CN110937134B - Vibration damping flexible adjusting device and method for aircraft auxiliary power device installation system - Google Patents
Vibration damping flexible adjusting device and method for aircraft auxiliary power device installation system Download PDFInfo
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- CN110937134B CN110937134B CN201911248040.7A CN201911248040A CN110937134B CN 110937134 B CN110937134 B CN 110937134B CN 201911248040 A CN201911248040 A CN 201911248040A CN 110937134 B CN110937134 B CN 110937134B
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- 238000013016 damping Methods 0.000 title claims abstract description 91
- 238000009434 installation Methods 0.000 title claims abstract description 20
- 238000000034 method Methods 0.000 title claims abstract description 17
- 210000001503 joint Anatomy 0.000 claims abstract description 24
- 229920001971 elastomer Polymers 0.000 claims description 33
- 239000000806 elastomer Substances 0.000 claims description 30
- 238000001125 extrusion Methods 0.000 claims description 4
- 230000009467 reduction Effects 0.000 claims description 4
- 230000000694 effects Effects 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 abstract 1
- 230000008569 process Effects 0.000 description 3
- 239000006096 absorbing agent Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Vibration Prevention Devices (AREA)
Abstract
A vibration damping flexible adjusting device and a method of an aircraft auxiliary power device installation system comprise that an integrated vibration damping brace rod is connected with an adapter on an auxiliary power device support through a vibration damping joint bearing at the end part. The vibration damping joint bearing is provided with an axial through pin hole, and the outside of the vibration damping joint bearing is wrapped with a lug; the damping joint bearing comprises a periphery connected with the integrated damping stay bar, and a through hole coaxial with the pin hole is arranged in the middle of the periphery; and a middle joint elastic body, elastic body bushings on two sides and a shaft sleeve are arranged in the peripheral through hole. The invention provides a device and a method capable of reducing the installation difficulty of an auxiliary power device.
Description
Technical Field
The invention relates to the field of installation and structural design of an auxiliary power device of an airplane, and provides a novel method for installing and adjusting a support of the auxiliary power device of the airplane, in particular to a method for damping and isolating vibration of the auxiliary power device by using a damping joint bearing and combining the damping joint bearing with a support rod to achieve local flexible adjustment of an installation system.
Background
The auxiliary power device mounting system is a bearing structure capable of reliably mounting an auxiliary power device on an airplane body, and is required to meet the requirement of multidirectional vibration reduction and have multidirectional bearing capacity, and simultaneously, the occupied space size and the occupied weight are required to be as small as possible.
The traditional auxiliary power device mounting system mainly comprises three parts, namely a front left mounting point, a front right mounting point and a rear mounting point. The basic construction unit of each mounting point is composed of an auxiliary power device support, a vibration isolator and a support rod. The vibration isolator is used as an independent component and is positioned between the auxiliary power device mounting section and the airplane stay bar, and the vibration isolator is provided with a conical bolt, a vibration reduction part, a structural shell and an auxiliary tensile connecting bolt from inside to outside. In general appearance, the isolator is short cylindrical, and the cylinder radius is great, requires during the installation that relevant auxiliary power device support cantilever is overhanging, just can realize the installation to auxiliary power device equipment, crowds to account for limited engine pipe-line system installation space, leads to compact structure nature poor, and the installation space who leaves for other parts is narrow and small.
In addition, in order to exert the vibration damping effect, the vibration isolators must be arranged in a specific direction, and when the auxiliary power device support is assembled with the vibration isolators and the strut assembly, the three mounting points are required to be assembled simultaneously. In view of the poor adjustability of the conventional auxiliary power device mounting system, the space posture of the auxiliary power device needs to be continuously adjusted in the assembling process, the operation is complex, and the consumed time is long.
Summary of the invention
In view of the above problems in the prior art, the present invention provides a damping flexible adjustment device and method for an aircraft auxiliary power unit mounting system.
In order to achieve the purpose, the invention adopts the technical scheme that: a vibration damping flexible adjusting device of an aircraft auxiliary power device mounting system is characterized in that: the damping device comprises an integrated damping support rod, wherein damping joint bearings are arranged at two ends of the integrated damping support rod; the vibration damping joint bearing is provided with an axial through pin hole, and the outside of the vibration damping joint bearing is wrapped with a lug; the damping joint bearing comprises a periphery connected with the integrated damping stay bar, and a through hole coaxial with the pin hole is arranged in the middle of the periphery; the through hole on the periphery is provided with a middle joint elastic body, elastic body bushings on two sides and a shaft sleeve; the middle joint elastic body is arranged in the center of the through hole, the elastic body bushings on the two sides are arranged on the two sides of the middle joint elastic body and extend out of the periphery, and the shaft sleeves are arranged on the inner outer sides of the elastic body bushings on the two sides; the lug plates are not contacted with the shaft sleeve.
The vibration damping joint bearing at one end of the integrated vibration damping support rod is connected with a support on the auxiliary power device through an adapter; and a pin shaft with threads on two sides is arranged on the adapter, passes through a pin hole of the vibration damping joint bearing, and is screwed down to enable the adapter to axially clamp the vibration damping joint bearing.
The other end of the integrated damping brace rod is arranged on the airplane body.
The middle joint elastic body is of a ball structure with a through hole in the middle.
The inner ends of the elastomer bushings on the two sides are connected with the middle joint elastomer, so that the end parts of the middle joint elastomer are embedded in the elastomer bushings on the two sides; one end of the shaft sleeve arranged inside the elastomer bushings on the two sides is propped against the middle joint elastomer, and the other end of the shaft sleeve is flush with the outer ends of the elastomer bushings on the two sides.
The method for mounting the auxiliary power device by using the vibration-damping flexible adjusting device is characterized in that:
1) The auxiliary power device is provided with a front left mounting point a, a front right mounting point b and a rear mounting point c;
2) Each mounting point is provided with more than or equal to one support, and each support is provided with more than or equal to one adapter;
3) Inserting one end of the integrated vibration damping support rod into the adapter for installation, and installing and connecting the other end of the integrated vibration damping support rod with the airplane body; each mounting point is provided with more than or equal to two integrated damping support rods;
in the step 3), a specific installation method of the integrated vibration reduction stay bar and the adapter comprises the following steps: a pin shaft with threads at two ends penetrates through a pin hole in the middle of the vibration damping joint bearing, two ends of the pin shaft are connected with an adapter through threads, and the integrated vibration damping support rod is rotated to a position to be positioned; the adapter is screwed up, so that the adapter axially extrudes the vibration damping joint bearing, the axial force acting on the shaft sleeve is adjusted, the radial extrusion of the pin shaft is increased by the joint elastomer in the middle of the inner part, and the positioning is controlled.
The beneficial effects created by the invention are as follows:
the invention is simple to operate, changes the axial force applied to the elastic body through the adapter, further adjusts the fit clearance between the integrated vibration-damping support rod and the assembling bolt, adjusts the required fit state according to the process requirement of the assembling process of the auxiliary power device body, and has clearance controllability. Under the state of close fit, the integrated vibration damping stay bar has the vibration damping characteristic in any direction, and the defect that the traditional independent vibration isolator needs to be arranged in a specific direction is overcome; under clearance fit state, the connecting piece degree of freedom can be released, makes it rotate around the axle, reduces the space adjustment operation when the auxiliary power device body installation, reduces assembly operation complexity, increases work efficiency.
The integrated damping support rod has the characteristics of a common joint bearing, the damping joint bearing has the axial deflection characteristic, the requirement on the direction of the support rod lug is weakened in the design process of an auxiliary power device mounting system, and the design difficulty of the lug and the support on one side of the machine body is reduced.
Drawings
FIG. 1 is a schematic view of the present invention in use;
FIG. 2 is a schematic view of the mounting point b in FIG. 1;
fig. 3 is a sectional view of the damped knuckle bearing of fig. 2.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. It is to be understood that the embodiments described are some, but not all embodiments of the inventive subject matter. All other embodiments, which can be obtained by a person skilled in the art without any inventive effort based on the described embodiments of the invention, belong to the scope of protection of the invention.
Unless defined otherwise, technical or scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The use of the terms "comprising" or "including" and the like in the creation of the present invention, means that the element or item appearing before the term covers the element or item listed after the term and its equivalents, without excluding other elements or items. The terms "connected" and "coupled" and the like are not restricted to physical or mechanical connections, but may also include electrical connections, whether direct or indirect. "front", "rear", "inside", "outside", and the like are used merely to indicate relative positional relationships, and when the absolute position of the object being described is changed, the relative positional relationships may also be changed accordingly.
In order to keep the following description of the embodiments of the invention clear and concise, a detailed description of known functions and known parts of the invention is omitted.
A vibration damping flexible adjusting device of an aircraft auxiliary power device installation system comprises an integrated vibration damping support rod 1, wherein vibration damping joint bearings 4 are arranged at two ends of the integrated vibration damping support rod 1; the vibration damping joint bearing 4 is provided with an axial through pin hole, and the outside of the vibration damping joint bearing is wrapped with a lug 9; the damping joint bearing 4 comprises a periphery 5 connected with the integrated damping stay bar 1, and a through hole coaxial with the pin hole is arranged in the middle of the periphery 5; a middle joint elastic body 6, elastic body bushes 7 at two sides and a shaft sleeve 8 are arranged in a through hole of the periphery 5; the middle joint elastic body 6 is arranged in the center of the through hole, the elastic body bushings 7 on the two sides are arranged on the two sides of the middle joint elastic body 6 and extend out of the periphery 5, and the shaft sleeves 8 are arranged on the inner outer sides of the elastic body bushings 7 on the two sides; the lug 9 and the shaft sleeve 8 are not contacted with each other.
The middle joint elastic body 6 is of a ball structure with a through hole in the middle.
The inner ends of the elastomer bushings 7 at the two sides are connected with the middle joint elastomer 6, so that the end parts of the middle joint elastomer 6 are embedded in the elastomer bushings 7 at the two sides; one end of the shaft sleeve 8 arranged inside the elastomer bushings 7 on the two sides props against the middle joint elastomer 6, and the other end of the shaft sleeve is flush with the outer ends of the elastomer bushings 7 on the two sides.
The vibration damping joint bearing 4 at one end of the integrated vibration damping stay bar 1 is connected with a support 3 on the auxiliary power device through an adapter 2; be equipped with the round pin axle that both sides have the screw thread on adapter 2, the round pin axle passes damping joint bearing 4's pinhole, screws up the round pin axle and makes adapter 2 axial clamp damping joint bearing 4. The other end of the integrated damping brace rod 1 is arranged on the airplane body.
The method for mounting the auxiliary power device by using the vibration damping flexible adjusting device comprises the following steps:
1, a front left mounting point a, a front right mounting point b and a rear mounting point c are arranged on an auxiliary power device;
2, each mounting point is provided with more than or equal to one support 3, and each support 3 is provided with more than or equal to one adapter 2;
3, inserting one end of the integrated vibration damping stay bar 1 into the adapter 2 for installation, and installing and connecting the other end of the integrated vibration damping stay bar with the airplane body; each mounting point is provided with more than or equal to two integrated damping support rods 1;
in step 3, the specific installation method of the integrated damping brace rod 1 and the adapter 2 is as follows: a pin shaft with threads at two ends penetrates through a pin hole in the middle of the vibration damping joint bearing 4, two ends of the pin shaft are connected with the adapter 2 through threads, and the integrated vibration damping support rod 1 is rotated to a position to be positioned; the adapter 2 is screwed down, so that the adapter 2 axially extrudes the vibration damping joint bearing 4, the axial force acting on the shaft sleeve 8 is adjusted, the radial extrusion of the pin shaft is increased by the joint elastic body 6 in the middle of the inside, and the positioning is controlled.
When in specific use:
the auxiliary power device mounting system combines the damping joint bearing with the integrated damping stay bar 1 to form an integrated damping structure. Fig. 3 depicts a damped oscillating bearing, the main configuration being in the order: the outer ring (5) and the stay bar (1) are integrated, and the inner surface of the outer ring (5) and the outer surface of the middle joint elastic body (7) form a joint bearing structure which is matched with each other; the inner surfaces of the elastomer bushings (7) at two sides are matched with the outer surface of the bent shaft sleeve (8), and the movement of the joint bearing is controlled by using the pressure generated by elastic expansion. The elastomer bushings (7) on the two sides comprise a left rubber elastomer and a right rubber elastomer, and the inner sides of the elastomer bushings are provided with axial through holes.
Axial force is applied to the left and right crimped shaft sleeves (8) so that the two rubber elastic bodies and the middle joint elastic body (6) are compressed and expanded, a radial assembling bolt is clamped, and the radial play of the oscillating bearing of the shock absorber is controlled by adjusting the axial force acting on the crimped shaft sleeves (8). The axial force of the bent side shaft sleeve (8) is increased, the radial clearance is reduced to be tightly attached, the circumferential expansion pressure is increased, the circumferential rotation of the assembling bolt is controlled, and the effect of the traditional shock absorber is realized by utilizing the damping characteristic of the elastomer material; the axial force of the bent shaft sleeve (8) is reduced, the radial clearance is increased, the expansion pressure between the elastomer material and the assembling bolt is reduced, the flexible adjusting function of the joint bearing is exerted, and the assembling difficulty is reduced.
Adapter (2) is as transition connection junction component between auxiliary power device support and integration damping vaulting pole, and adapter (2) and vaulting pole (1) constitute static indefinite structure, have the pivoting characteristic, under auxiliary power device support spatial position confirms, can manually carry out the adjustment of minizone and remove cooperation auxiliary power device support.
Although the present invention has been described with reference to a preferred embodiment, it should be understood that various changes, substitutions and alterations can be made herein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (7)
1. A damping flexible adjustment device of an aircraft auxiliary power unit mounting system is characterized in that: the damping device comprises an integrated damping support rod (1), wherein damping joint bearings (4) are arranged at two ends of the integrated damping support rod (1); the vibration damping joint bearing (4) is provided with an axial through pin hole, and the outside of the vibration damping joint bearing is wrapped with a lug (9); the damping joint bearing (4) comprises an outer periphery (5) connected with the integrated damping stay bar (1) inside, and a through hole coaxial with the pin hole is formed in the middle of the outer periphery (5); a middle joint elastic body (6), elastic body bushings (7) at two sides and a shaft sleeve (8) are arranged in a through hole of the periphery (5); the middle joint elastic body (6) is arranged in the center of the through hole, the elastic body bushings (7) on the two sides are arranged on the two sides of the middle joint elastic body (6) and extend out of the periphery (5), and the shaft sleeves (8) are arranged on the outer sides of the elastic body bushings (7) on the two sides; the lug (9) and the shaft sleeve (8) are not contacted with each other.
2. A vibration damping compliance adjustment device for an aircraft auxiliary power unit mounting system as claimed in claim 1, wherein: the vibration damping joint bearing (4) at one end of the integrated vibration damping brace rod (1) is connected with a support (3) on the auxiliary power device through an adapter (2); be equipped with the round pin axle that both sides take the screw thread on adapter (2), the round pin axle passes the pinhole of damping joint bearing (4), screws up the round pin axle and makes adapter (2) axial clamp damping joint bearing (4).
3. A vibration damping compliance adjustment device for an aircraft auxiliary power unit mounting system as claimed in claim 2, wherein: the other end of the integrated damping brace rod (1) is arranged on the airplane body.
4. A vibration damping compliance adjustment device for an aircraft auxiliary power unit mounting system as claimed in claim 1, wherein: the middle joint elastic body (6) is of a structure with a through hole in the middle.
5. A vibration damping compliance adjustment device for an aircraft auxiliary power unit mounting system as claimed in claim 1, wherein: the joint of the inner ends of the elastomer bushings (7) at the two sides and the middle joint elastomer (6) ensures that the end part of the middle joint elastomer (6) is embedded in the elastomer bushings (7) at the two sides; one end of a shaft sleeve (8) arranged inside the elastomer bushings (7) on the two sides props against the middle joint elastomer (6), and the other end of the shaft sleeve is flush with the outer ends of the elastomer bushings (7) on the two sides.
6. A method of auxiliary power unit installation using a vibration damping compliance adjusting device as claimed in any one of claims 1 to 5, wherein:
1) The auxiliary power device is provided with a front left mounting point a, a front right mounting point b and a rear mounting point c;
2) Each mounting point is provided with more than one support (3), and each support (3) is provided with more than one adapter (2);
3) One end of the integrated damping brace rod (1) is inserted into the adapter (2) for installation, and the other end of the integrated damping brace rod is connected with the airplane body in an installation manner; each mounting point is provided with more than or equal to two integrated damping support rods (1).
7. The auxiliary power unit mounting method according to claim 6, characterized in that: in the step 3), the specific installation method of the integrated vibration reduction support rod (1) and the adapter (2) is as follows: a pin shaft with threads at two ends penetrates through a pin hole in the middle of the vibration damping joint bearing (4), two ends of the pin shaft are connected with the adapter (2) through threads, and the integrated vibration damping support rod (1) is rotated to a position to be positioned; screwing up adapter (2), making adapter (2) axial extrusion damping joint bearing (4), the axial force of adjustment effect on axle sleeve (8) makes inside middle part joint elastomer (6) increase the radial extrusion to the round pin axle, the control location.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911248040.7A CN110937134B (en) | 2019-12-09 | 2019-12-09 | Vibration damping flexible adjusting device and method for aircraft auxiliary power device installation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911248040.7A CN110937134B (en) | 2019-12-09 | 2019-12-09 | Vibration damping flexible adjusting device and method for aircraft auxiliary power device installation system |
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| Publication Number | Publication Date |
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| CN110937134A CN110937134A (en) | 2020-03-31 |
| CN110937134B true CN110937134B (en) | 2022-12-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911248040.7A Active CN110937134B (en) | 2019-12-09 | 2019-12-09 | Vibration damping flexible adjusting device and method for aircraft auxiliary power device installation system |
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| CN106507766B (en) * | 2008-12-16 | 2014-03-19 | 成都飞机工业（集团）有限责任公司 | The auxiliary hanging beam of fixed unmanned vehicle engine |
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| CN107327480A (en) * | 2016-04-29 | 2017-11-07 | 株洲时代新材料科技股份有限公司 | A kind of combined rubber metal joint bearing and method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2763942T3 (en) * | 2014-12-30 | 2020-06-01 | Airbus Operations Sl | Suspension system for an auxiliary power unit of an aircraft |
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2019
- 2019-12-09 CN CN201911248040.7A patent/CN110937134B/en active Active
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|---|---|---|---|---|
| CN106507766B (en) * | 2008-12-16 | 2014-03-19 | 成都飞机工业（集团）有限责任公司 | The auxiliary hanging beam of fixed unmanned vehicle engine |
| CN201566696U (en) * | 2009-12-04 | 2010-09-01 | 湖南中联重科专用车有限责任公司 | Damping device of steering axle |
| CN102530254A (en) * | 2012-02-13 | 2012-07-04 | 丁慧 | Vibration-damping device for auxiliary engines of military aircrafts |
| CN204937535U (en) * | 2015-08-14 | 2016-01-06 | 中国航空工业集团公司西安飞机设计研究所 | A kind of setting device and there is its aircraft |
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Non-Patent Citations (1)
| Title |
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