CN103231799B - Integral joint used for connecting tail undercarriage - Google Patents
Integral joint used for connecting tail undercarriage Download PDFInfo
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- CN103231799B CN103231799B CN201310146183.3A CN201310146183A CN103231799B CN 103231799 B CN103231799 B CN 103231799B CN 201310146183 A CN201310146183 A CN 201310146183A CN 103231799 B CN103231799 B CN 103231799B
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- Prior art keywords
- joint
- tail undercarriage
- rocking arm
- tail
- arm joint
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- 230000007704 transition Effects 0.000 claims abstract description 9
- 210000001503 joint Anatomy 0.000 claims description 25
- 238000005516 engineering process Methods 0.000 abstract description 3
- 230000003139 buffering effect Effects 0.000 abstract 4
- 230000003014 reinforcing effect Effects 0.000 abstract 1
- 230000008030 elimination Effects 0.000 description 2
- 238000003379 elimination reaction Methods 0.000 description 2
- 241000260460 Buteogallus Species 0.000 description 1
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- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
Landscapes
- Vehicle Body Suspensions (AREA)
- Vibration Dampers (AREA)
Abstract
The invention belongs to the technology of helicopter design, and relates to an integral joint used for connecting a tail undercarriage. One surface of the integral joint is a bonding surface for bonding with an aircraft body, and the profile of the bonding surface is as the same as the skin of the aircraft body in shape; the other surface of the integral joint is a connecting surface, and a tail undercarriage rocker arm joint, a buffering strut joint and a connecting element between the tail undercarriage rocker arm joint and the buffering strut joint are arranged on the connecting surface; a triangular transition area is formed between the tail undercarriage rocker arm joint and the connecting element; four lug sheets are arranged on the tail undercarriage rocker arm joint in parallel; every two of the four lug sheets form a group and are arranged on the both sides of the tail undercarriage rocker arm joint; a bushing with a shoulder is embedded in each lug sheet; a joint bearing is installed on the lug sheet on the buffering strut joint; and a Y-shaped reinforcing rib is arranged between the tail undercarriage rocker arm joint and the buffering strut joint. The integral joint used disclosed by the invention is located outside the aircraft body, and connected with the tail undercarriage and the aircraft body respectively; and a large opening does not need to be formed in the skin of the aircraft body, thus reducing the stress concentration of the skin of the aircraft body.
Description
Technical field
The invention belongs to technology of helicopter design, relate to a kind of integral joint connected for tail undercarriage.
Background technology
At present, the alighting gear mounting means that tail wheel landing gear helicopter extensively adopts in the world is that alighting gear rocking arm and damper leg pass fuselage skin, is arranged on respectively on two frames in fuselage, is connected between frame with frame by reinforcement.This mounting means needs there is larger opening at fuselage bottom, makes power transmission herein complicated, cannot be used for monocoque.More famous has: Apache, blackhawk.
Summary of the invention
The object of the invention is to propose a kind of integral joint being suitable for the tail undercarriage connection of monocoque.Technical solution of the present invention is, integral joint 13 one side is the binding face with fuselage, the profile of binding face is identical with fuselage skin shape, another side is joint face, joint face is provided with tail undercarriage rocking arm joint 1, damper leg joint 2 and between attaching parts 4, " triangle " transition region 3 is had between tail undercarriage rocking arm joint 1 and attaching parts 4, tail undercarriage rocking arm joint 1 is provided with side by side four auricles 7, four every two of auricles 7 are one group of both sides being placed in tail undercarriage rocking arm joint 1, embedded shoulder piece cover 5 in each auricle 7, auricle 8 on damper leg joint 2 installs oscillating bearing 6, the reinforced rib 9 of " Y " shape is had between tail undercarriage rocking arm joint 1 and damper leg joint 2, one end of reinforced rib 9 connects with the auricle 8 on damper leg joint 2, the other two ends of reinforced rib 9 connect with the auricle 7 of tail undercarriage rocking arm joint 1 both sides respectively.The advantage that the present invention has and beneficial effect, this integral joint has the following advantages:
1. integral joint has taken into full account the various load that tail undercarriage produces in various harsh and unforgiving environments, the tensile, compressive, bending produced, turns round, the load such as to cut under comprising the situations such as fast landing (5.5m/s), the special deflection of tail wheel;
2. the rocking arm joint of tail undercarriage and the connection structure of damper leg joint and centre are integrated into one by integral joint, eliminate middle various attaching parts and fastener, simplify load path, decrease concentrated stress point, alleviate weight, improve the safety of connection;
3. integral joint connection is at external fuselage, does not need perforate on covering just the concentrated load of tail undercarriage can be converted to distractive load and is delivered on fuselage, thus solve the difficult problem that monocoque cannot transmit larger concentrated load.
This joint is positioned at external fuselage, connects tail undercarriage and fuselage respectively, does not need to open large mouth on fuselage skin, and the stress reducing fuselage skin is concentrated.The concentrated load of tail undercarriage effect can be converted into distractive load and be delivered on fuselage skin by this joint, can be widely used in various types of airframe structure, particularly can not bear the monocoque of concentrated load.
Accompanying drawing explanation
Fig. 1 is tail undercarriage integral joint structural representation.
Fig. 2 is the upward view of Fig. 1.
Fig. 3 is the present invention's installation site schematic diagram on helicopter.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is elaborated.
Integral joint 13 one side is the binding face with fuselage, the profile of binding face is identical with fuselage skin shape, another side is joint face, joint face is provided with tail undercarriage rocking arm joint 1, damper leg joint 2 and between attaching parts 4, " triangle " transition region 3 is had between tail undercarriage rocking arm joint 1 and attaching parts 4, tail undercarriage rocking arm joint 1 is provided with side by side four auricles 7, four every two of auricles 7 are one group of both sides being placed in tail undercarriage rocking arm joint 1, embedded shoulder piece cover 5 in each auricle 7, auricle 8 on damper leg joint 2 installs oscillating bearing 6, the reinforced rib 9 of " Y " shape is had between tail undercarriage rocking arm joint 1 and damper leg joint 2, one end of reinforced rib 9 connects with the auricle 8 on damper leg joint 2, the other two ends of reinforced rib 9 connect with the auricle 7 of tail undercarriage rocking arm joint 1 both sides respectively.
This invention adopts integrated machine to add joint 13 and is delivered on airframe structure by concentrated load on tail undercarriage 14,15.The rocking arm joint 1 of tail undercarriage and the attaching parts 4 of damper leg joint 2 and centre are integrated into one by this integral joint 13, eliminate middle various attaching parts and fastener, simplify load path, decrease concentrated stress point, alleviate weight, improve the safety of connection.This integral joint 13 is identical with fuselage skin shape with the binding face profile of fuselage, can ensure the laminating be connected with fuselage." triangle " transition region 3 is had between tail undercarriage rocking arm joint 1 and attaching parts 4, namely can be used as the transition region of stretching, clamp load, prevent stress from concentrating, the area of contact with fuselage can be increased again, reduce the shearing stress that the special deflection operating mode of tail wheel acts on joint.Tail undercarriage rocking arm joint 1 is provided with side by side four auricles 7, four every two of auricles 7 are one group of both sides being placed in tail undercarriage rocking arm joint 1, be connected with two joints of tail undercarriage rocking arm respectively; embedded shoulder piece cover 5 in each auricle 7 of rocking arm joint 1; prevent tail undercarriage from rotating the wearing and tearing of butt junction; the auricle 8 on damper leg joint 2 installs oscillating bearing 6, elimination alighting gear acts on the moment of flexure on joint, reduces stress level.The reinforced rib 9 of " Y " shape is had between tail undercarriage rocking arm joint 1 and damper leg joint 2, one end of reinforced rib 9 connects with the auricle 8 on damper leg joint 2, two ends connect with the auricle 7 of tail undercarriage rocking arm joint 1 both sides respectively in addition, for improving the stability of joint, rocking arm joint 1 auricle 7 and damper leg joint 2 auricle 8 can be reduced simultaneously and act on eccentricity on joint, reduce stress level.This integral joint 13 can not only transmit the load of X, Z-direction, and the moment of flexure that simultaneously tail undercarriage 14,15 can be acted on, torque axis turn to dynamic changes process that body can bear on fuselage.Thus make concentrated load be converted into distractive load to be delivered on airframe structure, to solve the problem that monocoque cannot transmit concentrated load.
Embodiment
Aircraft adopts the integrated machine of long 0.86 meter to add joint 13 and is delivered to by the concentrated load on tail undercarriage 14,15 on the airframe structure of employing monocoque.This integral joint 13 by tail undercarriage rocking arm joint 1, damper leg joint 2 and between attaching parts machine-shaping together, tail undercarriage rocking arm joint 1 is connected with tail boom transition phase 11 by 12 bolts, damper leg joint 2 is connected with duct 12 by 4 bolts, uniform load is transitioned on the bolt of tail boom and duct interface frame, mating frame 16 by middle " triangle " transition 3, reduce the stress level of duct 12 and tail boom transition phase 11 tie bolt, connecting portion is connected on duct 12 by self-plugging rivet.Embedded shoulder piece cover 5 in each auricle 7 of rocking arm joint 1, prevents tail undercarriage from rotating the wearing and tearing of butt junction auricle 7, damper leg joint 2 auricle 8 installs oscillating bearing 6, and elimination alighting gear acts on the moment of flexure on joint, reduces stress level.The reinforced rib 9 of " Y " shape is had between tail undercarriage rocking arm joint 1 and damper leg joint 2, one end of reinforced rib 9 connects with the auricle 8 on damper leg joint 2, two ends connect with the auricle 7 of tail undercarriage rocking arm joint 1 both sides respectively in addition, for improving the stability of joint, rocking arm joint 1 auricle 7 and damper leg joint 2 auricle 8 can be reduced simultaneously and act on eccentricity on joint, reduce stress level.
Claims (1)
1. the integral joint connected for tail undercarriage, it is characterized in that, integral joint (13) one side is the binding face with fuselage, the profile of binding face is identical with fuselage skin shape, another side is joint face, joint face is provided with tail undercarriage rocking arm joint (1), damper leg joint (2) and between attaching parts (4), " triangle " transition region (3) is had between tail undercarriage rocking arm joint (1) and attaching parts (4), tail undercarriage rocking arm joint (1) is provided with side by side four auricles (7), four every two of auricles (7) are one group of both sides being placed in tail undercarriage rocking arm joint (1), embedded shoulder piece cover (5) in each auricle (7), auricle (8) on damper leg joint (2) installs oscillating bearing (6), the reinforced rib (9) of " Y " shape is had between tail undercarriage rocking arm joint (1) and damper leg joint (2), one end of reinforced rib (9) connects with the auricle (8) on damper leg joint (2), the other two ends of reinforced rib (9) connect with the auricle (7) of tail undercarriage rocking arm joint (1) both sides respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310146183.3A CN103231799B (en) | 2013-04-24 | 2013-04-24 | Integral joint used for connecting tail undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310146183.3A CN103231799B (en) | 2013-04-24 | 2013-04-24 | Integral joint used for connecting tail undercarriage |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103231799A CN103231799A (en) | 2013-08-07 |
| CN103231799B true CN103231799B (en) | 2015-07-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310146183.3A Expired - Fee Related CN103231799B (en) | 2013-04-24 | 2013-04-24 | Integral joint used for connecting tail undercarriage |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107985560A (en) * | 2017-11-30 | 2018-05-04 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft main landing gear reinforced frame structure |
| CN108528678A (en) * | 2018-06-11 | 2018-09-14 | 中国人民解放军总参谋部第六十研究所 | A kind of unmanned helicopter buffering bindiny mechanism |
| CN112173083B (en) * | 2020-09-25 | 2023-01-31 | 中国直升机设计研究所 | Tail undercarriage attach fitting |
| CN112407243A (en) * | 2020-10-30 | 2021-02-26 | 哈尔滨飞机工业集团有限责任公司 | Helicopter horizontal tail wing connection support structure |
| CN112478140B (en) * | 2020-12-02 | 2023-09-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned aerial vehicle undercarriage connection structure |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201606331U (en) * | 2010-02-11 | 2010-10-13 | 哈尔滨飞机工业集团有限责任公司 | Landing gear uplock for airplanes |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7252266B2 (en) * | 2004-06-03 | 2007-08-07 | The Boeing Company | Landing assist apparatus eccentric bushing |
| DE102008046991A1 (en) * | 2008-09-12 | 2010-03-25 | Mt Aerospace Ag | Load-bearing thick-walled fiber composite structural component and method for its production |
| FR2955310B1 (en) * | 2010-01-19 | 2012-02-17 | Messier Dowty Sa | AIRCRAFT AIR TERMINAL TYPE OF BALANCING TYPE AND DEFORMABLE PARALLELOGRAM |
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2013
- 2013-04-24 CN CN201310146183.3A patent/CN103231799B/en not_active Expired - Fee Related
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201606331U (en) * | 2010-02-11 | 2010-10-13 | 哈尔滨飞机工业集团有限责任公司 | Landing gear uplock for airplanes |
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| Publication number | Publication date |
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| CN103231799A (en) | 2013-08-07 |
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Granted publication date: 20150701 |