287results about How to "Reduce the windward area" patented technology

The invention discloses an ultra wideband multi-band dual-polarized antenna, which comprises a reflection board, at least one low-frequency radiation unit and at least one high-frequency radiation unit, wherein the low-frequency radiation units and the high-frequency radiation units are arranged on the reflection board; the high-frequency radiation units are adjacent to the low-frequency radiation units; and each high-frequency radiation unit comprises a high-frequency vibrator insulated from the top surface of the reflection board and a bowl-shaped radiator arranged on the periphery of the high-frequency vibrator. According to the ultra wideband multi-band dual-polarized antenna, by the high-frequency radiation units, an operating frequency range is widened, and meanwhile, coupling with the low-frequency radiation units can be effectively reduced; and by the low-frequency radiation units, an operating frequency range is widened, and meanwhile, the radiation efficiency can be effectively improved. Therefore, the bandwidths of the low-frequency operating frequency range and the high-frequency operating frequency range can be greatly increased, and the ultra wideband multi-band dual-polarized antenna has the advantages of small frontal area and compact structure.

The invention provides a megawatt-stage vertical shaft wind power generator with an adjustable attack angle. The vertical axis wind power generator comprises an electric power conversion device, a speed increasing box, a power generator, a variable pitch motor, a main vertical shaft, a cantilever cylinder, blade crossbeams, and blades with airfoils, wherein the cantilever cylinder is sleeved on the outer side of the main vertical shaft; the main vertical shaft is connected with the cantilever cylinder through a bearing; one end of each blade crossbeam is fixed on the cantilever cylinder, and blade autorotation devices are mounted at the other end of each blade crossbeam; a lightning rod is mounted at the top end of the main vertical shaft; an anemoscope is connected with an electronic control device; and the electronic control device controls the blade autorotation devices on each cantilever crossbeam, so as to enable the blades to adjust the windward angles according to a preset program and enable the power generator to be throughout in a state capable of producing the maximum torque. The starting wind speed is effectively reduced, and the wind energy utilization rate is increased.

The invention discloses a method for designing a high-supersonic speed three-channel air inlet and relates to the high-supersonic speed air inlet of an aircraft. The method comprises the following steps of designing a punching channel, wherein the mach number Ma of work mach number range of the punching channel is between 3 and 4.5; designing a flow-distributing plate, wherein as air flow entering a turbine channel and the air flow entering an ejector rocket channel are allocated through the rotation of the flow-distributing plate, the flow-distributing plate should be designed by corresponding to the rocket channel, the turbine channel and the rocket channel; designing a turbine channel expanding section, wherein the mach number Ma of work mach number range of the turbine channel expanding section is between 0 and 1.8; and designing an ejector rocket channel expanding section, wherein the mach number Ma of work mach number range of the ejector rocket channel expanding section is between 1.8 and 3. The existing method for designing an inner parallel dual-channel turbine base combined circulating power air-inlet channel is improved, and the method for designing the three-dimensional inner rotation type high-supersonic speed three-channel turbine base combined circulating power air-inlet channel is provided.

A high voltage hollow composite insulator of diameter variable type is prepared as sticking end connection pieces firmly at two ends of winding tube, setting a unified structure of umbrella body at external of winding tube, setting said winding tube to be tube body in variable diameter, using high temperature silicon sulfide rubber to form a unified structure of umbrella body by injection forming process.

The invention relates to the technical field of bridge deflection tests, in particular to a bridge loading test deflection testing instrument. The technical scheme is that the bridge loading test deflection testing instrument comprises an instrument tank box and a leveling instrument which is arranged on the top face of the instrument tank body and used for measuring the levelness of the top face of the instrument tank body, and side face opening holes are formed in the side faces of the tank body. Three springs are fixedly hung on the upper portion of the tank body, a testing platform is connected at the lower ends of the springs, a testing instrument support is fixedly arranged above the testing platform, and the deflection testing instrument is fixedly arranged on the testing instrument support. A turn buckle which is used for adjusting the lengths of the springs before a deflection test is hung below the testing platform. The upper end of a deflection testing rope is fixedly arranged at the lower end of the turn buckle, and the lower end of the deflection testing rope is connected with a counterweight block placed on the ground. A large hang ring is arranged on the top face of the outer portion of the tank body. The bridge loading test deflection testing instrument is reasonable in structural design, convenient to manufacture, mount and arrange, high in deflection test precision, capable of effectively solving the problems that labor and materials are consumed, working at heights is needed, mounting and dismounting are troublesome, the test precision is hard to guarantee and the like of an existing deflection test system in load tests.

The invention provides a lower-jaw type supersonic/hypersonic inlet integrated with a forebody of an air vehicle and a design method of the lower-jaw type supersonic/hypersonic inlet. The lower-jaw type supersonic/hypersonic inlet comprises a local waverider compression surface, a rotation-formed axially symmetric compression surface, a rotation-formed axially symmetric lip cover, backswept side plates, an annular rotating round bent expanding pipeline, a forebody head upper surface, a forebody head transition surface and an aircraft fuselage profile. The forebody head of the air vehicle is designed asymmetrically, a non-regular capture surface is designed, accordingly, the theoretical capture area of the inlet and the utilization efficiency of the windward side of the air vehicle can be increased remarkably, and the shock wave intensity and the windward area above the forebody head of the air vehicle are reduced. The forebody of the air vehicle and the shock wave system of the lower-jaw type inlet are designed integrally, so that loss of strong shock waves and local reaccelerating areas can be avoided. Accordingly, the design method has a remarkable effect on improvement of the flow capture capacity and the total-pressure recovery capacity of the inlet as well as reduction of aerodynamic resistance of the air vehicle.

Disclosed is a rear-placed combustor with an annular porous medium head for an ultramicro turbojet engine. An annular reflux structure is adopted for the combustor which is formed by a combustor box, a flame tube wall, a combustor outlet and the annular porous medium head. Air flow passes through a centrifugal compressor of the engine for compression, enters an annular cavity channel of the combustor, and then is mixed with gas fuel which is jetted in horizontally; premixed gas is pre-heated through the flame tube wall and then flows back to enter a flame tube through the annular porous medium head, and stable ignition is achieved; the whole mixed gas combustion process is finished in the flame tube, and high-temperature gas is discharged from the outlet of the rear-placed combustor; and then the high-temperature gas is discharged into air through a tail pipe after turbine blades of an impact engine does work. The combustor box, the flame tube wall and the combustor outlet are connected through bolts with high temperature glue sprayed on annular edges to guarantee the sealing. According to the combustor, features and advantages of stable flame of the annular porous medium head can be adapted to and played to the greatest extent, proneness to flameout of ultramicro combustors can be improved, so that the combustor can work for the ultramicro turbojet engine reliably and stably.

The invention relates to a layout and control method of a tilting rotor-wing vertical take-off and landing aircraft. Tandem wing layout is adopted; the wing tips of two sides of front wings and rear wings are each provided with one set of rotor wings, and altogether, four sets of rotor wings are adopted, so that a power system can be formed; the wings and the rotor wings can rotate around rotatingshafts penetrating through the interiors of the wings within a certain angle range, so that the respective tilting of the rotor wings and the wings is achieved. According to the control method, the vertical take-off and landing and high-speed level flight of the aircraft can be achieved; the angles of the rotor wings and the wings can be properly adjusted in all stages of flight, and the overallefficiency of the aircraft is optimized; the rotor wings and the wings can tilt respectively, resistance is small in vertical take-off and landing stages, and airflow interference between the rotor wings and the wings is small; when the aircraft is switched between a vertical take-off mode and a landing mode, the utilization efficiency of the wings is high, the burden of the power system is low; and flight control over a whole flight process is simple. The vertical take-off and landing aircraft has a wide application prospect.

The invention discloses an outer rectifying cover of a scramjet engine and a method for designing the same. The main design thought comprises the following steps: firstly carrying out non-adhesion numerical analysis on a flow field generated on a front body of a hypersonic speed aerocraft; then designing the lower wall face shape of the outer rectifying cover in the flow field in a flown line tracing mode, and adopting a plane vertical to the lower wall on the side wall of the outer rectifying cover; and deflecting the outer rectifying cover by certain angle to obtain the outer rectifying cover of the scramjet engine according to the information such as flight attack angle, flight mach number and the like of the aerocraft by taking the lip opening position of the outer rectifying cover asa rotating point. The outer rectifying cover of the scramjet engine adopts the design principle of a waverider body, makes full use of a high pressure area after shocking waves to generate additionallift force, and reduces incident flow area and pressure difference resistance by deflecting the rectifying cover to make the whole aerodynamic performance of the aerocraft obviously improved. The outer rectifying cover can be directly applied to designing the hypersonic speed aerocraft taking various scramjet engines as power.

The invention discloses an electric vehicle and an energy recovery method for overcoming wind resistance in vehicle running. The electric vehicle comprises a vehicle body and a vehicle-mounted electric appliance, wherein a wind channel which extends in a straight line and communicates with the head end and the tail end of the vehicle body is arranged in the vehicle body, a wind inlet is arranged at the front end of the corresponding wind channel, the back end of the wind channel is provided with a wind outlet arranged at the tail end of the vehicle body, a blower fan with fan blades or wind wheels is arranged in the wind channel, a shaft of the blower fan is in drive connection with an input end of a reducing unit, the speed ratio of an input shaft to an output shaft of the reducing unit is greater than 1, the output end of the reducing unit is in drive connection with an input shaft of a generator arranged outside the wind channel on the vehicle body, and an output circuit of the generator is connected with a storage battery for supplying electricity to the vehicle-mounted electric appliance. The invention successfully recovers electricity consumption originally used for counteracting wind resistance to a standby storage battery, and the recovered energy can be used as a standby power supply for extending the continued voyage course and supplying in-vehicle air conditioning, lamps, electric glass, audio units and the like, thereby reducing the loss of a main battery.

The invention provides a multi-stage impeller wind-driven generator which comprises a tower post and a wind-driven generator, wherein the tower post is vertically provided with multiple layers of tower post bearing supports, each layer of tower post bearing support is provided with a perforation, the wind-driven generator comprises a vertical shaft and multiple wind-driven impellers, the verticalshaft penetrates through each layer of tower post bearing support and is rotatably fixed with each layer of tower post bearing support, the wind-driven impellers are respectively arranged in the spaces between the multiple layers of tower post bearing supports and are rotatably fixed on the vertical shaft, and the lower end of the vertical shaft is connected with a generator set. The multi-stage impeller wind-driven generator can be operated under the condition of a breeze with a wind speed of 2m/s to generate electricity, can also safely generate electricity under the condition of a strong wind, and has the advantages of reasonable structure, less easily worn parts, small maintenance capacity, convenient installation and maintenance and long service life up to 20-50 years.

The invention involves a micro-channel heat exchanger, which includes flat tubes (8), fins(9) and plate-type header pipes communicated with the flat tubes, (8) each plate-type header pipe comprising a flat tube groove plate, a distribution plate (2) and an outer side sealing plate (5), a plurality of flat tube groove through holes (3) are provided in the flat tube groove plate (1) along a length direction, throttling channels (4) communicated with the flat tube groove through holes (3) are provided in the distribution plate (2) along an arrangement direction of the flat tube groove through holes (3), the outer side sealing plate (5) is provided on one side, far away from the flat tube groove plate (1), of the distribution plate (2). The micro-channel heat exchanger can solve the problems of low heat exchange efficiency and small heat exchange area of the heat exchanger.

The invention discloses a longitudinal flow shell-and-tube heat exchanger, which belongs to shell-and-tube heat exchangers and solves the problem that the fluid dissipative work is increased during heat transfer enhancement of the conventional shell-and-tube heat exchanger. The longitudinal flow shell-and-tube heat exchanger comprises a shell, left and right tube plates and left and right seal heads, wherein the side wall of the shell is provided with a shell pass inlet and a shell pass outlet; the left and right tube plates are arranged in the shell respectively; a plurality of heat transfer tubes are fixed through the left and right tube plates; two ends of the shell are sealed by the left and right seal heads; the left and right seal heads are provided with a tube pass inlet and a tube pass outlet respectively; the heat transfer tubes are spiral heat transfer tubes; and in a direction vertical to a shell pass fluid flowing direction, the heat transfer tubes which contact the inner wall of the shell are supported through contact points of adjacent heat transfer tubes and contact points on the inner wall of the shell, and the other heat transfer tubes support and fix one another through the contact points of the adjacent heat transfer tubes. The longitudinal flow shell-and-tube heat exchanger is compact in structure, small in volume and large in heat exchange area, and saves the investment cost; and the contact points among tube bundles of the heat transfer tubes increase the turbulence intensity of the fluid during shell pass flow, the fluid is uniformly mixed, and the shell pass pressure drop is greatly reduced, so that the comprehensive heat exchange performance of the longitudinal flow shell-and-tube heat exchanger is improved.

The invention belongs to the technical field of gas pressurizing and relates to a birotor oppositely-rotating stamping gas compressor. The birotor oppositely-rotating stamping gas compressor comprisesrotors and a stator. Each rotor is composed of an impeller and a shaft. The rotors include a front rotor and a rear rotor. The impeller of the front rotor is an inclined flow impeller or an ultrawidestring axial-flow impeller. The impeller of the rear rotor can be an axial-flow impeller and can also be an inclined flow impeller or a centrifugal impeller according to specific needs. The stator comprises a machine box, an air inlet, an air outlet pipe and other subsidiary facilities. According to the birotor oppositely-rotating stamping gas compressor, the mechanism of stamping compressing isintroduced to a rotor power type gas compressor, by means of opposite rotating of the two rotors, outlet airflow of the front rotor reaches the supersonic speed relative to the rear rotor, and therefore conditions are created for the rear rotor through stamping compressing, and high-pressure ratio output can be achieved; and the birotor oppositely-rotating stamping gas compressor has the beneficial effects of being simple in structure, high in compression ratio, relatively high in efficiency and the like, and the birotor oppositely-rotating stamping gas compressor can serve as independent gascompressing equipment to be used and can also serve as a component of other devices such as an aero-engine and a gas turbine.

The invention discloses a construction method of a single vane installation technique of a large wind driven generator, and relates to the technical field of new energy technology. Firstly, a main crane and an auxiliary crane cooperate to install a first section of tower drum, a second section of tower drum and a third section of tower drum; then, an engine room and a fan hub are installed; finally, a first single vane is horizontally installed; then an impeller is rotated by 120 degrees to lock braking; a second vane and a third vane are installed in the same way; electricity is checked, anddebugging is performed to guarantee that faults are absent; test run is done; and installation is ended. By applying the construction method disclosed by the invention, the installation problem of thelarge wind driven generator under special environmental conditions, such as mountain regions, intertidal zones and coastal regions, can be effectively solved; construction is convenient; the construction speed is fat; investment is reduced; the cost is reduced; and the installation efficiency of the wind driven generator is increased.

The invention discloses a parallel flow integrated heat sink for superfine perforated pipes in a motor vehicle, which comprises an air-conditioning condenser, a water tank radiator and an engine oil cooler, wherein the water tank radiator and the engine oil cooler are arranged in parallel from side to side, separated by a heat-insulating layer, and positioned on the lower end of the air-conditioning condenser together; both ends of the air-conditioning condenser are provided with flow concentrating sections; a plurality of rows of the superfine perforated pipes are connected among the flow concentrating sections; wavy radiating fins are clamped between two rows of the superfine perforated pipes and respectively welded with one row of the superfine perforated pipes; a CO2 (R744) coolant gas-phase inlet pipe and a CO2 (R744) coolant gas-phase outlet pipe are respectively connected to the flow concentrating sections; and the flow concentrating sections on both ends are a plurality of sleeved structures capable of being arranged in the forward direction. The parallel flow integrated heat sink for the superfine perforated pipes in the motor vehicle integrates condensation of the prior vehicle air-conditioner, heat dissipation of a water tank and cooling of engine oil, is modularized, has light the overall mass and small occupied space, and adopts a multivariated parallel flow condenser and a segmented collecting pipe of the multivariated parallel flow condenser, so that refrigerant can flow to and fro for a plurality of times in the condenser and the heat exchange ability is strong.

The invention belongs to the microrobot field, and concretely relates to a two-dimensional flutter miniature flapping flight robot mechanism. The miniature flapping flight robot mechanism comprises wings, internal and external flexible transmission parts, a transmission mechanism, a body, a body rotation shaft, an empennage, a motor and a control plate, wherein one end of the body rotation shaft is arranged on the body, the other end of the body rotation shaft is hinged to the internal and external flexible transmission parts, the internal and external flexible transmission parts are connected with the wings respectively, and the empennage is arranged on the body; the motor is arranged on the body and is in electric connection with the control plate on the body, one end of the transmission mechanism is connected with the output shaft of the motor, and the other end of the transmission mechanism is connected with the internal and external flexible transmission parts respectively through connection rods; and the internal and external flexible transmission parts are respectively provided with a flexible semi-ring, and each of the internal and external flexible transmission parts and the wings connected thereby has a freedom degree for flapping around the body rotation shaft in an up and down manner and a freedom degree for rotating with the flexible semi-rings. The miniature flapping flight robot mechanism which adopts a passive submissive hinge to realize a two-dimensional flutter function has the advantages of reduction of the complex degree of the mechanism, and improvement of the flight efficiency.

The invention discloses a pantograph head balance device. The pantograph head balance device comprises a balance rod system located under an upper arm rod, and the balance rod system comprises a first rod hinged to the upper end of a lower arm rod, a second rod hinged to the upper end of the upper arm rod, a fourth rod hinged to a pantograph head rotating shaft and a third rod of which one end is hinged to the free end of the second rod and the other end is hinged to the free end of the fourth rod; the other end of the first rod is hinged to the middle of the second rod, the upper end of the upper arm rod extends to form a connection part, and the connection part is hinged to the pantograph head rotating shaft. According to the pantograph head balance device, a multi-connecting rod balance device with multi-sectional design is adopted to replace a traditional structure of one straight balance rod, the rotation angle of the pantograph head can remain unchanged in the rising and falling process of a pantograph, and the current collection stability is improved. Due to the fact that the balance device is arranged under the upper arm rod in a hidden mode, the windward area of the pantograph is decreased, wind resistance in high speed operation is reduced, and the aerodynamic performance of the pantograph is improved.

The invention relates to a bi-wheel vehicle and a sheltering system capable of lifting and descending. The sheltering system comprises a supporting device, a sheltering device and an automatic locking device, the sheltering device is hinged with the supporting device by a straight shaft, the automatic locking device is arranged between the sheltering device and the supporting device. When the sheltering device is rotated to a preset angle, the sheltering device is in an opened and lifted state, the sheltering device and the supporting device are automatically locked by the automatic locking device for sheltering; when the automatic locking device unlocks the sheltering device and the supporting device, the sheltering device rotates in reverse direction to shut and descend, so as to lower the gravity and frontal area of the sheltering device.

The invention relates to the technical field of wind turbine blades, in particular to an inflatable blade structure of a wind driven generator. The inflatable blade structure comprises a glass fiber blade root segment and an inflatable blade tip segment, wherein a plurality of clamping buckles are pre-buried at the edge of the end connected between the glass fiber blade root segment and the inflatable blade tip segment, a plurality of buckling holes are formed in the edge of the end connected between the glass fiber blade root segment and the inflatable blade tip segment, and the glass fiber blade root segment and the inflatable blade tip segment are connected through the clamping buckles and the buckle hole, and then are fixedly connected through rivets; the inflatable blade tip segment comprises an outline supporting structure, an inflatable main bearing component and an outer skin; and the inflatable main bearing component and the outline supporting structure are arranged inside theouter skin, the two ends of the outline supporting structure are respectively provided with a leading edge segmented foam and a tailing edge flexible tail fin, and the outer surface of the outer skinis coated with a coating. According to the inflatable blade structure of the wind driven generator, the weight of inflatable blades can be reduced to a maximum extent, the volume and the size in thetransportation process are greatly reduced, so that the transportation cost is reduced, the environmental protection performance is improved, and meanwhile, the fatigue service life of the blades is prolonged.