Abstract: In an embodiment, a method includes: adjusting a first flight control device of a rotorcraft to control flight around a first axis of the rotorcraft, the first flight control device exercising flight control authority around the first axis of the rotorcraft; detecting a failure of the first flight control device; transitioning at least a portion of the flight control authority around the first axis of the rotorcraft from the first flight control device to a second flight control device of the rotorcraft, the transitioning being performed automatically in response to detecting the failure of the first flight control device; and adjusting the second flight control device to control flight around the first axis of the rotorcraft, the second flight control device being adjusted by a first control process when the rotorcraft is in a first flight mode, the second flight control device being adjusted by a second control process when the rotorcraft is in a second flight mode.

Abstract: Embodiments described herein relate to a vertical take-off and landing aircraft, specifically an electric or hybrid electric aircraft having a plurality of ducted fans. The aircraft includes a plurality of axially oriented fans, laterally oriented fans, forward air intakes, side exit ports and rear exhaust ports. The aircraft achieves flight by capturing air in the intakes and diverting the air through the axially oriented fans or the laterally oriented fans through the channels selectively.

Abstract: The invention is in the field of engine building technology and may be used in space technology or aviation. Liquid-propellant rockets with Laval nozzles are well known, and they have the following insufficiencies: (1) high fuel consumption rates, which lead to increased dimensions and engine weight and boosters; (2) a relatively low combustion efficiency, because the low mass of the combustion products are emitted into the environment; (3) the large length of the de Laval nozzles with increased expansion ratios increase the dimensions and the engine weight; (4) use of high temperature rocket propellants—combustion products—in the camera and de Laval nozzle. These insufficiencies suppress using liquid-propellant rockets in space technology. The goal of the invention is decreasing the influence of these insufficiencies and obtaining an engine with improved efficiency.

Abstract: A modular unmanned aerial system includes a chassis for attaching components of the modular unmanned aerial system and one or more rotary wings. Each of the one or more rotary wings is drivable by a respective motor. A central controller is provided for controlling operation of the modular unmanned aerial system. A modular interface portion attached to the chassis and adapted for removably mounting one or more modular devices.

Abstract: A propulsion device includes a propulsion body and a diversion assembly. The propulsion body includes a propulsion system and a housing accommodating the propulsion system. The housing has an air-intake opening and an air-discharge opening respectively on two opposite sides of the propulsion system. The diversion assembly includes first and second diversion annular sheets. The first diversion annular sheet is disposed outside the air-discharge opening of the housing and having a surrounding center. The first diversion annular sheet is swung relative to the air discharge opening by a first axis passing through the surrounding center. The second diversion annular sheet is disposed outside the air-discharge opening of the housing and concentrically disposed with the first diversion annular sheet. The second diversion annular sheet is swung relative to the air-discharge opening by a second axis passing through the surrounding center, and first axis intersects the second axis.

Abstract: Systems and method for providing a soft landing of a wellhead connector onto a subsea wellhead are provided. One such system includes a wellhead connector configured to be coupled to a subsea wellhead, and a soft landing system disposed on a body of the wellhead connector. The soft landing system includes one or more cylinder assemblies coupled to the body of the wellhead connector, and one or more valve assemblies coupled to the body of the wellhead connector. Each cylinder assembly includes a barrel, a rod disposed within the barrel and extending in one direction from the barrel, and a pad attached to an extended end of the rod. The one or more valve assemblies are each fluidly coupled to the one or more cylinder assemblies.

Abstract: Disclosed are embodiments of flow diverting lift elements which, when placed in the proper orientation and propelled through a fluid, produce a lift force with improved lift versus velocity performance. The flow diverting lift elements can produce lift for rotary lift devices such as aircraft. The flow diverting lift devices include an airfoil and a diversion wall extending from an upper surface of the airfoil. The airfoil can be an annular airfoil.

Abstract: Provided is a disc-shaped aircraft including a rotatable disc-shaped wing inclined downward from a center to an edge of the wing and including a through hole vertically penetrating through a center of the wing, a body provided in a space under the wing, a driving mechanism for providing rotary power to the wing, a connector including an end connected to a side of the wing forming the through hole, and another end connected to the driving mechanism to transmit rotary power to the wing, a main channel provided between the wing and the body to serve as a passage for a gas sucked into the through hole, an ejection hole provided between a lower end of the wing and the body to eject the gas flowing along the main channel, downward, and a flight controller for adjusting an ejection amount of the gas ejected from the ejection hole, by changing a shape of the main channel by adjusting a height of the wing.

Abstract: A proprotor blade for a ducted aircraft including a duct includes a main body having a distal end and a sacrificial blade tip coupled to the distal end of the main body. The sacrificial blade tip includes a deformable core material and a shell layer at least partially covering the deformable core material. The sacrificial blade tip deforms upon contact with the duct, thereby reducing damage to the ducted aircraft.

Abstract: In an embodiment, a method includes: adjusting a first flight control device of a rotorcraft to control flight around a first axis of the rotorcraft, the first flight control device exercising flight control authority around the first axis of the rotorcraft; detecting a failure of the first flight control device; transitioning at least a portion of the flight control authority around the first axis of the rotorcraft from the first flight control device to a second flight control device of the rotorcraft, the transitioning being performed automatically in response to detecting the failure of the first flight control device; and adjusting the second flight control device to control flight around the first axis of the rotorcraft, the second flight control device being adjusted by a first control process when the rotorcraft is in a first flight mode, the second flight control device being adjusted by a second control process when the rotorcraft is in a second flight mode.

Abstract: An aircraft includes a fuselage having an upper surface and a lower surface that define an airfoil shape in cross-section along a vertical plane such that horizontal movement of the fuselage through air produces a lift force in a vertical direction. The aircraft also includes a plurality of modules attached to the fuselage. Each module includes an upper jet engine directed above the upper surface of the fuselage and an opposed lower jet engine directed below the lower surface of the fuselage.

Abstract: A ring-shaped airfoil aircraft capable of taking off and landing vertically, and hovering, comprising: a fuselage, a cockpit; a passenger cabin, a power bay, a tapered tail rudder, a ring-shaped airfoil; a flight controller. The ring-shaped airfoil aircraft has the flying abilities for vertical takeoff and landing and hovering at a fixed altitude of multiaxial rotary wing powered aircraft, but compared with multiaxial rotary wing powered aircraft, its flight attitude is hardly in by air side flow, the flight attitude is more reliable. In addition, it can implement the airspeed of fixed wing ducted aircraft, and the flight energy consumption is much less than the existing fixed wing ducted aircraft, and its takeoff and landing are free of runways. The ring-shaped airfoil aircraft can obtain the lift for aircraft, reduce the drag to aircraft and enhance its flight safety performance.

Abstract: One embodiment is a rotor system comprising a duct ring; a hub disposed centrally to the duct ring; first and second stators each connected between the duct ring and the hub; first and second control vanes rotatably connected to the first and second stators, respectively; and a structural hoop having a first end connected to the first control vane and a second end connected to the second control vane, the structural hoop for translating rotation of the first control vane about a vane axis to the second control vane.

Abstract: A rotary wing aircraft includes an airframe, a stationary mast fixedly engaged to the airframe and extending along a first axis, and an electric motor. The electric motor includes a stator assembly engaged to the mast and a rotor assembly disposed radially outward from the stator assembly and configured to rotate with respect to the stator assembly. A plurality of rotor blades project radially outward from the rotor assembly.

Abstract: The disclosure relates to an unmanned aerial vehicle, wherein the fuel cell provides a structural component of the vehicle.

Abstract: A hybrid power tri-propeller helicopter apparatus for efficient and quiet flying includes a helicopter body, a cockpit portion, an engine portion, a tail boom portion, a gas motor, a generator, a battery pack, and an electric nose motor. A nose propeller and a lift propeller support are coupled to the helicopter body. A pair of electric lift motors is coupled to the lift propeller support and is in operational communication with the battery pack. A pair of lift propellers is coupled to the pair of lift motors. A tail fin and a pair of horizontal rear stabilizer fins are coupled to the tail boom portion. A pair of front stabilizer fins is coupled to the cockpit portion. A plurality of controls is coupled to the cockpit portion and is in operational communication with the nose motor, the pair of lift motors, and the pair of rear stabilizer fins.

Abstract: A radial airfoil is an airfoil having a tip profile and a hub profile of an airfoil that were set apart at different angles of attack and joined by lofted top and bottom surfaces. The top surface is usually a convex surface, whereas the bottom surface is a slightly convex to substantially straight flat surface. The lift disc is a device including multiple radial airfoils that generate additional lift from the spent air from a VTOL (Vertical Take-off and Landing) machine, like a drone or helicopter. The lift disc can be used in several ways to assist the VTOL machines to generate lift. It can be used in a static mode where the lift disc is a non-moving element of the VTOL system. In a dynamic mode, the lift disc replaces the propeller and acts as a propeller to generate lift.

Abstract: UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods are disclosed. A representative configuration includes a fuselage, first and second wings coupled to and pivotable relative to the fuselage, and a plurality of lift rotors carried by the fuselage. A representative battery augmentation arrangement includes a DC-powered motor, an electronic speed controller, and a genset subsystem coupled to the electronic speed controller. The genset subsystem can include a battery set, an alternator, and a motor-gen controller having a phase control circuit configurable to rectify multiphase AC output from the alternator to produce rectified DC feed to the DC-powered motor. The motor-gen controller is configurable to draw DC power from the battery set to produce the rectified DC feed.

Abstract: Described is an apparatus and method of an aerial vehicle, such as an unmanned aerial vehicle (“UAV”) that can operate in either a vertical takeoff and landing (VTOL) orientation or a horizontal flight orientation. The aerial vehicle includes a plurality of propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll) when in the VTOL orientation. The aerial vehicle also includes a ring wing that surrounds the propulsion mechanisms and provides lift to the aerial vehicle when the aerial vehicle is operating in the horizontal flight orientation.

Abstract: A protection system for a classroom or other space to protect against a terrorist. The system includes a fixed control unit and a mobile control unit. The fixed control unit contains a hanger for drones to be launched against the terrorist. The fixed control unit also includes data storage units, a computer, a computer program and a memory, power storage units, a sighting laser for obtaining location information about the terrorist and an etching laser for marking the terrorist, an optics system for receiving visual information, and a telecommunication unit to send and receive information. The mobile control unit is worn by a protecting person in the space and includes some of the same components as the fixed control unit. It also has a local aiming system that includes for example a rifle type sight. The drone is a self-contained, self-propelled robotic flying vehicle that can be very small or even the size of a mouse. It has a mag-lev engine, electrical storage units and an aeronautically shaped body.

Abstract: A rotation-stabilized beamed-energy receiver, and associated systems and methods, including an aircraft carrying a rotating electromagnetic energy receiver that, when rotated, is supported by centripetal force in a selected shape and/or orientation. Accordingly, the receiver can be made from very thin and/or otherwise lightweight/flexible materials, while performing an energy-receiving function.

Abstract: Described is an unmanned aerial vehicle (“UAV”) that includes a lifting propulsion mechanism that is circumferentially-driven and includes a propeller assembly and a propeller rim enclosure. The propeller assembly includes a plurality of propeller blades that extend radially and are coupled to an inner side of a substantially circular propeller rim that encompasses the propeller blades. Permanent magnets are coupled to an outer side of the propeller rim. The propeller rim and the magnets are positioned within a cavity of the propeller rim enclosure such that the propeller rim will rotate within the propeller rim enclosure. Also within the cavity of the propeller rim enclosure are electromagnets that are used to cause the propeller rim to rotate.

Abstract: An aircraft is provided and includes an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe, at least one sensor and at least one inertial measurement unit (IMU) to sense current flight conditions of the aircraft, an interface to execute controls of a main rotor assembly in accordance with control commands and at least one flight control computer (FCC) to issue the control commands. The at least one FCC includes a central processing unit (CPU) and a memory having logic and executable instructions stored thereon, which, when executed, cause the CPU to issue the control commands based on the current flight conditions and a result of an execution of the logic for the current flight conditions.

Abstract: A tiltrotor assembly has a central hub with a plurality of rotor blades extending therefrom and is configured to rotate about a mast axis to generate lift in a hover position. The central hub is configured to rotate about a tilt axis between the hover position and a forward-flight position such that rotation about the mast axis generates forward thrust. The central hub is surrounded by a segmented duct that includes a thin rotatable inner ring and a wide fixed outer ring. The inner ring is configured to rotate with the central hub about the tilt axis leaving the wide outer ring in a generally horizontal position.

Abstract: Thermal management system for unmanned aerial vehicles are disclosed. An example housing for an unmanned aerial vehicle includes a central portion defining a cavity. The housing also includes a first arm to support a first propeller. The first arm has a first proximal end coupled to the central portion and a first distal end spaced from the central portion. The first distal end defines an inlet. The first arm defines a first fluid path in communication with the inlet and the central cavity. The housing also includes a second arm to support a second propeller. The second arm has a second proximal end coupled to the central portion and a second distal end spaced from the central portion. The second distal end defines an outlet. The second arm defines a second fluid path in communication with the outlet and the central cavity. The inlet and outlet are in fluid communication via the first path, the central cavity and the second path.

Abstract: Various embodiments include methods, devices, and aerial robotic vehicles for adjusting a proximity threshold implemented in a collision avoidance system based on whether propeller guards are installed. Methods may include an aerial robotic vehicle processor determining whether a propeller guard is installed, setting, a proximity threshold for collision avoidance based on the determination as to whether propeller guard(s) is/are installed on the aerial robotic vehicle, and controlling one or more motors of the aerial robotic vehicle using the proximity threshold for collision avoidance. When propeller guards are installed, the proximity threshold may be set at a smaller distance than when propeller guards are not installed. The determination of whether a propeller guard is installed may be based on sensor data from one or more sensors configured to detect or indicate the presence of a propeller guard, and/or based on rotor revolution rates determined from a motor or motor controller.

Abstract: An aircraft and an outer shell therefor. The aircraft includes an outer shell; and main body components, accommodated in the outer shell. The outer shell includes: an inner cavity, the inner cavity being provided with a space for at least accommodating the main body components of the aircraft; an outer surface, the outer surface enclosing the inner cavity.

Abstract: A rotor blade rotation system includes two or more rotor blades, each rotor blade in mechanical communication with a hub and pivotable about an axis of rotation, a bearing plate comprising a rotating portion and a non-rotating portion, a fold linkage coupled to the rotating portion of the bearing plate and in mechanical communication with the rotor blade, and an actuator coupled to the non-rotating portion of the bearing plate and operable to reposition the bearing plate from a first position to a second position such that the folding links pivot the rotor blades from a deployed position to a forward folded position.

Abstract: A flying vehicle with a fuselage having a longitudinal axis, a cockpit extending substantially from the center of the fuselage, a left front wing extending from the fuselage, a right front wing extending from the fuselage, a left rear wing extending from the fuselage, a right rear wing extending from the fuselage. Each wing contains a rotor rotatably mounted and a direct drive brushless motor providing directional control of the vehicle. A centrally located ducted fan encompasses the cockpit and provides VTOL capabilities. The central location of the cockpit and central ducted fan aid in balance and stability. The central ducted fan is itself a brushless motor with the stator windings encapsulated in the ducted fan housing and rotor magnets within the fan. All motors and rotatable mounts are controlled by a fly-by-wire system integrated into a central computer with avionics allowing for autonomous flight.

Abstract: An aerial platform having motive devices for obtaining and maintaining loft of the aerial platform, the motive devices being pivotable relative to a wing of the aerial platform for aerial maneuvering of the aerial platform while generally maintaining stable disposition of the wing relative to the ground. The motive devices may include blades having selectively adjustable pitch for varying output force of respective motive devices. The aerial platform may further include one or more bladed turbines outwardly coupled to the wing and drivable by wind for generating power for the aerial platform. In some cases, the aerial platform may be tethered via a flexible power cable to a power source.

Abstract: An aircraft includes a fuselage having an upper surface and a lower surface and a plurality of planetary modules housed in the fuselage, an individual planetary module having a first jet engine directed outward of the upper surface of the fuselage and a second jet engine directed outward of the lower surface of the fuselage, the individual planetary module rotatable within the fuselage about a vertical axis.

Abstract: Various embodiments of a propeller-enclosed airlifting air tube apparatus are disclosed. The propeller-enclosed airlifting air tube apparatus contains a unique multi air-tube structure that functions as a plurality of air outtakes to produce stable lift force with one or more propellers enclosed in the apparatus. By encapsulating the propellers within the outer shells, the airlifting air tube apparatus is able to reduce potential bodily harm and property damage risks during a flight operation in a densely-populated environment or in another environment involving tight spaces. Preferably, the airlifting air tube apparatus encapsulates one or more pairs of contra-rotating propellers inside a drone casing to enhance operational safety while minimizing the overall footprint of the apparatus. Furthermore, the airlifting air tube apparatus incorporates a novel flight control steering unit configured to change directions and altitudes of the apparatus by dynamically adjusting airflow to each outtake air tube.

Abstract: Described is an apparatus and method of an aerial vehicle, such as an unmanned aerial vehicle (“UAV”) that can operate in either a vertical takeoff and landing (VTOL) orientation or a horizontal flight orientation. The aerial vehicle includes a plurality of propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll) when in the VTOL orientation. The aerial vehicle also includes a ring wing that surrounds the propulsion mechanisms and provides lift to the aerial vehicle when the aerial vehicle is operating in the horizontal flight orientation.

Abstract: An unmanned aerial vehicle includes a housing, at least one driving module, and at least one driving module. The housing includes an outer structure made of shock-absorbing material, and an inner structure made of rigid material, the inner structure partially embedded into the outer structure. The at least one driving module is assembled to the housing. The at least one detecting module is fixed on the inner structure and surrounded by the outer structure.

Abstract: Disclosed is a multipurpose air vehicle including a frame (1) on which a propeller (11) and a mechanical unit (10) equipped with an engine are mounted, and a cabin (2) is coupled inside the frame (1). The frame (1) is constructed by upper and lower circular plates (101, 102) and curved posts (111, 112, 113, 114) that interconnect the upper and lower circular plates (101, 102), and is provided with two or more arms (12) that can protrude and retract, and a propeller (11) is provided on the tip end of each arm (12). The cabin (2) includes a circular plate member (3) and further includes at least four connectors (21) provided on the front, the rear, the left, and the right ends thereof, and each connector (21) has a tip end installed on a rail (13) of the frame (1) so as to guide pivoting of the cabin (2). The multipurpose air vehicle may freely perform upward and downward movement and forward and rearward movement, and thus may be used anywhere in the air, ground, or water.

Abstract: An aerial vehicle including a set of rotors, a processor configured to configured to control the set of rotors for aerial vehicle flight, and a housing defining a plurality of cooling channels, wherein, for each rotor of the set, a projection of the processor and the cooling channels onto the respective rotor plane does not intersect the swept area of the rotor, and a distance from the rotor axis of a first rotor of the set to a cooling channel is less than 75% of a rotor diameter of the first rotor. A method for aerial vehicle operation, including providing an aerial vehicle including a rotor, a processor, and a housing, flying the aerial vehicle, and, while flying the aerial vehicle, actively cooling the processor, including, at the rotor, forcing airflow toward the processor.

Abstract: Described is an unmanned aerial vehicle (“UAV”) that includes a lifting propulsion mechanism that is circumferentially-driven and includes a propeller assembly and a propeller rim enclosure. The propeller assembly includes a plurality of propeller blades that extend radially and are coupled to an inner side of a substantially circular propeller rim that encompasses the propeller blades. Permanent magnets are coupled to an outer side of the propeller rim. The propeller rim and the magnets are positioned within a cavity of the propeller rim enclosure such that the propeller rim will rotate within the propeller rim enclosure. Also within the cavity of the propeller rim enclosure are electromagnets that are used to cause the propeller rim to rotate.

Abstract: A personal propulsion device, including a platform configured to support a passenger's body; and at least one fluid discharge nozzle coupled to the platform and angled with respect to the platform, where the angle defined between the nozzle and the platform is between approximately 95° and 120°; where the personal propulsion device is configured to receive pressurized fluid from a remote pressurized fluid source, and where the personal propulsion device is configured to achieve flight.

Abstract: The sealed bottoms of aircraft passenger cabin have to be fastened with heavily sized fasteners so as to withstand loads induced by the cabin pressurization. Besides, the increase in aircrafts seating capacity makes an increase in passenger cabin widths of interest. Such a width increase however makes the structure delimiting passenger cabin less resistant to efforts induced by the cabin pressurization. The present invention proposes an aircraft wherein the structure delimiting passenger cabin extends over 360 degrees around a space defined outside structure. The invention allows structure to be more resistant to loads induced by the cabin pressurization, while allowing to reduce or even to avoid the need for a sealed bottom, and while allowing to increase the space available for passengers.

Abstract: The present disclosure provides a fuselage of an unmanned aerial vehicle. The fuselage comprises an upper plate, a lower plate opposite to the upper plate, a connecting plate, and a middle spacing plate; the connecting plate is connected between the upper plate and the lower plate; the upper plate, the lower plate, and the connecting plate are enclosed to define a receiving space; the upper plate, the lower plate, the connecting plate, and the middle spacing plate are integrally formed; the upper cavity is located between the middle spacing plate and the upper plate, and the lower cavity is located between the middle spacing plate and the lower plate; and a first mounting opening is defined in the upper plate allowing a component to enter the upper cavity, and a second mounting opening is defined in the lower plate allowing a component to enter the lower cavity.

Abstract: The invention relates to a device suitable for vertical and horizontal transport of loads, in particular heavy loads, in good weather conditions, using the load-bearing capacity obtained by means of blowing a stream of air, produced by a generator, on two longitudinal lifting wings, substantially rectilinear, arranged symmetrically on either side of a supporting structure, to which the wings are connected.

Abstract: Autonomous propulsion apparatus and methods are disclosed. An example autonomous propulsion unit includes a flight controller capable of executing flight control instructions stored in a memory of the autonomous propulsion unit; and a propulsor to generate propulsion in accordance with the instructions for a payload carrier to which the autonomous propulsion unit is coupled, wherein the flight controller is to provide flight control for the propulsor in an absence of flight control instructions from the payload carrier.

Abstract: A method and apparatus are disclosed for a turboprop-powered medium altitude long endurance (MALE) aircraft, having: a heat exchanger with a heat-storage material, for example a heat-storage wax; and an air recirculation path. The heat exchanger can be arranged to cool air recirculating around the air recirculation path which is arranged to provide cooling to the MALE aircraft, for example to an equipment bay. The heat-storage material may be cooled by ground-based cooling apparatus when the aircraft is on the ground and/or by ram air when the aircraft is in flight. The heat-storage material may have a melting point selected so as to be rendered solid during ground-based cooling and/or ram air cooling, and/or selected so as to undergo melting while cooling the air recirculating around the air recirculation path.

Abstract: A turbine creating fluid displacement or thrust having an outer frame superstructure comprised of opposed disk assemblies extending parallel, each joined concentrically to a central sun gear and central drive shaft housing, each spaced apart along a central axis defining an interior operating space to support a motor driven driveshaft joined to a rotatable interplanetary assembly that secures two or more orbiting evenly spaced planetary turbines by bearing means each having a pivoting wing/s which presents a maximum contact surface profile in drive maximally impinging on air or water and pivoting back to a position of least resistance in glide thereby creating current or thrust, each made to counter rotate, once around its axis as the interplanetary assembly rotates once around the propulsion turbine's central axis, each maintaining a transverse planetary turbine and wing orientation relative to the direction of created thrust or fluid displacement.

Abstract: This invention relates to a craft designed to move through or on a surface of a fluid. It is believed to be principally of use in relation to airborne craft and missiles but the theory behind the invention is equally applicable for example to submarines.

Abstract: A two-stage fan provides efficient aerodynamic lift by concentrating and directing a generated high velocity airstream through channels and over sets of airfoils and wings which are contained within a cylindrical housing. Horizontal and vertical control is achieved by manipulating angle-of-attack of the airfoils.

Abstract: A lift generating device is provided enabling vertical flight. The lift generating device includes a first revolution structure having a funnel shape and a second revolution structure having a funnel shape. Each revolution structure includes a circular open surface and an open stem. The second revolution structure is attached to the first revolution structure by a plurality of connectors so as to form a gap between the first revolution structure and the second revolution structure. A propeller is coupled to an open stem at a bottom end of the first revolution structure and a motor is operatively connected to the propeller to provide power for the propeller to suction air into the lift generating device.

Abstract: Methods and apparatus for vertical or short takeoff and landing. In one embodiment, the apparatus comprises two or more counter driven rings with one or more airfoils attached. In one variant, there is an upper ring and a lower ring, each with multiple airfoils attached. In one variant, lift is generated largely via ambient air currents, allowing for long term on-station operation of the device.

Abstract: The design and refinement of a tethered hovering platform into a feasible working system is presented. To determine a starting point for the design, a detailed historical search was conducted to find the history and the current state of such technology. Real world current needs are analyzed to produce a mission specification and to drive the preliminary vehicle design. Analysis of environmental conditions and decisions about an initial payload package are made in conjunction with motor and propeller sizing. Initial concept testing to discover feasibility and operational issues was performed; from this, instability issues were discovered. Analyzing these instability issues using known rotorcraft and momentum effects, in conjunction with flight testing, yields possible solutions to the problem. The use of constrained layer dampers as a means of passive stabilization is addressed and suggested as the preferred solution. Testing of passive constrained layer damping verifies the stability of the solution.

Abstract: A magnetic suspension electric rotor flying saucer comprises: a saucer shell (1), a saucer cabin (2), a rotor system (3), and a control system (4). The rotor wing system is a magnetic suspension electric rotor wing system (3) composed of a magnetic suspension rotor wing wheel (5), an electrodynamic ring (6), a magnetic suspension shaft (7) and magnetic suspension lead rails (8). The electrodynamic ring (6), the magnetic suspension shaft (7) and the magnetic suspension lead rails (8) are fixed on the saucer shell (1). The magnetic suspension rotor wing wheel (5) is suspended in space limited by the electrodynamic ring (6), the magnetic suspension shaft (7) and the magnetic suspension lead rails (8) and rotates around the magnetic suspension shaft (7) by the electromagnetic thrust.