247 results about "Wing section" patented technology

The invention provides a morphing wing integrating telescopic variable-elongation and rotary variable-sweepback functions and a morphing method. The morphing wing comprises an inner wing section, an outer wing section and an elastic skin, the inner wing section and the outer wing section are positioned in the same spanwise plane; the inner wing section stretches and retracts in the spanwise plane along the spanwise direction of the wing, so that the span length of the inner wing section is adjusted; the outer wing sections rotate in the chordwise direction relative to the inner wing sections in the spanwise plane, and then the sweepback angles of the outer wing sections are adjusted. By adjusting the extension length and the sweepback angle of the wings, the lift force of the aircraft during low-speed flight is improved, and the resistance of the aircraft during high-speed flight is reduced. Specifically, the extension length of the wings is increased during low-speed flight to improve lift force, and the extension length is reduced and the sweepback angle is increased during high-speed flight to reduce resistance. The optimal aerodynamic performance can be achieved no matter in a low-speed flight state or a high-speed flight state, and the adaptability and the flight performance of the aircraft are remarkably improved.

An aircraft wing has a leading edge, a fixed wing portion and a leading-edge spoiler device. The spoiler device is hingedly mounted relative to the fixed wing portion adjacent the leading edge, moveable between retracted and deployed positions. In the retracted position a spoiler surface forms a continuous surface with a fixed wing portion upper aerodynamic surface, and in the deployed position the spoiler surface is rotated relative to the upper aerodynamic surface. In the retracted position the spoiler surface has a first portion forward of the hinge and a second portion aft of the hinge. A center of pressure of the local wing section acts on the spoiler surface providing a moment about the hinge in a first direction to bias the spoiler device to the retracted position and providing a moment about the hinge in a second, opposite direction, rotating the spoiler device to the deployed position.

The invention discloses a reinforcement learning driven hypersonic variant aircraft reentry trajectory optimization method, and belongs to the field of hypersonic aircraft and trajectory optimization. The implementation method comprises the following steps: establishing a waverider-like hypersonic variant aircraft parameterized model comprising a waverider fuselage and two deformed wings based on a category shape conversion (CST) method; the influence of factors such as flight height H, flight Mach number Ma, attack angle alpha, inner wing section sweepback x1, outer wing section sweepback x2 and the like is considered, a Kriging agent model is established, and the aerodynamic performance of the hypersonic speed variant aircraft is obtained. Based on a DDPG reinforcement learning algorithm, according to flight characteristics of a hypersonic speed variant aircraft in a reentry section flight process, and in combination with expert experience and dynamics, start and end states, heat flow, overload and dynamic pressure constraints in the flight process, training of a reentry section trajectory optimization model driven by the DDPG algorithm is realized. Through flight simulation prediction of different hypersonic speed variant aircrafts, variant decisions are given in real time, and reentry section trajectory optimization of the hypersonic speed variant aircrafts is realized.

Vertical take-off and landing (VTOL) aircraft of the fixed-wing type, comprising a centre section defining a centreline of the aircraft, and a pair of wings, arranged on either side of the centre section, wherein the wings extend longitudinally from the centre section away from and mutually symmetrical with respect to a plane of symmetry extending through the centreline, wherein each wing comprises a main wing section extending longitudinally from the centre section, wherein the main wing section is configured for generating lift in an upward direction, a wingtip section extending longitudinally from the main wing section in a downwards sloping manner with respect to the main wing section, and a control surface provided in the wingtip section.

An aircraft wing includes a center wing section having a continuous structure that spans beyond a first side of an aircraft fuselage and beyond a second side of the aircraft fuselage. The aircraft wing also includes a first outboard wing section attached to a first end of the center wing section by a first truss system that is accessible via a first closeout panel. The first end of the center wing section in on the first side of the aircraft fuselage. The aircraft wing also includes a second outboard wing section attached to a second end of the center wing section by a second truss system that is accessible via a second closeout panel. The second end of the center wing section is on the second side of the aircraft fuselage.

The utility model relates to an aviation dynamic differential pressure propeller. The airfoil profile of the aviation dynamic differential pressure propeller comprises an upper airfoil surface and a lower airfoil surface, the section lines of the airfoils are all composed of curves of a monotonically decreasing function from the front edge to the rear edge. The structure is simple, and when the lower wing surface does work on windward airflow, the flow speed is reduced, the static pressure intensity is increased, and upward thrust is generated; the upper airfoil does not do work, airflow flows back, static pressure is reduced, upward pulling force is generated by the airfoils, so that the lift force of the upper airfoil and the lower airfoil is upward at the same time, the sum of the lift force is larger than the lift force of an existing single-face airfoil, and then the efficiency of the propeller wing is further improved by optimizing the lift-drag ratio. A front edge point is accurately positioned by adopting a wing section line rear corner, a spanwise line, a relative velocity line and a backward moving distance, a shock wave is weakened to be low-sound-velocity object surface static pressure, and the damage effect of the shock wave is avoided.

An aircraft wing tip that is movable by an actuator between a flight configuration, and a ground configuration which has a shorter wingspan for use in ground-based operations. Lugs that connect to arms of the actuator are integrally formed as part of the primary structure of either the fixed wing or outboard wing section, such as a folding tip section.

The present invention provides an extreme STOL airplane comprising: a fuselage and a wing having port and starboard wing sections. Each wing section has a body with top and bottom surfaces, leading and trailing edges, and a span, i.e., the distance between a wing section tip and root connected to the fuselage, and flap coves. Aerodynamic elements integrated into the wing sections include Fowler flaps, having leading and trailing edges and a span, flap tracks, wherein the flap tracks are external to the wing section body, extend aftward beyond the trailing edge of the wing section, and are configured to enable the Fowler flaps to rotate or deflect and to translate or extend and retract, Frise ailerons, wherein the Frise ailerons are located outboard of the Fowler flaps, and spoilerons located over the leading edge of the Fowler flaps when the flaps are in the fully extended position.

The utility model relates to a static aeroelastic force-measuring wind tunnel test model for a large-flexibility wing structure, which has the capability of testing the bending moment of a wing root and belongs to the technical field of aeroelastic tests of aircrafts. A static aeroelastic force measurement wind tunnel test model of a large flexible wing structure comprises a wing body fusion section, an outer wing section and a winglet, the wing body fusion section is arranged between the outer wing section and the winglet, the outer wing section comprises a wing section, an aileron, a spar and a steering engine, and the wing section is made of foam; the spar is bonded with the wing section, the length direction is consistent with that of the wing section, one end of the spar is connected with the winglet, and the other end of the spar extends out of the end part of the wing section to serve as a mounting end fixed with the side wall of the wind tunnel; the steering engine is connected with one side of the spar; the aileron serves as a part of the wing section, is bonded to the other side of the steering engine and can rotate along with actuation of the steering engine. The utility model has the advantages that: 1, the structural form is simple; 2, the assembly is simple, and the price is low; 3, the overall bearing load of the foam is reduced; and 4, the operation is easy.

The invention provides a folding wing force measuring device, a calibration structure of the force measuring device and a calibration method, and relates to the technical field of wind tunnel tests. The folding wing force measuring device comprises a wing root connecting piece, a folding wing inner section, a folding wing force measuring balance, a folding wing outer section, a plurality of angle connecting blocks and a plurality of folding patch blocks, wherein the angle connecting blocks and the folding patch blocks are matched with the folding angle of a folding wing. According to the invention, the balance and the wing part are fused into a whole and are integrally designed and processed, the connecting surface of the balance and the wing is canceled, the measuring end of the balance, namely the folding wing part section, is shaped by the cover plate, and the shape is kept consistent with that of the wing part section. Therefore, the load of the force measuring balance tends to be reasonable, the balance coordinate system changes along with the folding wing, the precision of the force measuring balance with the folding wing is improved, the data conversion difficulty of a wind tunnel test is reduced, and the precision of the wind tunnel test is improved.

In one aspect, a rear folding agricultural implement allows for first and second wing sections of a toolbar assembly to be folded relative to a central toolbar section of the toolbar assembly via independently actuatable wing roll sections coupled between the central toolbar section and the respective wing sections.

The invention provides a multi-propeller tilting wing dynamic test device for wing tilting. The multi-propeller tilting wing dynamic test device comprises a multi-propeller dynamic test model, a wing dynamic tilting system, an EX1629 data acquisition system and a structural deformation test system, wherein the multi-propeller dynamics test model is composed of one pair of half-expanded wings and three pairs of propellers; the wing dynamic tilting system is composed of a control cabinet and a wing dynamic tilting device, and the wing dynamic tilting device is used for controlling the wing tilt angle, has the capacity of realizing wing constant-speed tilting and triangular wave pulse excitation, and realizes synchronous change of the angles of the wing and the rotor; the EX1629 data acquisition system comprises a data acquisition and vibration monitoring system and is used for measuring a wing profile bending moment load and vibration loads of a nacelle and a wing; the structural deformation testing system is composed of an industrial camera and a high-frequency photography lamp and is used for measuring wing and blade position deformation; meanwhile, the invention further provides a multi-propeller tilting wing dynamics test method for wing tilting.

The invention discloses a novel tilting dual-rotor unmanned aerial vehicle, which belongs to the technical field of unmanned aerial vehicles, and comprises a wing body fusion fuselage and two outer wing sections, the two tilting rotor assemblies are used for providing power, controlling rolling, pitching and yawing in a vertical flight mode and controlling yawing in a horizontal flight mode, the two pitching and rolling rudder assemblies are used for controlling pitching and rolling in a horizontal flight state, and the two tilting rotor assemblies are symmetrically arranged in front of the wing body fusion fuselage; the pitching rolling rudder assembly is arranged in the middle of the outer wing section; the outer wing section is of a structure capable of being folded in the tail direction, so that the center of gravity is moved backwards to the position behind a stop point of the tail after the outer wing section is folded, and the unmanned aerial vehicle stably stops on a rod-shaped object with the diameter being 13 cm or less under the unpowered condition. On one hand, the problems that a tailstock type unmanned aerial vehicle is difficult to take off and land and a traditional unmanned aerial vehicle needs an undercarriage to take off and land are solved, and the problems that an existing unmanned aerial vehicle needs to be additionally provided with a parking actuator and needs to be parked with power are solved.

An aircraft apparatus is disclosed that has a fuselage; and a wing coupled to the fuselage, where the wing comprises a port outboard wing section and a starboard outboard wing section; where each of the port outboard wing section and the starboard outboard wing section comprise at least one of: curved leading edges of varying radii and curved trailing edges of varying radii.

A bag for carrying a set of golf clubs while playing golf and while traveling. The bag includes first, second, third and fourth panels. Each panel has a middle section with first and second opposing faces, and with first and second opposite sides edges; a first wing section extending at a first angle from the first side edge of each panel; and a second wing section extending at a second angle from the second side edge of each panel. A first hinge connects the second wing section of the first panel to the first wing section of the second panel. A second hinge connects the second wing section of the second panel to the first wing section of the third panel. A third hinge connects the second wing section of the third panel to the first wing section of the fourth panel. At least one closure releasably connects the first wing section of the first panel to the second wing section of the fourth panel. The bag also includes first, second, and third club holding components, each connected to one of the first, second, third and fourth panels, each of the club holding components comprising at least three sleeves for receiving shafts of golf clubs. All of the hinges and the closure allow the bag to be folded into a playing mode with the connected wing sections touching each other and the first faces of the middle sections and the club holding components facing outward. All of the hinges and the closure also allow the bag to be folded into a travel mode with two of the first, second, third and fourth panels being adjacent with the middle sections facing and club holding components facing inward and with an other two of the first, second, third and fourth panels are adjacent with the middle sections and club hold components facing inward.

The invention provides a hovercar which comprises a hovercar body, folding wings, a folding duct and a telescopic empennage, the folding wing on each side comprises a plurality of wing sections hinged in sequence, and the adjacent wing sections are connected with folding assemblies used for enabling the wing sections to be folded in a Z shape; the folding duct comprises two duct bodies, two short cabin doors, a lengthened cabin door and a driving device. The driving device is used for driving the lengthened cabin door to move up and down so as to drive the two duct bodies to be unfolded out of the hovercar body or stored in the hovercar body. The telescopic empennage comprises a shell, an empennage assembly, a locking assembly and a telescopic assembly, wherein the empennage assembly is slidably inserted into the shell; in the process of stretching out and locking the empennage, after the telescopic assembly pushes the empennage assembly to move to the clamping position of the shell, the locking assembly continues to slide relative to the empennage assembly till interference fit is achieved so as to lock the empennage assembly. According to the implementation mode, different design requirements of the flying state and the land running state on the flying car can be met.

An aircraft wing 13 has a leading edge 16, a trailing edge 17, a fixed wing portion 23 and a leading edge spoiler 30. The spoiler is rotatably mounted to the fixed wing portion adjacent the leading edge by a hinge 32 and is moveable between a retracted position and a deployed position. In the retracted position the spoiler has a spoiler surface 34 forming a continuous surface with an upper aerodynamic surface of the fixed wing portion, and in the deployed position the spoiler surface is rotated at an angle to the upper aerodynamic surface. In the retracted position the spoiler surface has a first portion forward of the hinge and a second portion aft of the hinge. When a centre of pressure of the local wing section acts on the spoiler surface to provide a moment about the hinge in a first direction the spoiler device is biased to the retracted position. When the centre of pressure of the local wing section acts on the spoiler surface to provide a moment about the hinge in a second direction opposite the first direction then the spoiler device is operable to rotate to the deployed position.

The present invention provides an extreme STOL airplane comprising: a fuselage and a wing having port and starboard wing sections. Each wing section has a body with top and bottom surfaces, leading and trailing edges, and a span, i.e., the distance between a wing section tip and root connected to the fuselage, and flap coves. Aerodynamic elements integrated into the wing sections include Fowler flaps, having leading and trailing edges and a span, flap tracks, wherein the flap tracks are external to the wing section body, extend aftward beyond the trailing edge of the wing section, and are configured to enable the Fowler flaps to rotate or deflect and to translate or extend and retract, Frise ailerons, wherein the Frise ailerons are located outboard of the Fowler flaps, and spoilerons located over the leading edge of the Fowler flaps when the flaps are in the fully extended position.

The invention discloses a blade optimization method and device, a storage medium, an electronic device and a computer program product, and relates to the field of blades, and the blade optimization method comprises the steps that the airfoil profile distribution condition of a target blade is determined, the airfoil profile distribution condition is used for indicating the distribution condition of N airfoil profiles in the target blade and the relative thickness of each airfoil profile in the N airfoil profiles, and N is an integer greater than or equal to 2; according to the airfoil profile distribution condition of the target blade, the optimal operation lift-drag ratio of each airfoil profile in the N airfoil profiles is determined, and the optimal operation lift-drag ratio is the operation lift-drag ratio corresponding to the maximum wind power conversion efficiency of the airfoil profile; and optimizing the airfoil profile of the target blade according to the optimal operation lift-drag ratio and the maximum operation lift-drag ratio of each airfoil profile in the N airfoil profiles. By the adoption of the technical scheme, the problem that the wing section of the blade cannot be optimized well is solved.

The application discloses a chord-wise folding and quick unfolding wing structure and relates to the technical field of aircraft design technology.The chord-wise folding and quick unfolding wing structure comprises chord-wise folding and unfolding wing sections, the chord-wise folding and unfolding wing sections are divided into a plurality of wing sections along the chord direction, the division surfaces of two adjacent wing sections are both planes, grooves are formed in the separation planes of the two adjacent wing ribs, buffer gaskets and strong magnets are arranged in the grooves, and the two adjacent wing sections are connected through a film hinge; and flow guides are arranged above the connecting gaps of the two adjacent wing ribs.The chord-wise folding and quick unfolding wing structure can be divided into a plurality of wing sections which can rotate around the lower surface division lines along the chord direction, so that the wing fully utilizes the circumferential storage size and can break through the limitation of the cylinder diameter on the chord length and area of the wing; the two adjacent wing sections are connected through the film hinge, so that the air resistance during flight is reduced; the automatic positioning and locking between the two adjacent wing sections are realized by using the suction force of the permanent magnet, and the structure is simple and has high reliability.

The invention discloses a wide-speed-range two-way flying wing aircraft mode conversion system and method, and the system comprises two foldable telescopic all-moving empennages (9) and a power system (10) which are arranged on an aircraft main body fuselage (11), and the number of the all-moving empennages (9) is two. The two all-moving empennages (9) are symmetrically arranged at the tail of the upper surface of an aircraft body (11) in the direction of the first axis of the aircraft, the first axis is perpendicular to the low-speed modal flight incoming flow direction of the aircraft and parallel to the high-speed modal flight incoming flow direction of the aircraft, and each all-moving empennage (9) comprises an outer wing section (1), an inner wing section (2) and a rotating shaft (3). The bottom of the inner wing section (2) is rotationally connected with an aircraft body through a rotating shaft (3), so that the outer wing section (1) and the inner wing section (2) are overturned and folded, the outer wing section (1) is connected to the top of the inner wing section (2), and the outer wing section (1) can be retracted into the inner wing section (2) and can also extend out of the inner wing section (2).

The invention relates to the technical field of aircraft wing folding, in particular to an aircraft wing large-angle folding mechanism and method.The aircraft wing large-angle folding mechanism comprises a fixed wing section connected with an aircraft body, a movable wing section connected with the fixed wing section in a folding mode and a folding drive connected with the fixed wing section and the movable wing section; the bottom of the folding end of the fixed wing section is rotationally connected with the bottom of the folding end of the movable wing section; the folding drive is used for driving the movable wing section to turn over and fold downwards to be close to the lower surface of the fixed wing section; the bottom of the folding end of the fixed wing section is rotationally connected with the bottom of the folding end of the movable wing section, and the movable wing section is driven by folding drive to turn downwards around the rotating connection position to be close to the lower surface of the fixed wing section, so that the movable wing section is folded downwards, the space below the fixed wing section is fully utilized, the space utilization rate is increased, and the fuselage width is reduced; the space occupied by the aircraft is reduced; the overall structure is simple, cost is low, and operation is easy and convenient.

A method for adjusting a header mounted on an agricultural harvester. The header includes a central section and at least one side wing section. The at least one side wing section extends between an inner portion and an outer portion, where the inner portion of the at least one side wing section is pivotally coupled to the central section. A ground engaging device is mounted on the at least one side wing section adjacent the outer portion. The ground engaging device has an adjustable height. The method comprises the steps of determining a flex position of the at least one side wing section relative to the central section, determining whether the flex position of the at least one side wing section exceeds a first threshold, and if it is determined that the flex position of the at least one side wing section exceeds the first threshold, decreasing the flex position.

Ride-on semi-trailer vehicle, which features: a panel (40) that covers a vehicle body from the sides; and a wing element (50) which is arranged on a side surface of the fairing (40), where the fairing (40) a front fairing (41) which covers the vehicle body from the front and the left and right sides at a front end section of the ride-on articulated vehicle, and the wing element (50) includes a wing section (51) which extends in the vehicle width direction from the fairing (40) to an outer side, characterized by the fact that the wing element (50) includes a mounting section (54) and an upper mounting section (55), wherein the mounting section (54) is attached to a base end section of the wing section (51) and is attached to a side surface of the front fairing (41), the upper mounting section (55) is positioned on the rear upper side of the mounting section (54), and the wing section (51) includes a front edge (51a) and a rear edge (51b), wherein the front edge (51a) is curved such that when the front edge (51a) extends outwards from a midpoint of the vehicle width direction, it is curved backwards, and When viewed from above, the width (A) of the wing section (51), which is a distance in the longitudinal direction of the vehicle between the front edge (51a) and the rear edge (51b), increases from the middle side in the vehicle width direction to the outside of the vehicle width direction.

The invention belongs to the technical field of fluid mechanics experiments, and relates to a flapping-fan-deformation coupling variable camber flapping wing ground experiment device which comprises a water tunnel frame and a deformation flapping wing movement mechanism, the deformation flapping wing movement mechanism comprises a linear sliding rail, a first motor, a long shaft, a second motor, a short shaft and a deformation flapping wing, and the deformation flapping wing comprises a front wing section and a rear wing section. The front wing section is rotationally connected with the rear wing section through a rotating shaft, the long shaft drives the front wing section, the short shaft drives the rear wing section, and the front wing section is connected with the rear wing section through the rotating shaft; according to the invention, through a force measuring mechanism in a deformation flapping wing movement mechanism, computer assistance and other regulation and control devices are utilized to collect torsional force and moment of force borne by a deformation wing during movement, and a visual image of a flow field vortex during pitching, sinking and floating and compound movement of the deformation wing in water flow is obtained, so that data processing and analysis are facilitated; therefore, a data foundation is laid for improvement of cruising ability, propelling performance, stability and the like of the flapping wing aircraft.

A row crop header for harvesting crop in a field comprises a header frame having a center section and a pair of side wing sections operatively coupled to the center section. An upper link is pivotally coupled between the center section and each one of the side wing sections adjacent the top portion thereof. A lower link is pivotally coupled between the center section and each one of the side wing sections adjacent the bottom portion thereof. The upper links and lower links provide independent pivotal movement of the side wing sections relative to the center section to contour to the surface of the field of crops to be harvested. An automatic float system is operatively coupled between the center section and each one of the side wing sections to adjust the weight of the side wing sections on the surface of the field and allow the side wing sections to float relative to the center section.

The invention discloses a wing section control method and device with a lifting force type vertical axis wind turbine generator, and the method comprises the steps that a function expression constructed for the wing section chord length of the lifting force type vertical axis wind turbine generator is obtained, aerodynamic design parameters at least comprise the incoming flow wind speed facing a transverse horizontal wing section and the wing section attack angle of the transverse horizontal wing section, and the function expression is constructed for the wing section chord length of the lifting force type vertical axis wind turbine generator; the vertical axis blade height, the vertical axis wind wheel diameter and the vertical axis unit efficiency; the current incoming flow wind speed is calculated through the function expression, and the chord length value of the first wing section is obtained; the first wing section chord length value is used for conducting performance testing on the lift type vertical axis wind turbine generator, a performance testing result is obtained, and under the condition that it is determined that the testing result is used for indicating that the unit performance of the lift type vertical axis wind turbine generator passes testing, the transverse horizontal wing section is replaced with a target transverse horizontal wing section with the first wing section chord length value, and controlling the target transverse horizontal wing section to rotate according to the current incoming flow wind speed.

To provide a presentation-type cream container for applying a suitable amount of a coating material such as cream, which can prevent the cream from deteriorating by minimizing contact with the outside air during use, and which can look good on social media or the like by forming a discharge hole in any shape, and is likely to be featured in the media. [Solution] By fitting the inner tray 5, rotor 4, and container 6 together, and then fitting the winged cap 2 after filling with cream, contact with outside air can be minimized during use. Furthermore, the winged cap's wings 3 and wing-over-wing section 8 allow rotation to be unidirectional, limiting the amount used and preventing reverse rotation. This ensures rotation in the direction that ensures reliable dispensing. The amount dispensed can be adjusted by changing the screw pitch of the rotor to match the amount used. Conventionally, when using a spatula or fingers to dispense the appropriate amount of cream or other dispensed material, there was a risk of the cream deteriorating due to bacteria or moisture on the spatula or fingers. Furthermore, the product lacked a distinctive appearance, making it difficult to create a visual impact on social media.

The invention belongs to the technical field of vertical-axis wind turbines, and particularly relates to a low-Reynolds-number vertical-axis fan adopting a KFm step wing section, a blade of the low-Reynolds-number vertical-axis fan and a blade forming method. According to the airfoil, eddy current reattachment is induced through the step design at the position of 50%-60% of the chord length, flow separation is delayed, the lift force performance and the stall resistance characteristic under the low Reynolds number are improved, and the lift-drag ratio is optimized. Meanwhile, the invention provides a segmented manufacturing method of the aluminum alloy blade, the blade is divided into the front edge and the rear edge, the front edge and the rear edge are independently formed through an aluminum pultrusion process and then are riveted and assembled, the problem of high mold cost is solved, the technological process is reduced to single riveting, and the production cost is remarkably reduced. During installation, aiming at the periodic windward / leeward working condition of the vertical axis fan, an installation positioning strategy that the blade steps face the outside of the circumference is specifically designed, and separation flow deterioration is avoided. The vertical axis wind turbine has the advantages of aerodynamic efficiency optimization, low cost and easiness in manufacturing, and is suitable for vertical axis wind power equipment in low-wind-speed and high-turbulence environments.

The invention relates to a propeller blade for an aircraft propeller, comprising a wing section (10) and a propeller blade root (20) connected thereto, as well as a method for repairing such a propeller blade. The wing section (10) can have a foam and / or honeycomb core (11, 12, 13) with a sheath (14) made of a fiber-reinforced polymer material. The propeller blade root (20) can be made of a metallic material and comprise a shaft (21) extending into and connected to the wing section (10), at least one outer bearing ring (23), and an adjustment pin (22). It is preferred that the bearing ring (23) has a running surface consisting of a layer (26) of a steel material welded or remelted onto the bearing ring (23), which has a yield strength Rp0.2 of over 750 N / mm² and a tensile strength Rm of over 1,000 N / mm².The bearing ring (23) with the running surface can have a core Vickers hardness HV10 of over 430.