16 results about "Rotary wing" patented technology

A blade for a rotary wing able to rotate about an axis of rotation, the blade extending along the pitch axis from a first end to a second end, the blade comprising a blade body having, from the first end to the second end, a succession of sections substantially perpendicular to the pitch axis. Along its pitch axis, the blade has sections having: increasing and then decreasing chords, a relative thickness that decreases from an initial section to a final section, twist angles that continuously increase from the origin section to an initial section and then decrease, and a changing offset relative to the pitch axis.

An apparatus to determine take-off and landing times for a Rotary wing aircraft by the measurement and analysis of the atmospheric pressure changes around or within the aircraft. This may be done acco

A split quick-release back-blowing rotary wing is characterized in that the back-blowing rotary wing is arranged in a filter core, and the back-blowing rotary wing comprises a central shaft, a rotary connecting piece and an air pipe, the upper end of the central shaft is connected with the rotary connecting piece, a bearing is arranged between the rotary connecting piece and the central shaft, the rotary connecting piece can rotate with the central shaft as the rotating shaft, the upper end of the air pipe is fixedly connected with the rotary connecting piece, a plurality of blow holes arranged vertically are arranged on the side of the air pipe, the lower end of the central shaft penetrates through the center of a connecting plate, the lower end of the air pipe is fixedly connected with the connecting plate, a gas receiving port is arranged on the upper end surface of the rotary connecting piece, and the gas receiving port is in air communication with the air pipe. The split quick-release back-blowing rotary wing is provided by arranging the back-blowing rotary wing in the filter core and adopting the technical scheme of the split quick-release structure, and the problems that the existing rotary wing device needs to be connected with a main machine first and then a filter cartridge is sleeved outside the rotary wing device, resulting in time-consuming and labor-consuming installation and disassembly, high operation skill requirement and poor working environment are solved.

The application relates to the technical field of water meters, in particular to a rotary-wing water meter which comprises a meter shell assembly and a metering module. The meter shell assembly comprises a lower shell and an upper shell. The lower shell comprises a water inlet, an inner cylinder cavity, an outer cylinder cavity and a water outlet. The outer cylinder cavity is located outside the inner cylinder cavity. The upper shell has a containing cavity. The upper shell is connected with the lower shell. The outer cylinder cavity is communicated with the containing cavity. The containing cavity and the outer cylinder cavity are coaxially arranged. The metering module comprises a filter screen box, an impeller box, a fine adjustment plate and a rotary impeller. The impeller box is abutted with the fine adjustment plate and the filter screen box respectively. The fine adjustment plate is also abutted with the bottom wall of the containing cavity. One end of the filter screen box is communicated with the inner cylinder cavity. The impeller box has an impeller cavity. The impeller cavity has an inflow port and an outflow port. The rotary impeller is rotatably installed in the impeller cavity. One end of the fine adjustment plate close to the impeller box has a convex rib. The convex rib extends into the impeller cavity. The upper and lower shells are designed in a split type, and the fine adjustment structure is arranged. The upper and lower shells are integrally sealed at the top of the middle section. The fine adjustment structure has the advantages.

The present application relates to a pivot wing (1) for use as an outwardly opening wing about a vertical axis of rotation (2) of a vertically oriented room boundary element (3), comprising a rectangular wing frame (4) formed by four wing profiles (6, 7, 8, 9) extending in a common wing plane (5), a planar infill (10) oriented parallel to the wing plane (5) and a wing seal (11) attached to the wing frame (4), wherein the wing seal (11) is provided and arranged to come into contact with the sealing system on a fixed frame (12) of the room boundary element (3) when the pivot wing (1) is in a closed position in a direction perpendicular to the wing plane (5), wherein an upper section (41) of the at least one wing seal (11) is attached to an upper horizontal wing profile (6) of the wing frame (4). To provide a casement window that also prevents water from entering the building under the described load conditions, an elongated, channel-shaped drainage profile (14) is proposed, which is arranged in a force-transmitting manner on the upper horizontal sash profile (6) and extends parallel to its profile axis (25) at least substantially over the entire length of the upper horizontal sash profile (6), wherein the drainage profile (14) is arranged on the upper horizontal sash profile (6) such that it is located below the upper section (41) of the sash seal (11), so that water can fall from the upper section (41) of the sash seal (11) onto the drainage profile (14), wherein the drainage profile (14) is closed at its longitudinally opposite ends with end caps (15).wherein a fluid-flow connection exists between the drainage profile (14) and at least one hollow chamber (16) of the upper horizontal wing profile (6).

This invention relates to the field of control technology for fuel-powered rotorcraft, and in particular to an automatic speed control method for fuel-powered rotorcraft engines. Through bench testing and flight experiments, a multi-dimensional adaptive control parameter table is constructed using current power, target power, and altitude as three-dimensional indexes to quantify engine acceleration and deceleration characteristics. After the flight control system identifies the power demand in real time, it calls the parameter table to query the engine power response time and attitude loop response time, and calculates the dynamic lead based on the formula, achieving a synchronization effect where "different control start times, the same target arrival time." Simultaneously, a feedforward + incremental PID feedback composite control is employed, and the parameter table is iteratively corrected online based on actual operating data. This invention fundamentally cuts off the positive feedback coupling link between speed and attitude, significantly reducing speed overshoot and attitude fluctuations, and improving flight stability, control precision, and fuel economy.

Provided are a frame unit for a compact rotary-wing aircraft, and a rotary wing using the same. A rotary-wing aircraft 2 comprises a frame unit 10 for the rotary-wing aircraft and an occupant seat 20. The frame unit 10 for the rotary-wing aircraft comprises a reference frame 11, an upper frame 12, and an upper support structure 13 that supports the upper frame 12. The main frame 11 comprises a front member 11F that is positioned at the front of the occupant seat 20, a back member 11B that is positioned at the back of the occupant seat 20, a left member 11L that is positioned at the left side of the occupant seat 20, a right member 11R that is positioned at the right side of the occupant seat 20, and eight rotors 11T that are provided to the front member 11F and the back member 11B. In a plan view along the Z direction, the reference frame 11 and the upper frame 12 overlap with rotational trajectories 11TR of the rotors 11T.

A mop system incorporating an arrangement of sliding pins which can be extended to blocking positions against surfaces of rotatable wings. When the pins are in the extended blocking state, they prevent distal wing portions from rotating downwardly. The pins may be normally biased to an inward withdrawn position such that an applied force is required to establish and maintain the blocking position. Actuating force may be applied by a wedge or other pushing structure to urge the pins outwardly such that removal of the wedge or other pushing structure causes the pins to move inwardly. The wedge or other pushing structure may be normally biased to the engagement position and may be displaced from that engagement position using a suitable transmission arrangement that can be activated by a user from the handle.

Described herein is a drag reduction system for an automotive rear wing assembly. According to some embodiments, the system described herein comprises a first fixed aerodynamic wing, a second rotatable aerodynamic wing, and at least one strut, the at least one strut mounted on the vehicle at its front end, and an actuator enclosed within the at least one strut. At its rear end, the at least one strut is fixedly connected to the first fixed aerodynamic wing and rotatably connected to the second rotatable aerodynamic wing. The actuator is adapted to move the second rotatable aerodynamic wing to a drag-reduced orientation while biasing an energy storage device, and to return the second rotatable aerodynamic wing to an increased drag orientation by releasing stored energy from the energy storage device.

A mobile robot includes a main body portion having a plurality of propulsion units configured to generate propulsion forces by driving rotary wings, and a plurality of support portions provided on the main body portion and configured to come into contact with a predetermined contact surface to be capable of supporting at least a part of the main body portion, wherein when movement control is performed while supporting the main body portion by the plurality of support portions, in assist control for the movement control, a part or all of the plurality of propulsion units are driven to generate an assistive support force in the outside of an actual support region, in a case where a target pressure position related to the transition of a center of gravity of the main body portion in the movement control is not inside the actual support region in which the main body portion is actually supported by predetermined support portions in contact with the predetermined contact surface among the plurality of support portions.

The application discloses a kind of anti-sticking reaming type rotary wing drill tools, it is related to well drilling tool technical field, including rotary wing stabilizer, rotary wing block and center drill bit, rotary wing stabilizer top surface rotating hole, sliding slot and limiting block;Rotary wing block is slidably connected in sliding slot, and elastic member is tightly arranged between rotary wing block and sliding slot;The end face of rotary wing block towards rotating hole is formed support surface, transition surface and limiting surface in sequence;The rotating shaft of center drill bit is rotatably connected with rotating hole, and the top end of rotating shaft is fixedly sleeved with support disc, the side wall of support disc has protruding support claw, the end face of support claw is in contact with limiting surface, and is clamped and limited by transition surface and limiting block.This application uses centrifugal force to force rotary wing block to slide, cooperates with elastic member to form certain buffer, prevents damage caused by rigid cooperation, at the same time, the rotation of support disc forces rotary wing block to completely unfold, and serves as the final support structure, both ensure the stable rotary wing unfolding structure, and effectively prevent the jamming problem in unfolding process.

This application relates to the field of unmanned aerial vehicle (UAV) flight control technology, specifically to an integrated UAV flight control and monitoring system for power transmission tower inspection. The system includes: a flight monitoring module for acquiring wind speed, rotational speed of each rotor, and tilt angle of the UAV's fuselage in its environment; a flight control module for acquiring disturbance values ​​of each rotor and tilt fluctuation of the UAV fuselage within preset time periods; acquiring disturbance factors of each rotor's current position; and adjusting the power of the brushless motors within each rotor; a flight obstacle avoidance module for planning flight paths to avoid obstacles; a tower monitoring module for monitoring damage information of the power transmission tower; and a wireless communication module for transmitting the damage information to a ground station. This application aims to improve the stability of the UAV fuselage during flight by correcting its flight attitude, thereby improving the efficiency and quality of power transmission tower inspection.

The invention relates to a spherical bearing structure (10) that provides active vibration isolation and motion control of rotary wing systems such as rotary wing aircraft and wind turbines.