CN114771843B - Seat vibration damping system in aviation aircraft manufacturing and vibration damping method thereof - Google Patents
Seat vibration damping system in aviation aircraft manufacturing and vibration damping method thereof Download PDFInfo
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- CN114771843B CN114771843B CN202210679636.8A CN202210679636A CN114771843B CN 114771843 B CN114771843 B CN 114771843B CN 202210679636 A CN202210679636 A CN 202210679636A CN 114771843 B CN114771843 B CN 114771843B
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 19
- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000013016 damping Methods 0.000 title claims description 64
- 230000003139 buffering effect Effects 0.000 claims description 45
- 230000000149 penetrating effect Effects 0.000 claims description 9
- 230000009467 reduction Effects 0.000 claims description 5
- 239000006096 absorbing agent Substances 0.000 claims description 4
- 230000000116 mitigating effect Effects 0.000 claims description 4
- 238000010276 construction Methods 0.000 claims description 2
- 238000009434 installation Methods 0.000 abstract description 7
- 230000002349 favourable effect Effects 0.000 abstract description 3
- 239000003638 chemical reducing agent Substances 0.000 abstract 1
- 230000002401 inhibitory effect Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 17
- 230000008569 process Effects 0.000 description 3
- 230000035939 shock Effects 0.000 description 3
- 230000000153 supplemental effect Effects 0.000 description 2
- 239000002390 adhesive tape Substances 0.000 description 1
- 230000001174 ascending effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
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- 238000000926 separation method Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
- B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
- B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
- B64D11/0619—Arrangements of seats, or adaptations or details specially adapted for aircraft seats with energy absorbing means specially adapted for mitigating impact loads for passenger seats, e.g. at a crash
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Abstract
The invention discloses a seat vibration reducing system and a seat vibration reducing method in the manufacturing of an aviation aircraft, and belongs to the technical field of aircraft manufacturing, wherein the vibration reducing system comprises a connecting assembly, a vibration reducing assembly and an elastic supporting assembly, the connecting assembly comprises an I-beam arranged at the bottom in an aircraft cabin and a seat slide rail arranged at the lower bottom surface of a buffer frame, the vibration reducing assembly comprises an elastic cushion block which is clamped with the seat slide rail and internally provided with a vibration reducing spring, and a lateral vibration reducer arranged between the I-beam and the seat slide rail, the elastic supporting assembly comprises a supporting base arranged on the buffer frame and an installation ball seat arranged at the lower bottom surface of the aircraft seat, a movable ball head which is circumferentially hinged with a supporting rod is clamped below the installation ball seat, a sliding rod is arranged on the supporting base, and the supporting rod is clamped with the sliding rod; the vibration reducing system has reasonable structural design and obvious low-frequency vibration inhibiting effect, and is favorable for improving the riding comfort of the passenger plane.
Description
Technical Field
The invention relates to the technical field of aircraft manufacturing, in particular to a seat vibration damping system and a vibration damping method in aviation aircraft manufacturing.
Background
With the rapid development of civil passenger aircraft design and manufacturing technology, the design emphasis of modern passenger aircraft has gradually transited from the initial design of aircraft structural safety to the design of passenger cabin environmental comfort. According to relevant foreign statistical data, the vibration environment of the passenger cabin is an important factor influencing the comfort of the human body. During the flight, the passengers sit on the aircraft seats for most of the time, so that the comfort of the passengers can be directly improved by reducing the vibration of the aircraft seats.
Generally, the aircraft seats are mounted on sliding rails on the floor of the passenger cabin, which in turn are mounted directly on the floor beam structure of the passenger cabin by means of rigid connections; if the floor beam structure of the airplane vibrates, the vibration is directly transmitted to the aviation seat through the connecting pieces, so that discomfort is caused to passengers, however, the vibration frequency of the passenger cabin structure of the airplane is low, the traditional vibration reduction method for adhering damping materials on the structure is poor in low-frequency control effect, the defects of large occupied space and high weight cost are caused by the fact that the structural rigidity is improved to restrain the structural vibration, and the method cannot be implemented in the passenger cabin.
Disclosure of Invention
Aiming at the technical problems, the invention provides a seat vibration damping system and a vibration damping method thereof in aviation aircraft manufacturing.
The technical scheme of the invention is as follows: a seat vibration mitigation system in the manufacturing of an aviation aircraft comprises a connecting assembly, a vibration reduction assembly and an elastic supporting assembly; the connecting assembly comprises two I-beams which are arranged at the bottom in the aircraft passenger cabin in parallel through fastening bolts respectively and two seat slide rails which are arranged above the I-beams and are arranged on two sides of the lower bottom surface of the buffer frame in parallel through the fastening bolts, the top ends of the two I-beams are respectively provided with a plurality of mounting holes in a penetrating manner, the two seat slide rails are respectively in one-to-one correspondence with the upper and lower positions of the two I-beams, and the lower ends of the two seat slide rails are respectively provided with a plurality of mounting clamping grooves;
the vibration damping assembly comprises a plurality of elastic cushion blocks movably clamped with the mounting clamping grooves in a one-to-one corresponding mode and a plurality of lateral vibration dampers which are arranged between the I-shaped beam and the seat slide rail and fixedly connected with the mounting holes in a one-to-one corresponding mode; the lateral shock absorber comprises an outer shell and a connecting screw rod, the outer shell is movably clamped in the mounting hole, an elastic rubber block is filled in the outer shell, the connecting screw rod sequentially penetrates through the seat slide rail and the elastic rubber block, and a nut with a cap is connected to the lower end of the connecting screw rod in a threaded manner;
the elastic support assembly comprises a plurality of support bases arranged on the upper end surface of the buffer frame and a plurality of mounting ball seats which are positioned above the support bases and fixedly connected with the lower bottom surface of the aircraft seat, and each mounting ball seat corresponds to each support base in a one-to-one manner; all activity joint below each installation ball seat has the activity bulb, and the circumference of each activity bulb all articulates there is the several bracing piece, and each supports the base up end and all is provided with the slide bar that corresponds with each bracing piece position, and from last to all overlapping in proper order down on each slide bar is equipped with sliding sleeve and first supporting spring, and each sliding sleeve is articulated with the lower tip one-to-one activity that corresponds the collateral branch vaulting pole respectively.
The auxiliary buffer assembly comprises a buffer sleeve, a connecting plate and buffer toothed plates, the buffer sleeve is arranged at the center of the lower bottom surface of the aircraft seat, a plurality of through grooves are uniformly distributed in the circumferential direction of the buffer sleeve, the connecting plate is arranged at the bottom in the aircraft cabin, a connecting shaft rod penetrating through the buffer sleeve is vertically arranged at the upper end of the connecting plate, a plurality of buffer transverse rods are uniformly distributed at the top end of the connecting shaft rod, each buffer transverse rod penetrates through the corresponding through groove, a buffer gear is rotatably clamped at the end part of each buffer transverse rod, a plurality of buffer toothed plates are arranged, each buffer toothed plate is vertically arranged on the upper end surface of the connecting plate, and each buffer toothed plate is meshed with the buffer gear on the corresponding side; through setting up supplementary buffering subassembly, receive the vibration and when reciprocating when aircraft seat, the buffer sleeve reciprocates along connecting shaft pole, and each buffering horizontal pole reciprocates in the logical inslot that corresponds this moment, and it is spacing to the ascending vibration of the vertical side of aircraft seat, and when the contact of buffering horizontal pole and logical groove top, buffer sleeve extrusion buffering horizontal pole downwardly moving to make the buffering gear on the buffering horizontal pole and the buffering pinion rack meshing that corresponds the side remove, realize the buffering of the vertical side of aircraft seat vibration.
Furthermore, the auxiliary buffer assembly also comprises a plurality of damping boxes which are arranged on the upper end surface of the connecting plate and are respectively positioned on the outer sides of the buffer toothed plates, piston plates are slidably clamped inside the damping boxes, piston rods which penetrate through the damping boxes and are externally sleeved with damping springs are arranged on the upper end surface of each piston plate, guide pulleys are rotatably clamped at the top ends of the buffer toothed plates, and elastic pull ropes which penetrate through the guide pulleys on the corresponding sides and are fixedly connected with the buffer transverse rods to be measured are arranged at the top ends of the piston rods; in the process that the buffering transverse rod moves downwards, the piston rod is pulled to move in the corresponding damping box through the elastic pull rope, the piston plate in the damping box compresses the damping spring at the moment, the vibration of the aircraft seat is buffered for the second time, and the improvement of the riding comfort of the aircraft seat is facilitated.
Further, damping spring lower extreme activity joint has the roating seat, and the I-beam up end is provided with the counter bore with the roating seat position department of corresponding, rotates the joint on the counter bore inner wall and has rotatory axle sleeve, and evenly distributed has the spring beam of several and roating seat activity grafting on the inner wall of rotatory axle sleeve, through setting up the inside wobbling roating seat that can be in the counter bore, is favorable to slowing down the vibration that all directions produced on the aircraft seat horizontal plane.
Furthermore, a flat gasket and a spring washer which are positioned between the outer shell and the nut with the cap are sleeved on the connecting screw rod; the flat gasket and the spring washer can be arranged to prevent the nut with the cap and the connecting screw rod from loosening and falling, so that the reliability of the vibration damping effect of the side damper is improved.
Further, support the base up end and all be provided with the spout with each slide bar position department of correspondence, each inside horizontal guide arm that all is provided with of spout, the bottom of each slide bar slides the joint with the horizontal guide arm that the position corresponds the department respectively, all overlap on each horizontal guide arm and be equipped with two second supporting spring that are located the slide bar both sides respectively, when the bracing piece reciprocates along the slide bar, the slide bar can remove about on the horizontal guide arm, thereby make the elastic support subassembly when bearing the vibration that comes from the bottom in the aircraft cabin, provide stable elastic support effect for aircraft seat.
Furthermore, the buffer transverse rod and the connecting part of the through groove are connected with a wear-resistant sleeve in a rotating mode, the wear-resistant sleeve is favorable for reducing friction between the buffer transverse rod and the through groove, and therefore the response time of the auxiliary buffer assembly is shortened.
Furthermore, a vibration damping rubber strip is arranged at the joint of the I-beam and the bottom in the airplane cabin; through setting up the effect that damping adhesive tape on the one hand can play the separation vibration, on the other hand also can improve the inside leakproofness of aircraft cabin.
Furthermore, a positioning groove is formed in the top of the mounting clamping groove, and an elastic positioning block movably clamped with the positioning groove is arranged on the outer wall of the elastic cushion block; the reliability of the elastic cushion block connected with the installation clamping groove can be improved by utilizing the positioning groove and the elastic positioning block.
The invention also provides a seat vibration reducing method in the manufacturing of the aviation aircraft, which comprises the following steps:
s1, respectively arranging two I-beams in parallel at the bottom in an airplane passenger cabin through fastening bolts, then respectively arranging two seat slide rails in parallel at the lower bottom surface of a buffer frame through the fastening bolts, and finally clamping elastic cushion blocks in mounting clamping grooves at the lower ends of the seat slide rails and clamping damping springs in the elastic cushion blocks; damping vibration generated in the vertical direction of the aircraft seat by using a damping spring;
s2, clamping the outer shell in each mounting hole on the I-beam, sequentially penetrating the connecting screw through the seat slide rail and the outer shell, screwing the connecting screw by using a nut with a cap, and buffering vibration generated in the horizontal direction of the airplane seat by using an elastic rubber block in the outer shell;
s3, fixedly arranging each mounting ball seat on the lower bottom surface of the aircraft seat through bolts, and clamping a movable ball head on each mounting ball seat; then all supporting bases are fixedly arranged on the upper end face of the buffer frame through bolts, and all supporting rods on the movable ball head are in sliding clamping connection with sliding rods at corresponding positions, so that elastic supporting of the airplane seat is realized.
Compared with the prior art, the beneficial effects of the invention are embodied in the following points:
firstly, the space inside the seat slide rail is fully utilized, and the elastic cushion block and the damping spring are clamped inside the seat slide rail, so that the way of transmitting vibration to the airplane seat through the I-beam in the operation process of the airplane is effectively blocked; meanwhile, the lateral shock absorber is arranged between the seat slide rail and the I-beam, so that the shock generated in the horizontal direction of the airplane seat can be relieved, and the riding comfort of the passenger plane is obviously improved;
secondly, the buffer frame is arranged between the aircraft seat and the seat slide rail, and the elastic support assembly is arranged between the buffer frame and the aircraft seat, so that the vibration generated in all directions of the aircraft seat can be buffered, the elastic support effect of the buffer frame on the aircraft seat can be improved, and the vibration reduction effect of the aircraft seat is improved;
thirdly, the vibration reducing system has reasonable structural design, has the advantages of small space occupation, low additional weight and good low-frequency vibration suppression effect, and has positive promotion effect on the development of aviation industry.
Drawings
FIG. 1 is a flow chart of the damping method of the present invention;
FIG. 2 is a longitudinal section of the present invention;
FIG. 3 is a left side view of the present invention;
FIG. 4 is a schematic structural view of the vibration damping assembly of the present invention;
FIG. 5 is a schematic view of the connection of the swivel base of the present invention to an I-beam;
FIG. 6 is a view of the resilient support assembly of the present invention in a configuration on a cushion frame;
FIG. 7 is a schematic structural view of the resilient support assembly of the present invention;
FIG. 8 is a view of the position of the I-beam and supplemental bumper assembly of the present invention within the interior bottom of an aircraft passenger cabin;
FIG. 9 is a schematic view of the construction of the supplemental bumper assembly of the present invention;
figure 10 is a schematic view of the connection of the damper gear of the present invention to the damper tooth plate;
wherein, 1-connecting component, 10-I-beam, 100-mounting hole, 11-seat slide rail, 110-mounting clamping groove, 111-positioning groove, 12-counter bore, 120-rotating shaft sleeve, 121-spring rod, 2-vibration damping component, 20-elastic cushion block, 200-vibration damping spring, 201-elastic positioning block, 21-lateral vibration damper, 210-outer shell, 211-connecting screw rod, 2110-nut with cap, 2111-flat gasket, 2112-spring washer, 212-elastic rubber block, 22-rotating seat, 3-elastic supporting component, 30-supporting base, 300-sliding groove, 301-horizontal guide rod, 302-second supporting spring, 31-mounting ball seat, 32-movable ball head, 320-supporting rod, etc, 33-sliding rod, 330-sliding sleeve, 331-first supporting spring, 4-buffer bracket, 5-aircraft seat, 6-auxiliary buffer assembly, 60-buffer sleeve, 600-through groove, 61-connecting plate, 610-connecting shaft rod, 62-buffer toothed plate, 620-guide pulley, 63-buffer transverse rod, 630-buffer gear, 631-wear-resistant sleeve, 64-buffer box, 640-piston plate, 641-buffer spring, 642-piston rod and 643-elastic pull rope.
Detailed Description
Example 1
Fig. 2, 3, 4 and 5 show a seat vibration damping system in the manufacture of an aircraft, comprising a connecting assembly 1, a vibration damping assembly 2 and a resilient support assembly 3; the connecting assembly 1 comprises two I-shaped beams 10 which are arranged at the bottom in an aircraft cabin in parallel through fastening bolts respectively and two seat slide rails 11 which are arranged above the I-shaped beams 10 and are arranged on two sides of the lower bottom surface of the buffer frame 4 in parallel through the fastening bolts, wherein 4 mounting holes 100 are formed in the top ends of the two I-shaped beams 10 in a penetrating mode, the two seat slide rails 11 correspond to the upper positions and the lower positions of the two I-shaped beams 10 one by one respectively, and two mounting clamping grooves 110 are formed in the lower ends of the two seat slide rails 11;
as shown in fig. 4, the vibration damping assembly 2 includes 4 elastic cushion blocks 20 movably clamped in the mounting slots 110 in a one-to-one correspondence manner, and 8 side dampers 21 disposed between the i-beam 10 and the seat rail 11 and fixedly connected to the mounting holes 100 in a one-to-one correspondence manner; the damping springs 200 abutted against the upper end face of the i-beam 10 are movably clamped in the elastic cushion blocks 20, the lateral damper 21 comprises an outer shell 210 and a connecting screw rod 211, the outer shell 210 is movably clamped in the mounting hole 100, the elastic rubber blocks 212 are filled in the outer shell 210, the connecting screw rod 211 sequentially penetrates through the seat slide rail 11 and the elastic rubber blocks 212, and the lower end of the connecting screw rod 211 is connected with a nut 2110 with a cap;
as shown in fig. 2, 6 and 7, the elastic support assembly 3 includes 4 support bases 30 disposed on the upper end surface of the cushion frame 4 and 4 mounting ball seats 31 located above the support bases 30 and fixedly connected to the lower bottom surface of the aircraft seat 5, and each mounting ball seat 31 corresponds to each support base 30 in a one-to-one manner; all activity joint in each installation ball seat 31 below has activity bulb 32, and each activity bulb 32 circumference all articulates there is 4 bracing pieces 320, and each supports the 30 up end of base and all is provided with the slide bar 33 that corresponds with each bracing piece 320 position, all overlaps from last to all being equipped with sliding sleeve 330 and first supporting spring 331 in proper order down on each slide bar 33, and each sliding sleeve 330 is articulated with the lower tip one-to-one correspondence activity of corresponding collateral branch bracing piece 320 respectively.
Example 2
This embodiment describes a vibration damping method of a seat vibration damping system in an aircraft manufacturing process according to embodiment 1, including the steps of:
s1, respectively arranging two I-beams 10 in parallel at the bottom in an airplane passenger cabin through fastening bolts, then respectively arranging two seat slide rails 11 in parallel at the lower bottom surface of a buffer frame 4 through the fastening bolts, and finally clamping and connecting elastic cushion blocks 20 in installation clamping grooves 110 at the lower ends of the seat slide rails 11, and clamping and connecting damping springs 200 in the elastic cushion blocks 20; the vibration generated in the vertical direction of the aircraft seat 5 is buffered by the damper spring 200;
s2, clamping the outer shell 210 inside each mounting hole 100 on the i-beam 10, sequentially penetrating the connecting screw 211 through the seat slide 11 and the outer shell 210, screwing the connecting screw 211 with a nut 2110, and buffering vibration generated in the horizontal direction of the aircraft seat 5 with the elastic rubber block 212 inside the outer shell 210;
s3, fixedly arranging each mounting ball seat 31 on the lower bottom surface of the aircraft seat 5 through bolts, and clamping a movable ball head 32 on each mounting ball seat 31; then, the support bases 30 are fixedly arranged on the upper end surface of the buffer frame 4 through bolts, and finally, the support rods 320 on the movable ball head 32 are in sliding clamping connection with the sliding rods 33 at the corresponding positions, so that the elastic support of the aircraft seat 5 is realized.
Example 3
The present embodiment is different from embodiment 1 in that:
as shown in fig. 2, 8, 9, and 10, the aircraft seat further comprises an auxiliary buffering assembly 6, the auxiliary buffering assembly 6 comprises a buffering sleeve 60, a connecting plate 61 and a buffering toothed plate 62, the buffering sleeve 60 is arranged at the central position of the lower bottom surface of the aircraft seat 5, 4 through grooves 600 are uniformly distributed in the circumferential direction of the buffering sleeve 60, the connecting plate 61 is arranged at the bottom in the aircraft cabin, a connecting shaft rod 610 penetrating through the buffering sleeve 60 is vertically arranged at the upper end of the connecting plate 61, 4 buffering transverse rods 63 are uniformly distributed at the top end of the connecting shaft rod 610, each buffering transverse rod 63 penetrates through the through groove 600 at the corresponding side respectively, and the end of each buffering transverse rod 63 is rotatably clamped with a buffering gear 630, 4 buffering toothed plates 62 are arranged, each buffering toothed plate 62 is vertically arranged at the upper end surface of the connecting plate 61, and each buffering toothed plate 62 is meshed with the buffering gear 630 at the corresponding side respectively; supplementary buffer unit 6 still includes 4 settings at connecting plate 61 up end and be located the damping box 64 in each buffering pinion rack 62 outside respectively, the inside equal slip joint of each damping box 64 has piston plate 640, the up end of each piston plate 640 all is provided with the piston rod 642 that runs through damping box 64 and outside cover and be equipped with damping spring 641, each buffering pinion rack 62 top all rotates the joint and has guide pulley 620, the top of each piston rod 642 all is provided with the elasticity stay cord 643 that passes behind the guide pulley 620 that corresponds the side and correspond the buffering horizontal pole 63 fixed connection who surveys.
Example 4
This embodiment describes a vibration damping method of a seat vibration damping system in the manufacture of an aircraft according to embodiment 3, which is different from embodiment 2 in that it further includes S4,
s4, when the aircraft seat 5 moves up and down due to vibration, the buffer sleeves 60 move up and down along the connecting shaft rod 610, at the moment, each buffer cross rod 63 moves up and down in the corresponding through groove 600 to limit the vibration of the aircraft seat 5 in the vertical direction, and when the buffer cross rods 63 contact the tops of the through grooves 600, the buffer sleeves 60 extrude the buffer cross rods 63 to move downwards, so that the buffer gears 630 on the buffer cross rods 63 are meshed with the corresponding buffer toothed plates 62 to move; meanwhile, in the process that the buffer cross bar 63 moves downwards, the piston rod 642 is pulled by the elastic pull rope 643 to move in the corresponding damping box 64, and at this time, the piston plate 640 inside the damping box 64 compresses the damping spring 641, so that the vibration of the aircraft seat 5 in the vertical direction is buffered.
Example 5
The present embodiment is different from embodiment 1 in that:
as shown in fig. 4 and 5, the lower end of the damping spring 200 is movably clamped with a rotating base 22, a counter bore 12 is arranged at a position corresponding to the position of the rotating base 22 on the upper end surface of the i-beam 10, a rotating shaft sleeve 120 is rotatably clamped on the inner wall of the counter bore 12, and 6 spring rods 121 movably inserted into the rotating base 22 are uniformly distributed on the inner wall of the rotating shaft sleeve 120.
Example 6
The present embodiment describes a vibration damping method of a seat vibration damping system in the manufacture of an aircraft according to embodiment 5, which is different from embodiment 2 in that:
in step S1, when the aircraft seat 5 is subjected to vibrations from different directions on the horizontal plane, the swivel 22 can respond on the corresponding spring bars 121, thereby damping the vibrations of the aircraft seat 5 generated in all directions on the horizontal plane.
Example 7
The present embodiment is different from embodiment 1 in that:
as shown in FIG. 4, the connecting screw 211 is sleeved with a flat washer 2111 and a spring washer 2112 between the outer housing 210 and the nut 2110 with a cap.
Example 8
The present embodiment is different from embodiment 1 in that:
as shown in fig. 7, sliding grooves 300 are respectively disposed at positions corresponding to the positions of the upper end surface of the supporting base 30 and the sliding rods 33, horizontal guide rods 301 are respectively disposed inside the sliding grooves 300, the bottom ends of the sliding rods 33 are respectively slidably clamped with the horizontal guide rods 301 at the positions corresponding to the positions, and two second supporting springs 302 respectively disposed at two sides of the sliding rods 33 are respectively sleeved on the horizontal guide rods 301.
Example 9
This embodiment describes a vibration damping method of a seat vibration damping system in the manufacture of an aircraft according to embodiment 8, which is different from embodiment 2 in that:
in step S3, when the support bar 320 moves up and down along the slide bar 33, the slide bar 33 can move left and right on the horizontal guide bar 301, so that the elastic support assembly 3 provides a stable elastic support function for the aircraft seat 5 when receiving vibration from the bottom in the aircraft cabin.
Example 10
The present embodiment is different from embodiment 3 in that:
as shown in fig. 10, the connection part of the buffer cross bar 63 and the through groove 600 is rotationally clamped with a wear-resistant sleeve 631.
Example 11
The present embodiment is different from embodiment 1 in that:
as shown in fig. 2, a vibration damping rubber strip is arranged at the connection position of the i-beam 10 and the inner bottom of the airplane passenger cabin.
Example 12
The present embodiment is different from embodiment 1 in that:
as shown in fig. 4, the top of the installation slot 110 is provided with a positioning slot 111, and the outer wall of the resilient cushion block 20 is provided with a resilient positioning block 201 movably engaged with the positioning slot 111.
Claims (5)
1. A seat vibration mitigation system in the manufacturing of an aviation aircraft is characterized by comprising a connecting component (1), a vibration reduction component (2) and an elastic supporting component (3); the connecting assembly (1) comprises two I-shaped beams (10) which are arranged at the bottom in an aircraft cabin in parallel through fastening bolts and two seat slide rails (11) which are arranged above the I-shaped beams (10) and are arranged on two sides of the lower bottom surface of the buffer frame (4) in parallel through the fastening bolts, a plurality of mounting holes (100) are formed in the top ends of the two I-shaped beams (10) in a penetrating mode, the two seat slide rails (11) correspond to the two I-shaped beams (10) in the vertical position one to one, and a plurality of mounting clamping grooves (110) are formed in the lower ends of the two seat slide rails (11);
the vibration reduction assembly (2) comprises a plurality of elastic cushion blocks (20) movably clamped with the mounting clamping grooves (110) in a one-to-one corresponding mode and a plurality of lateral vibration absorbers (21) which are arranged between the I-shaped beam (10) and the seat slide rail (11) and fixedly connected with the mounting holes (100) in a one-to-one corresponding mode; damping springs (200) which are abutted to the upper end face of the I-shaped beam (10) are movably clamped in the elastic cushion blocks (20), the lateral vibration absorbers (21) comprise outer shells (210) and connecting screw rods (211), the outer shells (210) are movably clamped in the mounting holes (100), elastic rubber blocks (212) are filled in the outer shells (210), the connecting screw rods (211) sequentially penetrate through the seat slide rails (11) and the elastic rubber blocks (212), and nuts (2110) with caps are in threaded connection with the lower end portions of the connecting screw rods (211);
the elastic support assembly (3) comprises a plurality of support bases (30) arranged on the upper end surface of the buffer frame (4) and a plurality of mounting ball seats (31) which are arranged above the support bases (30) and fixedly connected with the lower bottom surface of the aircraft seat (5), and the mounting ball seats (31) correspond to the support bases (30) in an up-down position one by one; a movable ball head (32) is movably clamped below each mounting ball seat (31), a plurality of support rods (320) are hinged to the periphery of each movable ball head (32), a sliding rod (33) corresponding to each support rod (320) is arranged on the upper end face of each support base (30), a sliding sleeve (330) and a first support spring (331) are sequentially sleeved on each sliding rod (33) from top to bottom, and each sliding sleeve (330) is movably hinged to the lower end part of the corresponding side support rod (320) in a one-to-one correspondence manner;
the aircraft seat is characterized by further comprising an auxiliary buffering assembly (6), wherein the auxiliary buffering assembly (6) comprises a buffering sleeve (60), a connecting plate (61) and a buffering toothed plate (62), the buffering sleeve (60) is arranged at the center of the lower bottom surface of the aircraft seat (5), a plurality of through grooves (600) are uniformly distributed in the circumferential direction of the buffering sleeve (60), the connecting plate (61) is arranged at the bottom in the aircraft cabin, a connecting shaft rod (610) penetrating through the buffering sleeve (60) is vertically arranged at the upper end of the connecting plate (61), a plurality of buffering transverse rods (63) are uniformly distributed at the top end of the connecting shaft rod (610), each buffering transverse rod (63) respectively penetrates through the through groove (600) at the corresponding side, a buffering gear (630) is rotatably clamped at the end part of each buffering transverse rod (63), a plurality of buffering toothed plates (62) are arranged, and each buffering toothed plate (62) is vertically arranged on the upper end surface of the connecting plate (61), each buffering toothed plate (62) is respectively meshed and connected with a buffering gear (630) on the corresponding side;
the auxiliary buffer assembly (6) further comprises a plurality of damping boxes (64) which are arranged on the upper end face of the connecting plate (61) and are respectively positioned on the outer sides of the buffer gear plates (62), a piston plate (640) is slidably clamped in each damping box (64), a piston rod (642) which penetrates through the damping box (64) and is externally sleeved with a damping spring (641) is arranged on the upper end face of each piston plate (640), a guide pulley (620) is rotatably clamped at the top end of each buffer gear plate (62), and an elastic pull rope (643) which penetrates through the guide pulley (620) on the corresponding side and is fixedly connected with the buffer cross rod (63) to be measured is arranged at the top end of each piston rod (642);
the lower end of the damping spring (200) is movably clamped with a rotating seat (22), a counter bore (12) is formed in the position, corresponding to the rotating seat (22), of the upper end face of the I-beam (10), a rotating shaft sleeve (120) is rotatably clamped on the inner wall of the counter bore (12), and a plurality of spring rods (121) which are movably inserted into the rotating seat (22) are uniformly distributed on the inner wall of the rotating shaft sleeve (120);
support base (30) up end and each slide bar (33) position department of correspondence all be provided with spout (300), each inside horizontal guide arm (301) that all is provided with of spout (300), the bottom of each slide bar (33) respectively with horizontal guide arm (301) slip joint of position department of correspondence, each all the cover is equipped with two second supporting spring (302) that are located slide bar (33) both sides respectively on horizontal guide arm (301).
2. A seat vibration mitigation system in aircraft construction according to claim 1, wherein said connection screw (211) is sleeved with a flat washer (2111) and a spring washer (2112) between the outer housing (210) and the nut with cap (2110).
3. The system for damping seat vibration in the manufacture of an aircraft according to claim 1, wherein a wear-resistant sleeve (631) is rotatably clamped at the joint of the buffer cross bar (63) and the through groove (600).
4. A seat vibration mitigation system in the manufacture of an aircraft according to claim 1, wherein the connection of the i-beam (10) to the bottom in the aircraft cabin is provided with a vibration damping strip.
5. A method of vibration damping in a seat vibration damping system in the manufacture of an aircraft according to any one of claims 1 to 4, characterised in that it comprises the following steps:
s1, respectively arranging two I-beams (10) in parallel at the bottom in an airplane passenger cabin through fastening bolts, then respectively arranging two seat sliding rails (11) in parallel at the lower bottom surface of a buffer frame (4) through the fastening bolts, and finally clamping elastic cushion blocks (20) in mounting clamping grooves (110) at the lower ends of the seat sliding rails (11), and clamping damping springs (200) in the elastic cushion blocks (20); the vibration generated in the vertical direction of the airplane seat (5) is buffered by using a damping spring (200);
s2, clamping the outer shell (210) in each mounting hole (100) on the I-beam (10), sequentially penetrating the connecting screw rod (211) through the seat slide rail (11) and the outer shell (210), screwing the connecting screw rod (211) by using a nut (2110) with a cap, and buffering vibration generated in the horizontal direction of the aircraft seat (5) by using an elastic rubber block (212) in the outer shell (210);
s3, fixedly arranging each mounting ball seat (31) on the lower bottom surface of the airplane seat (5) through bolts, and clamping a movable ball head (32) on each mounting ball seat (31); then all the supporting bases (30) are fixedly arranged on the upper end surface of the buffer frame (4) through bolts, and finally all the supporting rods (320) on the movable ball head (32) are in sliding clamping connection with the sliding rods (33) at the corresponding positions, so that the elastic support of the airplane seat (5) is realized.
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| CN116902016B (en) * | 2023-09-06 | 2023-12-01 | 黑龙江大学 | Indoor vibration reduction connection structure of rail train |
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