CN109455304B - Static and indefinite hanging structure of airplane - Google Patents
Static and indefinite hanging structure of airplane Download PDFInfo
- Publication number
- CN109455304B CN109455304B CN201811453200.7A CN201811453200A CN109455304B CN 109455304 B CN109455304 B CN 109455304B CN 201811453200 A CN201811453200 A CN 201811453200A CN 109455304 B CN109455304 B CN 109455304B
- Authority
- CN
- China
- Prior art keywords
- hanging
- middle joint
- wing
- lug
- short beam
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000003068 static effect Effects 0.000 title claims description 17
- 210000001503 joint Anatomy 0.000 claims abstract description 124
- 239000000725 suspension Substances 0.000 claims description 12
- 238000010008 shearing Methods 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 abstract description 7
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000008719 thickening Effects 0.000 description 1
Classifications
-
- 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
- B64D47/00—Equipment not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Load-Engaging Elements For Cranes (AREA)
- Connection Of Plates (AREA)
- Load-Bearing And Curtain Walls (AREA)
Abstract
The invention relates to the technical field of aircraft breakage safety, and provides an aircraft backup stationary and variable hanging structure, which comprises a left wall plate, a right wall plate, a hanging middle joint lug and a lateral connecting rod; the side wall plate lugs and the short beam middle joint lugs are overlapped back to jointly transmit heading load and vertical load, and when one lug is damaged, the other lug transmits load, so that the load of the hanging middle joint is unchanged; meanwhile, the middle connector of the wing hanging adopts a split design, so that the integral failure of the wing hanging connector caused by crack expansion is avoided. The side wall plate and the hanging short beam lug form a redundant design, the single side connecting rod is formed by two connecting sheets to form a backup design, meanwhile, the wing hanging joint adopts a split design, so that the force transmission path between the hanging and the wing is not changed under the condition of breakage of a single connecting piece, the concentrated force load of the lower wall plate of the wing is greatly reduced, and the weight of the lower wall plate assembly of the wing is reduced; novel structure, simplicity and wide application prospect.
Description
Technical Field
The invention relates to the technical field of aircraft breakage safety, in particular to an aircraft static and indefinite hanging structure with a backup design.
Background
The design of the hanging structure of the existing aircraft has two ideas, one is a static and indefinite hanging structure scheme, and as shown in fig. 1, the scheme is adopted by the aircraft of C919 and boeing series; a statically determinate hanging structure scheme is adopted by the aeroplane of the air passenger series as shown in figure 2.
The middle joint, the upper support rod joint and the lower support rod joint corresponding to the statically indeterminate hanging structure are all of single structure design, and if a single joint is damaged, the force transmission path is changed; the front hanging connector, the rear hanging connector and the lug which correspond to the statically determined hanging structure are all in backup design, for example, a single connector is damaged, and a force transmission path is not changed.
Based on the prior art, there are the following disadvantages:
1. if a static and indefinite hanging structure scheme is adopted, the hanging joint is excessively loaded under the condition of damage safety, the thickness of the lower wall plate is thickened, and the weight of the lower wall plate is obviously increased;
2. if a statically determined hanging structure scheme is adopted, emergency disconnection design is difficult, separation between hanging and a wing is difficult to realize, and safety of a wing oil tank is ensured.
Disclosure of Invention
The invention aims to solve the technical problems, and provides an aircraft static and indefinite hanging structure, which improves the scheme of the static and indefinite hanging structure, ensures that corresponding joints adopt a backup design, avoids the change of a force transmission path after a single joint is damaged, effectively reduces the corresponding load of the static and indefinite hanging joint, simultaneously reduces the load of a lower wall plate of a wing, avoids the local thickening of the lower wall plate, and reduces the weight of a box section of the wing.
The technical scheme of the invention is as follows:
an aircraft backup static and indefinite hanging structure comprises a left wall plate, a right wall plate, a hanging middle joint lug and a lateral connecting rod;
the hanging middle joint lug comprises a left middle joint lug and a right middle joint lug; the left middle joint lug comprises a left short beam middle joint lug arranged on a left short beam hung on the left side and a left wallboard lug arranged on the left wallboard, and the left short beam middle joint lug and the left wallboard lug form a backup design; the right middle joint lug comprises a right short beam middle joint lug arranged on a hanging right short beam and a right wallboard lug arranged on a right wallboard, and the right short beam middle joint lug and the right wallboard lug form a backup design; the backup design mentioned above refers to that when one of the joint lugs in the left (right) short beam and the left (right) wallboard lugs is damaged, the other one without damage bears the load commonly born by the 2 lugs, and the 2 lugs are mutually backed up.
The lateral links include 2 left lateral links and 2 right lateral links; one end of each of the 2 left side connecting rods is connected with a left side joint lug arranged on the left side short beam of the hanging, and the other end of each of the 2 left side connecting rods is connected with a wing hanging side connecting rod joint; one end of each of the 2 right lateral connecting rods is connected with a right lateral connector lug arranged on the hanging right short beam, and the other end of each of the 2 right lateral connecting rods is connected with a wing hanging lateral connecting rod connector; the 2 left side connecting rods form a backup design, and the 2 right side connecting rods form a backup design;
the middle hanging connector lug is connected with the middle wing hanging connector through a shearing pin.
Further, the left wall plate extends out of a first portion at the left short beam middle joint lug to form the left wall plate lug; the right wall panel extends beyond a first portion at the right short beam middle joint tab to form the right wall panel tab.
Further, the left side connecting rod and the right side connecting rod are respectively provided with 2 connecting sheets; the connecting pieces are positioned between the wing hanging lateral connecting rod connector and the hanging short beam lateral connecting lug; the symmetry centers of the left side connecting rod and the right side connecting rod are coincident with the symmetry centers of the joint lugs in the left short beam and the joint lugs in the right short beam.
Further, the left wallboard lug and the middle joint lug of the hanging left short beam are overlapped together, and the right wallboard lug and the middle joint lug of the hanging right short beam are overlapped together; the left wallboard lug, the hanging left short beam middle joint lug, the right wallboard lug and the hanging right short beam middle joint lug jointly transmit course load and vertical load.
Further, the wing hanging left middle joint comprises a wing hanging left middle joint left side part and a wing hanging left middle joint right side part, and the wing hanging left middle joint left side part and the wing hanging left middle joint right side part are of a split structure; the left side part of the wing hanging left middle joint is connected with the right side part of the wing hanging left middle joint, and then is integrally connected to the lower wall plate of the wing;
the wing hanging right middle joint comprises a wing hanging right middle joint left side part and a wing hanging right middle joint right side part, and the wing hanging right middle joint left side part and the wing hanging right middle joint right side part are of split structures; the left part of the right middle joint of the wing hanging is connected with the right part of the right middle joint of the wing hanging, and then is integrally connected to the lower wall plate of the wing.
Further, the left side part of the wing hanging left middle joint is connected with the right side part of the wing hanging left middle joint through a fastener; the left part of the right middle joint of the wing hanging is connected with the right part of the right middle joint of the wing hanging through a fastener.
An aircraft is provided with the aircraft backup static and indefinite hanging structure.
The beneficial effects of the invention are as follows: the middle joint area of the hanging box section is designed into a left wall plate, a right wall plate, a middle joint lug and a left lateral connecting rod, wherein the side wall plate lug and the middle joint lug of the short beam form a double-backup design; the single lateral connecting rod is formed by two connecting sheets to form a backup design, so that the force transmission path between the hanger and the wing is not changed under the condition of breakage of the single connecting piece, the concentrated force load of the lower wall plate of the wing is greatly reduced, and the weight of the lower wall plate assembly of the wing is reduced.
Drawings
Fig. 1 is a schematic view of a static and indefinite hanging structure in the prior art.
Fig. 2 is a schematic view of a statically determinate hanging structure in the prior art.
Fig. 3 is an overall schematic diagram of an aircraft backup static and unstable hanging structure according to an embodiment of the invention.
Fig. 4 shows an enlarged view of the portion a in fig. 3.
Fig. 5 is a schematic view of the left and right short beam middle joint lugs and the left and right lateral joint lugs in the left and right short beam arrangement positions.
Fig. 6 shows a schematic structural diagram of a left middle joint of a wing suspension (the structure of a right middle joint of the suspension is the same).
Wherein: 1-left wall plate lugs; 2-left short beam middle joint lugs; 3-lateral links (4); 4-hanging a left short beam; 5-hanging a right short beam; 6-left lateral tab (disposed on left side short beam); 7-right lateral tab (provided on the right side beam); 8-right short beam middle joint lugs; 11-a left middle joint of the wing hanger; 12-a right middle joint of the wing hanger; 111-left side portion of left middle joint of wing suspension; 112-the right portion of the left middle joint of the wing suspension.
Detailed Description
Specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the technical features or combinations of technical features described in the following embodiments should not be regarded as being isolated, and they may be combined with each other to achieve a better technical effect. In the drawings of the embodiments described below, like reference numerals appearing in the various drawings represent like features or components and are applicable to the various embodiments.
The embodiment of the invention discloses an aircraft backup static and indefinite hanging structure, and the whole structure is shown in figure 3; the device comprises a left wallboard, a right wallboard, a hanging middle joint lug and a lateral connecting rod;
the hanging middle joint lug comprises a left middle joint lug and a right middle joint lug; the left middle joint lug comprises a left short beam middle joint lug arranged on a left short beam hung on the left side and a left wallboard lug arranged on the left wallboard, and the left short beam middle joint lug and the left wallboard lug form a backup design (see figure 4); the right middle joint lug comprises a right short beam middle joint lug arranged on a hanging right short beam and a right wallboard lug arranged on a right wallboard, and the right short beam middle joint lug and the right wallboard lug form a backup design;
as shown in fig. 4, the lateral links include 2 left lateral links and 2 right lateral links; one end of each of the 2 left side connecting rods is connected with a left side joint lug (the position is shown in figure 5) arranged on the left side short beam of the hanging, and the other end of each of the 2 left side connecting rods is connected with a wing hanging side connecting rod joint; one end of each of the 2 right lateral connecting rods is connected with a right lateral connector lug (the position is shown in figure 5) arranged on the hanging right short beam, and the other end of each of the 2 right lateral connecting rods is connected with a wing hanging lateral connecting rod connector; the 2 left side connecting rods form a backup design, and the 2 right side connecting rods form a backup design;
the middle hanging connector lug is connected with the middle wing hanging connector through a shearing pin.
Preferably, the left wall panel extends beyond the first portion at the left lintel middle tab to form the left wall panel tab; the right wall panel extends beyond a first portion at the right short beam middle joint tab to form the right wall panel tab.
Preferably, the left side connecting rod and the right side connecting rod are respectively 2 connecting sheets; the connecting pieces are positioned between the wing hanging lateral connecting rod connector and the hanging short beam lateral connecting lug; the symmetry centers of the left side connecting rod and the right side connecting rod are coincident with the symmetry centers of the joint lugs in the left short beam and the joint lugs in the right short beam.
Preferably, the left wallboard lug and the middle joint lug of the hanging left short beam are overlapped together, and the right wallboard lug and the middle joint lug of the hanging right short beam are overlapped together; the left wallboard lug, the hanging left short beam middle joint lug, the right wallboard lug and the hanging right short beam middle joint lug jointly transmit course load and vertical load.
As shown in fig. 6, the wing hanging left middle joint comprises a wing hanging left middle joint left side part and a wing hanging left middle joint right side part, and the wing hanging left middle joint left side part and the wing hanging left middle joint right side part are of split structures; the left side part of the wing hanging left middle joint is connected with the right side part of the wing hanging left middle joint, and then is integrally connected to the lower wall plate of the wing;
the wing hanging right middle joint comprises a wing hanging right middle joint left side part and a wing hanging right middle joint right side part, and the wing hanging right middle joint left side part and the wing hanging right middle joint right side part are of split structures; the left part of the right middle joint of the wing hanging is connected with the right part of the right middle joint of the wing hanging, and then is integrally connected to the lower wall plate of the wing.
The left side part of the wing hanging left middle joint and the right side part of the wing hanging left middle joint can be connected through a fastener or in other connection modes; the left portion of the wing suspension right middle joint and the right portion of the wing suspension right middle joint may be connected by fasteners or otherwise.
An aircraft is provided with the aircraft backup static and indefinite hanging structure.
In actual use, the side wall panel tabs and the short beam middle joint tabs form a back-up design; the single lateral connecting rod is composed of 2 connecting sheets to form a backup design; under the condition of breakage, the force transmission path between the hanging structure and the wing is not changed, so that the concentrated force load of the lower wall plate of the wing is greatly reduced, and the weight of the lower wall plate assembly of the wing is reduced.
Specifically, the side wall plate lugs are stacked back to back with the short beam middle joint lugs to jointly transmit heading load and vertical load, and when one of the short beam middle joint lugs is damaged, the corresponding side wall plate lug is used for transmitting load, so that the load transmitted to the hanging middle joint is unchanged. Each lateral connecting rod consists of two connecting sheets, the two connecting sheets are respectively positioned at two sides of the lateral joint lug of the hanging short beam, and the design of the two connecting sheets is beneficial to preventing the whole lateral connecting rod from being invalid due to crack expansion; meanwhile, the wing hanging joint adopts a split type design, so that the force transmission path between the hanging joint and the wing is not changed under the condition of breakage of a single connecting piece, the concentrated force load of the lower wall plate of the wing is greatly reduced, and the weight of the lower wall plate assembly of the wing is reduced; novel structure, simplicity and wide application prospect.
The innovation point of the invention is mainly that:
1. through the backup design of the middle hanging joint and the middle wing joint, the joint load under the condition of single joint damage is effectively reduced by 30%, and the overload of the load and the overweight of the lower wall plate of the wing are avoided.
2. The left and right wall plate lugs are added to the side wall plate, so that the side wall plate lugs and the short beam middle joint lugs bear the middle joint load together.
3. The wing hanging connector corresponding to the hanging middle connector is designed to be a split structure and integrally connected to the lower wall plate of the wing.
Although a few embodiments of the present invention have been described herein, those skilled in the art will appreciate that changes can be made to the embodiments herein without departing from the spirit of the invention. The above-described embodiments are exemplary only, and should not be taken as limiting the scope of the claims herein.
Claims (5)
1. The aeroplane backup static and indefinite hanging structure is characterized by comprising a joint area in a hanging box section, wherein the joint area in the hanging box section comprises a left wall plate, a right wall plate, a hanging middle joint lug and a lateral connecting rod;
the hanging middle joint lug comprises a left middle joint lug and a right middle joint lug; the left middle joint lug comprises a left short beam middle joint lug arranged on a left short beam hung on the left side and a left wallboard lug arranged on the left wallboard, and the left short beam middle joint lug and the left wallboard lug form a backup design; the right middle joint lug comprises a right short beam middle joint lug arranged on a hanging right short beam and a right wallboard lug arranged on a right wallboard, and the right short beam middle joint lug and the right wallboard lug form a backup design; the left wallboard lug and the middle joint lug of the hanging left short beam are overlapped together, and the right wallboard lug and the middle joint lug of the hanging right short beam are overlapped together; the left wallboard lug, the hanging left short beam middle joint lug, the right wallboard lug and the hanging right short beam middle joint lug jointly transmit heading load and vertical load;
the lateral links include 2 left lateral links and 2 right lateral links; one end of each of the 2 left side connecting rods is connected with a left side joint lug arranged on the left side short beam of the hanging, and the other end of each of the 2 left side connecting rods is connected with a wing hanging side connecting rod joint; one end of each of the 2 right lateral connecting rods is connected with a right lateral connector lug arranged on the hanging right short beam, and the other end of each of the 2 right lateral connecting rods is connected with a wing hanging lateral connecting rod connector; the 2 left side connecting rods form a backup design, and the 2 right side connecting rods form a backup design;
the middle hanging connector lug is connected with the middle wing hanging connector through a shearing pin;
the wing hanging left middle joint comprises a wing hanging left middle joint left side part and a wing hanging left middle joint right side part, and the wing hanging left middle joint left side part and the wing hanging left middle joint right side part are of split structures; the left side part of the wing hanging left middle joint is connected with the right side part of the wing hanging left middle joint, and then is integrally connected to the lower wall plate of the wing;
the wing hanging right middle joint comprises a wing hanging right middle joint left side part and a wing hanging right middle joint right side part, and the wing hanging right middle joint left side part and the wing hanging right middle joint right side part are of split structures; the left part of the right middle joint of the wing hanging is connected with the right part of the right middle joint of the wing hanging, and then is integrally connected to the lower wall plate of the wing.
2. The aircraft backup static indefinite suspension structure of claim 1 wherein said left panel extends beyond a first portion at said left lintel middle tab to form said left panel tab; the right wall panel extends beyond a first portion at the right short beam middle joint tab to form the right wall panel tab.
3. The aircraft backup stationary suspension structure of claim 1, wherein the left and right lateral links are 2 connecting pieces, respectively; the connecting pieces are positioned between the wing hanging lateral connecting rod connector and the hanging short beam lateral connecting lug; the symmetry centers of the left side connecting rod and the right side connecting rod are coincident with the symmetry centers of the joint lugs in the left short beam and the joint lugs in the right short beam.
4. The aircraft backup static indefinite suspension structure of claim 1, wherein the left side portion of the wing suspension left middle joint and the right side portion of the wing suspension left middle joint are connected by a fastener; the left part of the right middle joint of the wing hanging is connected with the right part of the right middle joint of the wing hanging through a fastener.
5. An aircraft having an aircraft backup stiction suspension structure as defined in any one of claims 1-4.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811453200.7A CN109455304B (en) | 2018-11-30 | 2018-11-30 | Static and indefinite hanging structure of airplane |
| PCT/CN2018/120277 WO2020107533A1 (en) | 2018-11-30 | 2018-12-11 | Statically indeterminate hanging structure of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811453200.7A CN109455304B (en) | 2018-11-30 | 2018-11-30 | Static and indefinite hanging structure of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109455304A CN109455304A (en) | 2019-03-12 |
| CN109455304B true CN109455304B (en) | 2024-02-23 |
Family
ID=65612134
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811453200.7A Active CN109455304B (en) | 2018-11-30 | 2018-11-30 | Static and indefinite hanging structure of airplane |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN109455304B (en) |
| WO (1) | WO2020107533A1 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111008498B (en) * | 2019-12-09 | 2023-06-27 | 中航沈飞民用飞机有限责任公司 | Analysis method for structural size of hyperstatic hanging and wing connecting unit |
| CN111731493B (en) * | 2020-06-18 | 2022-04-22 | 天津爱思达新材料科技有限公司 | Light diffusion structure of aircraft fuel tank hoisting position |
| CN113237661B (en) * | 2021-05-10 | 2022-02-25 | 中国商用飞机有限责任公司 | Device and method for measuring dynamic test load of wing-mounted engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6095456A (en) * | 1996-12-23 | 2000-08-01 | The Boeing Company | Strut-wing interface having dual upper links |
| CN101801787A (en) * | 2007-06-22 | 2010-08-11 | 埃尔塞乐公司 | Securing plate and longitudinal handling member for a one-piece aircraft propulsion unit |
| CN105836143A (en) * | 2015-01-30 | 2016-08-10 | 空中客车运营简化股份公司 | Propulsion assembly incorporating a turbojet and a mounting pylon enabling a new distribution of the forces between the turbojet and the wing |
| US9611046B1 (en) * | 2013-01-25 | 2017-04-04 | Mitsubishi Aircraft Corporation | Link member for connecting aircraft pylon to wing of aircraft, aircraft pylon, and aircraft |
| CN107054670A (en) * | 2016-01-07 | 2017-08-18 | 波音公司 | The jet engine mounting column of performance enhancement |
| CN209739372U (en) * | 2018-11-30 | 2019-12-06 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Static and indefinite hanging structure for airplane backup |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7083143B2 (en) * | 2003-10-17 | 2006-08-01 | The Boeing Company | Apparatuses and methods for attaching engines and other structures to aircraft wings |
| FR2915178B1 (en) * | 2007-04-23 | 2009-07-10 | Airbus France Sa | ATTACHMENT OF A MAT BOX ON A SAIL, PINCING A SIDE PANEL OF THE HOUSING |
| FR2917713B1 (en) * | 2007-06-21 | 2009-09-25 | Airbus France Sas | APPARATUS FOR ATTACHING AN AIRCRAFT ENGINE AND AIRCRAFT HAVING AT LEAST ONE SUCH DEVICE. |
| US8205825B2 (en) * | 2008-02-27 | 2012-06-26 | Spirit Aerosystems, Inc. | Engine pylon made from composite material |
| US8342444B2 (en) * | 2008-12-16 | 2013-01-01 | The Boeing Company | Fail safe extended torque box strut-to-wing mount |
| JP6114043B2 (en) * | 2013-01-25 | 2017-04-12 | 三菱航空機株式会社 | Aircraft pylon and aircraft |
| US9238511B2 (en) * | 2014-03-04 | 2016-01-19 | Mra Systems, Inc. | Engine pylon structure |
| FR3032421B1 (en) * | 2015-02-06 | 2017-03-10 | Airbus Operations Sas | AIRCRAFT ASSEMBLY COMPRISING A PRIMARY STRUCTURE OF HITCHING MAT INTEGRATED WITH THE STRUCTURE OF THE VESSEL ELEMENT |
-
2018
- 2018-11-30 CN CN201811453200.7A patent/CN109455304B/en active Active
- 2018-12-11 WO PCT/CN2018/120277 patent/WO2020107533A1/en active Application Filing
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6095456A (en) * | 1996-12-23 | 2000-08-01 | The Boeing Company | Strut-wing interface having dual upper links |
| CN101801787A (en) * | 2007-06-22 | 2010-08-11 | 埃尔塞乐公司 | Securing plate and longitudinal handling member for a one-piece aircraft propulsion unit |
| US9611046B1 (en) * | 2013-01-25 | 2017-04-04 | Mitsubishi Aircraft Corporation | Link member for connecting aircraft pylon to wing of aircraft, aircraft pylon, and aircraft |
| CN105836143A (en) * | 2015-01-30 | 2016-08-10 | 空中客车运营简化股份公司 | Propulsion assembly incorporating a turbojet and a mounting pylon enabling a new distribution of the forces between the turbojet and the wing |
| CN107054670A (en) * | 2016-01-07 | 2017-08-18 | 波音公司 | The jet engine mounting column of performance enhancement |
| CN209739372U (en) * | 2018-11-30 | 2019-12-06 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Static and indefinite hanging structure for airplane backup |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2020107533A1 (en) | 2020-06-04 |
| CN109455304A (en) | 2019-03-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109455304B (en) | Static and indefinite hanging structure of airplane | |
| CN103101628B (en) | Front installation joint integrated with airplane hang | |
| RU2398713C2 (en) | Aircraft device comprising wing and suspension pylon | |
| US11319080B2 (en) | Assembly for an aircraft comprising a primary structure for an attachment pylon secured to a wing box by means of fittings that are more compact in the leading edge region | |
| US11319079B2 (en) | Assembly for an aircraft comprising a primary structure for an attachment pylon secured to a wing box by means of fittings that are more compact in the leading edge region | |
| CN111605716B (en) | Main structure of aircraft hanging frame and aircraft | |
| US2329133A (en) | Aircraft construction | |
| CN209739372U (en) | Static and indefinite hanging structure for airplane backup | |
| US10189575B2 (en) | Aircraft engine assembly comprising rear engine attachments in the form of shackles | |
| CN105523169A (en) | Bendable wing control surface | |
| CN107512399B (en) | Box-shaped beam type engine main mounting joint | |
| CN109592056B (en) | Method for hanging pod of oiling machine | |
| CN112623190B (en) | Butt joint device for box sections of plane stabilizer | |
| CN110712758A (en) | Installation hanging rack and aircraft comprising same | |
| CN215851853U (en) | Aircraft control surface suspension control integral joint | |
| CN113830285B (en) | Vertical main box section spar tip flat vertical butt joint for realizing damage safety | |
| CN102849218A (en) | Mounting beam for auxiliary power unit of aircraft | |
| CN113581476A (en) | Engine back support structure and airplane | |
| CN103466079A (en) | Manipulation and suspension coupled support arm component of airplane tail fin | |
| CN214986110U (en) | Hang butt joint main joint | |
| CN103818815A (en) | Engine lifting structure | |
| CN115056962B (en) | Upper single-wing aircraft wing body connecting structure | |
| CN105366025A (en) | Attachment joint for aircraft wing and fuselage of three-beam type monoplane | |
| CN216003090U (en) | Engine back support structure and airplane | |
| CN110979630A (en) | Composite vertical-fin main box section wing spar root joint considering damage safety and design method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |