CN116749940B - Detection and analysis device for aircraft electric brake system and application method thereof - Google Patents
Detection and analysis device for aircraft electric brake system and application method thereof Download PDFInfo
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- CN116749940B CN116749940B CN202311033094.8A CN202311033094A CN116749940B CN 116749940 B CN116749940 B CN 116749940B CN 202311033094 A CN202311033094 A CN 202311033094A CN 116749940 B CN116749940 B CN 116749940B
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- 238000001514 detection method Methods 0.000 title claims abstract description 35
- 238000004458 analytical method Methods 0.000 title claims abstract description 21
- 238000000034 method Methods 0.000 title claims abstract description 10
- 230000003068 static effect Effects 0.000 claims abstract description 26
- 230000000712 assembly Effects 0.000 claims abstract description 25
- 238000000429 assembly Methods 0.000 claims abstract description 25
- 230000001681 protective effect Effects 0.000 claims description 11
- 238000003780 insertion Methods 0.000 claims description 7
- 230000037431 insertion Effects 0.000 claims description 7
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000005299 abrasion Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T17/00—Component parts, details, or accessories of power brake systems not covered by groups B60T8/00, B60T13/00 or B60T15/00, or presenting other characteristic features
- B60T17/18—Safety devices; Monitoring
- B60T17/22—Devices for monitoring or checking brake systems; Signal devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T1/00—Arrangements of braking elements, i.e. of those parts where braking effect occurs specially for vehicles
- B60T1/02—Arrangements of braking elements, i.e. of those parts where braking effect occurs specially for vehicles acting by retarding wheels
- B60T1/06—Arrangements of braking elements, i.e. of those parts where braking effect occurs specially for vehicles acting by retarding wheels acting otherwise than on tread, e.g. employing rim, drum, disc, or transmission or on double wheels
- B60T1/065—Arrangements of braking elements, i.e. of those parts where braking effect occurs specially for vehicles acting by retarding wheels acting otherwise than on tread, e.g. employing rim, drum, disc, or transmission or on double wheels employing disc
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T17/00—Component parts, details, or accessories of power brake systems not covered by groups B60T8/00, B60T13/00 or B60T15/00, or presenting other characteristic features
- B60T17/18—Safety devices; Monitoring
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
- B64C25/44—Actuating mechanisms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T2270/00—Further aspects of brake control systems not otherwise provided for
- B60T2270/40—Failsafe aspects of brake control systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T2270/00—Further aspects of brake control systems not otherwise provided for
- B60T2270/40—Failsafe aspects of brake control systems
- B60T2270/406—Test-mode; Self-diagnosis
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Braking Arrangements (AREA)
Abstract
The invention belongs to the field of aircrafts, and discloses a detection and analysis device of an aircraft electric brake system and a use method thereof, wherein the detection and analysis device comprises a main shaft, detection assemblies are arranged at two ends of the main shaft, reset assemblies are arranged in the two detection assemblies, fixed assemblies are arranged outside the two detection assemblies, a rotating assembly is arranged at the center of the main shaft, brake assemblies are arranged at two ends of the rotating assembly, the detection assemblies comprise first bearings, and the first bearings are movably sleeved on the surface of the main shaft, and the beneficial effects achieved by the invention are that: when the brake static disc is contacted with the brake movable disc, the brake movable disc moves towards the inside of the clamping ring groove, the pressure sensor is pushed through the inner wall of the circular groove, the pressure received by the brake movable disc is intuitively sensed through the pressure sensor in the brake movable disc, so that the pressure received by the brake movable disc can be accurately fed back no matter how the brake disc is worn, and the brake is prevented from being out of control due to error in pressure analysis of a brake system.
Description
Technical Field
The invention belongs to the field of aircrafts, relates to a brake system detection and analysis device and a brake system detection and analysis method, and particularly relates to an aircraft electric brake system detection and analysis device and a use method thereof.
Background
Compared with the traditional braking system, the existing electric braking system senses the motion state and speed of the airplane through a sensor, then transmits the information to a control unit, the control unit calculates the optimal braking force and braking time according to the information, and controls an actuating mechanism to realize braking operation, and in the landing process of the airplane, the electronic braking system can automatically adjust the braking force and time, so that the airplane can be ensured to land stably and can be stopped at a correct position.
The pressure condition of the brake system is needed to be analyzed through a pressure sensor in the use process of the existing aircraft electric brake system, but the existing brake pressure sensor is arranged in brake oil of a brake assembly, when the brake oil is used for boosting a brake static disc, the pressure sensor feeds back pressure to accurately control a booster, but when the brake disc is used, the brake disc is worn, the worn brake disc needs the booster to apply larger pressure to enable a tire to stop in a preset time, the pressure fed back by the pressure sensor is not changed because of the wear, so that the brake system cannot be accurately controlled, the existing brake disc is fixed on a hub, a spindle is fixed on the hub through a bolt, the impact force received when the tire is contacted with the ground easily causes the bolt to loosen, the hub is inclined on the surface of the spindle, and the brake system is invalid.
Disclosure of Invention
The detection and analysis device for the aircraft electric brake system and the application method thereof effectively solve the problem that in the prior art, the pressure sensed by the pressure sensor does not correspond to the actual pressure required by braking due to abrasion of the brake disc.
In order to solve the technical problems, the invention provides the following technical scheme:
the invention provides a detection and analysis device of an aircraft electric brake system, which comprises a main shaft, wherein detection assemblies are arranged at two ends of the main shaft, reset assemblies are arranged in the two detection assemblies, fixed assemblies are arranged outside the two detection assemblies, a rotating assembly is arranged at the center of the main shaft, and brake assemblies are arranged at two ends of the rotating assembly;
the detection assembly comprises a first bearing, the first bearing is movably sleeved on the surface of the main shaft, the first bearing is clamped inside a conical groove, the conical groove is formed in the inner wall of a sleeve, a clamping ring groove is formed in one side wall of the sleeve, a plurality of fixed cylinders are annularly embedded in the inner wall of the clamping ring groove, pressure sensors are embedded in the fixed cylinders, the pressure sensors are inserted in a plurality of circular grooves, the circular grooves are formed in one side wall of the same brake disc, and hubs are fixedly sleeved on the outer wall of the sleeve.
As a preferable technical scheme of the invention, the reset assembly comprises a fixed ring, the fixed ring is fixedly connected to the inner wall of the clamping ring groove, the fixed ring is inserted into the ring slot, the ring slot is arranged on the side wall of the brake disc, a plurality of sliding grooves are formed in the outer wall of the fixed ring at equal intervals, sliding bolts are slidingly connected to the inner parts of the sliding grooves, the sliding bolts are in threaded connection with the inner parts of a plurality of screw holes, the screw holes are formed in the outer wall of the brake disc, a plurality of fixed grooves are formed in the side wall of the brake disc, and springs are clamped in the fixed grooves.
As a preferable embodiment of the present invention, the ring slot has a length longer than the width of the fixing ring, and the spring has a length longer than the fixing slot.
As a preferable technical scheme of the invention, the fixing component comprises a clamping groove, the clamping groove is formed in one end of a main shaft, fixing strips are clamped in the clamping groove, two ends of each fixing strip are fixedly connected with the same lantern ring, a plurality of round holes are formed in the side wall of the lantern ring, threaded cylinders are clamped in the round holes, the threaded cylinders are fixedly connected to the side wall of a hub, fixing bolts are connected in the threaded cylinders, sockets are formed in the inner walls of the two ends of the clamping groove, the same plugboard is inserted in the two sockets, and a protective sleeve is sleeved on the surface of the main shaft.
As a preferable technical scheme of the invention, the inner wall of the protective sleeve is attached to two ends of the plugboard, the protective sleeve is extruded on the surface of the fixing bolt, and the distance between the plugboard and the inner wall of the clamping groove is the same as the thickness of the fixing strip.
As a preferable technical scheme of the invention, the rotating assembly comprises two second bearings, the two second bearings are embedded in the center of the surface of the main shaft, the two second bearings are clamped in fixing ring grooves, the fixing ring grooves are formed in the inner walls of U-shaped frames, stop blocks are clamped at openings of the U-shaped frames, arc slots are formed in the inner walls of two sides of the U-shaped frames, arc racks are inserted in the arc slots, the arc racks are inserted in the arc insertion holes, the arc insertion holes are formed in the side walls of the stop blocks, fixing frames are fixedly connected to two ends of the U-shaped frames, gears are clamped in the inner walls of the fixing frames, the two gears are rotatably connected to the surfaces of the fixing shafts, the fixing shafts are fixedly connected to the center of the inner walls of the two fixing frames, and supporting shafts are fixedly connected to the outer walls of the upper ends of the U-shaped frames.
As a preferable technical scheme of the invention, the brake assembly comprises a fixed plate, wherein the fixed plate is fixedly connected to the outer wall of the U-shaped frame, a plurality of assistor are embedded on the surface of the fixed plate, the other ends of the assistor are fixedly connected with the same brake static disc, and a fixed sleeve is fixedly connected to the side wall of the U-shaped frame.
The using method of the detection and analysis device of the electric brake system of the aircraft comprises the following steps:
when the brake static disc is in contact with the brake movable disc, the brake static disc extrudes the brake movable disc to enable the brake movable disc to move towards the inside of the clamping ring groove, and then the brake movable disc pushes the pressure sensor through the inner wall of the circular groove;
secondly, when the pressure sensor is pushed by the brake disc in the first step, the pressure sensor starts to squeeze the pressure sensor, the pressure sensor converts the received pressure into a numerical value and feeds the numerical value back to the instrument panel, the pressure received by the brake disc is intuitively fed back through the instrument panel, when the pressure fed back by the pressure sensor is overlarge, the pilot controls the brake disc to retract, and when the pressure fed back by the pressure sensor is overlarge, the pilot controls the brake disc to move forwards;
and finally, when the pressure sensor is the same as a preset threshold value, the friction force provided by the brake static disc and the brake movable disc is used for controlling the aircraft to finish braking, and when the brake movable disc is worn, the booster is used for controlling the travel of the brake static disc to move, so that the pressure fed back by the pressure sensor is corresponding to the threshold value, and the brake static disc and the brake movable disc are used for providing friction force again to enable the aircraft to finish braking.
The beneficial effects achieved by the invention are as follows:
when the brake static disc is contacted with the brake movable disc, the brake movable disc moves towards the inside of the clamping ring groove, the pressure sensor is pushed through the inner wall of the circular groove, the pressure received by the brake movable disc is intuitively sensed through the pressure sensor in the brake movable disc, so that the pressure received by the brake movable disc can be accurately fed back no matter how the brake disc is worn, and the brake is prevented from being out of control due to error in pressure analysis of a brake system.
The main shaft is inserted into the sleeve and the hub, the lantern ring is sleeved on the surface of the main shaft, the fixing strips are clamped in the clamping grooves, the threaded cylinder is inserted into the round hole, then the inserting plate is inserted into the inserting opening, the fixing strips are supported through the inserting plate, the main shaft is fixedly connected with the hub, the hub and the main shaft are supported through the lantern ring and the fixing strips, the hub is prevented from inclining, and further brake failure caused by inclination of the brake moving disc is effectively prevented.
Drawings
The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate the invention and together with the embodiments of the invention, serve to explain the invention. In the drawings:
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic view of the sleeve structure of the present invention;
FIG. 3 is a schematic view of the U-shaped frame structure of the present invention;
FIG. 4 is an enlarged view of portion A of FIG. 1 in accordance with the present invention;
FIG. 5 is an enlarged view of portion B of FIG. 1 in accordance with the present invention;
FIG. 6 is a schematic view of a brake disc structure according to the present invention;
fig. 7 is a schematic view of the board plug structure of the present invention.
In the figure: 1. a main shaft; 2. a detection assembly; 21. a first bearing; 22. a conical groove; 23. a sleeve; 24. the clamping ring groove is connected; 25. a fixed cylinder; 26. a pressure sensor; 27. a circular groove; 28. a brake disc; 29. a hub; 3. a reset assembly; 31. a fixing ring; 32. a ring slot; 33. a chute; 34. a sliding bolt; 35. a screw hole; 36. a fixing groove; 37. a spring; 4. a fixing assembly; 41. a clamping groove; 42. a fixing strip; 43. a collar; 44. a round hole; 45. a thread cylinder; 46. a fixing bolt; 47. a socket; 48. inserting plate; 49. a protective sleeve; 5. a rotating assembly; 51. a second bearing; 52. a fixed ring groove; 53. a U-shaped frame; 54. a stop block; 55. an arc slot; 56. an arc-shaped rack; 57. arc jacks; 58. a fixed frame; 59. a gear; 510. a fixed shaft; 511. a support shaft; 6. a brake assembly; 61. a fixing plate; 62. a stress application device; 63. braking a static disc; 64. and (5) fixing the sleeve.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Examples: as shown in fig. 1-7, the detection and analysis device of the electric brake system of the aircraft comprises a main shaft 1, wherein detection assemblies 2 are arranged at two ends of the main shaft 1, reset assemblies 3 are arranged in the two detection assemblies 2, fixed assemblies 4 are arranged outside the two detection assemblies 2, a rotating assembly 5 is arranged at the center of the main shaft 1, and brake assemblies 6 are arranged at two ends of the rotating assembly 5;
the detection assembly 2 comprises a first bearing 21, the first bearing 21 is movably sleeved on the surface of the main shaft 1, the first bearing 21 is clamped in a conical groove 22, the conical groove 22 is formed in the inner wall of a sleeve 23, a clamping ring groove 24 is formed in one side wall of the sleeve 23, a plurality of fixed cylinders 25 are annularly embedded in the inner wall of the clamping ring groove 24, pressure sensors 26 are embedded in the fixed cylinders 25, the pressure sensors 26 are inserted in a plurality of circular grooves 27, the circular grooves 27 are formed in one side wall of the same brake disc 28, a hub 29 is fixedly sleeved on the outer wall of the sleeve 23, the pressure received by the brake disc 28 is intuitively sensed by the pressure sensors 26 in the brake disc 28, and therefore the pressure received by the brake disc 28 can be accurately fed back regardless of the abrasion of the brake disc, and the brake is prevented from being out of control caused by the error of the pressure analysis of the brake system.
Wherein, reset subassembly 3 includes solid fixed ring 31, gu fixed ring 31 fixed connection is on the inner wall of joint annular 24, gu fixed ring 31 peg graft in the inside of ring slot 32, ring slot 32 is seted up on the lateral wall of brake movable disk 28, a plurality of spouts 33 have been seted up to the equidistance on the outer wall of gu fixed ring 31, the inside of a plurality of spouts 33 all sliding connection has slide bolt 34, a plurality of slide bolt 34 threaded connection is inside a plurality of screw holes 35, a plurality of screw holes 35 are seted up on the outer wall of brake movable disk 28, a plurality of fixed slots 36 have been seted up on the lateral wall of brake movable disk 28, the inside of a plurality of fixed slots 36 all the joint has spring 37, support brake movable disk 28 through gu fixed ring 31 and ring slot 32, prevent that brake movable disk 28 position deviation from leading to brake failure.
The fixing assembly 4 comprises a clamping groove 41, the clamping groove 41 is formed in one end of the spindle 1, a fixing strip 42 is clamped in the clamping groove 41, two ends of the fixing strip 42 are fixedly connected with the same lantern ring 43, a plurality of round holes 44 are formed in the side wall of the lantern ring 43, threaded cylinders 45 are clamped in the round holes 44, the threaded cylinders 45 are fixedly connected to the side wall of the hub 29, fixing bolts 46 are fixedly connected to the inner walls of the two ends of the clamping groove 41, inserting holes 47 are formed in the inner walls of the two ends of the clamping groove 41, the same inserting plates 48 are inserted in the two inserting holes 47, a protective sleeve 49 is sleeved on the surface of the spindle 1, the spindle 1 is inserted into the sleeve 23 and the hub 29, the lantern ring 43 is sleeved on the surface of the spindle 1, the fixing strip 42 is clamped in the clamping groove 41, the threaded cylinders 45 are inserted into the round holes 44, then the inserting plates 48 are inserted into the inserting holes 47, the spindle 1 and the hub 29 are fixedly connected through the inserting plates 48, the lantern ring 43 and the hub 29 are supported by the fixing strip 42, the hub 29 and the spindle 1 are prevented from inclining, and the hub 29 is effectively prevented from inclining a brake disc 28.
The rotating assembly 5 comprises two second bearings 51, the two second bearings 51 are embedded in the center of the surface of the spindle 1, the two second bearings 51 are clamped in fixed ring grooves 52, the fixed ring grooves 52 are formed in the inner wall of a U-shaped frame 53, a stop block 54 is clamped in the opening of the U-shaped frame 53, arc slots 55 are formed in the inner walls of two sides of the U-shaped frame 53, arc racks 56 are inserted in the two arc slots 55, the two arc racks 56 are inserted in two arc insertion holes 57, the arc insertion holes 57 are formed in the side wall of the stop block 54, two ends of the U-shaped frame 53 are fixedly connected with fixed frames 58, gears 59 are clamped in the two fixed frames 58, the two gears 59 are rotatably connected to the surface of a fixed shaft 510, the two fixed shafts 510 are fixedly connected to the center of the inner wall of the two fixed frames 58, a supporting shaft 511 is fixedly connected to the outer wall of the upper end of the U-shaped frame 53, the arc racks 56 are driven to move through the gears 59, the arc racks 56 are clamped in the inner portions of the insertion holes 57, and the U-shaped frame 53 and the spindle 1 are fixed to the lower end of the supporting shaft 511 through the gears 59, and the lower end of the supporting shaft 511 can be conveniently maintained and detached.
Wherein, the brake assembly 6 includes a fixed plate 61, the fixed plate 61 is fixedly connected on the outer wall of the U-shaped frame 53, a plurality of assistor 62 are embedded on the surface of the fixed plate 61, the other end of the assistor 62 is fixedly connected with the same brake static disc 63, a fixed sleeve 64 is fixedly connected on the side wall of the U-shaped frame 53, and the assistor 62 is supported by the fixed plate 61.
The length of the ring slot 32 is longer than the width of the fixed ring 31, and the length of the spring 37 is longer than the length of the fixed slot 36, so that the spring 37 pushes the brake disc 28 to move out of the snap ring slot 24, preventing the pressure sensor 26 from being in a pressed state all the time, and thus increasing the service life of the pressure sensor 26.
Wherein, the inner wall of the protective sleeve 49 is attached to two ends of the insert plate 48, the protective sleeve 49 is extruded on the surface of the fixing bolt 46, the inner wall interval between the insert plate 48 and the clamping groove 41 is the same as the thickness of the fixing strip 42, and the insert plate 48 and the fixing bolt 46 are fixed through the protective sleeve 49.
A method for detecting and analyzing a device of an aircraft electric brake system, comprising the steps of:
when the brake static disc 63 is in contact with the brake dynamic disc 28, the brake static disc 63 presses the brake dynamic disc 28, so that the brake dynamic disc 28 moves towards the inside of the clamping ring groove 24, and the pressure sensor 26 is pushed by the brake dynamic disc 28 through the inner wall of the circular groove 27;
secondly, in the first step, after the brake disc 28 pushes the pressure sensor 26, the brake disc 28 starts to squeeze the pressure sensor 26, the pressure received by the pressure sensor 26 is converted into a numerical value and fed back to an instrument panel, the pressure received by the brake disc 28 is intuitively fed back through the instrument panel, when the pressure fed back by the pressure sensor 26 is overlarge, the pilot controls the brake disc 63 to retract, and when the pressure fed back by the pressure sensor 26 is overlarge, the pilot controls the brake disc 63 to move forwards;
and thirdly, finally, when the pressure sensor 26 is the same as a preset threshold value, the friction force provided when the brake static disc 63 is in contact with the brake movable disc 28 controls the aircraft to finish braking, and when the brake movable disc 28 is worn, the booster 62 controls the travel of the brake static disc 63 to move so that the pressure fed back by the pressure sensor 26 corresponds to the threshold value, and the brake static disc 63 and the brake movable disc 28 are again provided with enough friction force to finish braking the aircraft.
Specifically, when the invention is used, firstly, the second bearing 51 on the main shaft 1 is clamped into the fixed ring groove 52, then the stop block 54 is clamped into the U-shaped frame 53, then the two gears 59 are pushed to rotate, the arc-shaped rack 56 is driven to move by the gears 59, the arc-shaped rack 56 is clamped into the arc-shaped jack 57, further, the U-shaped frame 53 and the stop block 54 fix the main shaft 1 at the lower end of the supporting shaft 511, so that the main shaft 1 can be conveniently removed for maintaining a braking system, then the main shaft 1 is inserted into the sleeve 23 and the hub 29, then the lantern ring 43 is sleeved on the surface of the main shaft 1, the fixing strip 42 is clamped into the clamping groove 41, the threaded cylinder 45 is inserted into the circular hole 44, then the inserting plate 48 is inserted into the socket 47, the fixing strip 42 is supported by the inserting plate 48, the main shaft 1 and the hub 29 are supported by the lantern ring 43 and the fixing strip 42, the hub 29 and the main shaft 1 are prevented from inclining by the hub 29, further, the brake static disc 63 is effectively prevented from being pushed by the booster 62, the surface of the fixing sleeve 64 is conveniently removed, then the static disc 28 slides close to the braking system, the surface of the braking disc 28 is prevented from being in the fixing sleeve 64, then the static disc 28 is effectively prevented from inclining, the braking disc 28 is accurately, when the static disc 28 is in the braking disc 28 is in the error-free condition, the braking system is contacted with the inner groove 28, and the dynamic pressure of the braking disc 28 is accurately and the dynamic disc 28 is prevented from being in the inner channel 28, and the dynamic pressure of the dynamic disc 28 is accurately and lost, and the pressure is accurately, and the pressure is not lost, when the dynamic disc 28 is in the dynamic system.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. The detection and analysis device of the aircraft electric brake system comprises a main shaft (1), wherein detection assemblies (2) are arranged at two ends of the main shaft (1), reset assemblies (3) are arranged in the two detection assemblies (2), fixed assemblies (4) are arranged outside the two detection assemblies (2), a rotating assembly (5) is arranged at the center of the main shaft (1), and brake assemblies (6) are arranged at two ends of the rotating assembly (5);
the device is characterized in that the detection assembly (2) comprises a first bearing (21), the first bearing (21) is movably sleeved on the surface of the main shaft (1), the first bearing (21) is clamped inside a conical groove (22), the conical groove (22) is formed in the inner wall of a sleeve (23), a clamping ring groove (24) is formed in one side wall of the sleeve (23), a plurality of fixed cylinders (25) are annularly embedded in the inner wall of the clamping ring groove (24), pressure sensors (26) are embedded in the fixed cylinders (25), the pressure sensors (26) are inserted in a plurality of circular grooves (27), the circular grooves (27) are formed in one side wall of the same brake disc (28), and hubs (29) are fixedly sleeved on the outer wall of the sleeve (23);
the brake assembly (6) comprises a fixed plate (61), the fixed plate (61) is fixedly connected to the outer wall of the U-shaped frame (53), a plurality of assistor (62) are embedded in the surface of the fixed plate (61), the other ends of the assistor (62) are fixedly connected with the same brake static disc (63), and a fixed sleeve (64) is fixedly connected to the side wall of the U-shaped frame (53).
2. The detection and analysis device for the electric brake system of the aircraft according to claim 1, wherein the reset assembly (3) comprises a fixed ring (31), the fixed ring (31) is fixedly connected to the inner wall of the clamping ring groove (24), the fixed ring (31) is inserted into the ring slot (32), the ring slot (32) is formed in the side wall of the brake disc (28), a plurality of sliding grooves (33) are formed in the outer wall of the fixed ring (31) at equal intervals, sliding bolts (34) are slidably connected to the inner portions of the sliding grooves (33), the sliding bolts (34) are in threaded connection with the inner portions of a plurality of screw holes (35), the screw holes (35) are formed in the outer wall of the brake disc (28), a plurality of fixed grooves (36) are formed in the side wall of the brake disc (28), and springs (37) are clamped in the inner portions of the fixed grooves (36).
3. The aircraft electric brake system detection and analysis device according to claim 2, characterized in that the ring slot (32) has a length longer than the width of the stationary ring (31), and the spring (37) has a length longer than the stationary slot (36).
4. The detection and analysis device for the electric brake system of the aircraft according to claim 1, characterized in that the fixing component (4) comprises a clamping groove (41), one end of the main shaft (1) is provided with the clamping groove (41), a fixing strip (42) is clamped in the clamping groove (41), two ends of the fixing strip (42) are fixedly connected with the same lantern ring (43), a plurality of round holes (44) are formed in the side wall of the lantern ring (43), a plurality of threaded cylinders (45) are clamped in the round holes (44), the threaded cylinders (45) are fixedly connected to the side wall of the hub (29), a plurality of fixing bolts (46) are connected to the inner portions of the threaded cylinders (45), inserting holes (47) are formed in the inner walls of two ends of the clamping groove (41), the same inserting plate (48) is inserted in the inserting holes (47), and a protective sleeve (49) is sleeved on the surface of the main shaft (1).
5. The device for detecting and analyzing the electric brake system of the aircraft according to claim 4, wherein the inner wall of the protective sleeve (49) is attached to both ends of the insertion plate (48), the protective sleeve (49) is pressed on the surface of the fixing bolt (46), and the inner wall distance between the insertion plate (48) and the clamping groove (41) is the same as the thickness of the fixing strip (42).
6. The detection and analysis device for the electric brake system of the aircraft according to claim 1, wherein the rotating assembly (5) comprises two second bearings (51), the two second bearings (51) are embedded in the center of the surface of the main shaft (1), the two second bearings (51) are clamped in the fixing ring grooves (52), the fixing ring grooves (52) are formed in the inner wall of the U-shaped frame (53), the stop blocks (54) are clamped in the openings of the U-shaped frame (53), arc slots (55) are formed in the inner walls of the two sides of the U-shaped frame (53), arc racks (56) are inserted in the arc slots (55), the arc racks (56) are inserted in the arc slots (57), the arc slots (57) are formed in the side walls of the stop blocks (54), the two ends of the U-shaped frame (53) are fixedly connected with fixing frames (58), gears (59) are clamped in the inner walls of the fixing frames (58), and the two gears (53) are connected with the fixing shafts (510) at the center of the two fixing shafts (510) in a rotating mode.
7. A method of using an aircraft electric brake system detection and analysis device based on the aircraft electric brake system detection and analysis device of any one of claims 1-6, comprising the steps of:
when the brake static disc (63) is contacted with the brake dynamic disc (28), the brake static disc (63) extrudes the brake dynamic disc (28) so that the brake dynamic disc (28) moves towards the inside of the clamping ring groove (24), and the rear brake dynamic disc (28) pushes the pressure sensor (26) through the inner wall of the circular groove (27);
secondly, in the first step, after the brake disc (28) pushes the pressure sensor (26), the brake disc (28) starts to squeeze the pressure sensor (26), the pressure received by the pressure sensor (26) is converted into a numerical value and fed back to an instrument panel, the pressure received by the brake disc (28) is intuitively fed back through the instrument panel, when the pressure fed back by the pressure sensor (26) is overlarge, a pilot controls the brake disc (63) to retract, and when the pressure fed back by the pressure sensor (26) is overlarge, the pilot controls the brake disc (63) to move forwards;
and finally, when the pressure sensor (26) is the same as a preset threshold value, the friction force provided by the brake static disc (63) and the brake movable disc (28) controls the aircraft to finish braking, and when the brake movable disc (28) is worn, the booster (62) controls the travel of the brake static disc (63) to move so that the pressure fed back by the pressure sensor (26) corresponds to the threshold value, and the brake static disc (63) and the brake movable disc (28) provide friction force again so as to finish braking the aircraft.
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| CN202311033094.8A CN116749940B (en) | 2023-08-16 | 2023-08-16 | Detection and analysis device for aircraft electric brake system and application method thereof |
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| CN202311033094.8A CN116749940B (en) | 2023-08-16 | 2023-08-16 | Detection and analysis device for aircraft electric brake system and application method thereof |
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|---|---|
| CN116749940A (en) | 2023-09-15 |
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