187 results about "Pneumatics" patented technology

The invention relates to an all-dimensional automatic spraying production line, which is characterized in that a spray head assembly can perform multi-degree-of-freedom movement in different planes through rotation driving of a cross beam around a central fixed shaft and combination of a vertical and horizontal state switching function of a swinging cross rod; through the swing hinging design of the spray head assembly and the transmission assembly of the sliding rod, the angle of the spray head can be dynamically adjusted in the spraying process, a composite motion trail is formed, dead-corner-free covering on the surface of the workpiece is achieved, and the spraying uniformity is remarkably improved; due to the linkage design of the sliding rod and the transmission assembly, when the cross beam rotates, the reciprocating driving assembly can synchronously drive the sliding rod to slide along the swing cross rod, and the spray head assembly is forced to swing back and forth through the transmission assembly; due to the dynamic adjusting mechanism, the nozzle can simulate manual spraying, and the spraying effect is further improved; in addition, due to the design of mechanical linkage, response delay caused by traditional motor or pneumatic independent control can be reduced, and it is ensured that actions of all the nozzles are highly synchronous.

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 a bilateral support balance structure for measuring intake and exhaust influence, and belongs to the field of aerodynamics. The device comprises an aircraft fuselage shell, an air inlet channel upper cover, a double-support balance, a corrugated pipe and a fixed support, the double-support balance comprises a front shell matching section, a front air inlet channel, an air inlet channel lower cover, support balances and a rear shell matching section, the aircraft fuselage shell is connected with the double-support balance through the shell matching section, the air inlet channel lower cover is connected with the front shell matching section, and the two sides of the front shell matching section and the two sides of the rear shell matching section are connected through the support balances. The air inlet channel lower cover is provided with an air inlet channel upper cover, the air inlet channel upper cover and the air inlet channel lower cover jointly form a middle air inlet channel, the rear shell matching section is provided with a fixed support, and the rear air inlet channel of the rear shell matching section is communicated with the air inlet passage through a corrugated pipe. The problems that a complete air inlet channel is formed in the middle of an aircraft wing body, the internal space is narrow, a balance cannot be installed, and the six-component load measurement requirement cannot be met 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.

The invention provides a train transverse offset calculation method and system based on aerodynamic simulation, and the method comprises the steps: building an aerodynamic model, and obtaining aerodynamic data of the intersection of elevated crosswind and tunnels under different working conditions; the pneumatic data comprises wind pressure data and equivalent acting force and acting moment data acting on the train mass center in the X direction, the Y direction and the Z direction; and importing the pneumatic data into a multi-rigid-body dynamic model of the motor train unit to carry out pneumatic response analysis so as to obtain the maximum transverse offset of the train under each working condition. According to the method, linear superposition is conducted on the static part and the dynamic part, the final transverse offset of the train under different working conditions is obtained, and the method for calculating the transverse offset of the train is more accurate and reliable so that the safety of the train in complex environments such as elevated crosswind and tunnel intersection can be guaranteed.

A nacelle for an aircraft propulsion unit includes an air intake cowl, and an intermediate section including fixed and removable hoods defining an access space between front ends of the hoods and an outer rear end of the air intake cowl. The intermediate section includes an annular row of mutually spaced connecting parts which rigidly connect the outer rear end of the air intake cowl to the front ends of the hoods so as to transmit longitudinal forces, and an intermediate cowl extending between the air intake cowl and the hoods, around the connecting parts, thereby closing the access space and creating aerodynamic continuity with the air intake cowl and the hoods. The intermediate cowl is formed from at least one strip which is held in place by tangential clamping of the circumferential ends of the strip.

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 relates to the technical field of smoke exhaust equipment, in particular to a check valve and a flue system, which comprise a valve body and a check structure, the valve body is provided with a flue, and the flue is provided with a flue gas inlet and a flue gas outlet; the non-return structure comprises a valve plate, and the valve plate is located at the flue inner cavity or the smoke outlet or the smoke inlet. The valve plate is rotationally connected with the position close to the upper portion of the flue so as to open or close the flue. The surface of the side, deviating from the smoke inlet, of the valve block is provided with a wing-shaped imitating face and a main body face, and the wing-shaped imitating face is closer to the rotating joint of the valve block relative to the main body face. When the valve plate rotates to open the flue, a first gap and a second gap can be formed between the valve plate and the flue, and the second gap is larger than the first gap. By means of the airfoil-imitated surface on the valve plate, the aerodynamics principle can be utilized, the valve plate is easier to turn over, the turning amplitude is larger, and the turning effect is more stable, so that the smoke exhaust resistance is reduced, the space occupied by the valve plate in a flue is better released, the exhaust air rate is increased, and the smoke exhaust efficiency is improved.

A motionless pumping design that reduces operation and maintenance costs, and enhances reliability in three aspects of pneumatics system configuration. A motionless and corrosion-resistant pump which uses the continuous generation of pressure variation push / pull force by relying on the venturi effect induced by a pair of gas ejectors together with an argon pneumatic sub-system.

The utility model discloses a gas supply system and a gas simulation generation device, the gas supply system comprises a front-end gas supply pipeline and at least two rear-end gas supply pipelines arranged in parallel, and the front-end gas supply pipeline is communicated with the rear-end gas supply pipelines; the front-end air supply pipeline comprises a filter, a three-way ball valve and a one-way valve I which are sequentially communicated through a pipeline; the rear-end air supply pipeline comprises a needle valve, a pressure reducing valve, an electromagnetic valve I and a one-way valve II which are sequentially communicated through a pipeline; the gas simulation generation device comprises a case and a gas supply system. The gas supply device is convenient to operate, can output gas sources with different pressures, can meet the gas supply requirements of various gas supply environments, can simulate explosive gas generated by various gas generators, and can complete a gas dynamics test on the influence of the gas generators on other equipment.

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.

The utility model relates to the technical field of pneumatics, in particular to a stable pneumatic supporting cylinder which comprises a cylinder body, a rear cover is arranged at one end of the cylinder body, an upper cover is arranged at the other end of the cylinder body, a movable bottom piston is arranged on the inner wall of the rear cover, and the bottom piston is connected with the inner side of the rear cover through a first spring. One end of the supporting rod is connected with the rear cover, and the other end penetrates through the upper cover and is fixedly connected with the contact screw; and a connecting sleeve and the like are arranged in the supporting rod. The clamping sleeve, the lock sleeve, the clasping piston and other structures which are specially designed are adopted, the stability of the supporting cylinder is effectively improved, the structures can ensure that a workpiece can keep a stable position and posture in the supporting process, and therefore the machining precision and the workpiece quality are improved; the supporting force of the supporting cylinder can be easily adjusted by controlling the gas flow of the gas inlet and the gas outlet, the adjustability enables the supporting cylinder to adapt to different workpieces and machining requirements, and the flexibility and the applicability of the supporting cylinder are improved.

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.

A microfluidic device comprises a pneumatic interface for connecting the device to an analysis device and a fluidic channel system with a plurality of fluidic microchannels for transporting a fluid. The fluidic channel system comprises a plurality of microfluidic elements connected via the fluidic microchannels. The fluidic microchannels have first fluidics sections aligned along a first direction and second fluidics sections aligned along a second direction. The device comprises a pneumatic channel system with a plurality of pneumatic microchannels for controlling the microfluidic elements, wherein the pneumatic microchannels have first pneumatics sections aligned along the first direction and second pneumatics sections aligned along the second direction. An entire length of the first fluidics sections is greater than an entire length of the second fluidics sections and an entire length of the first pneumatics sections is smaller than an entire length of the second pneumatics sections.

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 present disclosure relates to diagnosing and locating fluid leakage within a pneumatic system (5) using a minimal amount of pressure sensors (55, 75, 89). In general, each branch (51, 71, 85) of a pneumatic system (5) includes an associated pressure sensor (55, 75, 89) and in accordance with how the pneumatic components (57, 59, 61, 77, 91, 93, 95) associated with the pneumatic branch (51, 71, 85) are toggled and monitored, leaks can be detected and located within the branch (51, 71, 85) using a minimal amount of pressure sensors (55, 75, 89). More specifically, pressure and pressure decay may be measured by the sensors (55, 75, 89) within a branch (51, 71, 85) while the pneumatic components (57, 59, 61, 77, 91, 93, 95) are in a particular configuration. The configuration is thereafter changed, and pressure and pressure decay are again measured by the sensors (55, 75, 89). The results of these two measurements may enable the pneumatic system (5) to derive the presence and location of a leak.