36results about How to "Aerodynamic Effects" patented technology

The invention discloses a flapping wing capable of automatically folding and unfolding for a flapping wing type micro aerial vehicle. The flapping wing consists of a power device, two hydraulic pipes, a plurality of creases, a plurality of supporting rods, a wing membrane and two folding devices, and the folding and unfolding of the flapping wing are realized by adopting a hydraulic principle. According to the flapping wing, the two hydraulic pipes and the plurality of supporting rods form wing veins of a bionic flapping wing, and the wing membrane is adhered to the bionic wing veins to form a wing surface. The flapping wing pumps liquid into different liquid chambers by virtue of a micro flow pump to generate a pressure so as to drive the flapping wing to fold up or unfold. The flapping wing disclosed by the invention has the beneficial effects of reducing the transverse size of flapping wing type micro aerial vehicle when the flapping wing type micro aerial vehicle does not fly, reducing the spaces required for carrying, transportation and storage, reducing transportation requirements, conveniently protecting the flapping wing of the aerial vehicle from being damaged, favorably replacing a damaged flapping wing to improve the service life of the micro aerial vehicle.

A wind tunnel testing system for annular rail models, vehicle models and bridge models includes a wind tunnel model test box (1) provided with at least one opening, wherein the space between opposite vertical side walls in one group on the wind tunnel model test box (1) is a wind tunnel testing zone; two opposite holes (18) are formed in the opposite vertical side walls in one group; a bridge model (5) is arranged between the two opposite holes (18); a rail is arranged on the bridge model (5); a vehicle model (4) for test is movably connected onto a rail (2); the rail (2) includes a guiding section rail (2) and a testing section rail (3); the guiding section rail (2) and the testing section rail (3) are connected from end to end to form an annular rail provided with an annular loop; the annular rail penetrates the two holes (18) simultaneously, or the annular rail simultaneously passes by the two holes (18) and the outer part of the wind tunnel model test box (1). According to the invention, the vehicle model can run on the rail in a cyclic manner, and the testing data obtained through testing more conforms to the actual condition.

A reflector antenna adapted for use with a mobile platform, in particular with an aircraft. The reflector antenna includes an antenna aperture, a first signal processing subsystem located closely adjacent the antenna aperture exteriorly of the mobile platform, a two channel coaxial rotary joint for allowing rotation of the antenna aperture about an azimuthal axis, and a second antenna signal processing subsystem located within the interior of the mobile platform. A feedhorn of the antenna aperture is disposed within an opening at a coaxial center of a main reflector to allow a longer length feedhorn to be employed without physically interfering with a subreflector of the antenna aperture. The first antenna signal processing subsystem includes separate channels for processing vertically polarized RF energy and horizontally polarized RF energy. The second antenna signal processing subsystem includes a transmit subsystem for amplifying and phase shifting transmit signals being sent to the antenna aperture for transmission, and a receive subsystem for processing received RF signals to provide right hand circularly polarized and left hand circularly polarized signals.

The invention relates to a leading edge capable of improving bird impact resistance of an airplane. A small front beam is added into the leading edge, front ribs are distributed on the small front beam, and an additional skin is tightly attached; when the leading edge meets bird impact, a stronger support effect on a front edge skin and the additional skin is achieved; thus, structural rigidity is improved, and structural appearance is kept as far as possible; in a deforming process, the additional skin can drive the front ribs to generate plastic deformation, so that more energy is absorbed. Rear ribs with an inclined angle can improve structural rigidity and are beneficial to buffering bird impact and protecting web plates. According to the leading edge disclosed by the invention, a requirement of an airplane structure on weight is fully taken into consideration, and structural weight is reasonably distributed; compared with an original structure, the thickness of the front edge skin and the thicknesses of the ribs are reduced by half to be used for adding the small front beam and the additional skin to design wing ribs again; structural weight is reduced by 3% compared with the original structure, so that the bird impact resistance of the leading edge is effectively improved.

The invention discloses a collector air inlet device of a centrifugal fan. A collector comprises an arc surface. A flow guide unit is arranged on the arc surface. The flow guide unit is fixedly connected with the arc surface as a whole. The highest point of the arc surface is tangent to the flow guide unit. The optimized air inlet collector does not generate great effect on the aerodynamic performance of the fan. The structure is relatively simple, and machining and shaping are easy. The replaceable flow guide unit component of the air inlet collector can be selected based on noise characteristics of the centrifugal fan, and structure parameters are optimized. The flow guide unit, as a replaceable component, has the characteristic of being convenient to use.

The invention discloses an airplane stall recovery device, which is capable of replacing an original airplane tail cone in an airplane stall test. The airplane stall recovery device comprises a shell, a parachute outlet mechanism, a load-carrying support and a plurality of long booms, wherein the shell is the same as the replaced airplane tail cone in shape; the parachute outlet mechanism is located above behind the interior of the shell; a stall parachute is put in the parachute outlet mechanism; the load-carrying support is located at the rear side of the interior of the shell and is connected with the parachute outlet mechanism; the load-carrying support is capable of transmitting the load of the parachute outlet mechanism to the shell of the recovery device; the long booms extend from the surface of the inner side of the shell to the joint of a stall device and a fuselage; and the long booms can be connected with the load-carrying structure of the fuselage so as to transmit the load on the shell of the recovery device to the fuselage. According to the airplane stall recovery device disclosed by the invention, the original airplane tail cone is integrally replaced in an airplane stall/tail spin trial flight test, and moreover, an appearance which is the same as the original airplane tail part is basically kept, thus, the pneumatic performance when airplane stall/tail spin trail flight is performed cannot be influenced.

The invention discloses an internal and external opening handle of a hatch cover and an opening method. The internal and external opening handle comprises an inner handle, an outer handle, a rotating shaft and a lock pin, wherein the inner handle is connected to one end of the rotating shaft; the outer handle is connected to the other end of the rotating shaft; the lock pin is connected to the rotating shaft; one end of the rotating shaft and the outer handle are located at the outer side of the hatch cover; the other end of the rotating shaft, the inner handle and the lock pin are located at the inner side of the hatch cover. When the hatch cover of an airplane is in a closed state, the hatch cover is opened through the inner handle under normal conditions, the inner handle is not linked with the outer handle, and the withdrawing state of the outer handle is kept; and in emergency, the hatch cover is opened through the outer handle.

The invention discloses a passive aileron buzzing stability augmenter based on a fluid-solid coupling effect. The stability augmenter is used for solving the technical problem that an existing passiveaileron buzzing suppression mechanism is poor in practicability. The stability augmenter comprises a base, a connecting piece, a mass block, a manganese steel sheet and viscoelastic damping strips. The base is connected with a rib plate inside an aileron through a bolt, one end of the manganese steel sheet is connected to the base, the other end of the manganese steel sheet is connected to the mass block, and the viscoelastic damping strips are longitudinally adhered to the upper surface and the lower surface of the manganese steel sheet along the manganese steel sheet. When the aileron buzzes, the manganese steel sheet is repeatedly bent and deformed, the mass block at the free end reciprocates up and down, when the frequency of the external carrier aerodynamic force is coupled with thefrequency of the stability augmenter, the stability boundary of the aileron is changed, the frequency range of buzzing is reduced, part of mechanical energy consumption is dissipated through repeatedstretching and contracting movement of the viscouselastic damping strips, the amplitude of buzzing is reduced, the fatigue life of the structure is prolonged, and the practicability is good.

The invention discloses a drag parachute housing with a combined rear cover for aircraft, relating to the field of speed-reducing assistance of the aircraft. The drag parachute housing comprises an outer drum, an inner drum, a small cover shell and a large cover shell, wherein the outer drum and the inner drum are connected by a Z-shaped rib; the large cover shell is hinged on the inner drum by a second support; the small cover shell is hinged on the inner drum by a first support; the large cover shell is provided with an electromagnetic unlocking device with a locking hook; the small cover shell is provided with a shaft pin adaptive to the locking hook on the electromagnetic unlocking device; the electromagnetic unlocking device is communicated with a cable arranged between the outer drum and the inner drum. The drag parachute housing disclosed by the invention has the advantages that the structure is simple, and excessive weight is not added; by the arrangement of an inner layer and an outer layer of the parachute housing, the unlocking and locking devices and an uncovering rotary shaft are integrated in the parachute housing, and no redundant structure is left on the surface of the parachute housing after locking, so that the adverse influence of the redundant structure on the surface of the parachute housing on the pneumatic performance of the aircraft in the prior art is solved.

The invention relates to a micropore seepage structure, an airplane anti-icing system and an airplane. The microporous seepage structure includes: a first panel including a plurality of micropores; asecond panel connected with the first panel, wherein a liquid storage cavity is formed between the first panel and the second panel, and an anti-icing liquid inlet is formed in the second panel; and adamping diaphragm arranged on the inner wall of the first panel and covering the multiple micropores, wherein, when the temperature is below 0 DEG C, the damping diaphragm generates a pressure difference of a preset value on the two sides. Ice prevention is conducted through micropore leakage, the operation energy consumption of the airplane anti-icing system is low, and the aerodynamic effect ofthe airfoil profile cannot be affected.

The invention is applicable to the technical field of aircraft anti-icing and deicing, and provides an anti-icing device which is characterized in that an anti-icing system is arranged at a pneumatic leading edge, micropores are partially or completely formed in a skin of a downstream wing of the anti-icing system, and a micropore skin is formed; at least one airtight cabin is arranged below the microporous skin; the aircraft further comprises a suction device, an air suction pipeline of the suction device extends into the airtight cabin, and an exhaust pipeline of the suction device is connected with an exhaust port in a wing. Micropores in the micropore skin can effectively'suck 'a turbulent boundary layer, can maintain most laminar boundary layers of the wing, can reduce the resistance of the aircraft and improve the separation control capability of a pneumatic surface, so that the fuel economy of the aircraft is improved, and the requirements of artificial laminar control and overflow water control are met at the same time by adopting one set of system; the deicing device does not need additional air supply, is simple in structure, can be modularly implemented, and can be conveniently applied to light aircrafts and unmanned aerial vehicle systems.

The invention relates to an unmanned aerial vehicle environment parameter acquisition device, unmanned aerial vehicle equipment and system, the device comprises an environment detection device, a data processing device, a lightweight structural member and a communication device, the environment detection device is arranged on an unmanned aerial vehicle shell through the lightweight structural member, and the environment detection device and the communication device are both connected with the data processing device. The environment detection device is arranged on the shell of the unmanned aerial vehicle through a light-weight structural member and can detect environment parameters of the unmanned aerial vehicle in a real flight environment, the accuracy of the collected environment parameters is improved, the data processing device enables the communication device to normally recognize the environment parameters, and the environment detection device is arranged on the shell of the unmanned aerial vehicle through the light-weight structural member. The influence of the increased weight on the overall aerodynamic performance of the unmanned aerial vehicle can be reduced, the working performance of the unmanned aerial vehicle can be improved, and the use reliability of the unmanned aerial vehicle is improved.

The invention provides a driving and supporting device for a vertical axis fan reduced scale model test. The driving and supporting device comprises a frame assembly, a power mechanism and a slip ring mechanism, and the power mechanism is in transmission connection with the slip ring mechanism through the frame assembly. According to the driving and supporting device for the vertical axis fan reduced scale model test, the fan body can be fixed to the bottom platform, and the fan body can be driven to stably run at the target rotating speed; meanwhile, the problem of motion interference when the sensor cable rotates is solved; in addition, a modular design concept is adopted, parts such as a driving motor, a transmission mechanism and a coupler can be flexibly replaced according to different test requirements, and certain universality is achieved.

The invention discloses an air preparation system, which comprises an air inlet, an air outlet, a compression device and a main refrigeration device, wherein the air inlet is used for introducing airinto the air preparation system; the air outlet is used for sending the air processed by the air preparation system out of the air preparation system; the compression device is arranged between the air inlet and the air outlet and is in fluid communication with the air inlet and the air outlet; the compression device causes the air which flows through the compression device to be pressurized; themain refrigeration device is arranged between the compression device and the air outlet and is in fluid communication with the compression device and the air outlet; the main refrigeration device enables the temperature of the air which flows through the main refrigeration device to be lowered; the compression device is subjected to energy supply by electricity; and in addition, the main refrigeration device is a heat exchange element subjected to the energy supply by electricity. According to the air preparation system disclosed by the invention, the air entraining flow, the installation system and the weight of the system can be reduced.

The invention provides a volute structure for a range hood with an inclined side wall and a circular arc inlet cone. The structure comprises a volute profile surface, a volute inclined side wall structure and the circular arc inlet cone. The volute inclined side wall structure is of a three-layer plate structure, a middle layer plate is of a solid plate structure, outer side plates and inner sideplates of the volute are inclined toward the outer side of the volute from the bottom to the up, micro-perforations are evenly formed in plates, a plurality of resonant cavities with different depthsare arranged between the three layers of the plates, and the cavities can be filled with sound absorbing materials to achieve the common sound absorption of the inner wall and the outer wall of the volute; the circular arc inlet cone is smoothly connected with the outer plates of the volute on both sides, a smooth cone without sharp angles smoothly guide flue gas from an air inlet at the bottom ofa shell to air inlets on both sides of the volute, and the adhesion of oil droplets in the lower portion of the volute is reduced; the cross section of an inlet flow passage between the shell and theinclined side wall structure of the range hood volute with the circular arc inlet cone is gradually reduced from the bottom to the up, the flue gas flow rate is gradually increased, a smooth gradientis formed, the flow resistance and the flow separation are smaller, and the aerodynamic and acoustic performance are better.