43results about "Influencers using Magnus effect" patented technology

A method for controlling a flying projectile which rotates during flight, comprising: determining an angle of rotation of an inertial mass spinning about an axis during flight; and controlling at least one actuator for altering at least a portion of an aerodynamic structure, selectively in dependence on the determined angle of rotation and a control input, to control aerodynamic forces during flight. An aerodynamic surface may rotate and interact with surrounding air during flight, to produce aerodynamic forces. A sensor determines an angular rotation of the spin during flight. A control system, responsive to the sensor, produces a control signal in dependence on the determined angular rotation. An actuator selectively alters an aerodynamic characteristic of the aerodynamic surface in response to the control signal.

In a wind power installation with a (hollow) axis tube member and a hollow shaft mounted thereon for the rotor there is provided only a single bearing which also carries moments, between the axis tube member and the hollow shaft, whereby the parts of the machine which are to be fixed to the machine carrier and thus on the top of the pylon are of a markedly lower weight without the required orientation between the rotating and stationary parts of the electrical generator being adversely affected. In that arrangement the rotating part of the generator is radially aligned substantially with the bearing. The bearing to be used is in particular a twin-row inclined roller bearing with rows of rollers arranged at an angle of about 45° relative to each other.

A rotor sail is provided having a base (2) and a rotary cylinder (3) mounted on the base (2) in a manner permitting rotation about its longitudinal axis designed as the rotor axis (r), and a drive (5) for rotating the rotary cylinder (3). An enclosing outer surface (4) of the rotary cylinder serves as a wind-exposed surface in operation. So that the rotor sail can be operated in a more environmentally friendly manner, it is provided with a photovoltaic system (7) having solar cells (8) to generate electric energy for the drive (5) having an electric motor (6). The solar cells (8) are located in the rotary cylinder (3) and have photoelectrically active layers facing toward the enclosing outer surface (4). The rotary cylinder (3) has a sleeve (9) which is transparent, at least in an area covering the solar cells (8).

A watercraft includes a deck and no more than two flettner rotors having a height to diameter ratio of less than five. At least one of the flettner rotors is elevated above the deck such that individuals on the deck can walk underneath the flettner rotor. A portion of a footprint of at least one of the flettner rotors is suspended over an edge of the deck.

A fuel feed apparatus accommodates a sub tank. The sub tank includes a pump module The pump module generates vibration, and is supported by a supporting member and a suction filter. The suction filter is covered with a nonwoven fabric. The nonwoven fabric is used as an additional filter for removing debris in fuel drawn by the pump module. The supporting member and the nonwoven fabric have resilience. The pump module is mounted on the sub tank via the supporting member and the non woven fabric. Therefore, vibration of the pump module is not apt to be transmitted to the sub tank. Additionally, the supporting member need not to be rigidly formed, so that the supporting member can be manufactured easily.

A pump is disclosed having one or more rotating discs within a housing. The discs have a plurality of relatively small surface perturbations covering at least half of one side of their surface. The perturbations may be recessed or raised. In operation, a boundary layer is formed near the surface of the rotating discs. The fluid within the pump flows in a circular and outward direction, thus moving fluid from a central coaxial inlet to an outlet located at the peripheral wall of the housing. The surface perturbations produce turbulence within the boundary layer during operation. The pump is suitable for pumping liquids with entrained gases, liquids with entrained solids, liquids with both gases and solids, and thick liquids.

The invention discloses a high-altitude unmanned plane equipped with a Magnus effect propulsion system, wherein double-fuselage layout is adopted by the high-altitude unmanned plane; wings are mounted on external sides of two fuselages; a Magnus effect propulsion system and an empennage are mounted between the two fuselages; a propeller is mounted on the head of the fuselage; and thin-film solar cells are covered on the upper surfaces of the wings. A Magnus effect rotor can be used as a lifting device in the daytime; under the same flow velocity, the lifting force can be greatly improved by only improving rotation speed of the Magnus effect rotor, so that enough lifting force is provided for the unmanned plane even in low-speed flight, the minimum takeoff speed and the cruising speed of the unmanned plane are reduced and the short takeoff and landing and aerial low-speed cruise investigation of the unmanned plane are facilitated; the Magnus effect rotor can be used as a wind power generation device in the night for generating power by using the high-altitude stable and sustained wind energy, so that the shortage of large wing area or wingspan of the unmanned plane with the sole capability of obtaining solar energy at low energy density in the daytime for storing energy for flight is avoided.

The invention relates to a duct single screw aircraft based on Magnus effect, relating to a duct single screw aircraft. The invention solves the problems of poor safety, complex structure and difficult realization of various flying behaviour control of the traditional coaxial double-screw unmanned aircraft. The invention has the technical scheme that a steering engine duct (I), an airflow regulation duct (II) and a power duct (III) are sequentially communicated; a power device (3) is used for generating spiral airflows in the power duct (III); an airflow regulation device (2) is used for converting the spiral airflows in the power duct (III) into vertical jet-type airflows; and the vertical jet-type airflows regulated in the steering engine duct (I) generate Magnus effect force on the lateral surfaces of a hollow core wheel (11). In the invention, the Magnus effect force generated during the rotation of the hollow core wheel is used as control input, and the aircraft further realizes various flying behaviours. The invention has the advantages of simple and compact structure, low energy consumption, safety, flexible behaviour, and the like.

The present invention concerns a Magnus rotor comprising a guide roller which is arranged at the lower outer periphery of the Magnus rotor and which bears against the Magnus rotor in play-free relationship, a walkway surface arranged beneath the guide roller, and a cover which covers the guide roller and the walkway surface. In an opened condition the cover exposes the guide roller and the walkway surface so that a person on the walkway surface can perform working operations at the guide roller.

The lift and drag performance of all vehicles is strongly influenced by viscous effects, and in turn, laminar separation bubbles. This application employs an effective fluid boundary layer control strategy that reduces parasitic drag, allows for more usable angles of attack, and delays or stops separation. In the approach of this application, the control surface effectively uses the Magnus effect to delay or stop a separation bubble from forming, which can increase lift, reduce drag, and delay degrees of stall by directly manipulating the velocity gradient in the fluid boundary layer.

The invention discloses a low-speed safety aircraft capable of controlling the flight attitude by an aerodynamic force. The low-speed safety aircraft comprises a flexible aircraft, an engine, a gas compressor, a supply air distributor, vortex chambers, high-pressure gas cells, strip-shaped jet flow seams, helium airbags, a safety cabin and the like. Compressed gas in the gas compressor is ejected to airfoils through the strip-shaped jet flow seams arranged at the transition positions of leading edges and the airfoils of wings to generate a lift force and a push force, and is ejected to airfoils through the strip-shaped jet flow seams arranged at the transition positions of leading edges and the airfoils of a horizontal tail and a vertical tail to generate a wing effect to control the flight attitude. Through the application of a flight control principle and the combination with flexible body-wings, the helium airbags and the safety cabinet, the super-safe low-speed aircraft is formed. The low-speed safety aircraft has the advantages that fuel consumption is reduced greatly; piloting is easy; due to super-strong low-speed safety and controllability, the low-speed safety aircraft can be widely applied to prospecting, shooting, urban road monitoring, aerial advertising and the like; a super entertainment project suitable for the crowds which have firsthand experience of piloting a plane to flight, without pilot licenses, can be further developed.

A heat dissipating module includes a rotational member, a stationary member and a driving member. The rotational member meshes with the driving member and has an uneven surface at a side thereof to space to the stationary member. The stationary member has plural flow passages and each flow passage has an air inlet at an end thereof and an air outlet at another end thereof. When the driving member actuates the rotational member to rotate with the fluid, the fluid enters the stationary member via the inlet and gathers at the outlet before being guided outward for concentrating the air and cooling the heat dissipated object.

The invention relates to a Magnus rotor comprising a cylindrical body of revolution for converting wind power into a feed force using the Magnus effect. The Magnus rotor comprises: a rotational shaft about which the body of revolution rotates; a support member on which the body of revolution is mounted; and a body of revolution which has means for the reinforcement thereof. The body of revolution is primed in at least two planes arranged at a mutual spacing in the axial direction perpendicular to the rotational shaft of the body of revolution in order to accommodate balancing weights. The invention further relates to a method for balancing a body of revolution according to the invention.

The invention concerns a ship, in particular a cargo ship, comprising at least one Magnus rotor for driving the ship, which has a stationary carrier. The invention concerns in particular a ship in which arranged on the carrier is a measuring device for determining a flexural loading on the carrier.

The invention further concerns a method of determining the thrust of a Magnus rotor, a Magnus rotor and a carrier for mounting a Magnus rotor.

A fluid flow device, a method of moving fluid, and a printing system incorporating the device are provided. The fluid flow device includes a passage for a fluid including a wall with the wall having a travel path. A fluid flow source is operable to cause the fluid to flow in a direction through the passage. The travel path of the wall is in the same direction as that of the fluid flow.

The invention discloses a lifting-force-reinforced wing section based on the Magnus principle. The lifting-force-reinforced wing section comprises a front wing body, a Magnus cylinder and a tail wing body; the longitudinal ends of the front wing body and the longitudinal ends of the tail wing body are respectively, vertically and fixedly connected with opening sealing bodies to form the lifting-force-reinforced wing section with the cross section in a streamline shape; the Magnus cylinder is embedded between the front wing body and the tail wing body, and a driving device of the Magnus cylinder is arranged in one opening sealing body and the tail wing body; and a plurality of air inlet pipe horizontally penetrating through the front wing body are longitudinally arranged in the front wing body at intervals. The Magnus cylinder is embedded between the front wing body and the tail wing body, so that wing wake flow is improved, and tail vortex is reduced. Furthermore, the Magnus cylinder is convenient to install, disassemble and replace. The air inlet pipes on the upper side of the central line of the Magnus cylinder can supplement the air volume to guarantee that the Magnus cylinder can generate pressure difference. Thus, the lifting force can be further reinforced.