55results about How to "Does not affect aerodynamic performance" patented technology

The invention discloses a wing-borne low-scattering ultra-wideband conformal phased array based on a strong coupling effect. The whole antenna structure of the array is subjected to conformal processing, and + / -45 degree scanning in the arraying direction is realized within a broadband of 0.5-2GHz. Compared with the traditional planar ultra-wideband phased array, the phased array disclosed by theinvention has significant low-scattering characteristics inside and outside the working band of the antenna. The whole antenna structure mainly includes a coaxial feeding structure of an antenna radiation unit, a gradient line balun used for connecting an antenna radiation patch and the feeding structure, a metal ground plate which is conformal with a flight carrier, a parasitic metal block located on the metal ground plate, a conformal dielectric substrate used for supporting the radiation structure of the whole phased array, connected long-slot conformal radiation patches based on the strongcoupling effect, a conformal dielectric substrate used for supporting a resistive electromagnetic metamaterial, a circular resistive electromagnetic metamaterial with an ultra-wideband electromagnetic wave absorbing effect and parasitic slots on both sides of the antenna radiation unit.

The invention discloses a rapid demounting method for cabin door of aeroengine and a latch lock. The method comprises steps of: pressing a trigger to open the lock, a bottom plate rotating under effect of a bottom plate torsional spring, a connecting rod hinged on the bottom plate pulling the pin to retract to open the cabin door rapidly; pressing the bottom plate to overcome the torsional elasticforce of the bottom plate to rotate the bottom plate inversely, the connecting rod hinged on the bottom plate pushing the pin to extend, meanwhile the lock being hanged on a lock hanging scroll to lock the cabin door rapidly. The invention can satisfy requirement of rapidly opening and closing the cabin door of the airplane, which is convenient to maintain the airplane and improves maintaining efficiency of the airplane as well as reduces time of rapidly opening and closing the cabin door of the airplane. The latch lock of the invention mounted to the airplane is aligned with skin of the surface of the airplane, which does not affect aeroperformance of the airplane.

The invention discloses a manufacturing method of a light aerofoil with super-high aspect ratio and high lift-drag ratio and an aerofoil manufactured thereby. At present, some used optimized design methods for improving the strength and the rigidity of the aerofoil with the high aspect ratio have the limited improvement space; and if a method for increasing geometrical characteristic parameters of the sections of the plasmodium is adopted, the structure weight of the aerofoil needs to be increased and the effect is poor. By the manufacturing method adopted by the invention, these problems are solved. According to the overall configuration of an aircraft, the aerofoil is divided into a plurality of sections; tensile wires are arranged according to a certain mode section by section. The research result shows that the original bending function of the aerofoil is replaced by the tension of the tensile wires and the impaction of the aerofoil, and under the premise that the structure weight is basically not increased, the rigidity and the strength of the aerofoil with the high aspect ratio are greatly improved, and the pneumatic elastic deformation is reduced to be within 10 percent of the traditional aerofoil. The manufacturing method is very important for the practical application of the aerofoil with super-high aspect ratio, the cruising efficiency of the aircraft can be greatly improved, and the fuel consumption and the cost are reduced.

The invention discloses blades, a blade synergistic system and a wind generating set. The blade synergistic system comprises diversion tubes, an air pump and a controller; the diversion tubes are pre-embedded at least in the suction faces in the suction faces and the pressure faces of the blades and located on the sides, close to the rear edges of the blades, of main beams of the blades, and the diversion tubes are each provided with a plurality of air ports so as to communicate with the outside world; the air pump is connected with the diversion tubes; and the controller controls the air pumpto conduct air suction or air injection through the diversion tubes at least based on the air speed and the current incoming flow attack angle. Through the blade synergistic system, on the basis thatthe structure and the aerodynamic performance of the blades are not changed, airflow on the surfaces of the blades is intervened, so that the stall phenomenon is avoided.

The invention discloses a wideband omnidirectional circularly-polarized printed antenna of an L-shaped load improved floor, and belongs to the technical field of omnidirectional circularly-polarized printed antennas. The wideband omnidirectional circularly-polarized printed antenna solves the problems of too narrow impedance bandwidth and axial ratio bandwidth existing in an existing wideband omnidirectional circularly-polarized printed antenna. A dielectric substrate and an upper radiation patch of the printed antenna are circular respectively; a lower floor is a circular metal floor with L-shaped branches on the outer circumference; the upper radiation patch is printed on the upper surface of the dielectric substrate, the lower floor is printed on the lower surface of the dielectric substrate, the centers of circles of the dielectric substrate, the upper radiation patch and the lower floor are coaxial, and coaxial probe feed is adopted; a plurality of drill holes are uniformly formed in the dielectric substrate, the upper radiation patch and the lower floor at corresponding positions along the circumferential direction, and the corresponding drill holes in the dielectric substrate, the upper radiation patch and the lower floor are connected through metal via holes; and five to ten L-shaped branches are uniformly distributed on the outer circumference of the lower floor. The printed antenna is a wideband omnidirectional circularly-polarized printed antenna.

The invention discloses a noise lowering method for aerodynamic noise of a wind turbine blade. Due to the impedance gradual changing attribute along with thickness decreasing of a sound absorbing material on the rear edge of the blade, mass point vibration generated by high-speed incoming flow gas nearby the rear edge of the blade is inhibited, and therefore sound diffraction is weakened and it isachieved that noise is lowered. According to the method, the active noise lowering technology is adopted, a noise source is removed fundamentally, and the noise lowering effect is obvious; and it isnot needed to change the shape of the wind turbine blade, and the aerodynamic performance of the blade is not affected. The rear edge structure of the blade is subjected to improved design, the process is simple, cost is low, integrated design is facilitated, and scale production can be achieved.

The invention discloses a dielectric barrier discharge plasma anti-icing device and method. A plurality of layers of polyimide adhesive tape are overlapped and pasted to serve as an insulation layer. Upper electrodes and lower electrodes are pasted along the two side faces of the insulation layer in a staggered mode. The upper electrodes are connected in parallel to be connected with a positive electrode of a plasma power source. The lower electrodes are connected in parallel to be connected with a negative electrode of the plasma power source. The insulation layer is fixed into a groove in the surface of an aircraft skin, and efficient anti-icing of the surface of an aircraft is achieved. Due to the fact that the thickness of the electrodes and the thickness of the insulation layer are very small, the effect of the electrodes and the insulation layer on the aerodynamic performance of the aircraft can be ignored. The dielectric barrier discharge plasma anti-icing device is simple in structure, and the electrodes can be flexibly distributed according to the different geometrical shapes of the frozen positions of the aircraft. When the voltage of the plasma power source is adjusted to 70 V and the current strength ranges from 1.5 A to 2.5 A, the voltage actually loaded to the electrodes can reach 10 KV or more, the responding time is short, the anti-icing effect is good, the implement method is convenient to implement and easy to achieve and has good application prospects, and no pollution exists.

The invention provides an engine lubricating oil cooling system which is composed of a lubricating oil tank, an air lubricating oil radiator, a fuel-lubricating oil radiator, a fuel tank and a fuel pump. High-temperature return lubricating oil of an engine enters the fuel-lubricating oil radiator for heat dissipation after passes through the air lubricating oil radiator, and then enters the lubricating oil tank for recycling; and low temperature fuel in the fuel tank is input to the fuel-lubricating oil radiator through the fuel pump to dissipate the heat of lubricating oil, and then enters acombustion chamber for combustion. The engine lubricating oil cooling system uses two types of radiators to cool the lubricating oil, and the problem that the fuel flow of a high-altitude cruise-typeaviation engine in a high-altitude low-speed state is small and the heat dissipation of the lubricating oil system cannot be met are solved.

The invention discloses an aircraft hardpoint sealing mechanism driven by springs. The aircraft hardpoint sealing mechanism comprises a casing (1), wherein a positioning ring (11) vertically extends upwards from the upper top surface of the casing (1), two sealing plates (5) which can be mutually connected in an abutting manner, springs (6) for driving the sealing plates (5) to close and handles (8) through which the sealing plates (5) can be opened are arranged in the positioning ring (11), and a lower hole (10) corresponding to the sealing plates (5) is formed in the middle part of the casing (1); a cover plate (4) is fixed on the positioning ring (11), and an upper hole (12) corresponding to the lower hole (10) is formed in the cover plate (4). The aircraft hardpoint sealing mechanism disclosed by the invention is simple in structure andconvenient to use, after the aircraft hardpoint sealing mechanism is closed, the casing and the sealing plates are completely flush with the outer surface of an aircraft and not protruded out of the surface of the aircraft completely, and aerodynamic performances of the aircraft are not influenced.

The invention discloses a low-noise centrifugal fan with a noise reduction lining. The fan comprises an impeller, a volute and a motor; the impeller and the motor are arranged in the volute, the motor is connected with the impeller, and is used for driving the impeller to rotate, and the fan is characterized in that the volute further comprises a perforated plate inner volute body and an outer volute body, the perforated plate inner volute body is arranged in the outer volute body, a containing cavity is formed and is filled with a soundproof sponge, and the outer surface of the perforated plate inner volute body is at least covered with a Kevlar laying layer serving as the noise reduction lining. The low-noise centrifugal fan has the good sound insulation effect and meanwhile has the higher noise absorbing effect, the noise of the low-noise centrifugal fan can be greatly reduced, and compared with a common centrifugal fan, the noise of the low-noise centrifugal fan is far lower than that of other centrifugal fans during running.

The invention discloses a method for rapidly disassembling a radome on an airplane and rotating locks. In the method, the edge of the radome is provided with a group of eye bolts (2), and a group of rotating locks are arranged on a radome frame which corresponds to the eye bolts (2); the eye bolts (2) are inserted into lock holes (4) of the rotating locks; a lock core (5) is rotated to lead a lock catch (6) on the lock core (5) to penetrate through bolt holes (3) of the eye bolts (2) and hook the eye bolts (2), and the eye bolts (2) can not be pulled out from the lock holes (4). The inventioncan improve the maintainability of a radar antenna, is convenient, rapid, time-saving and power-saving to assemble and disassemble the radome, saves the maintenance time and improves the maintenance efficiency.

The invention belongs to the field of aerospace technology research, in particular relates to an electrical separation device for an aircraft. The electrical separation device comprises a plug base, an electrical plug and an electrical socket, wherein the plug base is fixed on an aircraft launching rack or launching cylinder, the electrical socket is fixed on the aircraft, the electrical plug is arranged in the socket base and inserted into the electrical socket, and an electrical plug installation inclined surface is inserted into the electrical socket by a plug base inclined surface. The electrical separation device is novel in separation mode, the aircraft and the structure of the separation device are protected, the aerodynamic performance cannot be affected by the device part on the aircraft, and the structure is user friendly.

The present invention provides an F-type loading improvement floor broadband omnidirectional circular polarization printing antenna, belonging to the broadband omnidirectional circular polarization printing antenna field. The objective of the invention is to solve the problem that the current broadband omnidirectional circular polarization printing antenna has too narrow impedance bandwidth and axial ratio bandwidth. The dielectric substrate and an upper layer radiation paster are in circle shape; a lower layer floor is a circle metal floor having an external circumference with an F-type branch; the upper layer radiation paster is printed on the upper surface of the dielectric substrate, the lower layer floor is printed at the lower surface of the dielectric substrate, the circle centers of the dielectric substrate, the upper layer radiation paster and the lower layer floor are coaxial, and the coaxial probe feed is performed; the corresponding boreholes of the dielectric substrate, the upper layer radiation paster and the lower layer floor are connected through metal through holes; the external circumference of the lower layer floor uniformly distributes 5-10 F-type branches. The present invention provides a broadband omnidirectional circular polarization printing antenna.

The invention discloses a novel dielectric barrier discharge plasma exciter, which adopts an extremely thin metal wire as an upper electrode, wherein the metal wire upper electrode is connected to thehigh voltage end of a high-frequency high-voltage power supply, and the surface of the metal wire upper electrode is smooth and burr-free, with uniform discharge, no tip discharge and uneasy breakingdown, which can effectively extend the service life of the plasma exciter. When mounting on a metal model, the metal model is directly used as a lower electrode, the metal film lower electrode is connected to the low-voltage end of the high-frequency high-voltage power supply, the extremely thin metal wire on the surface of the model has little influence on the surface of the model, and the exciter is mounted on the model of high-precision shape to avoid interference with the shape without affecting its aerodynamic performance. The voltage and frequency of the high-frequency high-voltage power supply are adjustable, the metal wire upper electrode and the metal film lower electrode are separated by an insulating dielectric layer, and the metal wire upper electrode keeps in a tight state during installation and is fixed by the insulating countersunk screw, which is simple and reliable in arrangement, and easy to install.

The invention provides a wind turbine generator blade anti-thunder air-terminal system. The system comprises a blade tip air termination, a shielding device, a lower guiding body, and at least two pairs of blade intermediate air terminations. The blade tip air termination and each blade intermediate air termination are respectively arranged on the blade tip of a wind turbine generator blade and the position of a blade surface, far away from the blade tip. The lower guiding body is arranged in the wind turbine generator blade, one end is connected with the blade tip air termination, and the other end is connected with each pair of blade intermediate air terminations, and the lower guiding body is used to lead lightening current into ground. The shielding device is arranged on two surfaces of the wind turbine generator blade, one end is connected with the blade tip air termination, and the other end is connected with the blade intermediate air termination, and the shielding device is used to shield discharge effect of the surface of the lower guiding body. Through embedding the metal shielding device on a suction surface and a pressure surface of the blade, surface electric field ofthe internal lower guiding body can be effectively shielded, and possibility of discharge of the surface of the lower guiding body is reduced, so that probability of failure lightning protection caused by failure of an air-terminal structure is effectively reduced, and the number of lightning stroke subjected to the blade is reduced.

The invention discloses an aerostat pod skin conformal antenna and a manufacturing method. A sandwich structure is adopted, and the aerostat pod skin conformal antenna comprises an outer skin, a microstrip antenna and an inner skin which are sequentially arranged from outside to inside; According to the aerostat pod skin conformal antenna and the manufacturing method, the aerodynamic performance of an aerostat is not influenced; a parabolic antenna is replaced, and the weight reduction effect can be achieved; the installation is convenient, the required space is small, the profile is low, and the surface of a pod is easily attached; and 360-degree full-coverage detection of a radar is realized.

The invention provides an airborne navigation antenna, which comprises an antenna radiator 100, wherein the antenna radiator 100 is printed on a dielectric slab and comprises a gliding radiating unit 101, a heading radiating unit 102, a grounding wire 104 and a high-impedance strip-type line 103; the radiating units (101 and 102) are provided with vibrators consisting of strip-type lines and are connected with matched strip-type lines (106 and 107); the gliding radiating unit 101 is connected with the heading radiating unit 102 through the high-impedance strip-type line 103; the heading radiating unit 102 is connected with the grounding wire 104 through a loaded inductor 105; and the antenna radiator 100 feeds a signal through the gliding radiating unit 101. The airborne navigation antenna is compact in structure, attractive in appearance, and high in reliability, matching loss brought by a matching circuit is not generated, electrical performance is excellent, and the airborne navigation antenna can be used as a matching antenna of a landing system of a high-speed airborne instrument.

The invention discloses a huyghens source antenna. The huyghens source antenna comprises a dielectric substrate, a magnetic dipole, an excitation source, an electric dipole and a coaxial cable, wherein the dielectric substrate comprises a first surface and a second surface which are opposite to each other, the magnetic dipole is in contact with the first surface of the dielectric substrate, the excitation source is in contact with the second surface of the dielectric substrate, the electric dipole is arranged at one side of the second surface of the dielectric substrate, is arranged in parallel to the dielectric substrate and is separated from the dielectric substrate, and the coaxial cable is arranged in a groove hole formed in the electric dipole in a penetrating way and is connected with the excitation source. The huyghens source disclosed by the invention has the characteristics of low profile and favorable end emission radiation, is simple and compact in structure and is easy to process and fabricate, and the problems of relatively high profile, relatively low radiation efficiency and the like of an existing antenna are solved.

The invention relates to a method for changing airfoil distribution of a blade trailing edge side, a blade, a fan and a method for manufacturing the blade. According to the method, a plurality of fiber boards are stuck near the maximum chord length of a suction surface of the blade, and then the suction surface generates a positive pressure during a normal laminar flow process near the maximum chord length, the fiber boards will not deform, and the power of the blade cannot be affected; and when the incidence angle of a cross section near the maximum chord length is large, the negative pressure is generated, the fiber boards deform, and then the adverse pressure gradient is decreased, and the strength of a harmful eddy is decreased. When the blade trailing edge side generates a harmful eddy, the influence of the eddy on the power and the load can be relieved through automatic deformation, and the blade can operate stably.

The invention discloses an automobile outside airbag protecting and opening device. The automobile outside airbag protecting and opening device comprises airbag cabins for accommodating airbags, wherein the airbag cabins are arranged inside side doors, a front bumper and a back bumper of an automobile; each airbag cabin comprises a sliding cover plate; moving slide blocks connected with the sliding cover plate and sliding tables pushing the moving slide blocks are arranged inside the airbag cabin; in a working state, the sliding tables move the moving slide blocks to open the sliding cover plate so as to expose and further open the airbags to reduce collision loss. Before vehicle collision, the airbags are opened in advance, so that outside airbags of a vehicle can be opened in time on the premise of not affecting the aerodynamic performance of the vehicle and not reducing the strength of the vehicle; the automobile outside airbag protecting and opening device is mature in technology and simple in structure, is very suitable for wide-range popularization and application and has great significance for the safety of the vehicle.

The invention relates to a shoe comprising a sole (2) as well as an upper (3) that rises up from the sole (2), the upper comprising at least two portions (3a, 3b) that are at least partially mutually displaceable with respect to each other, thereby adjusting the housing size or volume (RZ) for a foot in the shoe, as well as tightening- release means of the mutually displaceable portions, the shoe also comprising control means (6, 7) of the tightening-release means (4, 5) operatable or arranged at the back or at the heel (8) of the shoe.

The invention discloses an electric heating unit mold and a method for preparing an electric heating unit. A base of the electric heating unit mold protrudes upwardly and is matched with a convex moldwith the same shape and size as a blade body leading edge at the inner position of 1-2 layer of a skin; the circumferences of the working surface end and the non-working surface end of the convex mold are the circumferences of an electric heating unit assembly wrapping from the boundary of the blade body leading edge to the working surface end and the non-working surface end; and the upper end surfaces, at the two ends of the convex mold, of the base change with connecting curves of the two edges of the electric heating unit and the blade body leading edge. One or more layers of insulating protective layer prepreg is laid on the convex mold of the electric heating unit mold, then the electric heating unit is laid, and finally the one or more layers of insulating protective layer prepreg is laid again; and sleeving of sealing bags is carried out, and vacuumizing and compaction are carried out. The electric heating unit assembly manufactured by using the electric heating unit mold is laid and installed at a prescribed position on the leading edge of a blade at a time, the probability of breaking and damage of a foam core is reduced, the laying layer is high in density, the strengthis high, the manufacturing accuracy is high ,and the aerodynamic performance of the blade is not affected.

The invention discloses a spray axial flow fan with side wall spray pipes. The spray axial flow fan comprises a current collector, a fan air duct, a motor, a hub, a movable vane, and drain booms. The movable vane is provided with radial water retaining devices. The spray axial flow fan is characterized in that the side wall spray pipes are arranged between the motor and the hub, the side wall spray pipes input water flow through annular water ducts out of the fan air duct, and the spray pipe head water outlet of the side wall spray pipe, extending in the fan air duct, faces the movable vane blades, and sprays water along the movable vane blades which axially rotate. Since the side wall spray pipes and the radial water retaining devices are arranged, compared with an existing spray axial flow fan, the spray axial flow fan can obviously improve efficiency of the fan and reduce power consumption of the motor.

The invention relates to an air pressure braking system. The air pressure braking system comprises a controller, an air compressor, an air supply pipe, a pressure / air power generation device, a pneumatic motor, a pneumatic power generation device, a storage battery and a storage battery management system, wherein the controller comprises a micro-processing control unit and a control electromagnetic valve. The air pressure braking system is mainly applied to a pneumatic-electric conversion and control method of a freight train. According to the pneumatic-electric conversion and control method of the freight train, an air braking signal of the air pressure braking system is converted into a voltage signal; energy is stored by using the storage battery management system; power is supplied toa control device by using an energy storage system; and therefore, the braking of the freight train is accurately controlled.

The invention discloses a maintaining clamp for jet braking C duct of a civil aviation passenger plane. The clamp comprises a horizontal tray, a support track arranged on the tray, at least three locking clamps arranged on the tray, at least three columns and upper locking clamps correspondingly located on the columns. The support track is circular and is matched with the shape of a torsion box V-shaped groove of the jet braking C duct to support the torsion box V-shaped groove on the top face of the support track. The columns are located on the periphery of the support track and distributed along the circle to form a working space in enclosing mode used for vertically placing the jet braking C duct. A clamp opening of the upper locking clamp faces downwards and is used for clamping the back end of the noise reduction inner wall of the jet braking C duct, and a clamping opening of the lower locking clamp faces upwards and is used for clamping the front end of the noise reduction outer wall of the jet braking C duct to fix the jet braking C duct. By means of the maintaining clamp, the jet braking C duct can be well fixed to be maintained. The clamp prevents parts of the jet braking C duct from being deformed and cannot affect plane aerodynamics performance of the jet braking C duct.

The invention discloses a lane departure warning-based car outer airbag pre-starting system which comprises an outer airbag device and a pre-warning system, wherein the pre-warning system comprises a video analysis unit which is arranged in the front of the car, a processing unit and a running state acquisition unit which is connected with a car bus in a communication manner; the video analysis unit is used for collecting the running line of the current lane; the running state acquisition unit is used for acquiring the angle and running speed of the guide wheels of the current car; the processing unit is used for judging the lane departure time of the current car according to the running line, the angles and the running speed, and controlling the outer airbag device to open when the lane departure time achieves a certain threshold. The lane departure warning-based car outer airbag pre-starting system is mature in technology, simple in structure and suitable for large-scale popularization and application, and has very important meaning for the safety of the car.

The invention discloses an on-line dynamic balance adjusting device for a propeller of a stratospheric aerostat. The on-line dynamic balance adjusting device comprises a vibration and rotating speed measuring mechanism used for detecting the rotating speed and the vibration form of a blade and a dynamic balance adjusting structure used for adjusting the dynamic balance of the blade. The dynamic balance adjusting structure comprises an analysis control module used for analyzing data collected by the vibration and rotating speed measuring mechanism and an adjusting module used for adjusting the dynamic balance of the paddle, the adjusting module comprises a balancing track arranged in the paddle, and a balancing block is connected to the balancing track in a sliding mode. The rotating speed and the vibration form of the blade are obtained in real time according to the vibration and rotating speed measuring mechanism, the dynamic balance adjusting structure analyzes data collected by the vibration and rotating speed measuring mechanism, a blade dynamic balance adjusting scheme is determined, and dynamic balance is carried out by adjusting the relative position of the balancing block and the blade. The dynamic balance degree range is large, the response speed is high, and the adjusting precision is high; and the dynamic balance of the propeller can be adjusted in real time in the working state of the propeller.

The invention is a split-type unmanned aerial vehicle. The body and the load compartment are connected by an annular connector and a spring latch, and can be quickly disassembled and assembled through a rotation operation. A spring pull rod is used between the hatch cover and the hatch shell to quickly compress and open. The quick-release hinges with embedded design can quickly assemble and separate the rudder surfaces on the wings and tail, and avoid the hinges being exposed to the outside and affecting the performance of the entire machine. The steering gear is built-in, which does not affect the aerodynamic performance of the drone and makes it easy to replace the steering gear. The canopy canopy locking structure adopts a built-in method to ensure the smoothness of the outside of the canopy canopy. The pipe fittings in the fuselage are connected using a quick plug-in method to facilitate the loading and unloading of pipe fittings. The drive motor is connected to the body through a motor mounting piece to facilitate the installation and removal of the propeller drive motor. The pitot tube and the wing are plugged and fixed for easy disassembly without affecting the aerodynamic performance of the entire aircraft.