201results about How to "Big lift" patented technology

A buttock lift support extends a lift band from each of a pair of elastic leg bands to a waistband so as to wrap around the buttocks of the wearer and exert an upward pressure thereon. Side, rear and front panels, and a thong strap can be incorporated to create a panty garment having the lift support integrated therein.

The invention discloses an aircraft generating a larger lift from its interior. The fluid channel inside the aircraft communicates with the engine and the ports on the upper surface of the outer shell. With the powerful suction of the engine, the fluid on the upper surface of the outer shell is quickly sucked into the fluid channel via respective ports under conditions of long path, large area, high speed and low air pressure, which results in large lift from the interior of the aircraft. In the course of generating the lift, the fluid resistances of the fluid wall and the fluid hole are sucked into the fluid channel through the ports at the front and the surrounding area of the aircraft, then high-speed fluid is emitted from the rear port. This approach contributes greatly to the transformation of the existing aircraft. The unified big wing significantly improves the lift, the speed and the carrying capacity of the existing aircraft with lowered energy consumption.

Food processing utensil comprising: paddles, central utensil comprising: shaft coupleable to food processor motor, and connected to base coupleable to food processor bowl, and cutting blades, the paddles coupled to the central utensil and the blades configured to allow uniform cutting of food, providing paddles are not on blades.

The invention discloses an aircraft generating a larger lift from its interior. The fluid channel inside the aircraft communicates with the engine and the ports on the upper surface of the outer shell. With the powerful suction of the engine, the fluid on the upper surface of the outer shell is quickly sucked into the fluid channel via respective ports under conditions of long path, large area, high speed and low air pressure, which results in large lift from the interior of the aircraft. In the course of generating the lift, the fluid resistances of the fluid wall and the fluid hole are sucked into the fluid channel through the ports at the front and the surrounding area of the aircraft, then high-speed fluid is emitted from the rear port. This approach contributes greatly to the transformation of the existing aircraft. The unified big wing significantly improves the lift, the speed and the carrying capacity of the existing aircraft with lowered energy consumption.

A rotor that consists of a central hub or shaft and a plurality of boot shaped integral blade / vane units that combine a pronounced elongated vane tip extending substantially toward the incoming flow and also the direction of rotation forming a helix or pitch angle to the rotation axis centreline, preferably normal to and joined to the outer frontward extremity of a slightly rearward tilted blade / wing section that is connected by its inner end to the central hub of shaft. The rotor revolves about the rotation axis by incoming gas / fluid flow as most of the fluid flow is encouraged to move substantially outward and rearward as it travels into and past the forwardly projecting vane tips located a substantial distance radially from the axis of rotation. This maximises the torque developed and transferred to the hub / shaft in a manner that does not greatly inhibit total through flow, because the combined gas / fluid flow exit area (or gaps between blades / vanes) is much greater than the maximum rotor diameter and subsequently the rotor inlet area, which has the effect of increasing the through flow velocity and thus overall performance. The blades may have slots within them.

A watercraft capable of operating in hydrofoil mode or ground-effect mode with self-righting retractable V-shaped foil, fiberoptic control systems, and a plurality of aircraft style engines with variable pitch propellers for speed and direction control. The V-shaped foil can be fully retracted into the hull allowing operation in shallow water, and the ability to execute a beach landing. Propeller pitch can be reversed allowing the craft to backup. Each engine and propeller can be controlled individually allowing rotating in-place for precise maneuvering control. The hull is a flying wing, airfoil shape for efficient high-speed operation. Engine nacelles are located on airfoil shaped struts, angled in a V-shape, for self-righting effect at high speed. Fuel tanks are within the nacelles, thus outside the main hull for safety.

The invention provides a section-variable tunnel-crossing lining trolley which comprises a portal system, a template system, a connecting part and a walking mechanism, wherein the portal system comprises a frame part, a jacking mechanism and a bracket part; the jacking mechanism comprises multiple sets of jacking single pieces; each of the jacking single pieces comprises a multi-level jacking part; the bracket part comprises a truss girder and an adjusting support frame for a walking mechanism; the template system comprises a top template, a left template and a right template; and the connecting part comprises a support jack and a hydraulic cylinder. The section-variable tunnel-crossing lining trolley provided by the invention has the effects that the whole structure is simple; the assembling is convenient; the jacking mechanism is in a multi-level jacking mode; the trolley not only can adapt to the construction for the tunnel sections in different heights but also can achieve higher lifting volume; the trolley can meet the requirement of constructing multiple parallel tunnels by one trolley in the manner of constructing the working tunnel; due to the design of the bracket part, the lining trolley can meet the stability requirement, and meanwhile, the structure is simplified and the whole trolley can be supported.

A rotor blade assembly for providing vertical lift to an aircraft, having a rotor head and a plurality of blades, with each blade attached to a mechanism such as a cam surface, whereby movement of the mechanism causes the radial distance between the distal tip of the attached blade and the center of the rotor head to alter, decreasing or increasing the length of the lifting surface. The blades are moved from a fully extended position providing maximum lift, to a retracted position in which the blades are removed from the airstream. The pitch of the blades may be controlled to achieve full helicopter responsiveness. A plurality of bladeletts may be positioned near the outer periphery of the rotor head. When they are moved into the airstream, passing air impacts the bladeletts exerting a pressure, causing rotational movement of the rotor blade assembly.

The invention discloses a lateral impact testing device for a target object. The device comprises a frame, an impact hammer, an impact hammer height measuring part, an impact hammer height adjusting part, an impact hammer speed measuring part, a secondary collision preventing part and a display screen, wherein the impact hammer height measuring part is composed of a displacement sensor arranged on the frame; the impact hammer height adjusting part comprises a stretchable connecting rod and an electric push rod, and the rear end of the impact hammer is fixed at the other end of the stretchable connecting rod; an electromagnetic relay is arranged on the stretchable connecting rod, and one end of the electric push rod is hinged to the frame while the other end is connected to the magnetic relay; the impact hammer speed measuring part comprises a photogate and a light barrier, the photogate is arranged on a lifting rod and the light barrier is fixed on the impact hammer; and the secondary collision preventing part comprises a rotary shaft, a brake pad, a brake caliper, a brake line and a controller. The device can provide a relatively great impulse, can effectively avoid secondary collision, is convenient to use and relatively low in cost, and can be applied to various lateral impact tests for the target object.

A power generation apparatus comprises a rotor rotatably mounted to a support and a plurality of vanes extending radially out from the rotor and positioned to be engaged by a moving fluid stream. Each vane includes a wing-shaped main blade having leading and trailing edges, and a co-extensive conditioner blade having leading and trailing edges. The conditioner blade is spaced parallel to the main blade so as to define therebetween a slot having an entrance and an exit. A lift-varying device boarders the slot to vary the lift produced by that vane inversely to the speed of the moving fluid stream so that the rotor turns at a relatively constant rate. The rotor, driven by wind or water, may be coupled to the armature of an induction motor / generator to produce electric power.

The invention relates to a portable drilling machine capable of implementing wire-line core drilling, which comprises a base, a post, a mast, an inclined support, a sliding sleeve device, a back plate, a hydraulic power supply, a hydraulic power head, a winch, a pulley, a steel wire rope, an elevator, a Trojans gripper and a feed lifting device, wherein the post is fixed on the base; the sliding sleeve device is arranged on the post; the back plate is connected with the sliding sleeve device; the hydraulic power source is connected with the hydraulic power head by a hydraulic oil pipe; the hydraulic power head is connected with the back plate; the winch is fixed on the base; the pulley is fixed on the upper end of the mast; one end of the steel wire rope is a free end bypassed through the pulley, and the other end of the steel wire rope is fixed on the winch; the elevator is connected with the free end of the steel wire rope; and the Trojans gripper is installed on the base. As the portable drilling machine disclosed by the invention is provided with the portable winch, the mast, the pulley, the steel wire rope, the elevator and the portable Trojans gripper, the wire-line core drilling can be realized.

The spacecraft structure is provide, the spacecraft structure for the spacecraft includes, a center fuselage, right wing side fuselage, left wing side fuselage, front wings, and rear wings of Arch-Wings, vertical winglets, and the first levels, the fuselage has a cross-section of substantially flat floor fuselage shape, being is wide enough to provide lifting force.The front wings of the Arch-Wings are disposed horizontally in rear portions of the fuselage the vertical winglets are disposed the top of the rear fuselage the first level disposed fuel tank storage, plurality of landing gear bays, cockpit with control panel, various avionic instruments, cabin doors.The top of the rear fuselage disposed jet-power plants and further more at compartment of the Arch-Wings disposed rocket power plants.The fuselage provide lifting force and the wings provides lifting force and steering force, he whole structure of spacecraft comprises carbon fiber honey comb composite molded structure which is makes the spacecraft lighter weight and shear strong.At the front portion of wing body compartment of the Arch-Wings comprises retro rocket power plant with covered door, and under belly of the Arch-Wings disposed pontoon systems which could provide float at sea port.

The invention relates to the technical field of an internal combustion engine, in particular to a device for adjusting a lift of an intake valve of a supercharged engine. The device comprises an intake channel, an exhaust channel, a lower intake valve section, an exhaust valve, an upper intake valve section, a volumetric cavity, a moving body, a penetrating tube, a moving block, a connecting tube and a spring, wherein the moving body is arranged in the volumetric cavity and is contacted with the inner wall surface of the volumetric cavity in a sealing way, the penetrating tube is arranged in a way of penetrating the upper wall surface and the lower wall surface of the moving body, the moving block is arranged in the penetrating tube and is contacted with the inner wall surface of the penetrating tube in a sealing way, a plane is adopted by the lower end face of the moving block, a slope is adopted by the upper end face of the moving block, two ends of the connecting tube are respectively communicated with the left wall surfaces of an intake tube and the volumetric cavity, and the right wall surface of the moving body is connected with the right wall surface of the volumetric cavity through the spring. When the pressure in an exhaust tube of the engine is relatively high, the moving body can move rightwards, and the lift of the intake valve can be increased; and when the pressure in the exhaust tube of the engine is relatively low, the moving body can move leftwards, and the lift of the intake valve can be decreased. The device has the advantages of reasonable design and simple structure and is suitable for a variable valve lift system of the supercharged engine.

A power generation apparatus comprises a rotor rotatably mounted to a support and a plurality of vanes extending radially out from the rotor and positioned to be engaged by a moving fluid stream. Each vane includes a wing-shaped main blade having leading and trailing edges, and a co-extensive conditioner blade having leading and trailing edges. The conditioner blade is spaced parallel to the main blade so as to define therebetween a slot having an entrance and an exit. A lift-varying device boarders the slot to vary the lift produced by that vane inversely to the speed of the moving fluid stream so that the rotor turns at a relatively constant rate. The rotor, driven by wind or water, may be coupled to the armature of an induction motor / generator to produce electric power.

A blade pitch controlling apparatus and an application thereof are described. The blade pitch controlling apparatus includes a centrifugal device and a blade pitch variable device, and the blade pitch variable device is arranged under the centrifugal device. The blade pitch variable device has a downward stroke that is variable by the centrifugal device according to a centrifugal force induced thereon so as to drive the blade pitch variable device to change the setting angle of the blades of the wind power generator.

In a rotatable duct type shrouded rotating wing, permanent magnets are arranged in the outer periphery of a rotatable duct, rotor blades are connected to the inner periphery of the rotatable duct, the rotor blades having a rotatable support portion at about every 2.5 m to prevent deflection or distortion. The shroud and the rotatable duct are constantly in vertical contact with each other, and an appropriate horizontal spacing is provided between the inner periphery of the shroud and the outer periphery of the rotatable duct to permit expansion and contraction of the rotatable duct and the rotor blades. Accordingly, even if the shrouded rotating wing is of a large radius, is used in a horizontal orientation and undergoes a rapid change of direction mounted to a turntable, it always rotates stably to generate lift and thrust.

A height-adjustable support (10) for semi-trailers or similar, comprising a locally fixed external support tube (13), an internal support tube (14), which is fixed to a nut (18) on a spindle (17), the spindle being driven by a change-over gear and a bevel gear assembly. The change-over gear has two gear wheel stages which can be alternately activated, a separate gear stage comprising bevel gear toothing being provided for the distribution of forces after each gear wheel stage.

The invention relates to a miniature ornithopter with a wing twisting function and multiple flight motion functions and belongs to the field of miniature ornithopters. A flapping torsional mechanism, an empennage, a fuselage direct-current motor, an empennage supporting rod and an electronic control module are installed on an ornithopter frame body. Wings are connected to torsional panels. An adjusting and steering rotor is connected to a fan motor. An empennage transmission mechanism is connected to the empennage supporting rod. The empennage supporting rod and the empennage are fixedly connected together by an empennage supporting rod fixing structure through screws. The miniature ornithopter has the beneficial effects that the structure is novel, the design structure is simplified, and miniaturization is easy to achieve. The ornithopter can generate larger pushing-up force compared with an aircraft only flapping up and down under the condition that the flapping frequencies are the same, the flight performance of the miniature ornithopter is greatly improved, the ornithopter flies flexibly, the aerodynamic characteristics are improved, the flight efficiency is high, the size is small, the weight is small, practicality is higher, and more flight functions can be achieved.

A centrifugal separator for separation of at least two components of a fluid mixture which are of different densities includes a frame, a hollow spindle rotatably supported by the frame, a centrifuge rotor mounted to a first end of the hollow spindle to rotate together with the spindle around an axis of rotation, wherein the centrifuge rotor includes a rotor casing enclosing a separation space in which a stack of separation discs is arranged, a duct arranged to be through-flown by process medium during operation of the centrifugal separator and extending through the hollow spindle and in fluid contact with said separation space, at least one liquid outlet for discharging a separated liquid phase from the separation space, and a plurality of peripheral ports extending from the separation space through the rotor casing to a surrounding space for discharging a phase from the periphery of the separation space. The centrifuge rotor includes a sliding bowl bottom movable between a closed position, in which the peripheral ports are closed, and an open position, in which the peripheral ports are open, an inlet channel for supplying hydraulic fluid to a closing chamber between the sliding bowl bottom and the rotor casing in order to hold the sliding bowl bottom in the closed position. The centrifugal separator further includes at least one hermetic seal at a second end, other than the first end, of the hollow spindle and the inlet channel for supplying hydraulic fluid to the closing chamber extends through the hollow spindle and is further arranged such that the hydraulic fluid is in thermal contact with the at least one hermetic seal when the hydraulic fluid is being supplied to the closing chamber.

A power generation apparatus comprises a rotor rotatably mounted to a support and a plurality of vanes extending radially out from the rotor and positioned to be engaged by a moving fluid stream. Each vane includes a wing-shaped main blade having leading and trailing edges, and a co-extensive conditioner blade having leading and trailing edges. The conditioner blade is spaced parallel to the main blade so as to define therebetween a slot having an entrance and an exit. A lift-varying device boarders the slot to vary the lift produced by that vane inversely to the speed of the moving fluid stream so that the rotor turns at a relatively constant rate. The rotor, driven by wind or water, may be coupled to the armature of an induction motor / generator to produce electric power.

Present invention relates to a heat exchanging apparatus, especially an all natural circulation atmospheric cooling tower used for normal pressure nuclear heat supply pile. Said all natural circulation atmospheric cooling tower includes tower body, heat transfer pipe, chimney, normal pressure pile secondary loop heat tube, rising pipe, expansion box, water tank, thermal insulation blanket and fins. Said structure characteristics effectively enlarge waterside natural circulation ability and air side reasonable natural circulation ability for ensuring transferring heat quantity to atmosphere for long time.

The invention discloses a series-parallel tilting drive mechanism of a tilt rotor aircraft, belonging to the technical field of helicopter manufacturing. The series-parallel tilting drive mechanism of the tilt rotor aircraft is formed by installing and connecting a swing engine, middle swing belt wheels, swing driving belts, a rotary engine, wing rotary belt wheels, rotary driving belts and a two-degree-of-freedom turning mechanism. The hybrid tilting drive mechanism is scientific and rational in structural design and capable of being applied to the tilt rotor aircrafts; the tilt rotor aircraft has vertical / short-distance taking-off and landing capacity; the tilt rotor aircraft has the advantages of low oil consumption, high speed, large air range, high load and the like, and the transportation cost of the tilt rotor aircraft is only half of that of helicopters.

A hair volumizing device is designed specifically for adding lift or volume to any hairstyle. The device comprises two arms with heated interlocking plates that employ interlocking two dimensional arrays of individual treatment elements with alternating spaces. The individual treatment element design and the two-dimensional array pattern provide substantial lift and holding strength. The individual treatment elements of the volumizing device transforms the under layer of hair of a person into a matrix that can support the outer or upper visible layer of hair to create volume. The various embodiments also minimize any discernible pattern left in the hair.

The invention discloses a device for automatically loading a loader rear frame onto an assembly line, belongs to the field of engineering machinery and overcomes defects that the loader rear frame needs to be manually hoisted and transferred by a traveling crane when the loader rear frame needs to be loaded onto the assembly line, and the hoisting and transferring operation is high in worker laborintensity and low in efficiency and has a potential safety hazard. The device comprises a frame and a working device and is characterized in that the frame comprises standing columns and rails, the working device comprises a traveling trolley, a lifting mechanism, a rotating mechanism and a clamping mechanism, the rails is connected with the traveling trolley, the traveling trolley is connected with the lifting mechanism, the lifting mechanism is connected with the rotating mechanism, and the rotating mechanism is connecting with the clamping mechanism. The device has the advantages that a series of actions such as the automatic grabbing, transferring, rotating and placing of the loader rear frame can be achieved, the transferring efficiency of the rear frame is increased, and labor intensity is lowered.

The invention discloses a lift source for an aircraft comprising a fuselage and wings, wherein first channels are formed in the wings, a plurality of first inlets are formed in upper surfaces of the wings, a plurality of first pressure ports are formed in lower surfaces of the wings and are communicated with the first inlets via the first channels; and spoiler devices are arranged in the first channels and under the effect of the spoiler devices, form high-speed fluid layers on the upper surfaces of the wings, thereby generating a pressure difference from the lower surfaces of the wings which counteracts an external fluid pressure on the upper surfaces of the wings in the opposite direction, so a lift is generated by reduction of fluid resistance when fluid flows through the upper and lower surfaces of the wings, thereby developing a high-speed aircraft with a larger lift and thrust.

The invention discloses an air intake valve lift-variable system in an air intake pressure regulating type, belonging to the technical field of internal combustion engines. The system comprises an air intake channel, an air exhaust channel, an air intake valve lower section, an air exhaust valve, an air intake valve upper section, a capacity cavity, a movable body, a perforation pipe, a movable block, an air inlet pipe, a connecting pipe and a spring, wherein the movable body is mounted in the capacity cavity and is contacted with the inner wall face of the capacity cavity in a sealing manner; the perforation pipe perforates the upper wall face and the lower wall face of the movable body; the movable block is mounted in the perforation pipe and is contacted with the inner wall face of the perforation pipe in a sealing manner; the lower end face of the movable block is a plane; the upper end face of the movable block is an inclined face; two ends of the connecting pipe are communicated with the left wall faces of the air intake pipe and the capacity cavity; the right wall face of the movable body is connected with the right wall face of the capacity cavity through the spring; when pressure in the air intake pipe is relatively large, the movable body is moved to right; the air intake valve lift is increased; when the pressure in the air intake pipe is relatively small, the movable body is moved to left; the air intake valve lift is reduced; and the intake valve variable-lift system is characterized by reasonable design and simple structure and is suitable for engine valve lift-variable systems.

A power generation apparatus comprises a rotor rotatably mounted to a support and a plurality of vanes extending radially out from the rotor and positioned to be engaged by a moving fluid stream. Each vane includes a wing-shaped main blade having leading and trailing edges, and a co-extensive conditioner blade having leading and trailing edges. The conditioner blade is spaced parallel to the main blade so as to define therebetween a slot having an entrance and an exit. A lift-varying device boarders the slot to vary the lift produced by that vane inversely to the speed of the moving fluid stream so that the rotor turns at a relatively constant rate. The rotor, driven by wind or water, may be coupled to the armature of an induction motor / generator to produce electric power.

A fuel injection valve, in particular an injection valve for fuel injection systems of internal combustion engines, has a valve closing body that can be activated by an activation device with the aid of a valve needle, the valve closing body interacting with a valve seat surface to produce a sealing seat, and the activation device having at least one piezoelectric first bending element for producing a valve needle lift of the valve needle, the first bending element bending when the activation device is activated. In this context, the bending element is made of a plurality of piezo elements stacked in a longitudinal direction of the first bending element, internal electrodes arranged between the piezo elements being oriented perpendicular to the longitudinal direction of the bending element.