Brake disc of aviation brake airplane wheel

Abstract

The invention discloses a brake disc of an aviation braking airplane wheel, and particularly relates to the field of braking of aviation braking airplane wheels. Comprising an annular flat plate, a plurality of fan-shaped through holes are formed in the circumferential direction, and bosses are formed on the two radial opposite side walls of the through holes respectively; two powder alloy fanning strips are arranged in each through hole; the powder alloy fanning strip comprises a fanning first fixing plate, one surface of the first fixing plate is covered with a powder alloy layer, the other surface of the first fixing plate is connected with a second fixing plate, the size length of the second fixing plate is smaller than that of the first fixing plate, and steps are formed on the two opposite sides of the second fixing plate. The two second fixing plates are connected through a connecting piece, a groove matched with the boss is formed between the two first fixing plates, and the boss is located in the groove. By means of the brake disc, during braking, the small framework and the large framework jointly bear the force in the circumferential direction, the connecting piece for connecting the two powder alloy fanning strips is not subjected to shear force, and the problem of fastener breakage cannot occur.

Description

Technical Field

[0001] This invention relates to the field of aircraft brake wheel braking, and more particularly to a brake disc for aircraft brake wheels. Background Technology

[0002] Due to the demands of aircraft takeoff, the weight and volume requirements for all components are extremely stringent. The goal of modern aircraft brake wheel technology is to design greater braking capacity within limited space and weight constraints. Aircraft brake wheels generally consist of a wheel assembly and a braking system. During operation, the moving brake disc on the braking system engages with the guide rails of the wheel assembly, rotating synchronously relative to the landing gear shaft, while the stationary brake disc on the braking system remains stationary relative to the landing gear shaft. When the pilot applies the brakes, the moving and stationary brake discs press against each other under the action of the piston, generating braking torque to achieve aircraft braking. Powder alloy brake discs are a widely used type of brake disc structure. Commonly used powder alloy brake discs are divided into integral sintered types and small-piece riveted types. Small-piece riveted structures are more widely used due to their ease of use and maintenance, stable torque, and relatively long wear life. Small-piece riveted powder alloy brake discs mainly consist of a frame, powder alloy fan-shaped plates, and rivets. The powder alloy fan-shaped plates are riveted to both sides of the frame, working together with other brake discs to generate braking torque.

[0003] As aircraft braking requirements increase, small-piece riveted powder alloy brake discs, due to their greater thickness, cannot accommodate more friction pairs within a limited space, making it difficult to meet higher braking torque demands. During the riveting process, the rivets exhibit varying degrees of upsetting, resulting in inconsistent contact between the powder alloy blades and the frame. This leads to poor uniformity of the riveted blades; some blades are tightly connected to the frame, while others are loosely connected. During braking, the rivets on the powder alloy brake disc experience uneven stress. In extreme cases, the rivets may break under this stress, reducing braking efficiency and generating debris, thus affecting aircraft safety. Summary of the Invention

[0004] The main purpose of this application is to provide a brake disc for aircraft brake wheels, which aims to solve the problem of rivet breakage under stress in existing brake discs.

[0005] To achieve the above objectives, this application provides a brake disc for an aircraft brake wheel, comprising an annular flat plate with multiple fan-shaped through holes circumferentially formed therein, and bosses formed on two radially opposite sidewalls of the through holes; two powder alloy fan-shaped pieces are disposed in each through hole; the powder alloy fan-shaped pieces include a fan-shaped first fixing plate, one surface of the first fixing plate is covered with a powder alloy layer, and the other surface is connected to a second fixing plate, the length of the second fixing plate is smaller than the length of the first fixing plate, and steps are formed on opposite sides; the two second fixing plates are connected by a connector, and a groove adapted to the bosses is formed between the two first fixing plates, with the bosses located in the grooves.

[0006] Optionally, the thickness of the plate is greater than twice the total thickness of the first and second fixing plates, but less than twice the thickness of the powder alloy fan-shaped sheet.

[0007] Optionally, the height of the step is greater than 0.5 times the thickness of the boss, and the difference is 0.02-0.05 mm.

[0008] Optionally, the connector includes a rivet and a sleeve, the rivet passing through two powder alloy sector plates, and the sleeve fitting around the outside of the rivet.

[0009] Optionally, the rivet includes a truncated cone, with a connecting rod and a ring truncated cone connected sequentially to the small-diameter end of the truncated cone. A blind hole is provided inside the ring truncated cone, and the outer diameter of the ring truncated cone is smaller than the outer diameter of the connecting rod. The total length of the connecting rod and the ring truncated cone is equal to the length of the sleeve. The sleeve includes a tapered first sleeve, with a second sleeve connected to the small-diameter end of the first sleeve. The first sleeve and the second sleeve are respectively fitted onto the outer sides of the ring truncated cone and the connecting rod, and the ring truncated cone is fitted against the inner side of the first sleeve by riveting.

[0010] Optionally, the powder alloy sector sheet has multiple rivet holes; in each through hole, the cone is located in the countersunk hole of the rivet hole of one of the powder alloy sector sheets, and the first sleeve is located in the countersunk hole of the rivet hole of another powder alloy sector sheet.

[0011] Compared with the prior art, the beneficial effects of this application are as follows: The brake disc of the aircraft brake wheel of the present invention comprises two powder alloy sector plates mounted back-to-back in a through hole. In the axial direction, the steps on the two powder alloy sector plates align to form a groove, and the boss is located in the groove. The side of the powder alloy sector plate fits against the side wall of the through hole, so that the powder alloy sector plate and the large frame are in circumferential surface contact. During braking, the braking torque is transmitted to the large frame through the small frame. Compared with the previous rivet and rivet hole stress, the stress is transmitted through the contact surface of the small frame and the large frame. Since the contact area is controllable, the accuracy of the calculation results is higher, which is more conducive to design. During braking, the circumferential stress is borne by the small frame and the large frame together, and the connecting piece connecting the two powder alloy sector plates is not subjected to shear force, so there will be no fastener breakage or foreign object problems, which is beneficial to improving the safety of the aircraft. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the structure of a brake disc for an aircraft brake wheel according to this application; Figure 2 for Figure 1 Schematic diagram of the medium and large skeleton; Figure 3 for Figure 1 A partial sectional view; Figure 4 for Figure 1 A three-dimensional view of a sector-shaped sheet made of powder metallurgy; Figure 5 for Figure 1 Cross-sectional view of a sector-shaped sheet of medium-density powder alloy; Figure 6 for Figure 1 Right view of a sector-shaped sheet of medium-density powder alloy; Figure 7 for Figure 1 Left view of a medium-density powder metallurgy sector sheet; Figure 8 for Figure 1 A 3D view of the center rivet; Figure 9 for Figure 1 A sectional view of the rivet rod; Figure 10 for Figure 1 A three-dimensional view of the middle sleeve; Figure 11 for Figure 1 A sectional view of the middle sleeve; Figure 12 for Figure 1 A sectional view (circumferential) of the riveted joint. Figure 13 for Figure 1 A sectional view (radial) of the riveted joint. Figure 14 This is a schematic diagram showing the installation position of the brake disc of an aircraft brake wheel in a heat storage assembly according to this application; Figure 15 This is a side view of the mounting position of the brake disc of an aircraft brake wheel in a heat storage assembly according to this application.

[0013] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0014] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0015] Embodiments of the present invention provide a brake disc for an aircraft brake wheel, such as... Figure 1-3 As shown, it includes an annular plate 1, with multiple driving protrusions 2 connected to the outer circumference of the plate 1. The number of protrusions 2 is the same as that of the wheel guide rail, and their dimensions are matched with the wheel guide rail. Multiple fan-shaped through holes 3 are opened along the circumference. Bosses 4 are formed on the two radially opposite side walls of the through holes 3, and the bosses 4 and the other two side walls of the through holes 3 form an isosceles trapezoid. Two powder alloy fan-shaped pieces 5 are arranged in each through hole 3. Figure 4-7 As shown, the powder alloy fan-shaped sheet 5 includes a fan-shaped first fixing plate 51. One surface of the first fixing plate 51 is covered with a powder alloy layer 52, and the other surface is connected to a second fixing plate 53. The length of the second fixing plate 53 is smaller than that of the first fixing plate 51, and steps are formed on opposite sides. The two second fixing plates 53 are connected by a connector, and a groove that matches the boss 4 is formed between the two first fixing plates 51. The boss 4 is located in the groove.

[0016] In this embodiment, the powder alloy layer 52 is sintered at high temperature on the surface of the first fixing plate 51, and does not expose the outline of the first fixing plate 51. A through hole 3 is formed on the flat plate 1 to form a large frame, and a first fixing plate 51 and a second fixing plate 53 form a small frame. The two second fixing plates 53 are connected and fitted together by a connector, so that the powder alloy layers 52 of the two powder alloy fan-shaped pieces 5 are set back to back, that is, the two powder alloy fan-shaped pieces 5 are installed back to back in the through hole 3. In the axial direction, the steps on the two powder alloy fan-shaped pieces 5 are aligned to form a groove, and the boss 4 is located in the groove. The side of the powder alloy fan-shaped piece 5 is fitted with the side wall of the through hole 3, so that the powder alloy fan-shaped piece 5 and the large frame are in circumferential surface contact. When braking, the braking torque is transmitted to the large frame through the small frame. Compared with the previous rivets and rivet holes, the force is transmitted through the contact surface of the small frame and the large frame. Since the contact area is controllable, the accuracy of the calculation results is higher and more conducive to design. When braking, the circumferential force is borne by the small frame and the large frame together, and the connector connecting the two powder alloy fan-shaped pieces 5 is not subjected to shear force, so there will be no fastener breakage or foreign object problems, which is beneficial to improving the safety of the aircraft.

[0017] In this embodiment, the thickness of the flat plate 1 is greater than twice the total thickness of the first fixing plate 51 and the second fixing plate 53, meaning the thickness of the large frame is greater than twice the thickness of the small frame, but less than twice the thickness of the powder alloy fan-shaped sheet 5. In this embodiment, the amount by which the sum of the thicknesses of the two powder alloy fan-shaped sheets 5 exceeds the thickness of the large frame is the single-sided wear amount of the brake disc, which can be determined based on wear life requirements and wear rate. The two powder alloy fan-shaped sheets 5 are bonded back-to-back, with the powder alloy layer 52 protruding from the plane of the large frame. The total thickness of the brake disc is equal to the sum of the thicknesses of the two powder alloy fan-shaped sheets 5. Compared to the previous method where the total thickness of the brake disc was equal to the sum of the thicknesses of two powder alloy brake discs and the large frame, this reduces the thickness of the large frame.

[0018] The height of the step is greater than 0.5 times the thickness of the boss 4, with a difference of 0.02-0.05mm. The sum of the step heights of the two small frames is slightly greater than the thickness of the boss 4 in the fan-shaped groove of the large frame, so that after riveting, the two powder alloy fan-shaped pieces 5 are in contact, rather than suspended. This ensures that the total thickness of the brake disc is independent of the frame thickness, and at the same time, it allows for a small axial gap between all the powder alloy fan-shaped pieces 5 and the large frame, resulting in good assembly consistency of the powder alloy fan-shaped pieces 5.

[0019] Specifically, the connecting components include a rivet 6 and a sleeve 7; such as Figure 8-9 As shown, the rivet 6 includes a truncated cone 61, with a connecting rod 62 and a ring 63 connected sequentially to the small-diameter end of the truncated cone 61. A blind hole is provided inside the ring 63, and the outer diameter of the ring 63 is smaller than the outer diameter of the connecting rod 62. The total length of the connecting rod 62 and the ring 63 is equal to the length of the sleeve 7. Figure 10-11As shown, the sleeve 7 includes a tapered first sleeve 71, with a second sleeve 72 connected to the small-diameter end of the first sleeve 71. The first sleeve 71 and the second sleeve 72 are respectively sleeved on the outer side of the annular platform 63 and the connecting rod 62, and are riveted to make the annular platform 63 fit against the inner side of the first sleeve 71. Multiple rivet holes 8 are provided on the powder alloy fan-shaped sheet 5; in each through hole 3, the tapered platform 61 is located in the countersunk hole of the rivet hole 8 of one of the powder alloy fan-shaped sheets 5, and the first sleeve 71 is located in the countersunk hole of the rivet hole 8 of another powder alloy fan-shaped sheet 5.

[0020] In this embodiment, the diameter of the connecting rod 62 is equal to the inner diameter of the second sleeve 72; the outer diameter of the ring platform 63 is slightly smaller than the diameter of the connecting rod 62 by 0.2-0.4 mm; the blind hole in the ring platform 63 is used to withstand deformation during riveting. The depth of the blind hole is equal to the length of the ring platform 63 and should not be too deep to prevent deformation of the connecting rod 62 during riveting. The inner conical surface of the first sleeve 71 acts as a limit when riveting the ring platform 63. The ring platform 63 fits tightly with the conical inner wall of the first sleeve 71 to achieve axial positioning and radial locking, thus fixing the sleeve 7 and the rivet 6 together. The outer diameter of the second sleeve 72 is 0.1-0.3 mm smaller than the minimum inner diameter of the rivet hole 8, typically 0.2 mm. Two powder alloy sector-shaped pieces 5 are fastened together using rivets 6 and sleeves 7. During riveting, only the semi-hollow part of the ring platform 63 undergoes plastic deformation, and after deformation, it fits into the first sleeve 71, preventing the powder alloy brake disc from detaching in the thickness direction. No upsetting deformation occurs at the connecting rod 62. Therefore, after riveting, a small gap always exists between the two powder alloy sector-shaped pieces 5 and the rivets 6 and sleeves 7, resulting in good assembly consistency of the powder alloy sector-shaped pieces 5. In this embodiment, the brake disc bears axial clamping force during braking, with the two powder alloy sector-shaped pieces 5 fitting back-to-back to transmit force. When not braking, there is a small gap between the brake discs. The fastening method using rivets 6 and sleeves 7 ensures that the two powder alloy sector-shaped pieces 5 do not detach, allowing the brake disc of this invention to be used normally both when braking and not braking.

[0021] The brake disc of this invention is suitable for structures where the drive key is on the outer or inner circumference; and it is applicable not only to aircraft brake wheels, but also to clutches and other mechanical equipment requiring brake discs, thus possessing strong practicality. The assembly method is as follows: like Figure 12-13As shown, when assembling the brake disc, two powder alloy sector pieces 5 are installed back-to-back in the through holes 3 of the large frame. The small frames of the two powder alloy sector pieces 5 are fitted together. In the axial direction, the steps of the small frames of the two powder alloy sector pieces 5 align to form a groove. The boss 4 of the large frame is located in the groove. The side of the powder alloy sector piece 5 fits against the side of the sector groove of the large frame. The rivet 6 is passed through the rivet holes 8 of the two powder alloy sector pieces 5 in sequence. The sleeve 7 is inserted from one end of the ring 63 into the rivet holes 8 of the two powder alloy sector pieces 5 and sleeved on the outside of the connecting rod 62. Through riveting, the ring 63 is deformed and fitted against the inner conical surface of the first sleeve 71. Using the same assembly method, a total of 2n powder alloy sector pieces 5 are assembled onto the brake disc, and the brake disc assembly is completed.

[0022] Example On a single brake disc, there is a large frame, 32 powder alloy fan-shaped pieces, 16 rivets, and 16 sleeves.

[0023] The step height h1 is 1.25mm, the total thickness δ1 of the small skeleton is 3.75mm, the thickness δ2 of the powder alloy fan-shaped sheet 5 is 5.3mm, the axial contact length between the powder alloy fan-shaped sheet 5 and the large skeleton is 89mm, and the minimum inner diameter φ1 of the riveting part of the rivet hole 8 is 5.2mm. The thickness δ3 of the large skeleton 2 is 8mm, the number of through holes 3 is n=16, and the thickness h2 of the boss 4 is 2mm.

[0024] In this embodiment, there are four riveting holes, forming an isosceles trapezoid. The total length L2 of the connecting rod 62 and the ring platform 63 is 4.2 mm, the diameter φ2 of the connecting rod 62 is 4.2 mm, the outer diameter φ3 of the ring platform 63 is 4 mm, and the length L4 of the ring platform 63 is 1.5 mm (the height L5 of the first sleeve 71 is 1.5 mm). The outer diameter of the second sleeve 72 is 5 mm.

[0025] After assembling the above parts, the axial gap between the small skeletons of the two powder alloy sector plates 5 and the large skeleton is 0.5mm, ensuring that the small skeletons of the powder alloy sector plates 5 are in contact. The thickness of the powder alloy sector plate 5 protruding from the large skeleton is 1.3mm, which is the design wear allowance, based on a wear rate of 2×10⁻⁶. -3 mm / face·time, calculated wear-resistant cycles are 650.

[0026] The total thickness of the powder alloy brake disc is 10.6mm, which is significantly thinner than that of similar brake discs.

[0027] The contact area between a single powder alloy fan-shaped sheet 5 and the large frame is S = δ1 × L1 = 333.75 mm. 2Assuming the pressure transmitted between a single powder alloy fan-shaped sheet 5 and the large frame is 10000N, the compressive stress at the contact surface is calculated as P=F÷S=29.96MPa. Ordinary steel can meet this strength requirement.

[0028] like Figure 14-15 As shown, in this embodiment, the brake disc 100 is located inside the pressure disc 200 and the pressure bearing disc 300. When braking, it bears the axial clamping force and transmits the axial braking force through the powder alloy fan-shaped sheet 5. When braking, the powder alloy fan-shaped sheet 5 bears the braking force and transmits the braking force to the large frame through the side.

[0029] The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. A brake disc for an aircraft brake wheel, characterized in that, include: A ring-shaped flat plate has multiple fan-shaped through holes along its circumference, and protrusions are formed on the two radially opposite sidewalls of the through holes respectively; Two powder alloy sector-shaped plates are provided in each through hole; The powder alloy fan-shaped sheet includes a fan-shaped first fixing plate, one surface of which is covered with a powder alloy layer, and the other surface is connected to a second fixing plate. The length of the second fixing plate is smaller than that of the first fixing plate, and steps are formed on opposite sides. The two second fixing plates are connected by a connector, and a groove that matches the boss is formed between the two first fixing plates, with the boss located in the groove.

2. The brake disc of the aircraft brake wheel according to claim 1, characterized in that, The thickness of the plate is greater than twice the total thickness of the first and second fixing plates, but less than twice the thickness of the powder alloy fan-shaped sheet.

3. The brake disc of the aircraft brake wheel according to claim 1, characterized in that, The height of the step is greater than 0.5 times the thickness of the boss, and the difference is 0.02-0.05 mm.

4. The brake disc of the aircraft brake wheel according to claim 1, characterized in that, The connector includes a rivet rod and a sleeve. The rivet rod passes through two powder alloy sector plates, and the sleeve is fitted onto the outside of the rivet rod.

5. The brake disc of the aircraft brake wheel according to claim 4, characterized in that, The rivet includes a truncated cone, and a connecting rod and a ring are connected in sequence to the small-diameter end of the truncated cone. A blind hole is opened in the ring, and the outer diameter of the ring is smaller than the outer diameter of the connecting rod. The total length of the connecting rod and the ring platform is equal to the length of the sleeve; The sleeve includes a tapered first sleeve, and a second sleeve is connected to the small-diameter end of the first sleeve; The first sleeve and the second sleeve are respectively sleeved on the outside of the ring platform and the connecting rod, and the ring platform is fitted to the inside of the first sleeve by riveting.

6. The brake disc of the aircraft brake wheel according to claim 5, characterized in that, The powder alloy fan-shaped sheet has multiple rivet holes; Within each through-hole, the cone is located within the countersunk hole of the rivet hole of one of the powder alloy sector pieces, and the first sleeve is located within the countersunk hole of the rivet hole of the other powder alloy sector piece.

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