191 results about "Aerodynamic drag" patented technology

The invention discloses a wind turbine fairing optimization design method, which relates to the technical field of fluid machinery and engineering, and comprises the following steps: a basic parameter acquisition and working condition defining step: collecting wind turbine model parameters, and measuring the wind condition of an operation area; the flow guide cover is divided into a windward section, a middle section and a wake flow section; a multi-objective optimization system construction step: determining aerodynamic resistance, structural strength, weight and wake flow influence optimization objectives; an optimization algorithm iteration solving step, wherein an improved non-dominated sorting genetic algorithm is adopted; a simulation verification and parameter correction step: selecting a scheme to perform CFD and finite element simulation; and a physical prototype manufacturing and performance testing step: manufacturing a prototype, and carrying out wind tunnel and field testing. The design efficiency of the air guide sleeve is improved, systematicness is optimized, pneumatic, structure and weight multi-target balance is achieved, cross-model universality is improved, and the problems that traditional design is dependent on experience and unbalanced in performance are solved.

The invention relates to a wheel device, a vehicle having the wheel device and a method of controlling the wheel device. The wheel device comprises a wheel body, a cover element and a transmission assembly. The wheel body is provided with a plurality of spokes which are arranged at intervals at a preset angle, and a through opening through which air can pass is formed between every two adjacent spokes; the cover element can cover the side face of the wheel body in a rotating mode relative to the wheel body around the rotating axis of the wheel body and is provided with at least one hole opening area. A transmission assembly is disposed between the wheel body and the shroud element and is configured to rotate the shroud element relative to the wheel body about a rotational axis of the wheel body when a rotational speed of the wheel body is greater than a predetermined threshold, therefore, the through opening of the wheel body is converted from an open state in which the through opening overlaps with the orifice area to a blocked state in which the through opening does not overlap with the orifice area. The invention has the advantages of reducing air resistance, increasing endurance mileage or fuel efficiency, and improving cooling performance, braking performance and appearance design.

Embodiments of the invention are directed to systems and methods for reducing drag on an aircraft. The aircraft can include at least one propulsion system with rotor blades configured to reduce aerodynamic drag when the propulsion system is deactivated. To reduce the amount of drag, the rotor blades can be locked into an aerodynamic position, and prevented from passively spinning. Additionally, the rotor blades can be configured to have angular positions that reduce drag. For example, the rotor blades as a group may be configured to generally point toward and / or away from an airflow current.

The invention relates to the technical field of road load testing, in particular to an automobile road load testing method and system. The method comprises the steps that a wind tunnel test environment is arranged, in the wind tunnel test environment, wheels of a to-be-tested vehicle are arranged on a wheel driving unit, a vehicle body is connected with a six-component force measuring balance through a vehicle skirt restraint system, and the vehicle skirt restraint system adopts a floating mode; airflow is controlled to blow through the surface of the vehicle, the central belt simulates ground motion, and the central belt and the wheel driving unit are synchronous with wind speed; the to-be-tested vehicle moves at each reference vehicle speed; after each reference vehicle speed is stable, determining the aerodynamic resistance of the to-be-measured vehicle at each reference vehicle speed based on a balance force transducer; meanwhile, based on the wheel driving unit, the rolling resistance of the wheel is determined; and determining the road load of the to-be-tested vehicle according to the rolling resistance and the aerodynamic resistance. According to the invention, the road load can be obtained more accurately, efficiently and quickly.

The invention belongs to the technical field of high-speed train aerodynamic optimization, and particularly relates to a train pneumatic drag reduction and wake flow regulation and control device and method based on bionic shark fins. The device comprises a base, the base is arranged on the lower surface of the vehicle body fairing through a plurality of bolts, a fin plate is arranged on the base, and a fixing block is arranged at the bottom of the fin plate; the base is provided with a plurality of limiting and locking mechanisms, the fin plate is limited through the limiting and locking mechanisms, the limiting and locking mechanisms are provided with driving mechanisms, the driving mechanisms are connected with rotating shafts, and the rotating shafts are connected with the fixing blocks and used for driving the fin plate to rotate; a lateral reinforcing plate is arranged on the outer side of the base, a pneumatic compensation plate is arranged between the lateral reinforcing plate and the fin plate, and the pneumatic compensation plate is fixedly connected with the base plate. By dynamically adjusting the attack angle and clearance compensation of an additional device on the surface of the vehicle body, aerodynamic resistance is reduced, wake flow stability is improved, and self-adaptive optimization under complex working conditions is achieved.

The invention relates to the technical field of wired power flight transportation equipment, in particular to a wired power low-altitude aircraft which comprises an aircraft body, a cargo carrying box used for transporting cargoes is arranged at the bottom of the aircraft body, and a power cable is arranged on one side of the aircraft body; the lifting force counteracting device comprises a descending deflection assembly arranged on one side of the aircraft body, a first magnet is arranged on the descending deflection assembly, a matching assembly is arranged on one side of the descending deflection assembly, a second magnet is arranged on the matching assembly, and the first magnet and the second magnet are located at the same horizontal height and are in the state that like poles repel each other. A horizontal force counteracting device is arranged on one side of the lifting force counteracting device. According to the device, when the wired electric aircraft ascends or flies in the horizontal direction, air resistance borne by a power cable in the moving process of the aircraft is effectively counteracted, so that the pulling force applied to the aircraft by the power cable is reduced, and the effect that the aircraft flies stably is ensured.

The invention relates to the technical field of digital twinning, and particularly discloses a cab wind resistance contour optimization method based on digital twinning, which comprises the following steps: S1, establishing a three-dimensional model of a cab, and calculating front wind resistance according to an included angle between planes; s2, marking a standard plane in the initial model, obtaining the air velocity of the standard plane, calculating the air pressure of the standard plane, and calculating the rising force based on the air pressure; s3, marking an influence surface in the initial model, obtaining the air velocity of the influence surface, calculating the air pressure of the influence surface, and calculating the downforce based on the air pressure; and S4, calculating the friction force and the wind resistance coefficient of the initial model, and selecting an optimal model based on the wind resistance coefficient. According to the method, the effect of the optimized cab wind resistance contour is judged through a more reasonable method, so that the cab wind resistance contour with the best effect is selected, the air resistance during vehicle running is reduced, the load and fuel consumption of an engine are reduced, and the running cost is saved.

To provide a simulator capable of appropriately reproducing acceleration acting on a user.SOLUTION: The control unit of the simulator receives the squaring angle detected by the first detecting unit or the squaring angle calculated from the angular velocity detected by the first detecting unit and the angle of attack detected by the second detecting unit, calculating an inertial force generated in the support plate in the turn action from an equation of motion related to a gravity of the user acting on the support plate, a frictional force between the support plate and the reference surface, and an air resistance acting on the user in the turn action, using a friction coefficient between the support plate and the reference surface in the turn action as a sum of a first friction coefficient between the support plate and the reference surface in a carving turn action in which the turn action is performed in a state of being inclined in the roll direction and a second friction coefficient between the support plate and the reference surface in a squatting turn action in which the turn action is performed so as to rotate in the yaw direction; The turning radius of the support plate in the turn operation is calculated, and the driving part is controlled based on the calculation result.SELECTED DRAWING: Figure 1

The present invention is directed to a novel vehicle configuration with at least one tunnel (2) enclosed inside the vehicle body, wherein the tunnel (2) comprises an inlet (9), an outlet (10) and a middle section forming a neck (14) of the tunnel (2), wherein the tunnel (2) is narrower at the neck (14) than at the inlet (9) and outlet (10) to achieve Venturi effect The tunnel (2) is applicable to any vehicle type, with all propulsion systems, and especially to electric sports cars. The vehicle configuration with the at least one enclosed tunnel (2) has the following main advantages: reduced drag coefficient, increased downforce, increased vehicle structural rigidity, and better stability of the vehicle travelling at high speeds.

This invention discloses a landing gear and an aircraft, relating to the field of aircraft structural components. The landing gear includes a nose landing gear and two main landing gears. The nose landing gear is located at the front of the fuselage and includes a nose wheel and a nose shock strut. One end of the nose shock strut is connected to the fuselage and located inside the fuselage, while the other end extends outside the fuselage and is elastically connected to the nose wheel. The two main landing gears are respectively located on opposite sides of the fuselage. Each main landing gear includes a rocker arm, a main shock absorber, and a main wheel. The rocker arm has a hinged end and a free end, respectively. The hinged end is hinged to the inside of the fuselage so that the rocker arm can only swing along the aircraft's heading. The free end is connected to the main wheel. This invention incorporates part of the nose landing gear structure inside the fuselage and directly hinges the rocker arms of the main landing gear to the fuselage, reducing the overall frontal area of ​​the landing gear, decreasing the aerodynamic drag and overall weight of the aircraft, thereby improving the overall performance and range of the aircraft.

This invention discloses a method for calculating the fuel consumption saving rate of a vehicle platoon based on topology and dynamic characteristics. The method includes establishing a vehicle dynamics model, an external flow field model, and a mathematical analysis model of the fuel consumption saving rate of the vehicle platoon. The proposed method conducts simulation experiments for different parameters such as longitudinal vehicle spacing, lateral vehicle offset distance, and vehicle speed. By analyzing the influence of longitudinal vehicle spacing, lateral vehicle offset distance, and vehicle speed on the vehicle's aerodynamic drag coefficient, the functional relationship between the vehicle platoon's aerodynamic drag coefficient and the above parameters is determined. Furthermore, the functional relationship between the aerodynamic drag coefficient and the fuel consumption saving rate is determined to calculate the vehicle platoon's fuel consumption saving rate.

Embodiments of the present application provide a wind speed estimation method, device and aircraft. In the wind speed estimation method, flight data of the aircraft is obtained, and then a horizontal disturbance acceleration of the aircraft in a navigation coordinate system is obtained according to a vertical acceleration, a horizontal acceleration and an attitude angle of the aircraft in the navigation coordinate system in the flight data. Further, an air resistance of the aircraft in the horizontal direction is obtained according to a mass of the aircraft and the horizontal disturbance acceleration of the aircraft in the navigation coordinate system. Finally, the wind speed of the flight environment of the aircraft is obtained according to the air resistance and a speed of the aircraft relative to the navigation coordinate system, so that the wind speed of the flight environment of the aircraft can be estimated, the accuracy of the wind speed estimation is improved, and in the flight adaptation to different climate environments, only a few key parameters need to be adapted, so that the engineering practicability of the model is greatly improved.

The invention provides a pneumatic drag reduction system and method for a carrying tool, and the system comprises the carrying tool which moves in the X direction; the excitation unit is used for generating unsteady pneumatic excitation, is arranged on the surface of the carrying tool and is located at the front section of the carrying tool, and the excitation unit comprises at least one exciter, and each exciter sprays gas in the X direction; each exciter injects gas towards the front of the vehicle, and all the injected gases form unsteady pneumatic excitation. A low-pressure area is generated through active control of a flow field at the front end of an object, so that high pressure generated by an airflow stagnation effect is counteracted to achieve resistance reduction.

1. Name of the product in this design: Aircraft Nacelle. 2. Purpose of this design: To enclose and protect aircraft engines, reduce aerodynamic drag, and transfer the load of the aircraft engine to the aircraft wings or fuselage. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: the right view.

An active aerodynamic vehicle underbody spare tire assembly improves airflow dynamics and reduces drag at an underbody and rearend of a vehicle, ultimately extending vehicle battery range in an electric vehicle and providing better fuel economy in a gas-powered vehicle. The active aerodynamic vehicle underbody spare tire assembly moves the spare tire between a stowed position and a deployed position based on vehicle speed. At lower vehicle speeds, the spare tire is kept at the stowed position. And at higher vehicle speeds, the spare tire is moved to the deployed position. In varying implementations, the active aerodynamic vehicle underbody spare tire assembly can include a spare tire carrier, an actuator, and a spare tire cover.

The invention discloses a ship ceiling structure which comprises a main framework, a ceiling framework and awning cloth, the awning cloth is laid on the ceiling framework, the ship ceiling structure further comprises a plurality of elastic connecting pieces, and the elastic connecting pieces are arranged between the main framework and the ceiling framework; the flow guide part is arranged on the ceiling framework; and the fixing assembly is used for fixing the awning cloth on the ceiling framework. By means of the elastic deformation characteristic of the elastic connecting pieces, alternating stress of the slamming effect can be effectively buffered, and the situation that the tarpaulin is damaged due to violent tearing is avoided; meanwhile, airflow around the ceiling can be optimized through the flow guide part, the air resistance, the vortex effect and the aerodynamic noise of the ceiling are reduced, continuous vibration of the awning cloth under the wind action is reduced, and the wind resistance of the ceiling is further enhanced; due to the arrangement of the fixing assemblies, stable connection between the awning cloth and the ceiling framework is ensured.

A vertical take-off and landing (VTOL) aircraft is disclosed, including a fuselage having an elevated front section configured to accommodate antennas for obstruction- free communication and a rear section configured to hold an engine, fuel storage, battery, and payload with easy and ergonomic access for loading, unloading, and maintenance A pair of wings extends laterally from fuselage to generate lift during flight, while a pair of canards are positioned forward of the wings to improve stability. The fuselage, the wings and canards are shaped to provide a significant nose-up pitching moment, enabling longitudinal stability at positive angles of attack. A pair of booms interconnect fuselage, wings, and canards to form an interconnected box-like structure that uniformly distributes loads across the aircraft. The aircraft includes VTOL rotors for vertical thrust, concealed landing gears for reduced air drag, and a cowling system with air inlets and outlets that provide efficient engine cooling.

A tire (1), intended in particular for a private passenger vehicle and comprising at least one sidewall (3) with a protuberance of the sidewall (3) close to the connection of the tire with its mounting rim (2), and intended to reduce the aerodynamic drag and hence the resistance to forward motion of the wheel, in order to contribute to the reduction in fuel consumption and hence to the reduction in CO2 emissions. According to the invention, when the tire (1) is mounted on the rim (2) and inflated to a pressure as defined by the “ETRTO” standard, the radially inner end I of the protuberance (6) is positioned radially inside the radially outermost point J of the rim flange (21) at a radial distance H1 at most equal to 10 mm, or radially outside the radially outermost point J of the rim flange (21) at a radial distance H1 at most equal to 4 mm.

There is a need for a club head having improved impact performance characteristics balanced against improved swing characteristics.SOLUTION: The present specification describes embodiments of the golf club head 100 that balance the following parameters: a low and rearward club head center of gravity location 170, a high moment of inertia, a large Ixy product of inertia, and low aerodynamic drag. Also described herein are methods of manufacturing embodiments of golf club heads having balanced club head center of gravity locations, moments of inertia, products of inertia, and aerodynamic drag.SELECTED DRAWING: Figure 1

The invention discloses an elastic compensation jet device and a using method and a design method thereof, and belongs to the technical field of high-speed jet. In order to solve the problems that a traditional jet device and a use method are seriously limited in use scene, the advantages of jet fluid cannot be played when the traditional jet device is used on an uneven bearing surface, and the speed of jet flow is seriously attenuated due to the influence of air resistance, the invention provides the elastic compensation jet device, and a jet part is connected with a mobile carrier through an elastic compensation structure; according to the using method, when the movable carrier drives the jet flow part to work through the elastic compensation structure, high-speed fluid sprayed out of the jet flow nozzle is in a film shape. A series of defects and limitations of low efficiency, poor effect, large fluid flow, easy abrasion of a working surface, limited use scene and the like of a traditional jet mode are overcome, and the beneficial effects of high efficiency and high-standard jet are achieved.

The invention relates to the technical field of model airplane flight control, and particularly discloses a landing damping baffle plate for a model airplane wing, which comprises a shell, a driving motor, a screw rod-sliding sleeve transmission mechanism and a connecting rod type movable top plate assembly. The driving motor drives the screw to rotate through the gear set, the sliding sleeve moves linearly, the movable top plate is driven to rise through the connecting rod to increase air resistance, and stable landing of the model airplane is achieved. The baffle is compact in structure and reliable in work.

The invention discloses a commercial vehicle transmission system equivalent rotational inertia calibration and mass real-time estimation method, and relates to the technical field of vehicle dynamics control. Identifying the product of the equivalent merging coefficient K1 of the rolling resistance and the ramp resistance and the current mass mk and the air resistance coefficient K2 under the no-load state of the vehicle; and under the acceleration working condition, based on the obtained K1mk and K2 values, the equivalent transmission system rotational inertia Ii and the servicing no-load mass mk are identified. And in a quality real-time estimation stage after leaving a factory, updating the sum of products with the current mass mtotal in real time in a constant-speed driving segment. And in an acceleration working condition, Ii calibrated before leaving a factory is implanted into the kinetic model as a fixed parameter, and based on the updated mtotal sum value, the current total mass mtotal is directly solved through the relation between the driving force and the acceleration. According to the method, the strong coupling problem of the rotational inertia and the mass during estimation is thoroughly solved, and the real-time performance, precision and reliability of mass estimation in the vehicle running process are remarkably improved.

This application provides a vehicle emergency braking control method, vehicle, and related equipment, belonging to the field of vehicle braking control technology. The method determines whether an emergency braking condition is currently occurring based on collected sensor data. If an emergency braking condition is present, it determines the current collision risk value based on the relative distance to obstacles and the theoretical braking distance. Based on this collision risk value, the vehicle's aerodynamic components are adjusted to improve the overall vehicle's drag coefficient. The higher the current collision risk value, the higher the drag coefficient corresponding to the target state of the aerodynamic components. This solution considers the relative distance to obstacles during emergency braking, calculates the risk value that may still result in a collision under emergency braking conditions, and then adaptively adjusts the aerodynamic components based on this risk value, thereby improving the safety and stability of the vehicle's emergency braking process.

The utility model relates to the technical field of power grids, and discloses a horizontal flywheel energy storage system, which is characterized in that a flywheel energy storage module is rigidly or flexibly connected with a rotor of a double-fed motor through a primary connector; a stator of the double-fed motor is electrically connected with an alternating current power grid; the system controller is electrically connected with the flywheel energy storage module, the primary connector and the double-feed motor; the flywheel energy storage module, the first-stage connector and the double-fed motor are all horizontally arranged, and the flywheel energy storage module is sealed in a vacuum mode. By adopting the horizontal arrangement, a larger and heavier flywheel rotor can be supported, so that the rotational inertia of the flywheel rotor is increased, and the capability of providing the rotational inertia for an alternating current power grid by the system is further improved; vacuum sealing is adopted, air resistance of a flywheel rotor of the flywheel energy storage module is reduced, energy conversion efficiency is improved, energy loss caused by air friction is avoided, the service life of the flywheel energy storage module is prolonged, corrosion of external air is avoided, and corrosion and oxidation of the flywheel rotor are reduced.

The invention relates to the technical field of train aerodynamics optimization, in particular to a train surface bionic microstructure partition arrangement and drag reduction optimization method and system.The method comprises the steps that the train surface is divided into design partitions which are geometrically continuous and relatively consistent in near-wall flow form according to train appearance geometric parameters and external flow field characteristics; resistance mechanisms in the same subarea tend to be the same; a turbulent flow correction model is adopted for the design partition where the bionic microstructure is arranged, geometric parameters of the bionic microstructure are mapped into near-wall dissipation correction, and the wall surface shear stress is equivalently changed; an initial turbulence model is adopted for the non-arranged partition, and physical quantity continuity is kept at the junction through data exchange of a virtual grid; and a stable and comparable aerodynamic resistance evaluation result is obtained, and a target partition arrangement scheme is screened from candidate arrangement schemes, so that the reliability of resistance reduction optimization is improved at relatively low calculation cost.

The invention provides an efficient, low-noise, medium-and-small-power propeller blade, and relates to the field of aviation aerodynamic design. Each propeller blade comprises a blade root, a blade body and a blade tip; the blade body is composed of a plurality of airfoils with different thicknesses, and the blade tip is obtained by extending the blade body. The cutting edge part of the horse-knife-shaped structure is an arc line, and the knife back part is a straight line. According to the technical scheme, the overall shape of the blade is a saber-shaped sweepback blade, the root of the blade is approximately circular, the blade body section from the blade root to the blade tip is composed of a plurality of advanced airfoil shapes similar to a wing, the thickness is in smooth transition from thick to thin, and a certain torsion angle is kept between the sections, so that the airfoil cannot stall in the working process of the blade, and the blade is more stable in performance. The whole shape of the propeller blade generates a saber-shaped sweepback by designing the continuous change of a wing-shaped pneumatic center, so that the noise of the propeller blade is smaller than that of the propeller blades in other shapes during working, and the pulling force and pneumatic efficiency of the propeller are improved.

This invention discloses a pneumatically drag-reducing autonomous underground robot and its control method, belonging to the field of underground robot technology. It includes a wedge-shaped head, a front shell, a rear shell, an electric actuator, anchoring units, a pneumatic system, and a control system. The wedge-shaped head ejects compressed gas in the forward direction. The wedge-shaped head is fixedly mounted at the front end of the front shell, which is positioned at the front end of the rear shell. The electric actuator is located within the cavity of the rear shell, driving either the front or rear shell to move. Two anchoring units are located on either side of the front shell to provide anchoring force. The pneumatic system provides compressed gas to the wedge-shaped head. The control system controls the operation of the electric actuator and the gas ejection, enabling the pneumatically drag-reducing autonomous underground robot to move autonomously in the soil. This invention not only significantly improves exploration efficiency but also effectively reduces reliance on external equipment, lowers labor costs and exploration time, while simultaneously improving the accuracy and real-time performance of exploration data.