6results about How to "Reduce aerodynamic drag" patented technology

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.

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.

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 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.