axis aircraft with a wind resistant unit includes a fuselage having an upper face and a lower face. The fuselage includes a central axis passing through the upper face and the lower face. A plurality of rotors is mounted to the fuselage. Each rotor includes a rotating axis parallel to the central axis. A wind resistant unit includes a plurality of wind barriers disposed in a radial direction perpendicular to a reference axis. Each wind barrier includes a plurality of rods fixed by at least one fixing member. Two adjacent rods have a passage therebetween. Each rod includes an axis proximal end facing the reference axis and an axis remote end remote to the reference axis. Each wind barrier includes a coupling end and an airflow diversion end. The coupling end is fixed by at least one coupling member to the upper face of the fuselage.

Abstract: A personal flight vehicle including a platform base assembly that provides a surface upon which the feet of an otherwise free-standing person are positionable, and including a plurality of axial flow propulsion systems positioned about a periphery of the platform base assembly. The propulsion systems generate a thrust flow in a direction substantially perpendicular to the surface of the platform base assembly, where the thrust flow is unobstructed by the platform base assembly. The thrust flow has a sufficient intensity to provide vertical takeoff and landing, flight, hovering and locomotion maneuvers. The vehicle allows the pilot to control the spatial orientation of the platform base assembly by the movement, preferably direct, of at least part of his or her body, and the spatial movement of the vehicle is thus controlled.

Abstract: A personal flight vehicle including a platform base assembly that provides a surface upon which the feet of an otherwise free-standing person are positionable, and including a plurality of axial flow propulsion systems positioned about a periphery of the platform base assembly. The propulsion systems generate a thrust flow in a direction substantially perpendicular to the surface of the platform base assembly, where the thrust flow is unobstructed by the platform base assembly. The thrust flow has a sufficient intensity to provide vertical takeoff and landing, flight, hovering and locomotion maneuvers. The vehicle allows the pilot to control the spatial orientation of the platform base assembly by the movement, preferably direct, of at least part of his or her body, and the spatial movement of the vehicle is thus controlled.

Abstract: A control surface assembly for an unmanned aerial vehicle (UAV) is disclosed. The control surface assembly has a fin configured to be rotatably coupled to a fuselage of the UAV, with a control surface member rotatably coupled to the fin. A control surface linkage is configured to be coupled between the control surface member and an actuator disposed in the fuselage. The fin is rotatable with respect to the fuselage between a stowed configuration and a deployed configuration. In the deployed configuration, the control surface linkage is configured to rotate the control surface member with respect to the fin, when the actuator actuates the control surface linkage. In the stowed configuration, however, the control surface linkage is configured to move with respect to the fin without rotating the control surface member, when the actuator actuates the control surface linkage.

Abstract: The embodiments relate to an apparatus for controlling the angular position of propeller guards of a multicopter. The apparatus includes a chassis having at least three sides, including first and second sides meeting at a first vertex and second and third sides meeting at a second vertex. Each side is in communication with at least one propeller. At least one guard is in communication with the chassis. Each guard corresponds to a respective side, and each guard has oppositely disposed first and second terminals. The apparatus further includes a rotation mechanism in communication with the at least one guard to control an angular position of at least one guard relative to the chassis. The angular position is controlled in real time to mitigate damage with regard to an approaching or potential obstacle.

Abstract: An autogyro plane (10) having a fuselage (12) with a cockpit with a pilot position (22), a tractor propeller (18) mounted at the front of the fuselage, a mast (14) projecting upwardly from the fuselage for supporting rotor blades (16), the pilot position being in front of the mast.

Abstract: A parachute support system for supporting a helicopter emergency parachute is provided, comprising a parachute support shaft located within a main rotor shaft, said parachute support shaft being rotationally separated from the rest of the helicopter through the use of bearing supports or enclosures. As the parachute support shaft is connected to the main rotor shaft at multiple distinct and distant points, the system described also provides a preferable load path transfer route, such that parachute system malfunction is minimized.

Abstract: A vertical take-off and landing aircraft that includes AC motors, which drive fans that propel the aircraft, and a control device for controlling the AC motors adaptively based on a thrust control amount from an attitude controller. In particular, the drive controller performs switching to convert DC from a power source to three-phase AC at a predetermined frequency to be supplied to the AC motors. The drive controller reduces the control frequency of the three-phase AC to be applied to the AC motor to reduce the control resolution when the flight mode is switched from a vertical flight control mode to a horizontal flight control mode, in which the control amount to correct the external forces is smaller. Therefore, it is possible to reduce the power loss in the controller and thus the power consumption compared to conventional vertical take-off and landing aircrafts, in which the control resolution is always constant.

Abstract: A helicopter includes a main rotor guided and protected in minor impacts by a guide-ring. In selected embodiments, the rotor is powered by an electric motor employing a magnetic field generator carried by the main rotor and stator coils installed on the guide-ring. The helicopter's main rotor thus effectively functions as the rotor of the electric power plant of the helicopter. In selected embodiments, the rotor's blades are arranged so as to create an opening in the center of the rotor, allowing pilot ejection or deployment of a parachute capable of safely lowering the helicopter in case of an emergency.

Abstract: Disclosed is a rotary winged aircraft. More specifically, this invention relates to an aircraft wherein lift is generated by two discs which rotate about a central axis. The discs generate equal and opposite forces such that the central axis remains fixed, thereby allowing it to be used for a crew compartment. In one embodiment, the two discs are concentrically located.

Abstract: Disclosed is a rotary winged aircraft. More specifically, this invention relates to an aircraft wherein lift is generated by two discs which rotate about a central axis. The discs generate equal and opposite forces such that the central axis remains fixed, thereby allowing it to be used for a crew compartment. In one embodiment, the two discs are concentrically located.

Abstract: A dual power helicopter without a tail rotor. The dual power helicopter of present invention primarily uses two power devices which can be rotated in opposite directions to control the flight of the helicopter. The two power devices are rotated in the opposite directions by steering gears from a same engine, such that the engine power can be completely transmitted to the two power devices, enabling the engine power to be completely developed, thereby improving performance of the helicopter.

Abstract: An anti-torque thruster system implemented onboard an aircraft comprising a propulsion means coupled to the aircraft, wherein the propulsion means is capable of providing a measure of anti-torque thrust to the aircraft, a fuel storage container coupled to the propulsion means via a fuel delivery conduit, wherein the fuel storage container is capable of storing an appropriate fuel for the propulsion means, a valve means disposed between the fuel storage container and the propulsion means, wherein the valve means may be useable to regulate the flow of fuel from the fuel storage container to the propulsion means, and a controller for controlling the valve means to regulate the flow of fuel from the fuel storage container to the propulsion means, wherein the controller is capable of receiving input from at least one input device.

Abstract: A safety system is provided on a helicopter by mounting a parachute within a cylinder located in a hollow drive shaft of the propeller or in an external container. Four auxiliary parachutes are located in front and behind, and to the left and right of the propeller. The propeller may be locked in a predetermined angular position by a braking system of the drive shaft when the helicopter is disabled in an air accident such that the auxiliary parachutes are located in the spaces between the propeller blades for their safe deployment for suspending the helicopter in air. Speed reducing jets are provided for reducing the falling speed of the helicopter and for landing it safely on the ground. Inflatable bags are provided for maintaining the helicopter afloat when it falls on to a body of water or to cushion its landing impact on the ground.

Abstract: A safety system is provided on a helicopter by mounting a parachute within a cylinder located in a hollow drive shaft of the propeller or in an external container. Four auxiliary parachutes are located in front and behind, and to the left and right of the propeller. The propeller may be locked in a predetermined angular position by a braking system of the drive shaft when the helicopter is disabled in an air accident such that the auxiliary parachutes are located in the spaces between the propeller blades for their safe deployment for suspending the helicopter in air. Speed reducing jets are provided for reducing the falling speed of the helicopter and for landing it safely on the ground. Inflatable bags are provided for maintaining the helicopter afloat when it falls on to a body of water or to cushion its landing impact on the ground.

Abstract: The invention is of an aviation incident surveillance system which is to be carried on-board aircraft and stand ready at any time for deployment to visually record the final seconds of the downed aircraft. The system of the present invention centers on a rotocraft capsule which suspends itself approximately at an altitude at which the capsule is deployed from the distress aircraft while on-board video cameras and data recording systems record the environment surrounding the capsule which, of course, will include the aircraft from which the capsule was deployed. The capsule is provided with a self deploying, ballistic parachute system for gently landing the School upon expiration of the capsule's internal power sources for driving the rotocraft components.

Abstract: Inflation of impact absorbing bags is effected on a portable platform positioned on an emergency landing zone after jettisoning of damaged landing gear from a helicopter fuselage. The impact absorbing bags when inflated form a cradle shape conforming to the bottom of the helicopter fuselage.

Abstract: Three methods of deploying safety parachutes from a helicopter for landing it in case of an accident are shown. They solve the problem of the parachutes becoming tangled with the large propeller of a helicopter in such circumstances. Additionally, speed reduction jets are provided to reduce the falling speed of the helicopter to achieve its safe landing. Inflatable air bags are provided on both sides of its belly and inflatable tubular gaskets are provided around the door joints for sealing these joints such that when falling onto water, the helicopter would float safely to await for rescue. Inflatable air bags are also provided to reduce the impact of the helicopter upon landing on the ground.

Abstract: A parachute device for a helicopter includes a canopy confining case having a stationary casing part, and a removable casing part mounted removably on the stationary casing part. The stationary and removable casing parts cooperatively form a compartment to receive a parachute canopy that has a release cord connected to the removable casing part, and a suspension line unit. An anchoring line has one end that extends into the canopy confining case and that is coupled to the suspension line unit of the parachute canopy. A rocket member includes a launch tube mounted on the stationary casing part externally of the compartment, and a rocket disposed in the launch tube and connected to the removable casing part. The rocket is capable of propelling from the launch tube when ignited. An ignition control line has a first end connected to the rocket member, and a second end provided with an ignition unit that is operable so as to ignite the rocket.

Abstract: An anti-torque thruster system implemented onboard an aircraft comprising a propulsion means coupled to the aircraft, wherein the propulsion means is capable of providing a measure of anti-torque thrust to the aircraft, a fuel storage container coupled to the propulsion means via a fuel delivery conduit, wherein the fuel storage container is capable of storing an appropriate fuel for the propulsion means, a valve means disposed between the fuel storage container and the propulsion means, wherein the valve means may be useable to regulate the flow of fuel from the fuel storage container to the propulsion means, and a controller for controlling the valve means to regulate the flow of fuel from the fuel storage container to the propulsion means, wherein the controller is capable of receiving input from at least one input device.