1473results about How to "Large thrust" patented technology

The invention discloses a three-dimensional printer with a replaceable nozzle. The three-dimensional printer comprises a three-dimensional adjusting mechanism, and the printing nozzle which performs three-dimensional printing under the adjustment of the three-dimensional adjusting mechanism, wherein the printing nozzle comprises a nozzle bottom plate, a nozzle thermal preservation sleeve which is fixed on the nozzle bottom plate and is provided with a printing through hole and a positioning notch, a material tube which is radially clamped on the nozzle bottom plate, and a linear stepping motor; the material tube is axially clamped in the positioning notch through a material tube pressing plate which is in sliding fit with the nozzle bottom plate; a piston presser used for pushing a piston in a first material tube is fixed at the output end of a lead screw of the motor. When materials in the material tube are used up or the materials are needed to be replaced, the printing nozzle is controlled to automatically replace the material tube, and a three-dimensional object consisting of multiple materials can be printed. The piston is driven to be extruded by adopting the linear stepping motor, thrust is high and can be accurately controlled, and the blockage of the nozzle is avoided. According to the printer, liquid foods and multiple liquid materials such as gel and ceramic powder can be printed.

The invention provides a fixed-wing multi-shaft aircraft, and belongs to the field of aircrafts. The fixed-wing multi-shaft aircraft comprises a fixed wing and a multi-shaft rotor wing rack which are connected with each other, and the multi-shaft rotor wing rack is provided with multiple rotor wing mechanisms; the rotor wing mechanisms comprise propellers and rotating shafts, the propellers are rotatably connected with drive devices, the drive devices are fixedly connected with the rotating shafts, and the rotating shafts are connected with rotating control mechanisms. The fixed-wing multi-shaft aircraft has the advantages of both a fixed-wing aircraft and a multi-shaft aircraft, can achieve a multi-shaft mode, a fixed-wing mode and a fixed-wing and multi-shaft mixed mode and also has the advantages of achieving vertical taking-off and landing and hovering and being high in flying speed and long in flying time.

The linear ultrasound electrical motor (LUEM) includes drive oscillator, mover, chassis, and relevant locking gear for fastening them. The drive oscillator includes piezoelectric element and metal elastic body (MEB). The piezoelectric element includes piezoelectric ceramic piece (PCP) of bending vibration, and PCP of longitudinal vibration in use for generating rectilinear vibration. At least one dogtooth contacted to mover is setup on MEB. Slider of guiding bulge is setup on side of mover. The guiding bulge is corresponding to straight-line guidance groove setup on the chassis. The disclosed LUEM is longitudinal and bending composite driving LUEM with prism type oscillator. The drive oscillator is prism type longitudinal bending composite oscillator composed of connection terminals, longitudinal vibration rectangular PCP and front cover board fastened by double end bolts and nuts. The oscillator is as stator of LUEM to generate longitudinal and bending vibration.

The invention discloses a high-temperature hot-melting micro-jet dispensing device with a piezoelectric drive diaphragm, belonging to the technical fields of mechanical engineering, microelectronic packaging and microelectronic component production. Piezoelectric ceramic is used as a drive component for pushing the drive diaphragm to deform and extrude a micro-jet material in a nozzle cavity, so that a fluid pressure is sharply changed and the micro-jet material is regularly jetted to form microdroplet adhesives. The piezoelectric ceramic is driven via a computer signal, so that the generation of the microdroplet adhesives can be accurately controlled. The temperature of the micro-jet material is adjusted via a heating device and a temperature control device so that the viscosity of the micro-jet material can be changed. A jet mechanism and a drive mechanism are independently designed and installed on a rack respectively, and heat isolation is performed between the drive mechanism and a heating area, so that the limit of the temperature characteristic of the piezoelectric ceramic on the heating temperature of the device can be reduced, and further the micro-jet material can be heated to a high temperature. The high-temperature hot-melting micro-jet dispensing device disclosed by the invention is high in thrust, small, precise and controllable in the dimensions of the generated microdroplet adhesives, suitable for low-viscosity and high-viscosity micro-jet materials at high temperature, and has great application and development prospects in the fields of microelectronic packaging and micro optical component production.

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.

A coordinates input device includes an operation unit that receives an operation input, a vibration generator that applies a vibration to the operation unit, and a vibration control unit that controls the vibration generator to apply the vibration to the operation unit when the operation input is received by the operation unit. The vibration generator includes a power feed unit provided to the operation unit, and a magnetic-field applying unit having sub-units. Each of the sub-units has first and second magnets spaced apart from each other with a given gap. The magnetic flux produced by the first and second magnets crosses a current flowing in the power feed unit.

The invention discloses an automatic door opener of a refrigerator and the refrigerator adopting the same. The device comprises a box body, a mandril, a driving component and a control component, wherein the mandril extends out of the box body between the extending position for opening a door and the retraction position for retracting the box body so as to be movably arranged in the box body; the mandril adopts a rectangular rod shape; the driving component is connected with the mandril for driving the mandril to move; the control component is connected with the driving component for controlling the moving direction of the mandril. According to the embodiment of the invention, through adopting the device, the door body of the refrigerator is opened automatically, the door-opening process of the refrigerator is intelligent and labor-saving, and as a result, the refrigerator adopting the automatic door opener is more intelligent.

The present invention discloses a turbo-rocket combined ramjet engine, which comprises an air turbine ramjet and a rocket based combined cycle engine that share an air intake passage and an exhaust nozzle. An air intake passage guiding device is disposed on a duct of the air intake passage. The air intake passage guiding device is used for turning to seal an inlet of the rocket based combined cycle engine at low-speed start of the air turbine ramjet to achieve internal communication of the air intake passage and the air turbine ramjet, and further used for turning to seal an inlet of the air turbine ramjet when a speed of the air turbine ramjet is greater than or equal to Mach, thereby achieving internal communication of the air intake passage and the rocket based combined cycle engine to start the ramjet. A solution is provided for the problem that two existing power systems cannot independently and completely meet the power requirements of modern warfare on weapon systems in such aspects as ultrahigh acoustic velocity, superaltitude, high maneuverability and high airspace.

The invention relates to an air floatation high-speed electric main shaft, in particular to an air floatation high-speed electric main shaft for a machining tool. A lower air bearing block assembly 7 is fixed on a thrust bearing 9, the upper part of the lower air bearing block assembly 7 is provided with a stator 6, the front end of a shaft core 5 is provided with a chuck accessory 11, an aluminum water jacket assembly 3 is fixed at the upper opening of a body assembly 10, and a tool changing cylinder assembly 1 is fixed on the upper part of the aluminum water jacket assembly 3; and the middle part of the shaft body of an upper air bearing 4 is provided with an upper air bearing cooling water passage 12. The main shaft is an electromechanical integrated base piece with high revolution number and high precision, has simple and compact structure, and is convenient to install, high in heat dissipation efficiency, multifunctional and convenient for popularization and application.

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 multi-rotor aircraft composed of a fuel engine and a motor. The aircraft comprises an electronic speed regulator, a flight control system, the fuel engine, the motor, a battery pack, a fuselage composed of multiple crankshafts, and multiple propellers, which can be divided into first propellers driven by the fuel engine and second propellers driven by the motor. The multiple first propellers provide the main lifting force of the whole aircraft, while the multiple second propellers are responsible for the balance, direction and a small part of the lifting force of the whole aircraft. Thus, most of the lifting force of the invention is provided by the fuel engine, and a small part of the lifting force, balance control, directional control, and height control are provided by the motor. Perfectly realizing fuel-electric hybrid, the aircraft of the invention is endowed with the maneuverability and flexibility of pure electric aircrafts as well as the large load capacity of fuel engines.

An exciting coil is wound on a cylindrical yoke provided with a pair of pole teeth, a cylindrical permanent magnet where N pole and S pole are magnetized in a radial direction is disposed so as to be movable in a hollow portion of the yoke and the permanent magnet is coupled toa spool byamagnet holder, and a displacement sensor is disposed in a hollow portion of the permanent magnet so as to be positioned on a center axial line of the permanent magnet, so that the displacement of the permanent magnet is detected by the displacement sensor and the degree of opening of the spool is controlled by performing feedback of the displacement to a control portion.

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.

A long journey big thrust permasyn brushless beeline direct electromotor that includes stator part, rotor part and position and speed controlling system of the electromotor. The stator part composes permanent-magnet (3) and magnetic yoke (2), magnetizer (5) is connected with rack (1) via coattail groove structure, and two windings (4) with different direction current circle the magnetizer to form rotor part. The invention adopts the two-sized stator structure to eliminate the single sized magnetic pull, and the thrust is big, journey is long, the weight of rotor is light, without contact running and cost is low, it is fit for common numerical control machine tool feeding system, special numerical control machine tool feeding system which adopts gas floating or magnet floating guiding track and other high speed and high acceleration direct feeding systems.

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.

The utility model discloses a moving coil permanent magnet linear motor having high power density. The utility model comprises a coil assembly, a coil assembly frame, an inner magnetic yoke, a permanent magnet, an outer magnetic yoke and other components; the coil assembly comprises a forward winding and a reverse winding; the coil assembly is fixed on the coil assembly frame, and is capable of making reciprocating linear motion in an air gap; the coil assembly frame is connected with the driven moving elements; the direction and the size of the current is regulated through an electric control system, and then the needed motion mode is realized. The permanent magnet group is arranged at one side or both sides of the coil assembly; the permanent magnet group alternately adopts permanent magnets with different magnetic directions along motion direction and forms a Halbach array. The utility model has the advantages that, the power density of the motor is improved obviously, which is 50% more than the power density of conventional linear motors; meanwhile, the utility model has better control characteristic. The utility model can be used as an executive element and applied to the situations where the volume and the mass of the linear motor need to be small, and the thrust and the accuracy of the linear motor need to be large; for example, the utility model can be applied to the electro-hydraulic proportional control field, the robot field or other fields.

The invention discloses a solid cool air micro-propelling system. The solid cool air micro-propelling system comprises an air storage chamber, a magnetic valve and a mini-type resistive heater which are sequentially connected, wherein the air storage chamber is provided with a pressure sensor and a plurality of nitrogen generators; the mini-type resistive heater is composed of a silicon wafer and a heating resistor; the silicon wafer is internally provided with a vent groove and a Laval type nozzle; the air inlet end of the vent groove is connected with the magnetic valve; the air outlet end of the vent groove is connected with the Laval type nozzle; the heating resistor is arranged on a glass substrate; the silicon wafer is bonded with the glass substrate. The solid nitrogen generators replace a high-pressure nitrogen storage tank to store nitrogen, and the size and mass of the whole system are reduced greatly; nitrogen is heated by the mini-type resistive heater before being sprayed out from the nozzle, and then is sprayed out after reaching a certain temperature, thrust generated after the nitrogen is sprayed out is increased, the propelling efficiency of the whole micro-propelling system is improved, thrust is small and precision is high.

The invention discloses an integration design method for a hypersonic slender body air vehicle and a three-dimensional inward rotation air inlet channel, and relates to near space aerocrafts. The method comprises the following steps that a three-dimensional shock wave hook face is designated according to the design requirement; a series of basic flow fields are derived reversely according to the relation between the discrete shock wave curve and the curvature center; a slender waverider vehicle lower surface molded line and the outlet section of the three-dimensional inward rotation air inlet channel are designed, and streamline tracing in the counter flow direction is conducted in the basic flow fields; the two-dimensional projection shape of a lip of the three-dimensional inward rotation air inlet channel is designed, and a three-dimensional configuration of the lip of the three-dimensional inward rotation air inlet channel is obtained according to the shock wave relation; and the hypersonic slender body air vehicle is subjected to geometric construction based on a compression molded face. The performance of an outer waverider vehicle front body and the performance of the three-dimensional inward rotation air inlet channel are simultaneously considered by the generated slender body hypersonic air vehicle and the air inlet channel, the lift drag characteristic is high, full-flow incoming flow capture can be ensured, engine thrust is increased, outflow resistance is reduced, the operation Mach number range of the air inlet channel is widened, and natural transition of an inner waverider part and an outer waverider part is achieved.

A variable rigidity bionic swinging propulsion unit comprises a support, more than two joints of swinging devices and a tail fin, wherein each swinging device comprises an upper platform, a lower platform, eighteen flexible hinge points, eight outriggers and a spinal column, a flexible hinge point o' is arranged at the center of the upper platform, a flexible hinge point o is arranged at the center of the lower platform, and the flexible hinge points o' and o are connected together through a spine; and the flexible hinge points are respectively connected with each other through the eight outriggers. The variable rigidity bionic swinging propulsion unit has the advantages that the variable rigidity bionic swinging propulsion unit has the characteristics of large thrust, continuous movement and good flexibility; and the propulsion efficiency is improved, and a variable rigidity energy-saving swimming mechanism for fishes is realized.

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.

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.

An electromagnetic drive variable-rigidity bionic swing propelling device comprises a support, at least two sections electromagnetic swing units and a tail fin. The whole shape of a fish body is sealed by a fish skin. The first section of electromagnetic swing unit is connected with the head of the head of the fish body. Other sections of electromagnetic swing units are connected with a flexible spine. The last section of electromagnetic swing unit is connected with the tail fin. The electromagnetic swing unit comprises an upper magnetic body, a lower magnetic body, control coils, the flexible spine and an armature. The flexible spine is hollow. A coil for controlling electric currents is embedded into the flexible spine. The upper magnetic body and the lower magnetic body are fixed on the flexible spine respectively. The armature is fixed in the middle of the upper magnetic body and the lower magnetic body. The middle of the armature is fixedly connected with the flexible spine. The control coils are sleeved at two ends of the armature. The flexible spine is driven to bend by the generated electromagnetic torque so as to drive the fish body to swing for propelling. The electromagnetic drive variable-rigidity bionic swing propelling device is small in size, light, continuous in action, easy to implement, low in noise and low in mechanical loss.

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.

The invention discloses a short-circuit fault-tolerant vector control method for an embedded hybrid magnetic material fault-tolerant cylindrical linear motor. The short-circuit fault-tolerant vector control method comprises the following steps: building a five-phase embedded hybrid magnetic material fault-tolerant cylindrical linear motor model; compensating normal thrust missing caused by a short-circuit fault phase and suppressing a thrust ripple caused by phase short-circuit current with non-fault phase current of the motor; and obtaining expected phase voltage by adopting a series of coordinate conversion and voltage feed-forward compensation strategies, and achieving a fault-tolerant vector control after the phase short-circuit fault of the motor by a zero-sequence voltage harmonic injection-based CPWM modulation mode. According to the short-circuit fault-tolerant vector control method, the motor can suppress the thrust ripple of the motor under the condition of a phase short-circuit fault-tolerant operation; more importantly, the dynamic property, the steady-state performance and the properties in a normal state are consistent; the switching frequency of a voltage source inverter is constant; a CPU is low in overhead; and a natural coordinate system only needs to counterclockwise rotate a certain angle in any phase short-circuit fault, so that the motor fault-tolerant operation can be achieved.