15results about How to "Increase lift coefficient" patented technology

The invention discloses an oscillating jet device parameter optimization method based on flow control, which belongs to the field of aircraft flow control, and comprises the following steps: establishing an oscillating jet device model, and parameterizing an oscillating jet device; the oscillating jet device is assembled on a wing for flow control; grid division is carried out on the wing and the oscillating jet device; carrying out numerical simulation calculation according to the research working condition; parameterization optimization is carried out on the oscillation jet device, the lift coefficient is used as a research target, and the oscillation jet controller with the optimal flow control is obtained. According to the mechanism that the geometrical parameters of the oscillation jet device can influence the oscillation characteristic of the oscillation jet device, the separation vortex size of the wing is effectively reduced by changing the geometrical parameters of the oscillation jet device according to the research working condition in flow control, and the lift augmentation performance of the wing is further improved.

This invention discloses a high lift-to-drag ratio, long-endurance, low-speed airfoil, revealing its maximum relative camber, maximum relative thickness, and the curve equations satisfied by its upper and lower edges. The origin of the coordinate system containing the airfoil is defined as the leading edge of the chord. The X-axis coincides with the chord line, pointing from the leading edge to the trailing edge of the airfoil. The Y-axis is perpendicular to the X-axis, pointing in the direction of the airfoil's curvature. The chord length is defined as C; therefore, the maximum relative camber is 6%C, and the maximum relative thickness is 4.5%C. The airfoil of this invention exhibits a higher lift-to-drag ratio and a higher lift coefficient while maintaining a lower drag coefficient. It reduces the weight of the wing structure, and its thin, curved shape results in a smaller internal wing cavity, optimizing aircraft weight while concentrating stress on the structure.

The invention relates to the technical field of new energy. The invention discloses a deep sea current energy water turbine airfoil generation method, device, equipment and medium, and the method comprises the steps: preprocessing an original airfoil data set to obtain a target airfoil data set; based on a preset airfoil leading edge generation rule, obtaining an airfoil leading edge curve according to the target airfoil data set; performing central symmetry setting on the airfoil leading edge curve to obtain an airfoil trailing edge curve; based on a preset curve connection rule, a first connection curve and a second connection curve are generated, the first connection curve and the second connection curve are connected with the airfoil profile leading edge curve and the airfoil profile trailing edge curve respectively, and a target airfoil profile curve is generated. According to the method, the problem of insufficient centrosymmetric airfoils in an existing airfoil database is solved, the generated centrosymmetric airfoils can keep a high lift coefficient under bidirectional incoming flow, and the ocean current turbine based on the generated centrosymmetric airfoils can utilize deep sea ocean current energy in most directions without a yaw device.

The invention relates to a large-skewness, large-retreat-amount and high-bearing double-slit flap mechanism and an aircraft. The double-slit flap mechanism comprises a driving mechanism, a sub-flap and a main flap. The driving mechanism comprises a rack, a linear driving part, a first rocker arm, a second rocker arm, a first connecting rod, a second connecting rod and a third connecting rod; the rack is arranged on the outer side wall of the duct, the lower end of the first rocker arm is hinged to the rack, and the upper end of the first rocker arm is fixedly connected with the sub-flap; one end of the second connecting rod can slide relative to the rack, the middle of the second connecting rod is hinged to the middle of the first rocker arm, the other end of the second connecting rod is hinged to one end of the third connecting rod, and the other end of the third connecting rod is hinged to the first connecting rod. The double-slit flap mechanism can meet the requirements for large retreating amount, large deflection angle and high aerodynamic load bearing, and the aerodynamic lift augmentation effect of an aircraft in the vertical take-off and landing stage is improved.

The present application relates to a kind of micro aircraft low-speed lift increasing wrinkle airfoil, including main wing, wind speed detection sensor, shape memory alloy wire, direct current power supply, remote control machine, the main wing is the wrinkle wing profile structure with lift increasing effect, the wind speed detection sensor is installed on main wing and the wind speed signal detected is passed to remote control machine, the shape memory alloy wire is electrically connected with direct current power supply, the shape memory alloy wire and direct current power supply are installed on main wing, the direct current power supply is connected with remote control machine and is controlled by remote control machine, the on-off electricity situation of shape memory alloy wire and direct current power supply is controlled by remote control machine, make main wing switch between wrinkle wing type and flat plate wing type.The present application can significantly improve the lift of micro aircraft wing, has the advantages such as controllable deformation, reliable structure, stable driving and low energy consumption.

The invention discloses an airfoil configuration capable of improving separation characteristics at large angles of attack and a design method thereof. The airfoil configuration comprises a main wing and an elliptical wing, wherein the elliptical wing is arranged on the suction surface of the leading edge point of the main wing through a chord structure, and under the action of the incoming flow, alternating downward vortices are generated on both sides of the elliptical wing; the chord structure comprises a first fixing ring lock, a second fixing ring lock and a rotating bolt, wherein the first fixing ring lock is arranged at 25% of the span direction of the main wing, the second fixing ring lock is arranged at 75% of the span direction of the main wing, and the rotating bolt is arranged at 100% of the span direction of the main wing; the airfoil configuration can effectively suppress airflow separation at large angles of attack of the airfoil without consuming energy and generating less additional resistance, and can improve the lift coefficient of the airfoil while reducing the drag coefficient, and has the characteristics of greatly improving the lift-to-drag ratio of the airfoil and improving the aerodynamic performance at large angles of attack.

The utility model relates to the technical field of wind power blades, in particular to an angle adjusting device of a wind power blade, which comprises a hub seat, a plurality of blades are arranged on the outer side of the hub seat, the blades are connected with the hub seat through a connecting assembly, a driving assembly used for driving the blades to rotate is arranged in the hub seat, and the driving assembly is connected with the hub seat. According to the utility model, the angles of the blades are adjusted through the driving assembly, and the blades are leveled when the wind is strong, so that the damage to the blades due to too high rotating speed of the strong wind is reduced, and the stable operation of equipment under the condition of various wind speeds is ensured; when the wind is small, the lift coefficient of the blades can be optimized by adjusting the angles of the blades and increasing the wind energy capture of the blades, and the energy conversion efficiency is improved.

The utility model relates to the technical field of air conditioners, in particular to an axial flow fan which comprises an installation disc, blades, a first reinforcing part and a second reinforcing part. The blades are arranged on the peripheral wall of the mounting disc; the first reinforcing part is arranged on the suction surface of the blade and is close to the front edge side of the blade; the first reinforcing part extends to the blade top of the blade from the blade root of the blade; the second reinforcing part is arranged on the suction surface of the blade and is close to the tail edge side of the blade; the second reinforcing part extends to the blade top of the blade from the blade root of the blade; the structural strength of the blades is improved, and therefore the strength requirement of the axial flow fan is met.

The invention provides a combined wing system based on distributed ducted fans and an application method thereof.The combined wing system is arranged on the two sides of a hovercar and comprises wings symmetrically arranged on the two sides of the hovercar, the wings comprise inner wings, outer wings, leading edge slats and trailing edge flaps, the inner wings and the outer wings are sequentially arranged in the direction from near to far away from a cabin, and the leading edge slats and the trailing edge flaps are arranged on the inner wings; a plurality of ducted fans which are parallel to the pneumatic chord and can deflect downwards are mounted on the trailing edge flap at uniform intervals; the wing-shaped front and rear edges of the outer wing are opposite to the inner wing, and the rear edge is preposed. When the EDF works, air flow is guided to flow through the upper surfaces of the wings in an air suction mode, negative pressure is generated, the wings do not move forwards during vertical take-off but also generate induced lift force, resultant force is formed by the induced lift force and upward Newton force counter-acting force generated by EDF jet flow, and the whole hovercar is pushed to the high altitude. And the outer wings with mounting angles are designed to further enhance lift and reduce drag, and meanwhile, a high-lift airfoil profile is adopted, so that the lift-drag ratio is efficiently improved, and the flight efficiency is effectively improved.

The present application belongs to the field of air flow, and relates to a blowing flap of a fixed-axle sub flap adaptive spoiler. The blowing flap comprises a fixed wing surface, a fixed rotating shaft, a main flap, a sub flap, a main flap blowing gap, a sub flap blowing gap, a spoiler rotating shaft and a spoiler. The main flap and the sub flap are downwardly deflected at a large angle, the spoiler is downwardly deflected to be attached to the upper surface of the sub flap, the blowing gaps on the sub flap and the main flap work in a certain blowing momentum coefficient matching relationship, the maximum lift coefficient of the aircraft is greatly improved, the lift-drag ratio is very high, and the super-circulation effect is realized.

The invention provides a vertical axis wind power blade airfoil suitable for medium and low wind speeds, a wind wheel and a generator. The maximum thickness of the airfoil is 18.37% of the chord length of the airfoil; the maximum thickness position of the airfoil is 31.20% of the chord length of the airfoil; the maximum camber of the airfoil is 2.11% of the chord length of the airfoil; and the maximum camber position of the airfoil profile is 23.20% of the maximum camber position of the airfoil profile. The blade airfoil provided by the invention has higher lift coefficient and lift-drag ratio under the working conditions of larger local attack angle and lower Reynolds number, the aerodynamic performance of a vertical axis wind turbine at medium and low wind speeds can be effectively improved, and the wind energy utilization efficiency of a unit is improved. The requirements of comprehensive smart energy and distributed wind power projects with complex topographic conditions and dense or mutual shielding buildings can be met, and the power generation efficiency of the vertical axis wind turbine under the working conditions of large wind resource change and low average wind speed is improved.

The invention discloses a flapping wing driving device, relates to the technical field of flapping wing aircrafts, and mainly aims to provide a flapping wing driving device with a wing shaft and a wing section for self-adaptive torsion. According to the main technical scheme, the flapping wing driving device comprises a rotating part, a rocker arm is arranged outside a first rod body in a sleeving mode, a protruding strip is arranged on the outer surface of a shaft body, one end of the shaft body is rotationally connected to the radial direction of the rocker arm, a base is arranged outside the rocker arm, one end of an inhaul cable is connected to the base, and the base is connected to one end of a tension spring body. The other end of the inhaul cable is wound outside the shaft body and is connected to the other end of the tension spring body; the shaft body penetrates through each shaft hole, the protruding strip penetrates through each displacement hole, the inflation pipes are arranged on the two sides of the protruding strip, a first space is formed between the protruding strip and the wing component, and the inflation pipes fill the first space; and the power part is connected to the inhaul cable. The flapping wing aircraft is mainly used for flapping wing flight.

The invention provides an aviation turbofan engine outer duct airflow high lift device and a vector control device, and belongs to the technical field of aerospace. The outer duct airflow high lift device of the aviation turbofan engine comprises an outer mounting ring, an inner fixing ring and an airflow high lift assembly. And the two airflow lift augmentation assemblies comprise lift augmentation front edge plates, the two lift augmentation front edge plates are fixedly connected with the opposite faces, in the transverse direction, of the outer mounting ring and the inner fixing ring correspondingly, and one sides of the two lift augmentation front edge plates are rotationally connected with lift augmentation rear edge plates. According to the high-bypass-ratio turbofan engine, the lift augmentation assembly and the direction control surface are additionally arranged on the outer duct of the high-bypass-ratio turbofan engine, airflow distribution and the vector direction in the outer duct are accurately regulated and controlled, collaborative optimization of thrust and lift force of the engine is achieved, and therefore the overall efficiency and fuel economy of the engine are improved.

This invention discloses an aircraft with an integrated fluid thrust vectoring nozzle and wing, comprising an integrated airfoil, an engine, an engine exhaust nozzle, and a fluid thrust vectoring nozzle; the engine is embedded within the integrated airfoil, and the engine exhaust nozzle is pre-deflected upwards. This aircraft with an integrated fluid thrust vectoring nozzle and wing effectively reduces the thickness of the wing's trailing edge, thereby reducing aft drag during flight; it is lightweight, has fewer moving parts, and exhibits fast deflection response, providing controllable pitching moment within the aircraft's cruise angle of attack; it improves the lift coefficient and control moment; and it enhances the aircraft's infrared stealth performance.

The invention provides a vertical axis wind turbine blade airfoil, a wind wheel and a wind turbine. The airfoil has a high lift-drag ratio at a low wind speed, and the maximum thickness of the airfoil is 13.19% of the chord length of the airfoil; the maximum thickness position of the airfoil is 32.30% of the chord length of the airfoil; the maximum camber of the airfoil is 2.27% of the chord length of the airfoil; and the maximum camber position of the airfoil profile is 58.90% of the maximum camber position of the airfoil profile. The blade airfoil has a high lift coefficient and lift-drag ratio under the low Reynolds number and the large-range local attack angle, and therefore the aerodynamic performance of the small vertical axis wind turbine at the medium-low wind speed can be effectively improved. The wind energy utilization efficiency of the small vertical axis wind driven generator under the low wind speed can be improved, the generating capacity is improved, the generating efficiency of a unit is improved, and the requirements of comprehensive smart energy projects and distributed wind power with ground wind resources greatly affected by the surrounding environment are better met.