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 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 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 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 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 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.