CN110466744B - Undercarriage actuator cylinder erection joint - Google Patents
Undercarriage actuator cylinder erection joint Download PDFInfo
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- CN110466744B CN110466744B CN201910741561.XA CN201910741561A CN110466744B CN 110466744 B CN110466744 B CN 110466744B CN 201910741561 A CN201910741561 A CN 201910741561A CN 110466744 B CN110466744 B CN 110466744B
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- carrier
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/22—Operating mechanisms fluid
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- Aviation & Aerospace Engineering (AREA)
- Supports Or Holders For Household Use (AREA)
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Abstract
The application belongs to the technical field of undercarriage actuation installation design, concretely relates to undercarriage actuator cylinder erection joint, include: the bearing plate is provided with a first bearing edge, a second bearing edge opposite to the first bearing edge and a bearing surface extending between the first bearing edge and the second bearing edge; the first bearing edge is used for being connected with a fuselage skin; the second bearing edge is used for being connected with the main bearing frame of the undercarriage; and the joint structure is arranged on the bearing surface and is used for being connected with one end of the undercarriage actuator cylinder.
Description
Technical Field
The application belongs to the technical field of undercarriage actuation installation design, and particularly relates to an undercarriage actuator cylinder installing joint.
Background
One end of the undercarriage actuator cylinder is connected with the undercarriage, and the other end of the undercarriage actuator cylinder is connected with the machine body so as to drive the undercarriage to retract and release, and the part of a load borne by the undercarriage is transmitted to the machine body, so that stress concentration at the joint of the undercarriage actuator cylinder and the machine body is easily caused, and the structure of the machine body is damaged.
The present application is made in view of this.
Disclosure of Invention
It is an object of the present application to provide a landing gear actuator mount joint that overcomes or mitigates at least one of the disadvantages of the prior art.
The technical scheme of the application is as follows:
a landing gear actuator mount joint comprising:
the bearing plate is provided with a first bearing edge, a second bearing edge opposite to the first bearing edge and a bearing surface extending between the first bearing edge and the second bearing edge; wherein the first bearing edge is for connection with a fuselage skin; the second bearing edge is used for being connected with the main bearing frame of the undercarriage;
and the joint structure is arranged on the bearing surface and is used for being connected with one end of the undercarriage actuator cylinder.
According to at least one embodiment of the present application, the landing gear actuator cylinder is provided with a single tab at one end for connection to the joint arrangement;
the joint structure comprises double lug pieces, and the double lug pieces are arranged on the bearing surface and are used for being matched and connected with the single lug pieces.
According to at least one embodiment of the application, two opposite bearing bulges are arranged on the landing gear main bearing frame;
the bearing plate is also provided with a third bearing edge extending between the first bearing edge and the second bearing edge and a fourth bearing edge opposite to the third bearing edge; wherein the third bearing edge is adapted to be connected to an inner side surface of one of the bearing projections; the fourth bearing edge is adapted to be connected to the inside surface of the other bearing projection.
According to at least one embodiment of the present application, the bearing plate further has a load transmitting surface opposite to the bearing surface;
the landing gear actuator cylinder mounting joint further comprises a transmission plate having opposite ends and a faying surface extending between the opposite ends; wherein, one end of the transmission plate is connected with the transmission surface; the fitting surface is used for fitting to the fuselage skin.
According to at least one embodiment of the present application, the transfer plate is connected to the fuselage skin by fasteners.
According to at least one embodiment of the present application, the fuselage skin has attachment holes thereon;
the binding surface is provided with a connecting protrusion which is used for being inserted into the connecting hole.
According to at least one embodiment of the present application, the conveying plate further has a supporting surface opposite to the abutting surface;
the landing gear actuator cylinder mounting joint further comprises a support plate having a first support edge, a second support edge adjacent the first support edge; wherein the first supporting edge is connected with the load transmission surface; the second support edge is connected to the support surface.
According to at least one embodiment of the present application, the support plate further has a third support edge opposite the second support edge;
the landing gear actuator mount joint further comprises:
the first ribs are arranged on the supporting plate, one end of each first rib extends to the third supporting edge, and the other end of each first rib extends to the second supporting edge and is connected with the supporting surface;
and the second ribs are arranged on the supporting plate in a staggered manner with the first ribs, and one end of each second rib extends to the first supporting edge and is connected with the load transfer surface.
According to at least one embodiment of the application, the support plate further has a fourth support edge opposite the first support edge;
the undercarriage actuator cylinder mounting joint further comprises a connecting plate, one side surface of the connecting plate is connected with the fourth supporting edge and one end, back to the bearing plate, of the load transmission plate; the connecting plate is used for being connected with the rear frame of the machine body.
According to at least one embodiment of the present application, the body rear frame has an opening;
the connecting plate is used for being clamped into the opening.
Drawings
Figure 1 is a schematic view of a landing gear actuator mount joint according to an embodiment of the present application;
FIG. 2 is a schematic view of the landing gear actuator mount joint provided by an embodiment of the present application;
wherein:
1-a carrier plate; 2-fuselage skin; 3-main bearing frame of landing gear; 4-a joint structure; 5-a landing gear actuator; 6-transferring the carrier plate; 7-a support plate; 8-first ribs; 9-second ribs; 10-a connecting plate; 11-a rear frame of the machine body; 12-connecting projection.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that, in the present application, the embodiments and features of the embodiments may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those skilled in the art according to specific situations.
The present application is described in further detail below with reference to fig. 1-2.
A landing gear actuator mount joint comprising:
the bearing plate 1 is provided with a first bearing edge, a second bearing edge opposite to the first bearing edge and a bearing surface extending between the first bearing edge and the second bearing edge; wherein the first bearing edge is intended for connection with the fuselage skin 2; the second bearing edge is used for being connected with the landing gear main bearing frame 3;
and the joint structure 4 is arranged on the bearing surface and is used for being connected with one end of the undercarriage actuator cylinder 5, the end of the undercarriage actuator cylinder 5 is used for being connected with the machine body, and the other end of the undercarriage actuator cylinder 5 is connected with the undercarriage.
As to the landing gear actuator mounting joint disclosed in the above embodiment, it is easily understood by those skilled in the art that the landing gear actuator mounting joint is connected to the landing gear actuator 5 through the joint structure 4 disposed on the bearing plate 1, and the load transmitted through the landing gear actuator 5 is dispersed on the bearing plate 1, so that the stress concentration on the airframe can be avoided, and the load part that the second bearing edge of the bearing plate 1 is connected to the landing gear main bearing frame 3 and can bear is transmitted to the landing gear main bearing frame 3, so that the force borne by the airframe can be reduced, and the possibility of the airframe being damaged can be reduced.
In alternative embodiments, the landing gear actuator 5 is provided with a single tab at the end for connection to the joint arrangement 4;
the joint structure 4 includes two ear pieces, which are disposed on the bearing surface and are used for matching and connecting with the single ear piece.
In some alternative embodiments, the landing gear main force-bearing frame 3 is provided with two opposite bearing bulges;
the bearing plate 1 further has a third bearing edge extending between the first bearing edge and the second bearing edge, and a fourth bearing edge opposite to the third bearing edge; wherein the third bearing edge is adapted to be connected to an inner side surface of one of the bearing projections; the fourth bearing edge is adapted to be connected to the inside surface of the other bearing projection.
For the landing gear actuator tube mounting joint disclosed in the above embodiment, it is easy to understand by those skilled in the art that the bearing plate 1 is clamped between two bearing protrusions on the landing gear main bearing frame 3, so that the bearing plate 1 and the landing gear main bearing frame 3 are tightly and stably connected.
In some optional embodiments, the bearing plate 1 further has a carrying surface opposite to the carrying surface;
the landing gear actuator strut mounting joint further comprises a transfer plate 6 having opposite ends with an abutment surface extending therebetween; wherein, one end of the load transmission plate 6 is connected with the load transmission surface; the attachment face is intended to be attached to the fuselage skin 2.
As will be readily understood by those skilled in the art in view of the landing gear ram installation joint disclosed in the above embodiments, the abutting surface of the load carrying plate 6 abuts against the fuselage skin 2, so as to provide good support for the installation joint, and to enlarge the contact area with the fuselage skin 2, so as to further disperse the load borne by the load carrying plate 1 and prevent the fuselage from being damaged.
In some alternative embodiments, the load carrying plates 6 are connected to the fuselage skin 2 by fasteners.
In some alternative embodiments, the fuselage skin 2 has attachment holes;
the binding face has a connecting protrusion 12 for inserting into the connecting hole.
With the landing gear ram installation joint disclosed in the above embodiments, it will be readily appreciated by those skilled in the art that the attachment projections 12 on the abutment surface are inserted into the attachment holes to enhance the stability of the attachment of the transfer plate 6 to the fuselage skin for effective load distribution.
In some alternative embodiments, the load carrying plate 6 also has a support face opposite to the abutment face;
the landing gear actuator mount joint further comprises a support plate 7 having a first support edge, a second support edge adjacent the first support edge; wherein the first support edge is connected with the load-carrying surface; the second support edge is connected to the support surface.
With respect to the landing gear ram adapter disclosed in the above embodiments, it will be readily appreciated by those skilled in the art that the support plate 7 provides support between the carrier plate 1 and the carrier plate 6, which increases the structural stability of the landing gear ram adapter as a whole.
In some alternative embodiments, the support plate 7 also has a third support edge opposite the second support edge;
the landing gear actuator mount joint further comprises:
a plurality of first ribs 8 are arranged on the support plate 7, one end of each first rib extends to the third support edge, and the other end of each first rib extends to the second support edge and is connected with the support surface;
and a plurality of second ribs 9 are arranged on the supporting plate 7 in a staggered manner with the first ribs 8, and one end of each second rib extends to the first supporting edge and is connected with the load transfer surface.
For the landing gear actuator tube mounting joint disclosed in the above embodiments, it is easily understood by those skilled in the art that the plurality of first ribs 8 and the plurality of second ribs 9 provided on the support plate 7 can effectively disperse and transfer the load thereon, and increase the bearing capacity of the support plate 7, and one end of the first rib 8 extends to the second support edge and is connected to the support surface; one end of the second rib 9 extends to the first supporting edge and is connected with the load transferring surface, so that the load can be well transferred to the loading plate 1 and the load transferring plate 6 in a dispersing manner.
In some alternative embodiments, the support plate 7 also has a fourth support edge opposite to the first support edge;
the landing gear actuator cylinder mounting joint further comprises a connecting plate 10, one side surface of which is connected with the fourth supporting edge and one end of the load transfer plate 6, which is opposite to the bearing plate 1; the connecting plate 10 is used for connecting with the machine body rear frame 11.
As will be readily understood by those skilled in the art, the landing gear actuator mounting joint disclosed in the above embodiment is provided with the connecting plate 10 connected to the rear frame 11 of the machine body, and one side surface connected to the fourth supporting edge and one end of the load transfer plate 6 facing away from the carrier plate 1, so that the landing gear actuator mounting joint can be effectively supported, and the load transferred from the supporting plate 1, the load transfer plate 6 and the supporting plate 7 can be partially transferred to the rear frame 11 of the machine body to achieve load distribution.
In some alternative embodiments, the body rear frame 11 has an opening;
the connection plate 10 is intended to be snapped into the opening.
In some optional embodiments, the bearing plate 1, the joint structure 4, the load transfer plate 6, the support plate 7, the first ribs 8, the second ribs 9, and the connecting plate 10 are made of titanium alloy powder by using a titanium alloy laser rapid prototyping technology.
So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.
Claims (4)
1. A landing gear actuator mount joint, comprising:
a carrier plate (1) having a first carrier edge, a second carrier edge opposite the first carrier edge, a carrier surface extending between the first carrier edge and the second carrier edge; wherein the first carrying edge is intended to be connected to a fuselage skin (2); the second bearing edge is used for being connected with a main bearing frame (3) of the undercarriage;
a joint arrangement (4) arranged on the bearing surface for connection to one end of a landing gear actuator cylinder (5);
the main bearing frame (3) of the landing gear is provided with two opposite bearing bulges;
the carrier plate (1) further has a third carrier edge extending between the first and second carrier edges, a fourth carrier edge opposite the third carrier edge; wherein the third bearing edge is adapted to engage an inside surface of one of the bearing projections; said fourth bearing edge for engaging the inside surface of another of said bearing projections;
the bearing plate (1) is also provided with a transmission and carrying surface opposite to the bearing surface;
the landing gear actuator strut mounting joint further comprises a transfer plate (6) having opposite ends, an abutment surface extending between the ends; wherein one end of the transmission carrier plate (6) is connected with the transmission carrier surface; the fitting surface is used for fitting to the fuselage skin (2);
the fuselage skin (2) is provided with a connecting hole;
the binding surface is provided with a connecting protrusion (12) which is used for being inserted into the connecting hole;
the conveying plate (6) is also provided with a supporting surface opposite to the binding surface;
the landing gear actuator mount joint further comprises a support plate (7) having a first support edge, a second support edge adjacent the first support edge; wherein the first support edge is connected with the carrying surface; the second support edge is connected with the support surface;
the support plate (7) further has a fourth support edge opposite to the first support edge;
the undercarriage actuator cylinder mounting joint further comprises a connecting plate (10), one side surface of which is connected with the fourth supporting edge and one end of the transmission carrier plate (6) facing away from the bearing plate (1); the connecting plate (10) is used for being connected with a rear frame (11) of the machine body;
the machine body rear frame (11) is provided with an opening;
the connecting plate (10) is used for being clamped into the opening.
2. The landing gear actuator mount joint of claim 1,
a single lug is arranged at one end, used for being connected with the joint structure (4), of the undercarriage actuating cylinder (5);
the joint structure (4) comprises double lugs arranged on the bearing surface and used for being matched and connected with the single lug.
3. The landing gear actuator mount joint of claim 1,
the transmission support plate (6) is connected with the fuselage skin (2) through a fastener.
4. The landing gear actuator mount joint of claim 1,
the support plate (7) further has a third support edge opposite the second support edge;
the landing gear actuator mount joint further comprises:
a plurality of first ribs (8) arranged on the support plate (7), one end of each first rib extending to the third support edge and the other end extending to the second support edge and connected with the support surface;
and the second ribs (9) are arranged on the supporting plate (7) and are staggered with the first ribs (8), and one end of each second rib extends to the first supporting edge and is connected with the load carrying surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910741561.XA CN110466744B (en) | 2019-08-12 | 2019-08-12 | Undercarriage actuator cylinder erection joint |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910741561.XA CN110466744B (en) | 2019-08-12 | 2019-08-12 | Undercarriage actuator cylinder erection joint |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110466744A CN110466744A (en) | 2019-11-19 |
| CN110466744B true CN110466744B (en) | 2022-11-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910741561.XA Active CN110466744B (en) | 2019-08-12 | 2019-08-12 | Undercarriage actuator cylinder erection joint |
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| Country | Link |
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| CN (1) | CN110466744B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173083B (en) * | 2020-09-25 | 2023-01-31 | 中国直升机设计研究所 | Tail undercarriage attach fitting |
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| CN205931219U (en) * | 2016-08-11 | 2017-02-08 | 中国航空工业集团公司西安飞机设计研究所 | Take two -way joint that bears of locking |
| 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 |
| CN207565831U (en) * | 2017-11-29 | 2018-07-03 | 中国直升机设计研究所 | A kind of integrated form helicopter landing gear damper leg connector |
| CN109573067A (en) * | 2018-12-04 | 2019-04-05 | 中国航空工业集团公司西安飞机设计研究所 | A kind of L-type engine hanging joint |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2998868B1 (en) * | 2012-11-30 | 2016-02-05 | Airbus Operations Sas | INTERMEDIATE FASTENING DEVICE BETWEEN AN AIRCRAFT FUSELAGE AND AN AIRCRAFT LANDING TRAIN |
| US9399507B2 (en) * | 2014-01-22 | 2016-07-26 | The Boeing Company | Joints between a composite skin and a load-bearing component and methods of forming same |
| GB2563826A (en) * | 2017-06-19 | 2019-01-02 | Airbus Operations Ltd | Landing Gear |
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2019
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Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101065292A (en) * | 2004-08-30 | 2007-10-31 | 梅西尔-道蒂（美国）公司 | Dual brace-determinate landing gear |
| CN202863759U (en) * | 2012-07-13 | 2013-04-10 | 哈尔滨飞机工业集团有限责任公司 | Stay bar structure of retractable nose landing gear |
| CN205203346U (en) * | 2015-12-04 | 2016-05-04 | 中国航空工业集团公司西安飞机设计研究所 | Close section baggage compartment bearing structure |
| CN205931219U (en) * | 2016-08-11 | 2017-02-08 | 中国航空工业集团公司西安飞机设计研究所 | Take two -way joint that bears of locking |
| CN207565831U (en) * | 2017-11-29 | 2018-07-03 | 中国直升机设计研究所 | A kind of integrated form helicopter landing gear damper leg connector |
| 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 |
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| Publication number | Publication date |
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| CN110466744A (en) | 2019-11-19 |
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