145 results about "Pneumatics" patented technology

The invention discloses a ramjet numerical simulation method, device and equipment and a storage medium, and relates to the technical field of aerodynamics, and the method comprises the steps: determining a dimensionless temperature corresponding to a gas component of an initial flow field; based on the dimensionless temperature, determining a molecular viscosity collision integral function of the gas component in a polynomial fraction fitting mode; determining the viscosity coefficient of the gas component according to the molecular viscosity collision integral function; and generating a computational grid of the ramjet based on the viscosity coefficient so as to perform numerical simulation operation on the ramjet. Therefore, in the numerical simulation process of the ramjet, the polynomial fraction is adopted to fit the viscosity collision integral function, the calculation time of the gas viscosity coefficient can be effectively shortened, and the calculation precision is kept to meet the use requirement; in addition, the method can adapt to the combustion flow field temperature requirement and the component requirement of the ramjet engine, and the numerical simulation efficiency of the ramjet engine can be improved.

The invention relates to a large-span bridge flutter critical wind speed prediction method based on an L-P perturbation method. The method comprises the following steps that S1, physical characteristics and aerodynamic parameters of a bridge are obtained through a wind tunnel test to serve as basic data; s2, establishing a bridge motion control matrix equation based on modal displacement; s3, deriving an explicit solution of the modal frequency, the damping ratio and the modal characteristic of each modal branch based on an L-P perturbation method; s4, iteratively solving the modal frequency, directly solving the damping ratio, the amplitude ratio and the phase difference on the basis, observing the change of the modal damping ratio xi in each direction along with the wind speed U, and determining the flutter critical wind speed; the problems that an explicit closed solution of an existing three-degree-of-freedom flutter starting condition needs to carry out multiple times of iterative calculation on modal frequency, damping ratio and vibration mode, the influence of structural parameters and pneumatic parameters on pneumatic instability is difficult to clearly explain, and the flutter critical wind speed of a large-span bridge cannot be well predicted are solved.

The invention discloses an unmanned aerial vehicle nest top cover dual-motor control method and device, and relates to the technical field of unmanned aerial vehicles, and the method comprises the steps: setting a system state variable and a control input vector based on nest top cover data, first motor drive data, second motor drive data, coaxial transmission data and top cover angle data; constructing a motor rotor kinetic equation based on corresponding data in combination with a shaft torsion effect; constructing an angle kinetic equation and an electrical kinetic equation of the nest roof based on the corresponding data; constructing a state space model based on a system state variable, a control input vector and the kinetic equation to generate LQR optimal control, integral control and coupling suppression control in combination with a current difference; and determining a comprehensive control model based on gravity feed-forward compensation in combination with LQR optimal control, integral control and coupling suppression control so as to control the double motors. According to the invention, global optimality and control stability are guaranteed, multi-target control is realized, and the control precision of double motors is significantly improved.

A tonneau system for a vehicle including a cargo bed comprises a frame including a leading edge and a trailing edge. A cover is coupled to the frame and movable between a deployed position and a retracted position. A mechanism is coupled to the frame and operable to move the frame and the cover between a home position, an aerodynamic position, and an extended box position. When at the home position, the frame extends substantially parallel to the ground at a first elevation. The leading edge of the frame is positioned at a second elevation higher than the first elevation and the trailing edge remains at the first elevation when the frame is at the aerodynamic position. The leading edge and the trailing edge of the frame are positioned at the second elevation when at the extended box position.

An air-moving device may include an aerodynamic stator. The aerodynamic stator may be positioned forward of a motor of the air-moving device and aftward of an aerodynamic rotor of the air-moving device. A control unit may be integrated in and in thermal communication with the aerodynamic stator. The aerodynamic stator may transfer heat from the control unit to thermally conductive stator vanes of the aerodynamic stator. An airflow generated by the aerodynamic rotor may facilitate heat dissipation from the thermally conductive stator vanes. The aerodynamic stator may include electrically conductive stator vanes. The electrically conductive stator vanes may provide at least one of power or control signaling to the control unit.

Disclosed is an aerodynamic system for an underside of a vehicle, the system comprising: an aerodynamic chassis, the aerodynamic chassis comprising a main compartment bounded by a plurality of walls and a floor extending between the walls; and an aerodynamic device, the aerodynamic device comprising: a mounting structure, the mounting structure being fixedly mounted to the floor of the aerodynamic chassis; and an aerodynamic body, the aerodynamic body comprising a leading edge, a trailing edge and at least two outboard edges, the aerodynamic body being fixable to the floor of the aerodynamic chassis by the mounting structure, the mounting structure being located wholly inboard of the outboard edges of the aerodynamic body.

The utility model discloses an exhaust silencing pipe, which relates to the technical field of pneumatics and comprises a pipe cavity main body, the inner wall of the pipe cavity main body is in threaded connection with a silencer body, and the inner wall of the silencer body is fixedly connected with first breathable cotton used for absorbing exhaust noise energy. The pipe cavity body is filled with second breathable cotton used for reducing exhaust noise. According to the utility model, a section of pipe cavity is additionally arranged on the original silencer, the ventilation cotton is filled in the pipe cavity, and the silencer is arranged at the foremost end of the pipe cavity, so that when compressed air passes through the pipe cavity, the flow rate of the compressed air can be reduced under the action of the ventilation cotton, and the flow rate of the compressed air can be reduced when the compressed air passes through the original silencer. And the exhaust noise can be reduced by 50%.

This invention discloses a dual-motor control method and device for the top cover of an unmanned aerial vehicle (UAV) nest, relating to the field of UAV technology. The method includes: setting system state variables and control input vectors based on nest top cover data, first motor drive data, second motor drive data, coaxial transmission data, and top cover angle data; constructing motor rotor dynamic equations based on the corresponding data and shaft torsional effects; constructing nest top cover angle dynamic equations and electrodynamic equations based on the corresponding data; constructing a state-space model based on the system state variables, control input vector, and the above dynamic equations to generate LQR optimal control, integral control, and coupling suppression control by combining current difference; and determining a comprehensive control model based on gravity feedforward compensation combined with LQR optimal control, integral control, and coupling suppression control for dual-motor control. This invention ensures global optimality and control stability, achieves multi-objective control, and significantly improves the control accuracy of the dual motors.

An airflow modifying element for a wind turbine blade (10) is provided. The wind turbine blade (10) comprises a blade body (20) having a leading edge (16), a suction surface (18) and a pressure surface (19). The airflow modifying element (30) is configured to provide a trailing edge (17) to at least a longitudinal section (15) of the wind turbine blade (10), where the airflow modifying element (30) forms an aerodynamic profile with the blade body (20). The airflow modifying element comprises: a trailing end (37) providing a trailing edge (17) of the aerodynamic profile; a suction surface extension section (38) extending a suction surface (18) of the blade body (20) towards the rear end (37); and a pressure surface extension section (39) extending a pressure surface (19) of the blade body (20) towards the aft end (37).

The invention discloses an airfoil pressure distribution elastic correction method, application, equipment and a storage medium, and relates to the technical field of aerodynamics, the airfoil pressure distribution elastic correction method comprises the following steps: S1, rigid pressure distribution pretreatment; s2, acquiring an elastic correction amount; s3, correcting the total load of pressure distribution; s4, correcting a pressure distribution spanwise pressure center; s5, after the spanwise pressure center is corrected, solving a new chordwise correction amount; and S6, correcting the chordwise pressure center of pressure distribution, performing static aeroelastic correction on CFD pressure distribution data or pressure measurement test data, obtaining pressure distribution data after considering elastic deformation, providing a basis for structural design, and ensuring flight safety.

Mechanical device for shutting down the suction operation of an automatic suction pump, which normally shuts down via hydraulics or pneumatics.

An engine for aeromechanical instability abatement includes a sensor configured to capture data from rotating blades of the engine system, a airflow effector device, and an engine controller. The engine controller is configured to control the airflow effector device according to a nominal schedule, detect, based on a signal from the sensor indicating a vibration amplitude of the rotating blades within a frequency band, an incipient instability condition, in response to the incipient instability condition being present, determine a modified control parameter for at least one of the airflow effector device, and control the airflow effector device according to the modified control parameter, deviating from the nominal schedule.

The invention relates to an electric motor vehicle (1000), the underbody (200) of which comprises a charging tray (300) closed by a hatch (400) facing the ground, and comprising a cleaning device (500) that cleans the underbody charging tray (300) by aerodynamic effect when the vehicle (1000) is in motion. This cleaning device (500) comprises at least one Venturi nozzle (600) arranged in a longitudinal direction (X) in the vicinity of the charging tray (300) and configured to subject its hatch (400) to a flow of pressurized or depressurized fluid for cleaning this hatch (400). Figure 1

A processing system for processing consumables, comprising: a container in which the consumables are arranged, the container comprising an RFID tag with at least one RFID tag storage section for storing consumables status information indicative of a filling-status of the consumables arranged in the container; an RFID reading unit configured to read information from the RFID tag; an RFID writing unit configured to write information on the RFID tag; and a removing unit configured to remove a part of the consumables from the container; wherein the processing system is configured to: read, by means of the RFID reading unit, the consumables status information from the at least one RFID tag storage section, remove, by means of the removing unit, a part of the consumables from the container, determine, based on the consumables status information read by the RFID reading unit, whether a predetermined prohibition condition is met after the removal of the part of the consumables from the container by the removing unit, and in case the prohibition condition is not met, update, by means of the RFID writing unit, the consumables status information on the RFID tag, and in case the prohibition condition is met, irreversibly modify the RFID tag such that the processing system is able to identify from the RFID tag that the prohibition condition is met.

Tire (1) for construction vehicle comprising two working layers (321, 322), comprising metallic reinforcements and at least two shrink-fit layers (331, 332), of axial widths less than those of the working layers (321, 322), and comprising metallic reinforcements, the innermost radial shrink-fit layer (332) being the shrink-fit layer of greatest axial width. At each axial end of the innermost radially enclosing layer (332), two contiguous rubber mixtures (51, 52, 61, 62), or decoupling mixtures, are arranged, one being radially inside the other, the decoupling mixture (51, 61) furthest radially from the end of the enclosing layer (332) has a dynamic modulus of elasticity measured at 23°C and 10% strain and at 10 Hz, at most equal to 0.7 times the dynamic modulus of elasticity of the decoupling mixture (52, 62) closest radially to the end of the innermost radially oriented shrinkage layer (332). Abstract figure: Figure 1.

The invention relates to the technical field of rotating machinery impellers, in particular to a high-efficiency low-power axial flow blade which comprises an irregular curved surface formed by sweeping a plurality of wing-shaped sections along a blade stacking line from a blade hub to the maximum circumferential direction of a blade top; the plurality of airfoil sections comprise a 0% blade height section airfoil section, a 25% blade height section airfoil section, a 50% blade height section airfoil section, a 75% blade height section airfoil section and a 100% blade height section airfoil section; the airfoil profile center line of the 0% blade height section airfoil profile is composed of three sections of control curves, and the airfoil profile center line of the 25% blade height section airfoil profile is composed of a section of control straight line and a section of control curve. The curve control equation of the control curve is a quadratic curve equation, the linear control equation of the control straight line is a linear equation, and the adjacently connected control curve in the three sections of control curves, the section of control straight line and the equation coefficient value of the section of control curve meet the continuity condition. The aerodynamic performance and noise are optimized through the angle distribution design of the axial flow blades.

The utility model provides a kind of positioning control structure of drive joint convenient to control, the utility model relates to industrial machinery technical field, including joint seat and positioning disc, joint seat and positioning disc are the matching pipe base of symmetrical arrangement, joint shaft is inserted between joint seat and positioning disc as drive joint part;The utility model has the beneficial effect that: through the joint structure of external connection butt joint to adapt joint movable end, its structure utilizes the axial brake structure set to carry out joint movable brake to external motor, and there is the core shaft that tooth disc corner displacement is matched in its brake structure, cooperation angle displacement sensor is used to real-time acquisition angle displacement data, to realize the adjustment to joint movable position according to the feedback of angle displacement data when joint movable, and can be combined with the axial locking structure of pneumatics to complete the locking to joint movable angle, realize the real-time positioning control to joint.

A self-contained breathing apparatus (SCBA) is presented that comprises a backframe configured to support a high-pressure air cylinder, a sensor module mounted to the backframe, and a console coupled to the SCBA. The console comprises a pneumatic connection coupled to the high pressure air cylinder, an electronics connection coupled to the sensor module, and a display component. The console is configured to operate in a functional mode and in an equipment check mode. In the equipment check mode, the console is configured to provide equipment check instructions to a user of the SCBA. In the equipment check mode, a sensor signal is received from the sensor module using the electronics connection. A pressure of the high-pressure air cylinder is measured using the pneumatics connection.

The invention relates to a manufacturing method and an electronic system (1) for pneumatics (100) comprising: An electronic board (6) including a printed circuit board (5) on which are fixed: A battery (4); A microcontroller (3); At least one sensor (2) for measuring a physical parameter of the fluid; The electronic board (6) being encapsulated in a cylindrical plastic encapsulation (20) about an axis of revolution (21) normal to the printed circuit board (5). Characterized in that the minimum distance between the external surface (22) of the plastic encapsulation (20) and the electronic board (6) is between 0.5 millimeters and 3 millimeters and in that the plastic encapsulation (20) has an opening (25) on the external surface (22) extending into the material to at least one measuring sensor (2). Fig. 3

The Solar Wind Turbine with Lever Assist via Compounded Mechanical Advantage is an innovation that allows energy-producing turbines to operate in all geographic regions of the world. Designed to reduce greenhouse emissions, the novelty of the proposed apparatus accommodates aerodynamically positioned ducted fans with included velocity-sensing pitot tubes perpendicular to the distal ends of the extension arms. The extension arms are further contributed into mechanical levers which applies additional torque to the central rotating fulcrum. Complementing established turbine models, this technology will produce stronger outputs of green energy while expanding the geographic regions where they can be operated at full capacity. Further, this downward force in combination with extending lever arms creates mechanical advantage for each lever which compounds the total output torque placed on the central rotating fulcrum. When you add more extendable lever arms, it compounds mechanical advantage by means of the law of the lever.

The invention belongs to the pneumatic field, and particularly relates to an execution device with higher positioning accuracy, a pushing mechanism is located outside a piston cavity, the execution device is provided with a first guide part, the pushing mechanism is provided with a first matching part matched with the first guide part, and the first guide part extends in the moving direction of a piston head, namely, the first matching part is matched with the first guide part. The first guiding part is arranged outside the piston cavity, the pushing mechanism is provided with the first matching part matched with the first guiding part, guiding of the pushing mechanism is achieved, and compared with the background technology, the probability that the piston assembly laterally deviates and shakes is reduced, and the positioning accuracy of the execution device is improved.

Road vehicle comprising: four wheels, at least a pair of them being drive wheels; a passenger compartment configured to accommodate at least a driver; a vehicle body comprising a front portion and a rear portion relative to the passenger compartment along a travel direction; a powertrain system; a central aerodynamic channel at least partially arranged under the passenger compartment along a central longitudinal axis of the road vehicle; wherein the central aerodynamic channel seamlessly extends from a first aperture arranged in the area of the front portion to a second aperture arranged in the area of the rear portion of the vehicle body; wherein the powertrain system is at least partially arranged laterally to the central aerodynamic channel.

A flow modifying element for a wind turbine blade is provided. A wind turbine blade (10) comprises a blade body (20) having a leading edge (16), a suction surface (18) and a pressure surface (19). The flow modifying element (30) is configured to provide a trailing edge (17) for at least a longitudinal section (15) of the wind turbine blade (10). The flow modifying element (30) and the blade body (20) form an aerodynamic profile. The flow modifying element (30) comprises: a suction side (32); a pressure side (33); a trailing end (37) providing a trailing edge (17) of the aerodynamic profile; and a pressure surface extension section (39) on the pressure side (33), the pressure surface extension section (39) configured to extend the pressure surface (19) of the blade body (20) towards the aft end (37). A pressure side contour section (40) of the flow modifying element has the shape of a concave curve and forms a recessed portion (44).

The present disclosure relates generally to systems, medical devices, and methods for closing an opening in a target tissue using hydraulics and / or pneumatics. In some embodiments, a medical device may include an endoscopic device operable to close an opening in a target tissue, and an actuator operable with the endoscopic device, wherein the actuator includes a piston within a chamber. The piston may include a piston head engaged with an interior surface of the chamber, and a piston rod coupled to a tissue engagement component of the endoscopic device, wherein pressure from a fluid within the chamber actuates the tissue engagement component.

The utility model provides a multistage axial flow electric aircraft engine. A power output unit comprises an axial magnetic flux motor, a water channel and a wing-shaped water tank. The aerodynamic suite comprises a fairing, paddles and blades; the axial magnetic flux motor and the aerodynamic suite are fixed through a cabin to form a complete all-electric aero-engine assembly; the axial magnetic flux motor is arranged in the cabin, a fairing is arranged outside the cabin, and a water channel of the axial magnetic flux motor extends out of the cabin and the fairing through a heat dissipation pipeline and is communicated with a wing-shaped water tank mounted on a wing to form a heat dissipation system; the blades are installed at the output end of the axial magnetic flux motor, and rotation of the blades is achieved. According to the utility model, a special geometric structure cabin is adopted, and a power pneumatic mode of axial flow internal circulation is realized by combining a multi-stage rotor, a multi-stage stator and a multi-stage blade; the pneumatic mode of an existing single-blade electric engine is replaced, the multi-stage blade has more redundancy than a single blade, and the axial flow type pneumatic layout improves the gas circulation efficiency.

The application discloses a kind of based on soft driver's lung profile one-way deformation control structure of soft robot of simulation lung, the circumferential of central fixed seat is evenly distributed with pneu-net soft driver connected by connector;Between each connector and central fixed seat, one bellows driver is fixedly connected;Trachea is communicated with pneu-net soft driver and bellows driver;Control structure is shown by the radial telescopic characteristics of the radial deformation of lung and the boundary curvature of lung quality of lung by the bending characteristics of the lung of the bellows driver and the pneu-net soft driver respectively by applying air pressure to bellows driver.It is effectively simulated by the driving mode of the above control structure pneumatics when the profile of lung one-way deformation, by multiple different structure parameters this kind of soft driver constitutes complete soft robot of simulation lung, on the basis of being able to accurately control model deformation, be applied to the deformation prediction of lung deformation and accurately predict lung tumor movement space.

Joining tool (100) comprising a hold-down (110) configured for holding and positioning fasteners, a process stroke (120) configured for screwing fasteners into two materials to be joined, and a distance cylinder (130) configured for providing and controlling a distance between the hold-down (110) and the process stroke (120), wherein the distance cylinder (130) is free of pneumatics.

The application relates to the technical field of boiler economizers, in particular to a through-wall pipe anti-abrasion device which comprises a protective plate and a filling layer; a plurality of protective plates are arranged to form a protective groove, the protective groove is used for covering the through-wall pipe outside, and the filling layer is arranged in the protective groove to fill the gap between the protective groove and the through-wall pipe; the anti-abrasion device is characterized in that the anti-skid groove is formed by the arrangement of the protective plate outside the through-wall pipe, and the filling layer is encapsulated, so that the through-wall pipe is protected, the problem that the through-wall pipe is easily subjected to the coupling damage of sulfuric acid dew point corrosion and ash particle impact abrasion under the complex flue gas dynamics environment between boilers in the prior art is solved, and the long-term operation of the equipment is ensured.

The invention belongs to the technical field of automobiles, and relates to an aerodynamic rim blade assembly and a using method thereof. The air pipeline is communicated with the compressed air supply unit; the blade movement mechanism is arranged on the rim blade and comprises an air cylinder and a blade which is in transmission connection with a piston rod of the air cylinder; wherein the air pipeline extends to the wheel end and is communicated with a working cavity of the air cylinder, an electromagnetic valve controlled by an electronic control unit of the whole vehicle is arranged on the air pipeline, and compressed air can be selectively guided into or discharged out of the working cavity of the air cylinder by controlling opening and closing of the electromagnetic valve. The driving device is used for driving the blades to move between the opening position and the closing position. A mature compressed air supply unit of the whole vehicle is directly shared, the development and manufacturing cost of the system is greatly reduced, meanwhile, the layout of the whole vehicle is simplified, and popularization and application of the assembly are more economic and feasible.

The invention relates to the technical field of laser cutting, and particularly discloses a laser cutting device with an efficient positioning function. According to the laser cutting device with the efficient positioning function, the purposes of facilitating observation and correcting deviation are achieved, the main frame and the bottom plate support integrally support equipment, the positioning device fixes and positions a plate, limiting is conducted through corresponding assemblies, and therefore positioning cutting of the plate is facilitated, and the working efficiency is improved. And meanwhile, the cutting device is driven by the electric sliding table to move so as to cut the plate, the cutting position is positioned through light rays, so that positioning of the cutting position is facilitated, heat dissipation is conducted through the corresponding pneumatic device, and smoke dust generated during cutting is dispelled. Therefore, the specific condition of the cutting position can be observed during cutting, deviation correction is facilitated, heat dissipation is conducted on the laser head in a pneumatic mode, the laser head is driven to rotate, and therefore the machining precision is improved.