CN107701621B - Steel brake disc of aircraft wheel and manufacturing method - Google Patents
Steel brake disc of aircraft wheel and manufacturing method Download PDFInfo
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- CN107701621B CN107701621B CN201711161953.6A CN201711161953A CN107701621B CN 107701621 B CN107701621 B CN 107701621B CN 201711161953 A CN201711161953 A CN 201711161953A CN 107701621 B CN107701621 B CN 107701621B
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- brake disc
- sector
- riveting
- groove
- key
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D65/00—Parts or details
- F16D65/02—Braking members; Mounting thereof
- F16D65/12—Discs; Drums for disc brakes
- F16D65/121—Discs; Drums for disc brakes consisting of at least three circumferentially arranged segments
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J15/00—Riveting
- B21J15/10—Riveting machines
- B21J15/14—Riveting machines specially adapted for riveting specific articles, e.g. brake lining machines
- B21J15/142—Aerospace structures
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D65/00—Parts or details
- F16D65/02—Braking members; Mounting thereof
- F16D65/12—Discs; Drums for disc brakes
- F16D65/123—Discs; Drums for disc brakes comprising an annular disc secured to a hub member; Discs characterised by means for mounting
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D65/00—Parts or details
- F16D65/02—Braking members; Mounting thereof
- F16D2065/13—Parts or details of discs or drums
- F16D2065/1304—Structure
- F16D2065/1312—Structure circumferentially segmented
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D65/00—Parts or details
- F16D65/02—Braking members; Mounting thereof
- F16D2065/13—Parts or details of discs or drums
- F16D2065/134—Connection
Abstract
A steel brake disc for the airplane wheel of airplane is composed of 8-12 segments, and the convex lugs on the external arc surfaces of two ends of each segment. And two side surfaces of each sector are respectively connected with the side surfaces of other sectors. When the segments are connected, a groove is formed between lugs of two adjacent segment ends; key grooves are respectively arranged in the grooves through rivets, and the segments are connected and combined through the key grooves to form the annular steel brake disc of the aircraft wheel. The invention avoids additional assembly stress, thermal stress and stress concentration by optimizing and selecting reasonable clearance and switching radius R; and simultaneously improves the riveting process to improve the riveting consistency and the riveting quality. The invention has good operation, no abnormal connection of the key and the groove, reasonable stress of the brake disc, uniform abrasion, no warping and deformation clamping stagnation, and can reach or partially exceed the technical specification requirements of products and prolong the service life of the brake disc.
Description
Technical Field
The invention relates to the field of aircraft wheel brake devices. In particular to a small block type aircraft wheel steel brake disc and a manufacturing method thereof.
Background
The aircraft brake disc is a main component of a disk type brake wheel brake device of an aircraft landing gear, and comprises a movable disk and a static disk, wherein the movable disk is a brake disc capable of rotating along with a wheel, and the static disk is a brake disc incapable of rotating along with the wheel. The surface of the static disc of the aircraft steel brake is provided with a powder metallurgy friction material, the surface of the movable disc is usually not provided with the powder metallurgy friction material and is used as a friction couple of the static disc, and a pair of friction surfaces are formed during braking to generate braking torque so as to decelerate and brake the aircraft brake. The movable disc used for the aircraft steel brake has an integral structural formula and a small structural formula, the integral structural formula is easy to warp and deform, the movable disc is stuck in severe cases and is not suitable for large-energy-load application occasions, and the small structural formula has the advantage of obvious small warping deformation, so that the movable disc is applied more, particularly on large-scale, heavy-load and high-speed aircraft wheel brake devices.
The small block structure is made by dividing a whole brake disc into a plurality of same small brake blocks, namely brake blocks, usually fan-shaped blocks, equally in the circumferential direction, and the plurality of same small blocks are connected and combined into the whole brake disc through a connecting device comprising a ring, a lug and the like. The connecting ring is thin in thickness, low in rigidity and easy to deform and break; the spliced connecting ring is too loose to connect with a brake disc, so that the wheel is inconvenient to assemble and disassemble, and the problems of deformation and brake block separation and blocking also exist; the lug is positioned on the central circumference of the small friction ring belt of the brake disc, is greatly influenced by high brake temperature and thermal shock, has short service life and is easy to have the connection failure of the rivet and the lug; the tenon-and-mortise nested connection is formed by that a protruding lug or a round head is arranged in the middle of one end of each sector, a groove or a concave groove is formed in the other end of each sector, and the protruding lug or the round head is inserted into the groove or the concave groove of the adjacent sector, so that the integrity is poor, the frame is easy to be scattered, and the assembly and disassembly of an outfield on a airplane wheel are inconvenient. The brake disc adopting the small block structure connected by the ring, the lug, the mortise and tenon and the like has obvious defects and limited application.
The key connection of the groove type key groove key, also called the connection block, is a connection with better integrity, overcomes the defects of the connection form of the small blocks, and is considered to be ideal in application. The brake disc is arranged on the outer circumference of a brake disc, and the brake disc blocks are connected into an integral brake disc by key grooves riveted on the brake blocks. The keyway key connection not only serves to connect the brake disc segments into a unitary brake disc, but the keyway key also cooperates with the wheel key, commonly referred to as a guide rail, to transmit motion and torque. However, in application, the structural design is found to have the defects that the riveting is too tight, the gap between the bottom of the key groove and the brake block is too small or no gap exists, the brake block is directly abutted, and a necessary movable gap is lacked, so that the structural rigidity of the brake disc is too large, the advantages of the small block structure are greatly weakened, the key groove and the rivet are subjected to additional assembly stress and huge thermal deformation and thermal shock stress in a brake, the rivet and key groove connection is early failed, and the use safety is endangered. In practical application of an external field, cracks and fracture faults of key grooves and rivets occur for many times when the key grooves of the aircraft steel brake disc such as Boeing 737 are connected.
Us patent 3550740 discloses a small block type friction brake disc, which is connected by a key groove (connecting block) (referred to as torque link) riveted on a small block (fan block) of the brake disc, wherein the riveting of the key groove has a hinging characteristic, the limited relative displacement of the fan block is allowed, certain flexibility is noticed while the rigidity of the small block type brake disc is increased, but the patent does not give a specific value of a gap between a rivet and a rivet hole and the degree (magnitude and detection method) of the relative displacement of the fan block after riveting, and the problem that the bottom of the key groove (connecting block) and the fan block of the brake disc are directly abutted without a gap or an excessively small gap exists.
US 4747473 discloses a small block type friction brake disc, which is connected by offset, i.e. antisymmetric key slot (connecting block) riveted on the small block (sector) of the brake disc, the lugs of the sector block are axially offset, the end parts of the adjacent sector blocks are overlapped, and the sector blocks are fastened by rivets. In addition, the end part of the sector block is lapped, so that the structure is complex, the processing and the manufacturing are not facilitated, and the possibility of brake vibration is caused.
The problem that the rigidity of the connection of a small structural brake disc connected by the existing groove type key groove key is too high brings that the key groove and the rivet bear extra assembly stress and huge thermal deformation and thermal shock stress in a brake, and the problem is a potential threat to the normal safe operation of an airplane, and the problem is urgently needed to be fundamentally solved from the design and the manufacture.
Disclosure of Invention
In order to overcome the defects of potential safety hazards caused by extra assembly stress borne by key grooves and rivets and huge thermal deformation and thermal impact stress in a brake in the prior art, the invention provides a steel brake disc for an aircraft wheel and a manufacturing method thereof.
The invention comprises 8-12 fan-shaped blocks, key slots with the same number as the fan-shaped blocks and countersunk rivets with the number twice that of the fan-shaped blocks. Wherein: and the outer circular arc surfaces of the fan-shaped blocks close to the two ends are provided with lugs protruding in the radial direction. And two side surfaces of each sector are respectively connected with the side surfaces of other sectors. When the segments are connected, a groove is formed between the lugs of two adjacent segment ends; key grooves are respectively arranged in the grooves through rivets, and the segments are connected and combined through the key grooves to form the annular steel brake disc of the aircraft wheel.
And a fit clearance of 1.2-2.5 mm is reserved between the side surfaces of two adjacent fan-shaped blocks for circumferential expansion. The lower surface of the key groove and the plane on the outer circumference of the fan-shaped block are implemented by a fit clearance of 1.5-2.5 mm.
Planes are processed at two ends of each sector block, which are close to the outer circumferential surface of the sector block, and the planes are respectively provided with lugs which protrude in the radial direction, and the two lugs are staggered front and back in the axial direction of the sector block, namely, one lug is positioned at one end of the outer circumferential surface of the brake disc of the formed aircraft wheel steel brake disc, and the other lug is positioned at the other end of the outer circumferential surface of the brake disc of the formed aircraft wheel steel brake disc; the axial length of the two lugs is 1/2 of the axial length of the fan-shaped block. The circumferential surfaces of the segments outside the two lugs of each segment are processed into planes to form a key groove mounting surface.
The key groove is in a block shape. The lower surface of the key groove is a plane, and the upper surface of the key groove is an arc surface. And the middle part of the upper surface is provided with a U-shaped groove which is a medium for cross-linking the brake disc and the brake wheel and is used for matching with the brake wheel hub guide rail. The inner wall surfaces of two sides of the U-shaped groove are vertical to the groove bottom surface of the U-shaped groove, and arc transition is carried out between the inner wall surfaces and the groove bottom surface; the radius R of the arc is adaptive to the hub guide rail and cannot interfere with the hub guide rail; r =1.5-2.8mm. Convex connecting plates are arranged on two sides of the outer surface of the groove wall of the U-shaped groove, and the connecting plates on the two sides are in reverse symmetry, so that the connecting plates can be respectively matched with planes at two ends of the sector. Rivet holes are respectively arranged on the two connecting plates, and the aperture of each rivet hole is slightly larger than the diameter of the countersunk head rivet.
The rivet hole is a cylindrical counter bore, and the large-bore end of the cylindrical counter bore is positioned on the outer surface of the connecting plate; the large hole bottom surface of the cylindrical counter bore is in chamfer transition with the small hole diameter end of the cylindrical counter bore; the chamfer angle is 30-60 degrees.
The axial dimension of the key groove is equal to the axial dimension of the sector, or is 0.5-1 mm smaller than the thickness of the sector, and two ends of the key groove are not higher than two sector surfaces of the sector after assembly. Two parallel sector planes of the sector are used as friction surfaces, and the sector friction surfaces of a plurality of identical sectors form the friction surface of a brake disc and are used as a pair of a brake disc static disc in the brake device.
The fan-shaped blocks are made of single metal or double metals.
The method comprises the following steps of (1) assembling the steel brake disc of the aircraft wheel during the assembling:
step 1, preparing parts. Blanking and processing the fan-shaped blocks, the key grooves and the rivets according to the design pattern requirements, and carrying out matched riveting according to the required quantity of brake discs of each disc after the inspection is qualified;
and 2, riveting. And riveting the key slot and the fan-shaped blocks together by spin riveting on a spin riveting machine, and forming the plurality of fan-shaped blocks into a circular integral brake disc.
The spin riveting process parameters are as follows:
main shaft rotating speed: 750 to 1440r/min
Riveting pressure: 6 to 25Kn
Riveting time: 3.5-10s;
when a part is riveted and placed, the inner arcs of the two segments, namely the first segment and the second segment, face to the same side, the side end lugs of the two segments are opposite, the bottom surface of the key groove faces to the top surface of the segments, and the outer side wall of the key groove is attached to the side wall surface of the lug of the segments; riveting a third sector block, namely riveting the third sector block, wherein the first sector block is riveted with the second sector block; this operation is repeated, riveting one by one, riveting the last segment to the first segment.
The riveted segments are able to rotate about the rivet; when the last sector is riveted, the rivet can be freely sleeved on the key slot and the hole of the sector; the integral brake disc has proper tightness degree, specifically, the brake disc is placed on a platform, 50-100N force is applied to radially press or pull the brake disc, and the deflection deformation of the integral brake disc is 10-30mm.
And 3, grinding a plane. And (3) grinding the plane of the riveted integral brake disc on a grinding machine to achieve the flatness required by the whole designed disc, wherein the flatness range is 0.1-0.25mm, and thus obtaining the small-block type aircraft wheel steel brake disc.
The technical approach adopted by the invention is as follows: firstly, the design is optimized, reasonable gaps and transfer radiuses R are selected, and additional assembly stress, thermal stress and stress concentration are avoided; and secondly, riveting is improved, and riveting consistency and riveting quality are improved by adopting spin riveting.
The invention combines a plurality of same fan-shaped blocks into an annular brake disc through key grooves, and then the planes of two surfaces are ground to obtain a finished product of the small block type aircraft wheel steel brake disc.
The invention selects reasonable clearance and transfer radius R, avoids additional assembly stress, thermal stress and stress concentration; meanwhile, riveting is improved, and riveting consistency and riveting quality are improved by adopting a spin riveting technology. A gap is reserved between the rivet and the rivet hole, so that adjacent fan-shaped blocks can rotate properly relative to the rivet; a gap is reserved between the outer surface of the bottom end of the key groove and the sector block, and brake force transmission is mainly transmitted to the side wall of a lug of the sector block through the side wall of the key groove, so that not only is the riveting assembly stress of a brake disc eliminated, but also the huge stress of the thermal deformation action of the sector block on the key groove and a rivet when the brake disc is used, particularly during heavy braking and high-strength braking, is eliminated, and the fatigue failure of the key groove key connection caused by thermal shock and thermal deformation additional stress is effectively prevented. The invention also provides a spin-riveting assembly method, spin-riveting technological parameters and an integral brake disc tightness checking method, and realizes rigid and flexible design and manufacturing of the small block type aircraft wheel steel brake disc. The invention has reasonable structure and feasible process, can effectively solve the problem that the connection failure of the steel brake disc of the small-block type aircraft wheel endangers the flight safety, and improves the service life, the safety and the economic benefit of the aircraft wheel product. Through bench performance test, service life test, high-kinetic energy brake test and take-off stopping test, the steel brake disc of the invention has good operation, no abnormal connection of the key slot and the key, reasonable stress of the brake disc, uniform abrasion, no phenomena of warping, deformation, clamping stagnation and the like, and meets or partially exceeds the technical specification requirement of products; the product is delivered to an outfield for use, no broken rivet, broken key groove and stuck fault report exists, the service life is obviously prolonged, and the product can still be used after 3 times of the prior art.
Drawings
FIG. 1 is a partial view of the present invention;
FIG. 2 is a partial view of the keyway coupling of FIG. 1;
FIG. 3 is a sector block diagram;
FIG. 4 is a partial view of FIG. 3P;
FIG. 5 is a partial view of FIG. 3K;
FIG. 6 is a key slot perspective view;
FIG. 7 is a keyway view;
fig. 8 isbase:Sub>A cross-sectional view of fig. 7A-base:Sub>A. In the figure:
1. a sector block; 2. a key slot; 3. countersunk rivets; 4. a sector lug; 5. a key groove mounting surface; 6. the outer surface of the bottom of the groove; 7. and (6) rivet holes.
Detailed Description
This embodiment is a modified fritter formula aircraft wheel steel brake disc, includes: 8-12 segments 1, key slots 2 with the same number as the segments and countersunk rivets 3 with twice the number of the segments. Wherein: and the outer circular arc surfaces of the fan-shaped blocks close to the two ends are provided with lugs protruding in the radial direction. Two side surfaces of each sector are respectively connected with side surfaces of other sectors. When the segments are connected, a groove is formed between lugs at the ends of two adjacent segments 1; key grooves 2 are respectively arranged in the grooves through rivets 3, and the segments 1 are connected and combined through the key grooves to form an annular aircraft wheel steel brake disc.
A fit clearance of 1.2-2.5 mm, in this embodiment 2mm, is reserved between the side surfaces of two adjacent segments 1 for circumferential expansion.
The matching requirement between each key slot and each sector is that a 1.5-2.5 mm matching clearance, 2mm in the embodiment, is formed between the lower surface of the key slot 2 and the plane on the outer circumference of the sector 1.
In this embodiment, the number of the segments and the number of the key slots 2 are 9, and the number of the countersunk head rivets is 18.
The sector block 1 is a sector block made of single metal or bimetal. Two parallel sector planes of the sector 1 are used as friction surfaces, and the sector friction surfaces of a plurality of identical sectors form the friction surface of a brake disc and are used as a pair of a brake disc static disc in the brake device.
Planes are processed at two ends of each sector 1, which are close to the outer circumferential surface of the sector, and radially protruding lugs are respectively arranged on the planes, and the two lugs are staggered front and back in the axial direction of the sector, namely, one lug is positioned at one end of the outer circumferential surface of the formed aircraft wheel steel brake disc, and the other lug is positioned at the other end of the outer circumferential surface of the formed aircraft wheel steel brake disc; the axial length of the two lugs is 1/2 of the axial length of the fan-shaped block. The circumferential surfaces of the segments outside the two lugs of each segment are machined to be flat surfaces, and a key groove mounting surface 5 is formed.
In this embodiment, the segments are formed by stamping a single metal alloy steel plate.
The key groove 2 is in a block shape. The lower surface of the key groove is a plane, and the upper surface of the key groove is an arc surface. And the middle part of the upper surface is provided with a U-shaped groove which is a medium for cross-linking the brake disc and the brake wheel and is used for matching with the brake wheel hub guide rail. The inner wall surfaces of two sides of the U-shaped groove are vertical to the groove bottom surface of the U-shaped groove, and arc transition is carried out between the inner wall surfaces and the groove bottom surface; the radius R of the circular arc is adaptive to the hub guide rail and cannot interfere with the hub guide rail; r =1.5-2.8mm. In this example, R =2.5mm. Convex connecting plates are arranged on two sides of the outer surface of the groove wall of the U-shaped groove, and the connecting plates on the two sides are in reverse symmetry, so that the connecting plates can be respectively matched with planes at two ends of the sector. Rivet holes 22 are respectively formed in the two connecting plates, and the diameter of each rivet hole is slightly larger than the diameter of the countersunk rivet.
The rivet hole 22 is a cylindrical counter bore, and the large-bore end of the cylindrical counter bore is positioned on the outer surface of the connecting plate; the large hole bottom surface of the cylindrical counter bore is in chamfer transition with the small hole diameter end of the cylindrical counter bore; the chamfer angle is 30-60 deg., 45 deg. being selected in this embodiment.
The axial dimension of the key groove is equal to the axial dimension of the sector block 1, or is 0.5-1 mm smaller than the thickness of the sector block 1, and two ends of the key groove 2 are not higher than two sector surfaces of the sector block 1 after assembly. In the embodiment, the alloy steel forging is adopted for manufacturing; the axial dimension of the key slot is equal to the axial dimension of segment 1.
In the embodiment, the side surface of one sector block 1 is spliced with the side surface of the other sector block, and a circumferential expansion gap of 2mm is reserved between the two sector blocks; a key groove is embedded in a groove formed between the adjacent lugs of the two segments and is connected through a countersunk rivet. And a radial expansion gap of 2mm is formed between the lower surface of the connected key groove 2 and the plane of the circumferential surface of the segment. And repeating the above process, and respectively splicing the 9 fan-shaped blocks and connecting the fan-shaped blocks through the key grooves to obtain the annular steel brake disc of the aircraft wheel. The brake disc is pressed or pulled in the radial direction, and each sector block can rotate relative to the rivet; a gap is reserved between the bottom end face of the key groove and the fan-shaped block, and a gap is reserved between the rivet and the rivet hole. In use, the brake torque is mainly transmitted to the side wall of the lug of the sector block by the side wall of the key groove, so that the riveting assembly stress of the brake disc is eliminated, the huge stress of the thermal deformation action of the sector block on the key groove and the rivet when in use, particularly heavy braking and high-strength braking, is eliminated, and the fatigue failure of the key groove key connection caused by thermal shock and thermal deformation additional stress is effectively prevented.
The assembly manufacturing method of the embodiment includes:
step 1, preparing parts. Blanking and processing the sector, the key slot and the rivet according to the design pattern requirement, and carrying out matched riveting according to the required quantity of brake discs of each disc after the test is qualified;
and 2, riveting. And riveting the key slot 2 and the fan-shaped blocks 1 together by spin riveting on a spin riveting machine, and forming a circular integral brake disc by the plurality of fan-shaped blocks 1. The spin riveting process parameters are as follows:
main shaft rotating speed: 750-1440r/min
Riveting pressure: 6-25Kn
Riveting time: 3.5-10s;
the diameter of the rivet of this embodiment is phi 6.5mm steel rivet, rivets with hydraulic pressure spin riveting machine, and spin riveting technological parameter: the rotation speed of the main shaft is 1000r/min, the riveting pressure is 10Kn, and the riveting time is 5s;
when a part is riveted and placed, the inner arcs of the two segments, namely the first segment and the second segment, face to the same side, the side end lugs of the two segments are opposite, the bottom surface of the key groove faces to the top surface of the segments, and the outer side wall of the key groove is attached to the side wall surface of the lug of the segments; riveting a third sector block, namely riveting the third sector block, wherein the first sector block is riveted with the second sector block; this operation is repeated, riveting one by one, riveting the last segment to the first segment. The number of the fan-shaped blocks is 9, namely, the ninth fan-shaped block is riveted on the first fan-shaped block, and a plurality of fan-shaped blocks are riveted into an integral brake disc with proper tightness;
the riveted segments can rotate around the rivet; when the last sector is riveted, the rivet can be freely sleeved on the key slot and the hole of the sector; the integral brake disc has proper tightness degree;
the tightness degree checking method of the integral brake disc is that the brake disc is placed on a platform, 50-100N force is applied to radially press or pull the brake disc, and the deflection deformation of the integral brake disc is 10-30mm.
And 3, grinding a plane. And (3) grinding the plane of the riveted integral brake disc on a grinding machine to achieve the flatness required by the whole disc of the design pattern, wherein the flatness range is 0.1-0.25mm, and the flatness required by the whole disc of the embodiment is 0.2mm, so that the finished product of the small block type aircraft wheel steel brake disc is obtained.
Claims (5)
1. The steel brake disc for the airplane wheel of the aircraft is characterized by comprising 8-12 fan-shaped blocks, key grooves with the number equal to that of the fan-shaped blocks and countersunk rivets with the number twice that of the fan-shaped blocks; wherein: the outer arc surfaces of the fan-shaped blocks close to the two ends are provided with lugs protruding in the radial direction; two side surfaces of each sector are respectively connected with side surfaces of other sectors; when the segments are connected, a groove is formed between the lugs of two adjacent segment ends; key grooves are respectively arranged in the grooves through rivets, and the fan-shaped blocks are connected and combined through the key grooves to form an annular aircraft wheel steel brake disc; a fit clearance of 1.2-2.5 mm is reserved between the side surfaces of two adjacent fan-shaped blocks for circumferential expansion; a fit clearance of 1.5-2.5 mm is formed between the lower surface of the key slot and the plane on the outer circumference of the fan-shaped block;
planes are processed at two ends of each sector block, which are close to the outer circumferential surface of the sector block, and lugs which protrude in the radial direction are respectively arranged on the planes, and the two lugs are staggered front and back in the axial direction of the sector block, namely, one lug is positioned at one end of the outer circumferential surface of the formed aircraft wheel steel brake disc, and the other lug is positioned at the other end of the outer circumferential surface of the formed aircraft wheel steel brake disc; the axial length of the two lugs is 1/2 of the axial length of the fan-shaped block; the circumferential surfaces of the segments outside the two lugs of each segment are processed into planes to form a key groove mounting surface;
the specific process of the assembling and manufacturing method of the aircraft wheel steel brake disc comprises the following steps:
step 1, preparing parts; blanking and processing the sector, the key slot and the rivet according to the design pattern requirement, and carrying out matched riveting according to the quantity required by each brake disc after the test is qualified;
step 2, riveting; riveting the key groove and the fan-shaped blocks together by spin riveting on a spin riveting machine, and forming a plurality of fan-shaped blocks into an annular integral brake disc;
the spin riveting process parameters are as follows:
main shaft rotating speed: 750 to 1440r/min
Riveting pressure: 6 to 25Kn
Riveting time: 3.5-10s;
when a part is riveted and placed, the inner arcs of the two segments, namely the first segment and the second segment, face to the same side, the lugs at the side ends of the two segments are opposite, the bottom surface of the key groove faces to the top surface of the segments, and the outer side wall of the key groove is attached to the side wall surface of the lug of the segments; riveting a third sector block, namely riveting the third sector block, wherein the first sector block is riveted with the second sector block; repeating the operation, riveting one by one, and riveting the last segment to the first segment;
the riveted segments can rotate around the rivet; when the last sector is riveted, the rivet can be freely sleeved on the key slot and the hole of the sector; the integral brake disc has proper tightness degree, specifically, the brake disc is placed on a platform, 50-100N force is applied to radially press or pull the brake disc, and the deflection deformation of the integral brake disc is 10-30 mm;
step 3, grinding a plane; and (3) grinding the plane of the riveted integral brake disc on a grinding machine to achieve the flatness required by the design pattern integral disc, wherein the flatness range is 0.1-0.25mm, and thus obtaining the small block type aircraft wheel steel brake disc.
2. An aircraft wheel steel brake rotor as claimed in claim 1, wherein said keyway is block-shaped; the lower surface of the key groove is a plane, and the upper surface of the key groove is a cambered surface; a U-shaped groove is formed in the middle of the upper surface, is a medium for cross-linking a brake disc and a brake wheel, and is used for matching with a brake wheel hub guide rail; the inner wall surfaces of two sides of the U-shaped groove are vertical to the groove bottom surface of the U-shaped groove, and arc transition is carried out between the inner wall surfaces and the groove bottom surface; the radius R of the arc is adaptive to the hub guide rail and cannot interfere with the hub guide rail; r =1.5-2.8mm; the two sides of the outer surface of the groove wall of the U-shaped groove are provided with convex connecting plates, and the connecting plates at the two sides are in reverse symmetry, so that each connecting plate can be respectively matched with the planes at the two ends of the fan-shaped block; rivet holes are respectively arranged on the two connecting plates, and the aperture of each rivet hole is slightly larger than the diameter of the countersunk head rivet.
3. An aircraft wheel steel brake disc rotor as claimed in claim 2, wherein the rivet hole is a cylindrical counterbore having a large bore end located on the outer surface of the connecting plate; the large hole bottom surface of the cylindrical counter bore is in chamfer transition with the small hole diameter end of the cylindrical counter bore; the chamfer angle is 30-60 degrees.
4. An aircraft wheel steel brake disc rotor as claimed in claim 1, wherein the axial dimension of the key slot is equal to the axial dimension of the sector, or 0.5-1 mm less than the thickness of the sector, and the two ends of the key slot are not higher than the two sectors of the sector after assembly; two parallel sector planes of the sector are used as friction surfaces, and the sector friction surfaces of a plurality of identical sectors form the friction surface of a brake disc and are used as a dual of a brake disc static disc in the brake device.
5. An aircraft wheel steel brake rotor as claimed in claim 1 wherein the segments are formed of a single metal or a bi-metal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711161953.6A CN107701621B (en) | 2017-11-21 | 2017-11-21 | Steel brake disc of aircraft wheel and manufacturing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711161953.6A CN107701621B (en) | 2017-11-21 | 2017-11-21 | Steel brake disc of aircraft wheel and manufacturing method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107701621A CN107701621A (en) | 2018-02-16 |
| CN107701621B true CN107701621B (en) | 2023-04-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201711161953.6A Active CN107701621B (en) | 2017-11-21 | 2017-11-21 | Steel brake disc of aircraft wheel and manufacturing method |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111594559B (en) * | 2020-06-10 | 2021-12-10 | 南京中车浦镇海泰制动设备有限公司 | Split wheel-mounted brake disc |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2206253Y (en) * | 1994-09-30 | 1995-08-30 | 中国航空工业总公司第六二一研究所 | Airplane brake disc |
| CN201037519Y (en) * | 2007-02-09 | 2008-03-19 | 王淑敏 | Undercarriage brake disc |
| CN102042356A (en) * | 2010-12-16 | 2011-05-04 | 西安航空制动科技有限公司 | Steel brake disc with stress release holes |
| CN201884524U (en) * | 2010-11-01 | 2011-06-29 | 陕西蓝太航空设备有限责任公司 | Aircraft carbon brake disc rotor of small-clearance assembly steel clip |
| CN203601561U (en) * | 2013-08-05 | 2014-05-21 | 西安航空制动科技有限公司 | Carbon landing braking wheel |
| CN106218870A (en) * | 2016-04-29 | 2016-12-14 | 西安航空制动科技有限公司 | A kind of single-wheel double-brake brake machine wheel |
| CN106218869A (en) * | 2016-04-29 | 2016-12-14 | 西安航空制动科技有限公司 | A kind of wheel of Contiuum type Twin brakes |
-
2017
- 2017-11-21 CN CN201711161953.6A patent/CN107701621B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2206253Y (en) * | 1994-09-30 | 1995-08-30 | 中国航空工业总公司第六二一研究所 | Airplane brake disc |
| CN201037519Y (en) * | 2007-02-09 | 2008-03-19 | 王淑敏 | Undercarriage brake disc |
| CN201884524U (en) * | 2010-11-01 | 2011-06-29 | 陕西蓝太航空设备有限责任公司 | Aircraft carbon brake disc rotor of small-clearance assembly steel clip |
| CN102042356A (en) * | 2010-12-16 | 2011-05-04 | 西安航空制动科技有限公司 | Steel brake disc with stress release holes |
| CN203601561U (en) * | 2013-08-05 | 2014-05-21 | 西安航空制动科技有限公司 | Carbon landing braking wheel |
| CN106218870A (en) * | 2016-04-29 | 2016-12-14 | 西安航空制动科技有限公司 | A kind of single-wheel double-brake brake machine wheel |
| CN106218869A (en) * | 2016-04-29 | 2016-12-14 | 西安航空制动科技有限公司 | A kind of wheel of Contiuum type Twin brakes |
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| CN107701621A (en) | 2018-02-16 |
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