Abstract: The invention discloses an aircraft generating a larger thrust and lift by fluid continuity. First open channels used to extend fluid paths are formed in front parts and/or middle parts of windward sides of wings of the aircraft and extend from sides, close to the fuselage, of the wings to sides, away from the fuselage, of the wings, and the first open channels are concave channels or convex channels, so that a pressure difference in a direction identical with a moving direction is generated from back to front due to different flow speeds of fluid flowing over the windward sides of the wings in a lengthwise direction and a widthwise direction to reduce fluid resistance, and a larger pressure difference and lift are generated due to different flow speeds on the windward sides and leeward sides of the wings.

Abstract: The present invention provides a power device generating greater propelling force and finds that traditional power devices do not include all propelling forces based on the fundamental core propelling force source problem. External pressure is guided to the traditional power devices since the inner speed is higher the outer speed, power consumption for overcoming fluid resistance is high, and mutual contradiction results are obtained. The unique difference between the present invention and general common sense lies in opposite fluid pressure directions; inner fluid channels and outer fluid channels with higher flow speeds are formed to generate pressure differences which guides the fluid pressure to the outside and serve as propelling force, thus the present invention creatively finds three propelling force sources, two lifting force or propelling force sources of helicopters or airplanes driven by propellers and two propelling force sources for sufficient burning of fuel in combustion chambers of engines.

Abstract: The present invention provides a power device generating greater propelling force and finds that traditional power devices do not include all propelling forces based on the fundamental core propelling force source problem. External pressure is guided to the traditional power devices since the inner speed is higher the outer speed, power consumption for overcoming fluid resistance is high, and mutual contradiction results are obtained. The unique difference between the present invention and general common sense lies in opposite fluid pressure directions; inner fluid channels and outer fluid channels with higher flow speeds are formed to generate pressure differences which guides the fluid pressure to the outside and serve as propelling force, thus the present invention creatively finds three propelling force sources, two lifting force or propelling force sources of helicopters or airplanes driven by propellers and two propelling force sources for sufficient burning of fuel in combustion chambers of engines.

Abstract: The invention discloses an aircraft generating a larger thrust and lift by fluid continuity. First open channels used to extend fluid paths are formed in front parts and/or middle parts of windward sides of wings of the aircraft and extend from sides, close to the fuselage, of the wings to sides, away from the fuselage, of the wings, and the first open channels are concave channels or convex channels, so that a pressure difference in a direction identical with a moving direction is generated from back to front due to different flow speeds of fluid flowing over the windward sides of the wings in a lengthwise direction and a widthwise direction to reduce fluid resistance, and a larger pressure difference and lift are generated due to different flow speeds on the windward sides and leeward sides of the wings.

Abstract: A fluid supercharging device (3, 5), comprising: a rotating shaft (7); a vane disc (308) coaxially fixed to the rotating shaft (7); a plurality of fan blades (301) fixed around a perimeter of the vane disc (308); the back side of the fan blades 301 being provided with at least one fluid guiding inlet (305), an end of the back side distal from the vane disc (308) is provided with a fluid guiding outlet (306, 307), a fluid channel (304) communicating the fluid guiding inlet (305) with the fluid guiding outlet (306, 307) is provided along a lengthwise direction inside the fan blades; the fan blades (301) rotate to generate a centrifugal force such that a fluid flows into the fluid channel via the fluid guiding inlet on the back side, and flows out of the fluid guiding outlet along the lengthwise direction of the fan blades.

Abstract: The present disclosure provides methods for the rapid synthesis of pyranoanthocyanins.

Abstract: The present invention provides a power device generating greater propelling force and finds that traditional power devices do not include all propelling forces based on the fundamental core propelling force source problem. External pressure is guided to the traditional power devices since the inner speed is higher the outer speed, power consumption for overcoming fluid resistance is high, and mutual contradiction results are obtained. The unique difference between the present invention and general common sense lies in opposite fluid pressure directions; inner fluid channels and outer fluid channels with higher flow speeds are formed to generate pressure differences which guides the fluid pressure to the outside and serve as propelling force, thus the present invention creatively finds three propelling force sources, two lifting force or propelling force sources of helicopters or airplanes driven by propellers and two propelling force sources for sufficient burning of fuel in combustion chambers of engines.

Abstract: The invention discloses a propeller-driven helicopter or airplane which comprises a fuselage and a propeller comprising a plurality of blades, wherein a plurality of pressure pipes are uniformly distributed between windward sides and leeward sides of the blades; a plurality of first inlets are formed in the windward sides and are communicated with outside via first channels in the blades and second outlets at tails of the blades; a high-pressure fluid of a low-speed fluid layer formed when a fluid flows through the leeward sides in a widthwise direction flows towards a low-pressure fluid of a high-speed fluid layer formed when the fluid flows through the first inlets, the first channels and the second outlets; and an upward pressure generated by the high-pressure fluid is opposite to a downward pressure generated by an external fluid above the windward sides, so that a fluid pressure above the propeller is decreased.

Abstract: The present invention provides a power device generating greater propelling force and finds that traditional power devices do not include all propelling forces based on the fundamental core propelling force source problem. External pressure is guided to the traditional power devices since the inner speed is higher the outer speed, power consumption for overcoming fluid resistance is high, and mutual contradiction results are obtained.

Abstract: The invention discloses an aircraft generating a larger thrust and lift by fluid continuity. First open channels used to extend fluid paths are formed in front parts and/or middle parts of windward sides of wings of the aircraft and extend from sides, close to the fuselage, of the wings to sides, away from the fuselage, of the wings, and the first open channels are concave channels or convex channels, so that a pressure difference in a direction identical with a moving direction is generated from back to front due to different flow speeds of fluid flowing over the windward sides of the wings in a lengthwise direction and a widthwise direction to reduce fluid resistance, and a larger pressure difference and lift are generated due to different flow speeds on the windward sides and leeward sides of the wings.

Abstract: The invention discloses an aircraft generating a larger thrust and lift by fluid continuity. First open channels used to extend fluid paths are formed in front parts and/or middle parts of windward sides of wings of the aircraft and extend from sides, close to the fuselage, of the wings to sides, away from the fuselage, of the wings, and the first open channels are concave channels or convex channels, so that a pressure difference in a direction identical with a moving direction is generated from back to front due to different flow speeds of fluid flowing over the windward sides of the wings in a lengthwise direction and a widthwise direction to reduce fluid resistance, and a larger pressure difference and lift are generated due to different flow speeds on the windward sides and leeward sides of the wings.

Abstract: Embodiments include devices and methods for processing an image captured by an image sensor of a robotic vehicle. A processor of the robotic vehicle may calculate an image output orientation matrix for an image that is output by the image sensor. The processor may calculate image sensor orientation matrix the image sensor. The processor may calculate a body orientation matrix of the robotic vehicle. The processor may transform the image captured by the image sensor based on the image output orientation matrix, the image sensor orientation matrix, and the body orientation matrix.

Abstract: A fluid supercharging device (3, 5), comprising: a rotating shaft (7); a vane disc (308) coaxially fixed to the rotating shaft (7); a plurality of fan blades (301) fixed around a perimeter of the vane disc (308); the back side of the fan blades 301 being provided with at least one fluid guiding inlet (305), an end of the back side distal from the vane disc (308) is provided with a fluid guiding outlet (306, 307), a fluid channel (304) communicating the fluid guiding inlet (305) with the fluid guiding outlet (306, 307) is provided along a lengthwise direction inside the fan blades; the fan blades (301) rotate to generate a centrifugal force such that a fluid flows into the fluid channel via the fluid guiding inlet on the back side, and flows out of the fluid guiding outlet along the lengthwise direction of the fan blades.

Abstract: A fluid supercharging device, comprising: a rotating shaft; a vane disc coaxially fixed to the rotating shaft; a plurality of fan blades fixed around a perimeter of the vane disc; the back side of the fan blades being provided with at least one fluid guiding inlet, an end of the back side distal from the vane disc is provided with a fluid guiding outlet, a fluid channel communicating the fluid guiding inlet with the fluid guiding outlet is provided along a lengthwise direction inside the fan blades; the fan blades rotate to generate a centrifugal force such that a fluid flows into the fluid channel via the fluid guiding inlet on the back side, and flows out of the fluid guiding outlet along the lengthwise direction of the fan blades.

Abstract: The invention discloses a propeller-driven helicopter or airplane which comprises a fuselage and a propeller comprising a plurality of blades, wherein a plurality of pressure pipes are uniformly distributed between windward sides and leeward sides of the blades; a plurality of first inlets are formed in the windward sides and are communicated with outside via first channels in the blades and second outlets at tails of the blades; a high-pressure fluid of a low-speed fluid layer formed when a fluid flows through the leeward sides in a widthwise direction flows towards a low-pressure fluid of a high-speed fluid layer formed when the fluid flows through the first inlets, the first channels and the second outlets; and an upward pressure generated by the high-pressure fluid is opposite to a downward pressure generated by an external fluid above the windward sides, so that a fluid pressure above the propeller is decreased.

Abstract: The invention discloses a lift source for an aircraft comprising a fuselage and wings, wherein first channels are formed in the wings, a plurality of first inlets are formed in upper surfaces of the wings, a plurality of first pressure ports are formed in lower surfaces of the wings and are communicated with the first inlets via the first channels; and spoiler devices are arranged in the first channels and under the effect of the spoiler devices, form high-speed fluid layers on the upper surfaces of the wings, thereby generating a pressure difference from the lower surfaces of the wings which counteracts an external fluid pressure on the upper surfaces of the wings in the opposite direction, so a lift is generated by reduction of fluid resistance when fluid flows through the upper and lower surfaces of the wings, thereby developing a high-speed aircraft with a larger lift and thrust.

Abstract: The present disclosure relates to a bladeless fan, which includes a housing and a power device, wherein the power device communicates with a fluid passage and a negative pressure passage disposed in the housing respectively; the fluid passage communicates with the outside through a plurality of exhaust ports, and the negative pressure communicates with the outside through a plurality of suction ports; a middle region inside the fluid passage is provided with a spoiler device so that a path along which the fluid passes through the spoiler device is larger than a path along which the fluid passes around the corresponding inner wall, thereby generating a pressure difference. The present disclosure enables a higher-speed flow of the fluid inside the fluid passage through pressure difference without adding extra power, and generates a faster air speed in a more energy-saving way, thereby achieving a remarkable effect of cooling.

Abstract: Embodiments include devices and methods for processing an image captured by an image sensor of an unmanned autonomous vehicle (UAV). A processor of the UAV may determine a body coordinate matrix of the UAV. The processor may determine an estimated rotation of the image sensor of the UAV. The processor may determine an estimated rotation of the UAV. The processor may transform an image captured by the image sensor based on the body coordinate matrix, the estimated rotation of the image sensor, and the estimated rotation of the UAV.

Abstract: Embodiments include devices and methods for adaptive image processing in an unmanned autonomous vehicle (UAV). In various embodiments, an image sensor may capture an image, while a processor of the UAV obtains attitude information from one or more attitude sensors. Such information may include the relative attitude of the UAV and changes in attitude. The processor of the UAV may determine a UAV motion mode based, at least in part, on the obtained attitude information. The UAV motion mode may result in the modification of yaw correction parameters. The processor of the UAV may further execute yaw filtering on the image based, at least in part, on the determined motion mode.

Abstract: Disclosed is an automobile, comprising an automobile body, wheels, a suspension device and a spoiler. The path of a fluid flowing through a lower spoiler surface is longer than the path of the fluid flowing through the upper spoiler surface, so that a lift force generated in the driving process of the automobile is reduced or even eliminated. The general understanding that the wheels bear the dead weight of the automobile, loads and all weights generated by the gravitational acceleration is changed. The dead weight of the automobile body is reduced by the lift force generated by the automobile body, the road holding of the automobile is improved after the wheels eliminate the lift force, and thus, the automobile can save more energy and can run more safely.