CN210212812U - General aircraft traction lever - Google Patents
General aircraft traction lever Download PDFInfo
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- CN210212812U CN210212812U CN201920877624.XU CN201920877624U CN210212812U CN 210212812 U CN210212812 U CN 210212812U CN 201920877624 U CN201920877624 U CN 201920877624U CN 210212812 U CN210212812 U CN 210212812U
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- 238000013016 damping Methods 0.000 claims abstract description 78
- 230000001360 synchronised effect Effects 0.000 claims abstract description 40
- 230000005540 biological transmission Effects 0.000 claims abstract description 18
- 229920001971 elastomer Polymers 0.000 claims abstract description 16
- 239000000806 elastomer Substances 0.000 claims abstract description 16
- 229910052802 copper Inorganic materials 0.000 claims description 14
- 239000010949 copper Substances 0.000 claims description 14
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 13
- 230000000694 effects Effects 0.000 description 5
- 241000227287 Elliottia pyroliflora Species 0.000 description 4
- 230000002950 deficient Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
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Abstract
The utility model discloses a general aircraft traction rod, which comprises a damping shell, a traction rod, a positioning bracket, a rotating rod, a positioner, a first movable plate, a second movable plate, a torque motor, a driving synchronous pulley, a driven synchronous pulley and a transmission synchronous belt, wherein one end of the traction rod is connected with the first damping plate and the second damping plate, the traction rod passes through one end of the damping shell and extends outwards, and a damping flange at the other end of the damping shell is connected with a bracket flange at one end of the positioning bracket through a screw; a magnetorheological elastomer is arranged in a unit cavity of the inner cavity of the vibration damping shell divided by the first vibration damping plate and the second vibration damping plate, and an electrode is arranged in the magnetorheological elastomer; the utility model discloses simple structure, convenient to use, the damping is effectual, and work efficiency is high, can extensively promote and use.
Description
[ technical field ] A method for producing a semiconductor device
The utility model relates to a technical field of general aircraft, especially the technical field of general aircraft traction lever.
[ background of the invention ]
Before ninety years, the draw bar of military aircraft at home and abroad is light in weight and small in overall dimension, the draw bar is of a single truss draw bar structure, and the draw bar is simple in structure, light in weight and incapable of lifting adjustment and tension load limitation. In the nineties, the overall size and weight of the aircraft of the combat aircraft equipped by various countries, air and navy greatly exceed those of the prior military aircraft. Due to the structural form change of the landing gear strut of the airplane, the airplane has strict requirements on airplane traction due to various high-precision electronic equipment and fire control equipment. Therefore, the conventional frame-type tow bar cannot meet the towing work requirement of the airplane.
Through retrieval, although the utility model CN207759071U discloses an aircraft drawbar, although a spring is installed to make the drawbar have a vibration damping function, the drawbar can be conveniently replaced by a towing ring, there are some problems, firstly, the spring has a defective vibration damping effect, the vibration damping force is relatively constant, and the spring stiffness can not be adjusted according to the impact force; secondly, the positioning pin on the positioning bracket needs to be screwed up manually, which is troublesome and wastes time, and reduces the working efficiency; in view of the above problems, there is a need to design a new universal airplane tow bar.
[ Utility model ] content
The utility model aims to solve the problems in the prior art and provide a general airplane traction rod, which can adjust the damping strength and meet the damping effect of different impact forces; can plug into the locator in the aircraft pulls downtheholely automatically, work efficiency is high.
In order to achieve the purpose, the utility model provides a general aircraft traction lever, which comprises a damping shell, a traction lever, a positioning bracket, a rotating lever, a positioner, a first movable plate, a second movable plate, a torque motor, a driving synchronous pulley, a driven synchronous pulley and a transmission synchronous belt, wherein one end of the traction lever is connected with a first damping plate and a second damping plate, the traction lever passes through one end of the damping shell and extends outwards, and a damping flange at the other end of the damping shell is connected with a bracket flange at one end of the positioning bracket through a screw; a magnetorheological elastomer is arranged in a unit cavity of the inner cavity of the vibration damping shell divided by the first vibration damping plate and the second vibration damping plate, and an electrode is arranged in the magnetorheological elastomer;
a first bracket and a second bracket are oppositely arranged at one end of the positioning bracket, a first through hole and a second through hole are arranged on the first bracket, a third through hole and a fourth through hole are arranged on the second bracket, the first through hole and the third through hole are opposite in position and are internally provided with copper sleeves, and the second through hole and the fourth through hole are opposite in position and are internally provided with bearings; the rotating rod penetrates through the bearing, the two ends of the rotating rod are symmetrically provided with a transmission thread, a first clamping groove and a second clamping groove, and bearing retainer rings are clamped in the first clamping groove and the second clamping groove; the number of the positioners is two, the sliding rod of one positioner is arranged in the copper sleeve of the first through hole, and the connecting thread of the positioner is arranged in the first threaded hole of the first moving plate; the sliding rod of the other positioner is arranged in the copper bush of the third through hole, and the connecting thread of the positioner is arranged in the third threaded hole of the second moving plate; the transmission threads at the two ends of the rotating rod are respectively and correspondingly arranged in the second threaded hole and the fourth threaded hole;
one end of the rotating rod is connected with a driven synchronous belt pulley, a torque motor is arranged on the outer side of the positioning support, a driving synchronous belt pulley is arranged on an output shaft of the torque motor, and the driving synchronous belt pulley is connected with the driven synchronous belt pulley through a transmission synchronous belt.
Preferably, the distance between the first damping plate and the second damping plate is 30-50 mm; the first damping plate and the second damping plate are arranged in the inner cavity of the damping shell and are in sliding fit with the inner cavity of the damping shell; the rotation directions of the second threaded hole and the fourth threaded hole are opposite.
Preferably, the distance between the first and second detent grooves is slightly greater than the thickness of the bearing.
Preferably, one end of the sliding rod of the positioner is provided with a positioning head, and the diameter of the positioning head is larger than that of the copper sleeve.
The utility model has the advantages that: the utility model is characterized in that the rotating rod is arranged in the bearing in a penetrating way, the two ends of the rotating rod are symmetrically provided with a transmission thread, a first clamping groove and a second clamping groove, and the first clamping groove and the second clamping groove are internally provided with bearing retainer rings in a clamping way; the number of the positioners is two, the sliding rod of one positioner is arranged in the copper sleeve of the first through hole, and the connecting thread of the positioner is arranged in the first threaded hole of the first moving plate; the sliding rod of the other positioner is arranged in the copper bush of the third through hole, and the connecting thread of the positioner is arranged in the third threaded hole of the second moving plate; the transmission threads at the two ends of the rotating rod are respectively and correspondingly arranged in the second threaded hole and the fourth threaded hole, and the driving synchronous belt wheel and the driven synchronous belt wheel can be driven to rotate through the rotation of the torque motor, so that the first moving plate and the second moving plate on the rotating rod move relatively or in a back-to-back manner, the two positioners move relatively or in a back-to-back manner, the positioners are automatically inserted into or withdrawn from the traction holes, and the traction working efficiency is improved; one end of the traction rod is connected with a first damping plate and a second damping plate, a magnetorheological elastomer is arranged in a unit cavity of the inner cavity of the damping shell divided by the first damping plate and the second damping plate, and an electrode is arranged in the magnetorheological elastomer; the rigidity of the magnetorheological elastomer can be influenced by adjusting the current of the electrode, and the vibration reduction effect of different impact forces can be realized; the utility model discloses simple structure, convenient to use, the damping is effectual, and work efficiency is high, can extensively promote and use.
The features and advantages of the present invention will be described in detail by embodiments with reference to the accompanying drawings.
[ description of the drawings ]
Fig. 1 is a front view of a universal aircraft tow bar of the present invention;
fig. 2 is a front view of a turning rod of a universal aircraft tow bar according to the present invention;
fig. 3 is a front view of a first moving plate of the traction rod of the general-purpose aircraft according to the present invention;
fig. 4 is a front view of a second movable plate of the traction rod of the general-purpose aircraft according to the present invention;
fig. 5 is a front view of the locator of the universal aircraft tow bar of the present invention.
In the figure: 1-damping shell, 2-traction rod, 3-first damping plate, 4-second damping plate, 5-damping flange, 6-magnetorheological elastomer, 7-electrode, 8-positioning bracket, 9-first bracket, 10-first through hole, 11-second through hole, 12-second bracket, 13-third through hole, 14-fourth through hole, 15-copper sleeve, 16-bearing, 17-rotating rod, 171-transmission thread, 172-first clamping groove, 173-second clamping groove, 18-positioner, 181-sliding rod, 182-positioning head, 183-connecting thread, 19-first moving plate, 191-first threaded hole, 192-second threaded hole, 20-second moving plate, 201-third threaded hole, 202-a fourth threaded hole, 21-a torque motor, 22-a driving synchronous pulley, 23-a driven synchronous pulley, 24-a transmission synchronous belt and 25-a bracket flange.
[ detailed description ] embodiments
Referring to fig. 1-5, the utility model relates to a general aircraft traction lever, including damping casing 1, traction lever 2, locating support 8, dwang 17, locator 18, first movable plate 19, second movable plate 20, torque motor 21, driving synchronous pulley 22, driven synchronous pulley 23 and drive synchronous belt 24, traction lever 2 one end is connected with first damping plate 3 and second damping plate 4, and traction lever 2 passes damping casing 1 one end and outwards extends, and damping flange 5 of the other end of damping casing 1 is connected through the screw with the support flange 25 of locating support 8 one end; a magnetorheological elastomer 6 is arranged in a unit cavity of the inner cavity of the vibration damping shell 1 divided by the first damping plate 3 and the second damping plate 4, and an electrode 7 is arranged in the magnetorheological elastomer 6; a first support 9 and a second support 12 are oppositely arranged at one end of the positioning support 8, a first through hole 10 and a second through hole 11 are arranged on the first support 9, a third through hole 13 and a fourth through hole 14 are arranged on the second support 12, the first through hole 10 and the third through hole 13 are opposite in position and are internally provided with copper sleeves 15, and bearings 16 are oppositely arranged at the second through hole 11 and the fourth through hole 14 and are internally provided with bearings; the rotating rod 17 penetrates through the bearing 16, the two ends of the rotating rod 17 are symmetrically provided with a transmission thread 171, a first clamping groove 172 and a second clamping groove 173, and bearing retaining rings are clamped in the first clamping groove 172 and the second clamping groove 173; the number of the locators 18 is two, wherein the sliding rod 181 of one locator 18 is arranged in the copper sleeve 15 of the first through hole 10 and the connecting thread 183 of the locator 18 is arranged in the first threaded hole 191 of the first moving plate 19; the sliding rod 181 of the other retainer 18 is disposed in the copper bush 15 of the third through hole 13 and the connecting screw 183 of this retainer 18 is disposed in the third screw hole 201 of the second moving plate 20; the transmission threads 171 at the two ends of the rotating rod 17 are respectively and correspondingly arranged in the second threaded hole 192 and the fourth threaded hole 202; one end of the rotating rod 17 is connected with a driven synchronous pulley 23, a torque motor 21 is arranged on the outer side of the positioning support 8, a driving synchronous pulley 22 is arranged on an output shaft of the torque motor 21, and the driving synchronous pulley 22 is connected with the driven synchronous pulley 23 through a transmission synchronous belt 24; the distance between the first damping plate 3 and the second damping plate 4 is 30-50 mm; the first damping plate 3 and the second damping plate 4 are arranged in the inner cavity of the damping shell 1 and are in sliding fit with the inner cavity of the damping shell 1; the rotation directions of the second threaded hole 192 and the fourth threaded hole 202 are opposite; the distance between the first detent groove 172 and the second detent groove 173 is slightly greater than the thickness of the bearing 16; one end of the sliding rod 181 of the positioner 18 is provided with a positioning head 182, and the diameter of the positioning head 182 is larger than that of the copper sleeve 15.
The utility model discloses the working process:
the utility model relates to a general aircraft traction lever is in the course of the work, connect traction lever 2 one end with the couple of tractor, connect torque motor 21 and electrode 7 with the power, let first support 9 and second support 12 of locating support 8 move to the aircraft front wheel, make locator 18 aim at aircraft front wheel pulling hole, control torque motor 21 forward rotation makes initiative synchronous pulley 22 drive driven synchronous pulley 23 through drive synchronous belt 24 and rotate, dwang 17 rotates in bearing 16, thus make first movable plate 19 and second movable plate 20 relative motion, thus make two locator 18 relative motion so as to place locator 18 in aircraft front wheel pulling hole, then just can drag the aircraft and carry out forward motion, in order to reduce the vibration of traction lever 2, prolong the life of traction lever 2, when meeting the condition of road surface jolt or having great impact force, the current of a lead connected with the electrode 7 can be controlled, so that the rigidity of the magnetorheological elastomer 6 is changed, a better vibration damping effect of the traction rod 2 is achieved, the amplitude of the current is adjusted, and a user can perform experiments according to the road surface bumping condition; when the airplane moves to a parking position, a user can control the torque motor 21 to rotate reversely, so that the driving synchronous pulley 22 drives the driven synchronous pulley 23 to rotate through the transmission synchronous belt 24, the rotating rod 17 rotates in the bearing 16, the first moving plate 19 and the second moving plate 20 move backwards, the two positioners 18 move backwards, the positioners 18 are withdrawn to airplane front wheel traction holes until the positioning head 182 abuts against the side surface of the copper sleeve 15, the torque motor 21 exceeds a rotating torque range, the rotation is stopped, and finally the tractor and the traction rod 2 are moved away.
The utility model is characterized in that the rotating rod 17 is arranged in the bearing 16, the two ends of the rotating rod 17 are symmetrically provided with the transmission screw 171, the first clamping groove 172 and the second clamping groove 173, and the bearing retainer rings are clamped in the first clamping groove 172 and the second clamping groove 173; the number of the locators 18 is two, wherein the sliding rod 181 of one locator 18 is arranged in the copper sleeve 15 of the first through hole 10 and the connecting thread 183 of the locator 18 is arranged in the first threaded hole 191 of the first moving plate 19; the sliding rod 181 of the other retainer 18 is disposed in the copper bush 15 of the third through hole 13 and the connecting screw 183 of this retainer 18 is disposed in the third screw hole 13 of the second moving plate 20; the transmission threads 171 at the two ends of the rotating rod 17 are respectively and correspondingly arranged in the second threaded hole 192 and the fourth threaded hole 202, and can rotate through the torque motor 21 to drive the driving synchronous pulley 22 and the driven synchronous pulley 23 to rotate, so that the first moving plate 19 and the second moving plate 20 on the rotating rod 17 move relatively or move back to back, and the two positioners 18 move relatively or move back to back, thereby automatically completing the insertion or withdrawal of the positioners 18 into or out of the traction holes, and improving the traction efficiency; one end of the traction rod 2 is connected with a first damping plate 3 and a second damping plate 4, a magnetorheological elastomer 6 is arranged in a unit cavity of the inner cavity of the damping shell 1 divided by the first damping plate 3 and the second damping plate 4, and an electrode 7 is arranged in the magnetorheological elastomer 6; the rigidity of the magnetorheological elastomer 6 can be influenced by adjusting the current of the electrode 7, so that the vibration reduction effect of different impact forces can be realized; the utility model discloses simple structure, convenient to use, the damping is effectual, and work efficiency is high, can extensively promote and use.
The above-mentioned embodiment is right the utility model discloses an explanation, it is not right the utility model discloses a limited, any right the scheme after the simple transform of the utility model all belongs to the protection scope of the utility model.
Claims (4)
1. A universal aircraft tow bar characterized by: the damping device comprises a damping shell (1), a traction rod (2), a positioning support (8), a rotating rod (17), a positioner (18), a first moving plate (19), a second moving plate (20), a torque motor (21), a driving synchronous pulley (22), a driven synchronous pulley (23) and a transmission synchronous belt (24), wherein one end of the traction rod (2) is connected with a first damping plate (3) and a second damping plate (4), the traction rod (2) penetrates through one end of the damping shell (1) and extends outwards, and a damping flange (5) at the other end of the damping shell (1) is connected with a support flange (25) at one end of the positioning support (8) through screws; a magnetorheological elastomer (6) is arranged in a unit cavity of the inner cavity of the vibration damping shell (1) divided by the first vibration damping plate (3) and the second vibration damping plate (4), and an electrode (7) is arranged in the magnetorheological elastomer (6);
a first support (9) and a second support (12) are oppositely arranged at one end of the positioning support (8), a first through hole (10) and a second through hole (11) are arranged on the first support (9), a third through hole (13) and a fourth through hole (14) are arranged on the second support (12), copper sleeves (15) are arranged at the positions, opposite to each other, of the first through hole (10) and the third through hole (13) and inside the first through hole (10) and the third through hole (13), and bearings (16) are arranged at the positions, opposite to each other, of the second through hole (11) and the fourth through hole (14) and inside the second through hole (11); the rotating rod (17) penetrates through the bearing (16), the two ends of the rotating rod (17) are symmetrically provided with a transmission thread (171), a first clamping groove (172) and a second clamping groove (173), and bearing retaining rings are clamped in the first clamping groove (172) and the second clamping groove (173); the number of the locators (18) is two, wherein the sliding rod (181) of one locator (18) is arranged in the copper sleeve (15) of the first through hole (10), and the connecting thread (183) of the locator (18) is arranged in the first threaded hole (191) of the first moving plate (19); a sliding rod (181) of another locator (18) is arranged in a copper sleeve (15) of the third through hole (13) and a connecting thread (183) of the locator (18) is arranged in a third threaded hole (201) of the second moving plate (20); the transmission threads (171) at the two ends of the rotating rod (17) are respectively and correspondingly arranged in the second threaded hole (192) and the fourth threaded hole (202);
one end of the rotating rod (17) is connected with a driven synchronous pulley (23), a torque motor (21) is arranged on the outer side of the positioning support (8), a driving synchronous pulley (22) is arranged on an output shaft of the torque motor (21), and the driving synchronous pulley (22) is connected with the driven synchronous pulley (23) through a transmission synchronous belt (24).
2. A universal aircraft tow bar according to claim 1 wherein: the distance between the first damping plate (3) and the second damping plate (4) is 30-50 mm; the first damping plate (3) and the second damping plate (4) are arranged in the inner cavity of the damping shell (1) and form sliding fit with the inner cavity of the damping shell (1); the second threaded hole (192) and the fourth threaded hole (202) have opposite rotation directions.
3. A universal aircraft tow bar according to claim 1 wherein: the distance between the first detent groove (172) and the second detent groove (173) is slightly greater than the thickness of the bearing (16).
4. A universal aircraft tow bar according to claim 1 wherein: one end of a sliding rod (181) of the positioner (18) is provided with a positioning head (182), and the diameter of the positioning head (182) is larger than that of the copper sleeve (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920877624.XU CN210212812U (en) | 2019-06-12 | 2019-06-12 | General aircraft traction lever |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920877624.XU CN210212812U (en) | 2019-06-12 | 2019-06-12 | General aircraft traction lever |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210212812U true CN210212812U (en) | 2020-03-31 |
Family
ID=69931426
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920877624.XU Active CN210212812U (en) | 2019-06-12 | 2019-06-12 | General aircraft traction lever |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210212812U (en) |
-
2019
- 2019-06-12 CN CN201920877624.XU patent/CN210212812U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20240624 Granted publication date: 20200331 |
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| PP01 | Preservation of patent right | ||
| PD01 | Discharge of preservation of patent |
Date of cancellation: 20240805 Granted publication date: 20200331 |
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| PD01 | Discharge of preservation of patent |