16results about How to "Reduce aerodynamic drag" patented technology

The invention discloses a multi-rotor aircraft with lift-enhanced wings, which comprises rotor power devices, a fuselage for mounting airborne equipment and connecting the rotor power devices, and a pair of independent and controllable lift-enhanced wings, the high-lift wings are mounted on the fuselage; when the multi-rotor aircraft with the high-lift wings flies, a flight control algorithm controls the tilting angles of the high-lift wings according to the attitude and the flight speed of the aircraft, so that the high-lift wings are in a proper attack angle state, and proper lift force can be provided for the aircraft. The flying speed can be increased, the cruising ability is improved, and transportation and storage are convenient.

This invention proposes a symmetrically arranged cross-wing unmanned aerial vehicle (UAV) system, relating to the field of UAVs. It includes a fuselage structure, a power module, and a flight control module. The fuselage structure comprises a cylindrical fuselage and four wings symmetrically arranged in a cross pattern around the cylindrical surface of the fuselage; the four wings are arranged in an X-shape or a cross shape. The power module includes motors and propellers. The motors are located at the wingtips, with their output shafts aligned with the fuselage axis and facing the tail of the fuselage. The propellers are connected to the motor output shafts. The flight control module is located inside the fuselage and is used to control the output speed of the four motors. This system combines the advantages of a quadcopter FPV and a fixed-wing UAV, generating lift from the wings while also cruising and sprinting in fixed-wing form. Furthermore, by changing the motor speeds, it can control the pitch, yaw, and roll attitude of the UAV, eliminating the need for separate control surfaces, thus simplifying the structure and reducing costs.

The invention relates to a corrugated wall surface airfoil profile and a design method thereof, which are applied to an unmanned aerial vehicle, and are characterized in that a corrugated wall surface is arranged in a chordwise region of the upper surface of the airfoil profile, and the corrugated wall surface is used for inducing a boundary layer of the upper surface of the airfoil profile to transition in advance and inhibiting generation of laminar flow separation bubbles; the corrugated wall surface is of a sine function corrugated structure, and the sine curve of the corrugated wall surface meets the following formula. According to the invention, the sine wave pattern-shaped wall surface structure with specific geometric parameters is arranged in the chordwise middle rear area of the upper surface of the wing profile, so that local pressure distribution of the surface of the wing profile is changed, a boundary layer is induced to transit in advance, generation of laminar separation bubbles is inhibited, wall surface friction resistance and differential pressure resistance are reduced, and the stability of the wing profile is improved. The problem that the low-altitude low-speed unmanned aerial vehicle wing type drag reduction effect is limited is solved.

This invention relates to a drag-reducing and heat-cooling device combining a partitioned base with a liftable central structure. The device includes a central base structure, a peripheral base structure, a drive mechanism, and a cold air flow control system. The central base structure comprises an arc-shaped surface and a lifting rod. The arc-shaped surface is located at the center of the peripheral base structure surface. When the lifting rod is compressed, the arc-shaped surface remains flush with the peripheral base structure, forming an integrated heat shield. The cold air flow control system includes a gas pipeline, a cold air storage cylinder, and an ejector device. Cold air is uniformly injected from the ejector device through the gas pipeline and the lifting rod onto the surface of the central base structure, forming a gas film. The drive mechanism is located inside the reentry capsule and drives the lifting rod to extend or retract into the reentry capsule, thereby raising or lowering the arc-shaped surface of the central base structure. This invention effectively reduces the impact of heat flow while reducing aerodynamic load, improving the safety and reliability of reentry.

The utility model belongs to the technical field of shape design and control of aircrafts, and relates to an electric tilt-rotor aircraft. Comprising a fuselage, two wings located on the two sides of the fuselage, an empennage, a plurality of supporting rods arranged below the wings and rotors arranged at the two ends of the supporting rods. The rotor wings comprise a plurality of tilting rotor wings and a plurality of fixed rotor wings; the number of the supporting rods is even, and the supporting rods are divided into two sets with the same number and are symmetrically arranged on the two sides of the machine body. A tilting rotor wing is arranged at the front end of each supporting rod; a fixed rotor wing is arranged at the rear end of each supporting rod; the tilting rotor wings are connected with the front ends of the supporting rods through tilting mechanisms, and the tilting mechanisms are used for adjusting the orientation of the tilting rotor wings. The electric tilting rotor aircraft provided by the utility model can realize the functions of vertical take-off and landing, tilting transition and cruise flight.

The invention relates to the technical field of communication and transportation engineering, and discloses an overwater ground effect aircraft which comprises an aircraft body, wings, limiting rings and adjusting plates. During takeoff, extension wings extend out of hydrofoils to increase the contact area, provide extra hydrodynamic force lift force and reduce the head wave resistance, and hydraulic rods adjust the underwater depth and included angle of the hydrofoils in real time; the taxiing distance is shortened, and the takeoff power is reduced; and the hydrofoils are automatically retracted after lift-off, so that aerodynamic resistance is reduced. During landing, the hydrofoil is unfolded, the angle is adjusted and controlled to form a buffering lift force area, water entry impact is reduced, the flight control system adjusts the posture of the hydrofoil in real time, underwater additional torque is provided, posture controllability is improved, the taxiing distance is shortened, energy consumption is reduced, and stability is enhanced. When the wing ship mode is switched, pneumatic propulsion is closed, and the driving shaft drives the underwater driving paddle to drive the aircraft under low-power operation; and when the direction is adjusted, the direction of the driving paddle is changed through rotation of the first worm wheel, and the design can quickly switch modes, greatly reduce energy consumption and widen the use scene.

The application discloses a kind of folding wing cruise vehicle mounting and launching device and launching method, device is by launching barrel, force frame, hanging point, separation ring, control device, buffer pad, torsion spring hinge, guide frame, hatch control steering gear, hatch and mounting rack composition;The mounting and launching device reduces the aerodynamic interference between the folding wing cruise vehicle launching process and carrying platform, greatly improves the launching safety.And the mounting and launching device has no pyrotechnics and deceleration parachute, simple mechanism, safe, reliable, low cost, can be reused repeatedly;At the same time, its working process is given, and the launching device is opened, the folding wing cruise vehicle is separated from the launching barrel, the separation ring is unlocked, the separation ring is separated from the cruise vehicle, the cruise vehicle folding wing is unlocked and unfolded, the cruise vehicle enters the flight state, the separation ring is recycled, and the hatch is closed. The launching separation process completes the launching of the cruise vehicle.

The invention relates to an electric machine (1), comprising a stator (2), which is accommodated in a manner fixed to a housing, and a rotor (4), which is rotatably mounted relative to the stator and which is spaced apart from the stator (2) by a radial gap (3). The rotor (4) and / or the stator (2) each comprise a lamination stack (5, 6) consisting of a plurality of laminations (7) stacked one on top of the other in the axial direction. A surface structure (9) that reduces aerodynamic resistance is formed on a surface (8) of the rotor (4) and / or the stator (2) facing the radial gap (3). In this case, the surface structure (9) is formed by stacking the laminations (7) on one another, said laminations having a circumferential structure (10), which forms the circumferential side on at least some of the laminations (7).

This invention discloses an underactuated robot leg and a flying robot with adaptive landing and grasping capabilities. The underactuated robot leg includes a frame assembly, symmetrically arranged first and second leg units, a first actuator, a second actuator, and a corresponding transmission mechanism. The frame assembly includes a frame plate and two support components. Each leg unit has a first leg structure and a second leg structure arranged side by side. Connected by the support components, the mounting plane of the first leg structure is lower than that of the second leg structure, forming a staggered layout. This invention reliably switches the underactuated robot leg between a passive adaptive stable support configuration, an active grasping configuration, and a folding and storage configuration simply by controlling the extension and retraction of the first and second actuators, solving the contradictory problem of balancing passive adaptive landing on undulating terrain and active grasping of objects within the same mechanism.

The utility model discloses a low scattering and pneumatic integrated telescopic hexagonal groove countersunk head screw, it includes screw cap, countersunk head round platform thread and stem. Screw cap includes six prismatic marbles spring and six prismatic inner groove, when not considering the tolerance gap between six prismatic marbles and six prismatic inner groove, the stem is the cylinder that is connected with the bottom surface of screw cap, and the thread is the ordinary thread that is equidistantly surrounded in the stem, that is, the triangular tooth shape. The low scattering pneumatic telescopic hexagonal groove countersunk head screw provided by the utility model provides the design principle of low scattering pneumatic screw radar stealth and pneumatic shape, which is a design method for the comprehensive mechanical properties of the low detectability of the screw pneumatic, and the design idea is unique and ingenious, the pneumatic low detectability effect is remarkable, the mechanical properties are good, and the design part has high universality. It can be operated and used by using the general hexagonal screwdriver, and it is convenient to couple all the screws with the whole in the gap direction.

The application discloses a bogie bottom drag reduction cladding plate and a high-speed train bogie, and the cladding plate comprises a torsion bar cladding plate for cladding a torsion bar of a bogie frame, a first cladding plate for connecting a cross beam on one side of the torsion bar, and a second cladding plate for connecting a cross beam on the other side of the torsion bar. The first cladding plate and the torsion bar cladding plate form a first flow guide slope, the second cladding plate and the torsion bar cladding plate form a second flow guide slope, and the flow guide directions of the first flow guide slope and the second flow guide slope are symmetrically arranged. The application guides the airflow originally acting on the region near the center pin hole and the torsion bar to the lower side of the torsion bar cladding plate, optimizes the partial cladding and flow guide of the originally complex and abrupt bottom profile near the center pin hole and the torsion bar, forms a relatively continuous bottom flow guide surface, weakens the direct interference between the airflow and the complex components of the bottom, reduces the local flow separation, backflow and vortex intensity, improves the bogie bottom flow field distribution, and further achieves the purpose of reducing the aerodynamic drag of the bogie region.

The invention relates to the technical field of spacecraft supporting devices, and discloses a freight aircraft support which comprises an upper connecting cylinder, a cylinder body, a lower connecting cylinder and a loading platform. The upper connecting cylinder is located at the top of the cylinder body and connected with the cylinder body, and a first opening is formed in the upper connecting cylinder and used for containing the tail of the freight aircraft; a second opening is formed in the side wall of the barrel, and a through channel is formed between the first opening and the second opening; the lower connecting cylinder is located at the bottom of the cylinder body, connected with the cylinder body and used for being connected with a carrier rocket. The loading platform is located in the barrel and located below the through channel, one end of the loading platform is connected with the barrel, and the other end of the loading platform is used for being connected with a carrier rocket. The present invention can improve loading convenience and separation reliability.

The invention discloses a gas-fired boiler low-nitrogen burner convenient to adjust gas inflow, and relates to the technical field of boilers, the gas-fired boiler low-nitrogen burner convenient to adjust gas inflow comprises a motor, a gas inlet pipe and a driving mechanism, a first adjusting mechanism is arranged in the gas inlet pipe, and the driving mechanism comprises a fixing disc coaxially fixed to an output shaft of the motor; the outer edge of the side wall of the fixed disc is provided with a plurality of fixed frames which are distributed along the circumferential direction of the fixed disc in an array manner; according to the device, motor rotating speed regulation and control and air door opening and closing regulation and control are combined, when the rotating speed of the motor is increased, centrifugal force drives a balancing weight to move outwards, a first telescopic rod, a fixing pipe and a second telescopic rod push a spiral rod to move axially, the spiral rod is matched with a limiting column, and linear motion is converted into rotation of a first annular fluted disc; therefore, all the blades are driven to integrally and synchronously change the deflection angles of the blades, a sensor and a complex circuit are omitted, the occupied area and the manufacturing cost of the system are reduced, the air inlet amount can be adjusted in a stepless mode in real time according to the air inlet requirement, and different air inlet requirements are met.

The utility model discloses a kind of unmanned aerial vehicle for realizing vertical take-off and attitude control using rotor steering, there are two across installation in left and right wings in flight direction on hanger, hanger front end and rear end are equipped with rotors and power device that can be steered;When horizontal flight, front rotor generates pull, rear rotor generates thrust;Front rotor and power device vertically upward rotate 90 ° and generate upward pull, rear rotor and power device downward rotate 90 ° and generate upward thrust, realize unmanned aerial vehicle vertical take-off;Unmanned aerial vehicle flight attitude is controlled using deflection combination of front two rotors and rear two rotors, and using deflection combination of same side hanger front and rear rotors;Make unmanned aerial vehicle have good maneuverability, save horizontal stabilizer and elevator, save vertical stabilizer and rudder, thereby reduce flight resistance, it is favorable to improve the effective load of unmanned aerial vehicle.

The application discloses a lower apron assembly and a vehicle, and solves the technical problem that the lower apron of the prior art does not cover the position of a suspension, so that the coverage of the lower apron in the area is discontinuous, vortex and turbulence phenomena caused by gas flow are obvious, and the aerodynamic drag of the whole vehicle is large. The lower apron assembly comprises a lower apron body and a suspension lower apron, the suspension lower apron covers the suspension part of a vehicle chassis, the suspension lower apron is connected with the lower apron body and a suspension assembly of the vehicle respectively, the suspension lower apron is made of an elastic material so that it can deform correspondingly with the up-and-down swing of the suspension assembly, and the suspension lower apron is provided with a avoiding part at the position of a vehicle wheel, which can avoid motion interference, the suspension lower apron covers the suspension part of the vehicle chassis, so that the coverage of the lower apron assembly in the suspension area is continuous, vortex and turbulence phenomena caused by gas flow are avoided, and the aerodynamic drag of the whole vehicle is reduced.

The invention discloses an automobile drag reduction control method and system based on a follow-up wave generation device, and relates to the technical field of active flow control, and the method comprises the steps that an exciter array distributed in a master-slave partition mode is arranged based on a key pneumatic area of a target vehicle; acquiring vehicle state data and flow field state data of the target vehicle in real time; acquiring a time delay and a space-time trigger sequence based on the vehicle state data; acquiring an external modulation frequency and a duty ratio of the exciter array based on the flow field state data; a high-voltage electric signal conforming to time delay, a space-time trigger sequence, external modulation frequency and a duty ratio is generated to serve as a control instruction; the exciter array is controlled to generate plasma volume force based on the control instruction, a follow-up wave regulation and control flow field is formed, and the aerodynamic resistance of the target vehicle is reduced. Generation and development of separation vortexes are actively regulated and controlled, flow separation is delayed, and a wake flow area is reduced, so that aerodynamic resistance of an automobile under various running working conditions is remarkably and stably reduced, and the energy efficiency ratio is increased.