CN109795704A - A kind of joint assembly - Google Patents
A kind of joint assembly Download PDFInfo
- Publication number
- CN109795704A CN109795704A CN201711140566.4A CN201711140566A CN109795704A CN 109795704 A CN109795704 A CN 109795704A CN 201711140566 A CN201711140566 A CN 201711140566A CN 109795704 A CN109795704 A CN 109795704A
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- Prior art keywords
- boss
- gondola
- joint
- hole
- major joint
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Abstract
The present invention provides a kind of joint assemblies, are related to field of airplane structure, and component includes: major joint (1), Front wing spar, gondola hanger and tension bolt (6).Gondola hanger is connected on Front wing spar by the component by major joint (1), when not executing refueling mission, it can be achieved that the fast quick-detach of structure for pod, restores basic transportation type, does not increase the construction weight of aircraft, to improve the mission payload of aircraft；It and after dismantling gondola, can preferably guarantee the aerodynamic configuration of original machine type, realize oiling type being quickly converted to conventional transport type.
Description
Technical field
The present invention relates to field of airplane structure, in particular to a kind of joint assembly.
Background technique
Current fuel charger model both domestic and external, fuel charger gondola major joint and gondola are non-removable structure.It is not executing
When refueling mission, the gondola of fuel charger can not be dismantled, and when flight increases aero-structure weight, reduce mission payload.
Summary of the invention
The present invention provides a kind of joint assemblies, to solve the problems, such as that gondola can not be dismantled.
In order to achieve the above object, the present invention adopts the following technical scheme:
A kind of joint assembly is, it can be achieved that the fast quick-detach of gondola, comprising:
Major joint is in concave shape, and the lower end of the major joint is provided with edge strip, in the left part and right half of the major joint
Not She Zhi boss, each boss is provided with lateral round first through hole at the position of the edge strip, described
Nut is installed in one through-hole, and passes through the edge strip and opens up longitudinal bolt hole in each boss lower end；
Front wing spar offers the second through-hole compatible with the bolt hole of the boss on the Front wing spar；
Gondola hanger is provided with auricle compatible with the bolt hole of the boss on the gondola hanger；
Tension bolt, the tension bolt sequentially pass through auricle, the Front wing spar of the gondola hanger of respective side
The second through-hole and the bolt hole of the major joint boss be fixedly connected with the nut.
Optionally, reinforcing rib is respectively arranged at left and right sides of each boss.
Optionally, it is provided with prominent auricle on the major joint edge strip, for being fixedly connected for leading edge lid.
Beneficial effects of the present invention: the joint assembly connect by major joint, by gondola hanger with Front wing spar, it can be achieved that
The fast quick-detach of structure for pod can be restored basic transportation type, no when aircraft does not execute refueling mission by the fast quick-detach of gondola
The construction weight for increasing aircraft, to improve the mission payload of aircraft；And after dismantling gondola, it can preferably guarantee original machine type
Aerodynamic configuration, realize oiling type being quickly converted to conventional transport type.
Detailed description of the invention
The drawings herein are incorporated into the specification and forms part of this specification, and shows and meets implementation of the invention
Example, and be used to explain the principle of the present invention together with specification.
Fig. 1 is inventive joint assemble cross-section；
Fig. 2 is inventive joint component side view；
Fig. 3 is inventive joint assembly plan view.
Specific embodiment
Example embodiments are described in detail here, and the example is illustrated in the accompanying drawings.Following description is related to
When attached drawing, unless otherwise indicated, the same numbers in different drawings indicate the same or similar elements.
As shown in Figure 1 to Figure 3, joint assembly of the invention, it can be achieved that gondola fast quick-detach, component includes: major joint
1, Front wing spar, gondola hanger, tension bolt 6.
Specifically, major joint 1 is in concave shape, and the lower end of major joint is provided with edge strip 2, in the left part and right half of major joint
Not She Zhi boss 3, each boss 3 is provided with lateral round first through hole 4 at the position of edge strip 2, in first through hole 4
Barrel nut 5 is installed, the internal diameter of first through hole 4 is equal with the outer diameter of nut 5, and passes through edge strip 2 and open in each 3 lower end of boss
Equipped with longitudinal bolt hole；Second through-hole compatible with the bolt hole of boss 3 is offered on Front wing spar；It is set on gondola hanger
It is equipped with auricle compatible with the bolt hole of boss 3；The bolt hole internal diameter phase of 6 light bar segment outer diameter of tension bolt and 3 lower end of boss
Deng tension bolt 6 sequentially passes through the auricle of the gondola hanger of respective side, the second through-hole of Front wing spar and major joint boss
Bolt hole is fixedly connected with nut 5.In the present embodiment, reinforcing rib 7 is preferably respectively set at left and right sides of boss, increases master
The stability of connector 1 improves the reliability of connection.Further, it is also set up on the edge strip 2 of major joint 1 there are three prominent auricle,
For being fixedly connected for leading edge lid.In the present embodiment, the air-flow unfavourable balance of boss 3 and wing lower surface is less than 0.3mm.
Using the aircraft of joint assembly of the invention, in flight, gondola reaches the course of wing and lateral load is led to
It crosses 6 light bar segment of tension bolt and is directly transmitted to major joint 1, longitudinal loading is transmitted to major joint 1 by nut 5, furthermore the two tensions
For bolt 6 with gondola hanger also subject to the pitching, yaw and rolling moment of gondola, structure load path is clearly reliable.
Joint assembly of the invention, gondola hanger is connected on Front wing spar by major joint 1, it can be achieved that gondola it is fast
Quick-detach.Aircraft is when executing refueling mission, Fast Installation structure for pod, and aircraft is made to become oiling type, realizes refueling mission；
Aircraft, it can be achieved that the fast quick-detach of structure for pod, restores basic transportation type, does not increase the knot of aircraft when not executing refueling mission
Structure weight, to improve the mission payload of aircraft；In addition, aircraft can preferably guarantee the gas of original machine type after gondola disassembly
Dynamic shape, realizes oiling type being quickly converted to conventional transport type.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of protection of the claims
It is quasi-.
Claims (3)
1. a kind of joint assembly is, it can be achieved that the fast quick-detach of gondola characterized by comprising
Major joint (1) is in concave shape, and the lower end of the major joint (1) is provided with edge strip (2), the left part in the major joint (1)
It is respectively set boss (3) with right part, each boss (3) is provided with lateral circle at the position of the edge strip (2)
First through hole (4) is equipped with nut (5) in the first through hole (4), and passes through the edge strip (2) in each boss
(3) lower end opens up longitudinal bolt hole；
Front wing spar offers the second through-hole compatible with the bolt hole of the boss (3) on the Front wing spar；
Gondola hanger is provided with auricle compatible with the bolt hole of the boss (3) on the gondola hanger；
Tension bolt (6), before the tension bolt (6) sequentially passes through the auricle of the gondola hanger of respective side, the wing
The bolt hole of second through-hole of beam and the major joint boss (3) is fixedly connected with the nut (5).
2. joint assembly according to claim 1, which is characterized in that distinguish in the left and right sides of each boss (3)
It is provided with reinforcing rib (7).
3. joint assembly according to claim 1, which is characterized in that be provided with prominent ear on the major joint edge strip (2)
Piece is fixedly connected for leading edge lid.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711140566.4A CN109795704A (en) | 2017-11-16 | 2017-11-16 | A kind of joint assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711140566.4A CN109795704A (en) | 2017-11-16 | 2017-11-16 | A kind of joint assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109795704A true CN109795704A (en) | 2019-05-24 |
Family
ID=66555928
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711140566.4A Pending CN109795704A (en) | 2017-11-16 | 2017-11-16 | A kind of joint assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109795704A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112498696A (en) * | 2020-12-09 | 2021-03-16 | 中国航空工业集团公司沈阳飞机设计研究所 | Swing stopper for airplane nacelle |
| CN113232877A (en) * | 2021-06-11 | 2021-08-10 | 江西洪都航空工业集团有限责任公司 | Nacelle quick-release suspension joint |
-
2017
- 2017-11-16 CN CN201711140566.4A patent/CN109795704A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112498696A (en) * | 2020-12-09 | 2021-03-16 | 中国航空工业集团公司沈阳飞机设计研究所 | Swing stopper for airplane nacelle |
| CN113232877A (en) * | 2021-06-11 | 2021-08-10 | 江西洪都航空工业集团有限责任公司 | Nacelle quick-release suspension joint |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190524 |
|
| WD01 | Invention patent application deemed withdrawn after publication |