1472results about How to "Large thrust" patented technology

The invention discloses a flapping wing device for achieving active torsion of flapping wings and wing planes of an aerofoil, and belongs to the field of bionics flapping wing flight driving devices. The flapping wing device comprises a flapping wing swing rod, two spherical hinge pins, an aerofoil torsion connecting rod, a driven conical gear, an aerofoil torsion crank, a right side flapping wing connecting rod, a right side flapping wing crank, a right side flapping wing straight gear, a left side flapping wing straight gear, a left side flapping wing crank, a left side flapping wing connecting rod, a speed reduction gear, a motor output gear, an electromotor, two aerofoil frameworks, two rotary pairs and two moving pairs. A flapping flight vehicle by adopting the flapping wing device can achieve wing plane flapping and torsion flight of wings at the same time without installing an additional torsion driving motor and a matched drive device thereof for the wings on two sides, and the driving device is integrally simple to design and is light in weight, so that the flapping flight vehicle can obtain great lifting force and push force; and the maneuverability of the flight vehicle is improved to a certain degree.

The invention provides an internal waverider-derived hypersonic inlet based on arbitrary shockwave shape and a design method thereof. The structure of the internal waverider-derived hypersonic inlet comprises an inlet contraction section and an inlet insulation section; wherein the inlet contracting section is inward contracted in three-dimension; hypersonic velocity incoming flow forms irregular initial incident three-dimensional shockwave at the inlet; and the shockwave closes the three-dimensional inlet surface completely. The design method comprises the following steps: an internally contracted axisymmetric basic flow field used as a base is formed by the combination of ICFA flow field and partial Buesemann flow field; and after shapes of shockwave sections with different centers of curvature and directions of curvature are appointed, flown line tracing of the basic flow field with different centers and different radial positions is carried out on a plane in each circle of the hypersonic inlet to obtain the internal waverider-derived hypersonic inlet based on arbitrary shockwave shape. The internal waverider-derived hypersonic inlet and the method have the advantages of ensuring that the hypersonic inlet captures the incoming flow in full flow, increasing thrust force of an engine while reducing overflow resistance, improving pneumatic performance of an outlet of the hypersonic inlet, reducing windward external resistance of the hypersonic inlet, and improving starting performance of low-mach number of the hypersonic inlet.

The invention relates to a multi-freedom degree bird-like flapping wing air vehicle. The multi-freedom degree bird-like flapping wing air vehicle comprises a driving mechanism, two twisting mechanisms, an empennage mechanism, two flexible joint structures and a machine frame. The multi-freedom degree bird-like flapping wing air vehicle is simple and compact in structure, and fully-symmetrical flapping wing movement can be realized. Two rubber flexible grooved mechanisms are arranged, so that the flapping wing air vehicle can fly like a bird; flapping wings are curved and folded, so that when the flapping wings flap upwards, a stressed area is reduced, and the resistance is reduced; when the flapping wings flap downwards, the wing extending area is the largest; besides, outer wings can also be passively bent in a flight direction by air resistance, so that great lifting force and great thrust are generated; steering engines are adopted to control inner wing rods so as to change the elevation angle of the flapping wings, the multi-freedom degree bird-like flapping wing air vehicle conforms to the effect that upward flapping resistance is less than downward flapping lifting force in aerodynamics, and the aerodynamic efficiency is improved; the two steering engines are utilized to control the deflection of the empennage, so that operating and controlling of the flight attitude of the flapping wing air vehicle are facilitated. The multi-freedom degree bird-like flapping wing air vehicle disclosed by the invention can be used in the fields of models, aerial photography monitoring, information collecting, disaster searching and rescuing, airport bird expelling and the like.

The present invention is to provide a vertical axis wind engine comprising at least one arm each having its center rotatably coupled to a vertical axis mounted on a base on the ground, each pair of the upper and lower arms adapted to define an airfoil receiving space for pivotably mounting an airfoil by pivot pins thereof; and at least one elastic stop member each provided on the arm proximate the airfoil and spaced from the pivot pins, each stop member adapted to limit a pivot angle of the airfoil and lift the pivot limitation for allowing the airfoil to pivot when the airfoil experiences a wind force larger than a maximum resistance force thereof, preventing the components of the wind engine from being damaged by strong wind or when the wind engine is operating in high speed.

The subject invention provides a thrust bearing assembly having only three thrust flanges in total. One portion of the thrust bearing assembly comprises a main bearing having an arcuate bearing shell with a concave inner surface and a convex outer surface. A thrust washer having hydrodynamic features abuts one of the edges of the main bearing and extends radially outwardly from the outer surface thereof forming a thrust surface. The other of the edges of the main bearing is free of a flange. The free edge of the main bearing is preferably spaced inward from other thrust surfaces and the edge has a substantially narrower width than the other thrust surfaces. The other portion of the assembly may include a traditional thrust bearing having one thrust flange with hydrodynamic features and another thrust flange free of hydrodynamic features, both extending radially outwardly therefrom or may include another main bearing abutting a pair of thrust washers, one having hydrodynamic features and one free of hydrodynamic features, extending radially outwardly from the other main bearing. In either configuration, the thrust flange or thrust washer that is free of hydrodynamic features is opposite the thrust washer having hydrodynamic features of the main bearing.

An electromagnetic actuator comprises: a fixed core of a magnetic material provided with one pair of pole teeth, which are cylindrical and face each other; exciting coils wound on the fixed core; and a moving object which is movably disposed in the direction of the axis line coaxially with the pole teeth, wherein the moving object includes: cylindrical permanent magnet, in which the N pole and the S pole have been magnetized in the radial direction; and a cylindrical movable core of magnetic material which is coaxially connected to the permanent magnet and is displaced together with the permanent magnet.

The invention relates to a working handpiece of a numerical control wire bending machine, which comprises the working handpiece of the numerical control wire bending machine. Two die heads in the die-changing and die head steering lifting position-hiding mechanism in the numerical control wire bending machine are connected with two spline shafts without relative displacement; the bottom parts of the spline shafts are contacted with the lower end of a pressure spring; the upper end of the pressure spring is contacted with the inner step of a main shaft and drives the spline shafts to move downwards; a swing arm of the position changing and swinging mechanism of the bending die head in the numerical control wire bending machine is connected with a wire bending power driving device without relative displacement; one end of a connecting rod is moveably connected with the swing arm, while the other end is moveably connected with the swing arm; the swing arm is connected with a rotating shaft of a numerical angle graduator without relative displacement; a driving device takes a worm-gear case as a main body; a worm is supported by a bearing without axial displacement, and at the same time drives two worm gears which are connected with the main shaft without relative displacement; splines are arranged in the main shaft; the spline shafts are connected with the splines in the main shaft; the main shaft and the worm-gear case are supported by the bearing without axial displacement; and two bending die heads are connected with the two spline shafts respectively without relative displacement.

A linear actuator may include a fixed body having a coil wound around in a ring-shaped manner and a movable body. The movable body may include a first movable body side yoke which is disposed on the inner side of the coil and a pair of magnets which is laminated on both sides in an axial direction of the first movable body side yoke such that the same polarities of the magnets face the first movable body side yoke. The movable body may be driven in the axial direction. The linear actuator may be applied to a valve device and a pump device.

An impact hammer drill capable of performing drilling operation at a high speed with low noise and without requiring a large thrust. The drill includes a main shaft rotatable by an output shaft of a motor, and a spindle having an impact-receiving section and disposed over the main shaft slidably in its axial direction and rotatable together with the rotation of the main shaft. A piston is reciprocatingly slidably disposed over the main shaft for impacting against the impact-receiving section. A piston drive unit is disposed for driving the piston with a compressed fluid. A compressed fluid supplying unit is disposed for supplying the compressed fluid to the piston drive unit. A drill bit is attachable to the spindle. When performing drilling operation, the drill bit is imparted with a combined rotational motion and the reciprocal impact motion.

The invention discloses a multi-connecting rod loading mechanism, which comprises a first driving rod, a first connecting rod, a swinging arm, a pull rod, a movable arm, a movable arm elevating mechanism and a scraper bucket, wherein one end of the movable arm is connected with a frame, and the other end of the movable arm is connected with the scraper bucket and is elevated and lowered under theaction of the movable arm elevating mechanism; one end of the first driving rod is connected with the frame, and the other end of the first driving rod is connected with the first connecting rod; thefirst connecting rod is connected with the swinging arm; one end of the swinging arm is connected to the movable arm, and the other end of the swinging arm is connected with the pull rod; the other end of the pull rod is connected with the scraper bucket; and the first driving rod is used for controlling the scraper bucket to rotate around the movable arm under the driving action of a motor. In the invention, a hydraulic transmission system is replaced by the multi-connecting-rod loading mechanism, so that the defects of high maintenance cost and the like of a hydraulic excavator are overcome; and simultaneously, the first connecting rod, the swinging arm and the pull rod are connected with one another, so that the strange phenomenon and an oversize or undersize transmission angle among the first connecting rod, the swinging arm and the pull rod due to the approach or reach of the scraper bucket of a mechanical loader to a limit position can be avoided easily on the premise of meetingthe requirement of loading, and the reliability of an electric loader is improved.

The invention discloses an internal waverider-derived high supersonic inlet duct, the shapes of the inlet and outlet of which can be customized, and a design method thereof. The structure of the internal waverider-derived high supersonic inlet duct comprises an inlet duct contraction section and an isolated section, wherein the shape of the inlet duct contraction section is in three dimensional inward contraction. The design method is that a non-axisymmetric internal contraction basic flow field is taken as the base, the non-axisymmetric internal contraction basic flow field comprises an axisymmetric internal contraction rotary wall surface and a non-axisymmetric variable radius central body, wherein the axisymmetric internal contraction rotary wall surface keeps no changing, and the radius of the central body is adjustable. The invention has the advantages that the internal waverider-derived high supersonic inlet duct can capture the inflow by full flow and has low Mach number automatic overflow; the shapes of the inlet and the outlet can be customized according to the layout requirement, and the parallel module installation or the integrated design with various aircrafts can be easily realized.