21results about How to "Improve aerodynamic efficiency" patented technology

This invention provides an active flow control method and system based on intelligent algorithms. The method includes: determining the number of inlet parameter sets for a typical flight state point, constrained by simulation economy and sampling efficiency; performing numerical simulations according to the number of inlet parameter sets to obtain dataset 1, with inlet parameters as independent variables and flow field characteristics as dependent variables; obtaining dataset 2, with flight state as independent variables and flow field characteristics as dependent variables, through numerical simulation for a certain set of inlet parameters; constructing a proxy model of inlet flow field characteristics for a typical flight state point using deep learning based on dataset 1; constructing a proxy model of inlet flow field characteristics for a wide-speed-domain flight state based on the proxy model of inlet flow field characteristics for the flight state point, using a transfer learning algorithm and dataset 2; constructing an environment-agent interaction model based on a deep reinforcement learning algorithm, using the proxy model of inlet flow field characteristics for a wide-speed-domain flight state as the environment model for deep reinforcement learning; setting optimization termination conditions based on the environment-agent interaction model, and obtaining a control sequence with continuously optimal inlet performance under different flight states through deep reinforcement learning. This invention can stably adapt to flight scenarios with a wide speed range and a large airspace, and achieve real-time optimal control of the air intake flow field under a wide speed range, solving the problem of poor generalization ability of traditional methods under different operating conditions.

The application discloses a longitudinally foldable water-air dual-purpose propeller, and belongs to the technical field of cross-medium aircraft propulsion, comprising a new-configuration hub, a longitudinal folding mechanism, a limiting structure and a down-bending propeller blade with a preset down-bending angle; the configuration of the propeller enables the down-bending propeller blade to be completely unfolded to form a first working configuration through centrifugal force in air, and the down-bending propeller blade to be passively folded and limited to form a second working configuration through hydrodynamic lift in water; the longitudinally foldable water-air dual-purpose propeller can automatically complete mode switching according to the difference between working media without any active control mechanism, and can maintain high efficient propulsion performance in both media.

The invention belongs to the field of aviation, and discloses a rotor aerodynamic configuration of a light tilting rotorcraft. The light tilting rotorcraft rotor comprises the steps of overall parameter selection, airfoil profile selection, blade torsion angle distribution, blade chord length distribution, blade pneumatic analysis and the like. The designed light tilting rotorcraft rotor has high aerodynamic efficiency, can meet the aerodynamic requirements of different flight states, can meet the task requirements in the vertical take-off and landing stage, the hovering stage and the forward flight stage, meets the performance requirements of the light tilting rotorcraft, and has high practical value.

This invention discloses a plant protection drone for precision seeding, belonging to the field of agricultural drone technology. It includes a central body and four arc-shaped arms that can move relative to the central body. Each arm is equipped with a power unit and rotors. Driven by a deformation drive mechanism, the arms can switch between a cruising state (forming a circular shape) and an operational state (arching inward to form a three-dimensional structure). In the cruising state, the rotor planes are coplanar, resulting in high aerodynamic efficiency; in the operational state, the rotor planes are raised and moved away from the seeding device, effectively isolating the downwash airflow from interfering with the seeded material, significantly improving seeding accuracy and uniformity. This invention solves the technical problem of seeding drift caused by rotor wind fields in existing plant protection drones.

The utility model discloses an MIM (metal injection molding) turbocharging blade, which relates to the technical field of turbocharging blades and comprises a connecting seat, a group of blades are fixedly connected to the annular side surface of the connecting seat, two reinforcing ribs are fixedly connected between the group of blades, a group of grooves for turbulent flow are formed in the surface of each reinforcing rib, and a fixing rod is fixedly connected to the lower surface of the connecting seat. A connecting shaft is arranged on the lower surface of the fixing rod, the annular side face of the fixing rod is sleeved with a threaded ring in a threaded mode, the grooves in the surfaces of the blades can disturb airflow, the airflow forms a specific flow state on the surfaces of the blades, and the change of the flow state can increase the turbulence degree of the airflow and promote mixing of boundary layers. When the airflow flows through the blades, the airflow can flow in a mode of being attached to the surfaces of the blades, separation of the airflow on the surfaces of the blades and generation of vortexes are reduced, air resistance is reduced, the aerodynamic efficiency of the blades is improved, and then the turbocharging effect is enhanced.

This utility model discloses a blade, a propeller, and an aircraft, belonging to the field of aircraft technology. The blade includes a connected root and a shaft. The root has a root centerline, and the distance from the end of the blade furthest from the root to the root centerline is a first length. At the first position of the blade, the angle of attack is 18.38°±2.5°; at the second position, the angle of attack is 9.58°±2.5°; and at the third position, the angle of attack is 6.61°±2.5°. The distance from the first position of the blade to the root centerline is 20% to 25% of the first length; the distance from the second position of the blade to the root centerline is 50% to 58% of the first length; and the distance from the third position of the blade to the root centerline is 80% to 95% of the first length. The blade of this utility model, through the design of the angle of attack at multiple key positions of the main body of the propeller shaft, reduces air resistance and improves aerodynamic efficiency. The propeller and aircraft of this invention improve the aerodynamic efficiency of the propeller and the flight efficiency of the aircraft.

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.

The utility model belongs to the technical field of shape design and control of aircrafts, and relates to an electric tilt-rotor aircraft. Comprising a fuselage, two wings located on the two sides of the fuselage, an empennage, a plurality of supporting rods arranged below the wings and rotors arranged at the two ends of the supporting rods. The rotor wings comprise a plurality of tilting rotor wings and a plurality of fixed rotor wings; the number of the supporting rods is even, and the supporting rods are divided into two sets with the same number and are symmetrically arranged on the two sides of the machine body. A tilting rotor wing is arranged at the front end of each supporting rod; a fixed rotor wing is arranged at the rear end of each supporting rod; the tilting rotor wings are connected with the front ends of the supporting rods through tilting mechanisms, and the tilting mechanisms are used for adjusting the orientation of the tilting rotor wings. The electric tilting rotor aircraft provided by the utility model can realize the functions of vertical take-off and landing, tilting transition and cruise flight.

This utility model provides a sealing cylinder assembly and a blow molding equipment, relating to the field of blow molding equipment technology. The sealing cylinder assembly includes a sealing cylinder and a high-pressure valve group. The sealing cylinder includes a first end face and a receiving groove disposed on the first end face. The high-pressure valve group includes multiple valve cores and a valve cover structure. The valve cover structure includes at least one valve cover that is sealed to the sealing cylinder and covers the receiving groove. The valve cover can divide the receiving groove into at least one valve cavity, and each valve core is disposed in one valve cavity. This utility model can embed the valve cores of the high-pressure valve group into the valve cavities, making the shell of the sealing cylinder part of the shell of the high-pressure valve group, eliminating the need for an additional valve shell. Compared with the prior art, which manufactures and assembles the high-pressure valve group and the sealing cylinder separately, this reduces the number of parts and assembly complexity, lowers manufacturing and assembly costs, improves aesthetics, and helps to shorten the gas flow channel length and reduce gas loss.

The utility model discloses a multifunctional screw conveying device capable of conveying gas in two directions, which comprises a cylinder body, a first main shaft and a second main shaft are arranged in the cylinder body side by side, a symmetrical molded line male screw is mounted on the first main shaft, a symmetrical molded line female screw is mounted on the second main shaft, and the first main shaft and the second main shaft are arranged in parallel. The symmetrical molded line male screw and the symmetrical molded line female screw are meshed with each other in a sealed mode, a first gas transmission port and a second gas transmission port which can be commonly used with each other are formed in the two ends of the cylinder body respectively, any one of the first gas transmission port and the second gas transmission port serves as a gas suction port, and the other one serves as a gas exhaust port. A synchronous linkage structure is arranged between the first main shaft and the second main shaft, one end of one of the first main shaft and the second main shaft is connected with a main shaft of a motor, and the motor is provided with a matched frequency converter. The one-way gas conveying device can solve various problems caused by the fact that an existing one-way gas conveying device needs to achieve two-way gas conveying.

The application discloses a kind of wing-body fusion layout unmanned aerial vehicle's aerodynamic shape, it is related to low-altitude economic unmanned aerial vehicle high lift-drag ratio flight technical field, including wing-body part, the rear end of the upper surface of wing-body part is equipped with V-tail, engine is installed between the opposite surface of V-tail, the wing-body part with the V-tail is equipped with control surface part on;The lower surface of wing-body part is equipped with landing gear;The wing-body part includes inner wing and outer wing, the inner wing with the outer wing is symmetrically arranged, the edge of outer wing is equipped with wing tip;The leading edge sweep angle of wing-body part is 20 °, the trailing edge sweep angle of wing-body part is 17 °.The application discloses a kind of wing-body fusion layout unmanned aerial vehicle's aerodynamic shape, has better aerodynamic performance, stronger carrying capacity and lower noise;Appearance is simple, and cruise efficiency is high, suitable for engineering practical application.

This invention discloses an engine intake mechanism, an engine system, and a vehicle, belonging to the field of engine technology. The engine intake mechanism of this invention makes the inner wall of the airflow guide passage smoother; in other words, there are no geometric abrupt changes in the inner wall of the airflow guide passage. This reduces flow losses in the airflow guide passage, resulting in smaller variations in airflow velocity. Consequently, the airflow pressure and velocity at the turbocharger inlet are more uniform, improving aerodynamic efficiency and thus increasing boost efficiency. The engine system and vehicle of this invention, by applying the aforementioned engine intake mechanism, can improve the engine system's power performance and fuel economy, and enhance the driving experience.

This invention provides a centrifugal compressor and its impeller, wherein the impeller includes a plurality of blades arranged circumferentially, with a flow channel formed between each pair of adjacent blades; each blade is backward-curved, gradually bending away from the impeller's rotation direction from its inlet end to its outlet end; and in the direction from the inlet end to the outlet end, the thickness of each blade first gradually increases and then gradually decreases. The impeller of this invention has higher aerodynamic efficiency, which is beneficial for miniaturizing the centrifugal compressor.

This utility model discloses a handlebar with a rest handle, fixed to the upper part of the bicycle head tube for the rider to grip and steer. It includes a stem and handlebars connected to each other. The handlebars have two ends, each connected to a resting part for the elbow. The end of the resting part away from the handlebars is connected to a drop handle for the rider to grip from below. This invention improves aerodynamic efficiency and riding comfort by sequentially connecting and integrally molding the stem, handlebars, rest handle, and drop handle.

The invention relates to the technical field of centrifugal fans, in particular to a multi-wing centrifugal fan which comprises a volute and an impeller. The volute is provided with an air outlet and two air inlets; the impeller comprises a hub disc, a hub, two reinforcing rings and two sets of blade assemblies, the hub is fixedly connected to the center of the hub disc, the two sets of blade assemblies are arranged on the two opposite side faces of the hub disc in a staggered mode, and each set of blade assembly is fixedly connected with the inner ring of one reinforcing ring; each blade assembly comprises a plurality of blades, and the blades of the two blade assemblies are the same in structure. The impeller is installed in the volute according to the preset size proportion and structure parameters. The structural design of the impeller and the volute is optimized, key size parameters are accurately matched, the positioning relation of all parts is defined, the aerodynamic performance, operation stability and assembly consistency of the fan are improved, and operation noise and abrasion are reduced.

This invention discloses a short takeoff / vertical landing (STOVL) aircraft with a hybrid propulsion system. It employs a fuselage frame as the main load-bearing structure, combined with an aerodynamic layout of all-moving canards, main wings, mid-section wings, and twin vertical tails. The hybrid propulsion system comprises four sets of cross-rotating motor-propellers and thrust-direction-adjustable STOVL level flight engines. The engines operate throughout the entire flight, while the motor-propellers are only engaged during STOVL and mode switching. Through linear adjustment of motor power, coordinated changes in engine thrust direction and magnitude, and speed-dependent aerodynamic lift of the wings, seamless and smooth transitions are achieved between STOVL / hovering, mode switching, high-speed level flight, and payload modes. Compared to existing technologies, this design reduces structural dead weight and control complexity, extends endurance, and balances STOVL flexibility with high-speed cruise efficiency.

The invention discloses a coaxial main rotor-double vector slave rotor heterogeneous multi-rotor layout, and relates to the technical field of unmanned aerial vehicle aircraft design, the layout comprises a coaxial main rotor system arranged in the middle of a fuselage and used for providing main lift force; the two vector slave rotor systems are symmetrically arranged on the two sides of the fuselage and used for providing control torque; an upper rotor wing and a lower rotor wing in the coaxial main rotor wing system rotate in opposite directions so as to counteract the reverse torsional moment; the vector slave rotor system has a tilting function and can change the pulling force direction of the vector slave rotor system; the flight control of the unmanned aerial vehicle is realized by coordinating and adjusting the rotating speeds and vectors of all the rotors from the tilting angle of the rotor system. Through the function decoupling design, unification of high aerodynamic efficiency and strong control capability is achieved.

This invention belongs to the field of rotor airfoil design and discloses a rotor airfoil design method and system based on an improved Bayesian optimization algorithm. The method includes constructing a surrogate model using initial airfoil parameters and corresponding performance indices; iteratively selecting new candidate points and updating the surrogate model through a data acquisition function until the maximum number of iterations is reached; calculating the global expected regret based on the currently observed dataset; if the global expected regret is greater than a threshold, resampling the candidate evaluation point set, using the current optimal surrogate model, resetting the iteration count to zero, and returning to iteratively selecting new candidate points and updating the surrogate model through the data acquisition function; if the global expected regret is less than or equal to the threshold, outputting the optimal airfoil parameters or Pareto optimal airfoil parameters based on the currently observed dataset. This invention significantly improves the utilization efficiency of computational resources while ensuring high-quality solutions.

The utility model relates to fan impeller technical field, concretely is a kind of high-strength aluminum alloy impeller structure for high pressure fan, including the base disc and front cover assembly made of high-strength aluminum alloy, leaf blade assembly is arranged between the base disc with the front cover assembly, annular reinforcing assembly is provided at the back of base disc, connecting piece is fixed in the center of annular reinforcing assembly, the inside of base disc is equipped with multiple annular distribution counterweight, the utility model is designed and cooperates with counterweight etc. structure of base disc, front cover assembly, leaf blade assembly, annular reinforcing assembly, connecting piece, multiple technical promotion is realized, high-strength aluminum alloy is used as main material, while having good strength basis in the guarantee light weight.

The special-shaped curve air duct structure comprises an inlet contraction section, a throat steady flow section and an outlet diffusion section which are used for the axial flow fan, the inlet contraction section and the outlet diffusion section are in continuous smooth curve transition, and the diameter of the throat steady flow section is smaller than that of the inlet contraction section and that of the outlet diffusion section. A venturi tube imitating structure is formed; a gap between the inner wall of the air duct and the impeller is in nonlinear change in the axial direction, and the gap at the throat part is minimum; the special-shaped curve air duct structure for the axial flow fan is simple and reasonable in structure and ingenious in design, the contour curve of the air duct is optimized through the Venturi effect, the gap self-adaptive design and the modular manufacturing process are combined, the machining cost is reduced while the aerodynamic efficiency is improved, and experiments show that the special-shaped curve air duct structure for the axial flow fan is suitable for large-scale popularization and application. According to the design, the fan efficiency can be improved by more than 20%, the noise is reduced by 7dB (A), and the fan is suitable for the fields of industrial ventilation, air conditioning systems and the like.

This invention belongs to the field of numerical simulation and analysis technology for unmanned aerial vehicles (UAVs), and relates to an optimization design method for a deformable wing with a variable camber range and rigid-flexible coupling. The method includes the following steps: obtaining the operating conditions of the aircraft to determine the airfoil and basic parameters of the wing; establishing a three-dimensional aerodynamic model of the wing; performing aerodynamic simulations of the aircraft under takeoff and cruise conditions with varying angles of attack; determining the optimal camber value and corresponding aerodynamic loads of the wing under multiple operating conditions; adjusting the position of the rotating joint of the deformable wing rib to obtain a first-optimized deformable wing rib; dividing the optimization range of the first-optimized deformable wing rib into a fixed region and an optimizable region; applying aerodynamic loads at the optimal camber value to the optimizable region and performing aerodynamic simulations to obtain a second-optimized deformable wing rib and structural optimization; making deformable wing rib samples and conducting performance tests; adjusting the optimizable region until the wing performance meets the preset requirements. This invention can improve the aerodynamic efficiency of the entire flight envelope.