CN111003184A - Aircraft external hanging article support - Google Patents
Aircraft external hanging article support Download PDFInfo
- Publication number
- CN111003184A CN111003184A CN201911362780.3A CN201911362780A CN111003184A CN 111003184 A CN111003184 A CN 111003184A CN 201911362780 A CN201911362780 A CN 201911362780A CN 111003184 A CN111003184 A CN 111003184A
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- Prior art keywords
- edge skin
- aircraft
- trailing edge
- shell
- skin assembly
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- 238000005192 partition Methods 0.000 claims abstract description 8
- 230000002787 reinforcement Effects 0.000 claims description 10
- 239000002131 composite material Substances 0.000 claims description 6
- 239000003351 stiffener Substances 0.000 claims 1
- 230000005540 biological transmission Effects 0.000 abstract description 5
- 230000003014 reinforcing effect Effects 0.000 description 13
- 238000012423 maintenance Methods 0.000 description 10
- 239000002184 metal Substances 0.000 description 8
- 238000004519 manufacturing process Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 238000003754 machining Methods 0.000 description 3
- 239000000725 suspension Substances 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000006260 foam Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000009659 non-destructive testing Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
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
- B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/38—Constructions adapted to reduce effects of aerodynamic or other external heating
-
- 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
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- Connection Of Plates (AREA)
Abstract
The embodiment of the invention discloses an aircraft external hanging article bracket, which comprises: a leading edge skin shell, a trailing edge skin assembly, an I-beam connected between the leading edge skin shell and the trailing edge skin assembly; the I-beam comprises beam flanges at two sides, a beam web plate arranged between the beam flanges at the two sides, a beam front connecting edge arranged at the front end of each beam flange, a beam rear connecting edge arranged at the rear end of each beam flange, a plurality of beam front partition plates arranged at the front part of the beam web plate and a plurality of beam rear partition plates arranged at the rear part of the beam web plate; and the inside of the rear edge skin assembly is provided with rear edge clapboards which are correspondingly connected with the beam rear clapboards one by one. On the premise of meeting the structural strength, the embodiment of the invention provides the aircraft external hanger bracket which is simple in structure, good in force transmission characteristic, convenient to maintain and light in weight.
Description
Technical Field
The application relates to but is not limited to the technical field of aviation, especially indicates an aircraft stores outward thing support.
Background
For a special machine or a modified airplane, suspended objects such as an early warning radar, a nacelle, a rain enhancement device, a rocket tube, a detection radar, remote sensing equipment and the like are often arranged on the back of the airplane or below wings. In order to prevent interference, the suspension is generally spaced from the body structure, and a transition piece, i.e., an external suspension bracket, is generally arranged for connecting the suspension and the body structure. In the structural arrangement of the airplane, strict requirements are provided for aerodynamic data such as resistance of the external hanging object bracket. Factors to be considered in general are: pneumatic, weight, strength and rigidity, maintainability, etc.
The external hanging object supports with the same function and different structural forms have poor bearing effect and many fasteners if being made into sheet metal parts. If the alloy is made into a casting, the bearing force is poor, the defects are more, and the weight is heavy. In addition, the beam with a closed section has poor manufacturability, is not easy to assemble and is not easy to maintain.
The invention is in a structural form that the bearing structure is an open-section integral numerical control machine added part, not only is the force transmission structure more reasonable, but also the number of parts of the single-side hanging rack is reduced from that of a conventional sheet metal structure, the number of connecting nails is reduced, the production cost and the maintenance difficulty are greatly reduced, and the rigidity of the hanging rack is good.
Disclosure of Invention
In order to solve the technical problems, the embodiment of the invention provides an aircraft plug-in support which has the advantages of simple structure, good force transmission characteristic, convenience in maintenance and light weight on the premise of meeting the structural strength.
The embodiment of the invention provides an aircraft external hanging article bracket, which comprises: a leading edge skin shell, a trailing edge skin assembly, an I-beam connected between the leading edge skin shell and the trailing edge skin assembly;
the I-beam comprises beam flanges at two sides, a beam web plate arranged between the beam flanges at the two sides, a beam front connecting edge arranged at the front end of each beam flange, a beam rear connecting edge arranged at the rear end of each beam flange, a plurality of beam front partition plates arranged at the front part of the beam web plate and a plurality of beam rear partition plates arranged at the rear part of the beam web plate;
and the inside of the rear edge skin assembly is provided with rear edge clapboards which are correspondingly connected with the beam rear clapboards one by one.
Optionally, in the aircraft pylon described above, the integral shell structure formed by the leading edge skin shell, the trailing edge skin assembly and the i-beam of the pylon is an aerofoil structure.
Optionally, in the aircraft external hanger bracket as described above, the leading edge skin shell is an integrated structure made of composite materials, and reinforcing ribs are provided on an inner side of the leading edge skin shell.
Optionally, in the aircraft pylon described above, the trailing edge skin assembly includes two side trailing edge skins, and a wedge disposed aft of the trailing edge skin assembly for connecting the two side trailing edge skins.
Optionally, the aircraft external hanger bracket as described above further includes: the one-to-one sets up in every first angular form reinforcement on the trailing edge baffle face, and run through the second angular form reinforcement of first angular form reinforcement, the two sides of second angular form reinforcement is laminated respectively first angular form reinforcement and trailing edge covering.
Optionally, in the aircraft pylon support as described above, a system through hole is provided in the trailing edge skin assembly, and the system through hole is used for laying a system pipeline of an aircraft.
Optionally, in the aircraft external hanger bracket as described above, the trailing edge skin assembly and the beam rear connecting edge are connected by a pallet nut, and the leading edge skin shell and the beam front connecting edge are connected by a quick release lock.
Optionally, in the aircraft external hanger bracket described above, the two ends of the i-beam are provided with connecting holes, joint bearings are installed in the connecting holes, one end of the i-beam is connected to the bottom of the aircraft through the joint bearings and bolts, and the other end of the i-beam is connected to the external hanger through the joint bearings and bolts.
According to the aircraft external hanging object support provided by the embodiment of the invention, the bearing structure is in an open-section integral numerical control machining part adding structure form, so that the force transmission structure is more reasonable, the number of parts of a single-side hanging rack is smaller than that of a conventional sheet metal structure, the number of connecting nails is also small, the production cost and the maintenance difficulty are greatly reduced, and the rigidity of the hanging rack is improved; in addition, the front edge skin shell, the I-shaped bearing beam and the rear edge skin assembly are combined into the airfoil support structure, and the support structure integrally taking the airfoil shape has the advantages of low aerodynamic resistance, high bearing efficiency, light weight, good manufacturability and convenience for system installation and maintenance.
Drawings
The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the example serve to explain the principles of the invention and not to limit the invention.
FIG. 1 is a schematic structural view of an aircraft external hanger bracket according to an embodiment of the present invention;
fig. 2 is a schematic structural view of an i-beam in the aircraft external hanger bracket according to the embodiment of the invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.
The invention provides a special airplane or a modified airplane, which can bear an external hanging object support easy for system maintenance on the premise of ensuring the aerodynamic appearance, and meets the overall requirements of the airplane.
The following specific embodiments of the present invention may be combined, and the same or similar concepts or processes may not be described in detail in some embodiments.
Fig. 1 is a schematic structural view of an aircraft external hanger bracket according to an embodiment of the present invention. The aircraft external hanger bracket provided by the embodiment can comprise: a leading edge skin shell 1, a trailing edge skin assembly (including 9 to 12 in fig. 1), an i-beam (including 2 to 7 in fig. 1) connected between the leading edge skin shell 1 and the trailing edge skin assembly;
fig. 2 is a schematic structural view of an i-beam in the aircraft external hanger bracket according to the embodiment of the invention. Referring to fig. 1 and 2, in the aircraft external hanger bracket according to the embodiment of the present invention, an i-beam includes: the beam comprises beam flanges 3 on two sides, a beam web 7 arranged between the two beam flanges 3, a beam front connecting edge 2 arranged at the front end of each beam flange 3, a beam rear connecting edge 4 arranged at the rear end of each beam flange 3, a plurality of beam front partition plates 6 arranged at the front part of the beam web 7 and a plurality of beam rear partition plates 5 arranged at the rear part of the beam web 7;
in the embodiment of the invention, the inner side of the leading edge skin shell 1 is provided with a reinforcing rib, such as a foam core and a wall plate reinforcing rib; and the inside of the rear edge skin assembly is provided with rear edge clapboards 11 which are correspondingly connected with the beam rear clapboards 5 one by one.
Optionally, the integral shell structure formed by the leading edge skin shell 1, the trailing edge skin assembly and the i-beam of the plug-in bracket in the embodiment of the invention is of an airfoil structure. When the whole external hanging object support is arranged, the wing shape of the support can be fully considered, the minimum pneumatic resistance is ensured, the pneumatic blowing result is adopted, the pneumatic appearance is taken as a framework model, and the design needs to bear the weight and meet the requirements of light weight, good manufacturability, easy maintenance and the like.
Optionally, the leading edge skin shell 1 in the embodiment of the present invention is an integrated structure made of a composite material, and the inner side of the leading edge skin shell 1 is provided with a reinforcing rib 17; wherein, the composite material has light weight and strong specific stiffness; the bearing capacity is stronger than that of metal under the same weight.
Alternatively, as shown in fig. 1, in the pylon of the embodiment of the invention, the trailing edge skin assembly includes: two sides of the trailing edge skin (comprising one side of the trailing edge skin 9 and the other side of the trailing edge skin 12) are provided with wedges 10 which are arranged at the tail part of the trailing edge skin assembly and are used for connecting the two sides of the trailing edge skin.
Optionally, as shown in fig. 1, the external hanger bracket according to the embodiment of the present invention may further include: a corresponding first angle-shaped reinforcing part 8 arranged on the surface of each rear edge clapboard 11 and a second angle-shaped reinforcing part 13 penetrating through the first angle-shaped reinforcing part 8, wherein two surfaces of the second angle-shaped reinforcing part 13 are respectively jointed with the first angle-shaped reinforcing part 8 and the rear edge skin.
Alternatively, as shown in FIG. 1, in the external hanger bracket of the embodiment of the invention, a system through hole 14 is arranged in the trailing edge skin assembly, and the system through hole 14 is used for laying system pipelines of the airplane. The front edge and the rear edge of the bracket are detachable fairings, the system pipeline can pass through the fairings (via hole function), and the system pipeline can be maintained after being detached.
Alternatively, in the external hanger bracket according to the embodiment of the present invention, the rear edge skin assembly and the beam rear connecting edge 4 are connected by the pallet nut 15, and the front edge skin shell 1 and the beam front connecting edge 2 are connected by the quick release 16, and the release 16 is, for example, a screw.
Optionally, in the bracket for an external hanging object according to the embodiment of the present invention, two ends of the i-beam are provided with connection holes, a knuckle bearing is installed in the connection hole, one end of the i-beam is connected to the bottom of the aircraft through the knuckle bearing and a bolt, and the other end of the i-beam is connected to the external hanging object through the knuckle bearing and a bolt.
The following explains the manufacturing method of the aircraft external hanger bracket provided by the embodiment of the invention:
firstly, a front edge skin shell made of composite materials is molded according to a mold and then enters an autoclave to be manufactured, a carrier beam is machined according to a design digital-analog numerical control machine, a rear edge skin assembly is manufactured according to all parts of the design digital-analog numerical control machine, a connecting piece is purchased, and the inspection and nondestructive testing are carried out.
The bearing beam is firstly fixed on a frame, the front edge skin shell is connected on the front connecting edges 2 of the beams on the two sides of the I-beam by quick release locks, the sheet metal of the rear edge part is combined into a complete rear edge, the system pipeline penetrates into the rear edge part, and then the system pipeline is connected on the rear connecting edges 4 of the two side beams of the I-beam by the supporting plate nuts.
The integrally connected external hanger bracket for ensuring the wing shape is assembled on the airplane, then the external hanger is connected on the external hanger bracket, and horizontal measurement is carried out, so that form and position tolerance and precision are ensured, and the overall requirements of the airplane are met.
The aircraft external hanging bracket provided by the embodiment of the invention has the advantages that the integral external hanging bracket is of a wing-shaped structure, the main stress structure is the cross-section-opening I-shaped beam, in practical application, the cross-section-opening I-shaped beam can be connected with double lugs on a reinforcing frame of a machine body or a skirt section of the bracket through bolts and joint bearings, the joint bearings can be selected to not only relieve bending moment on a joint, but also adjust deviation during assembly, and the stress characteristic is good.
The I-beam provided by the embodiment of the invention is provided with the front connecting edge and the rear connecting edge, the connecting edges are designed according to equal stress, the front edge and the rear edge can be conveniently connected, the weight can be reduced, the beam flange and the beam web plate which are mainly stressed are thicker, and the corner R is also large. In order to reduce connection and increase the bearing characteristic of the beam, flanges on two sides of the beam are provided with appearances and are not covered with skins. It is also convenient for numerical control machining.
The front edge part of the embodiment of the invention can be made into a composite material piece, an integral piece, a skin is provided with a reinforcing rib, the rigidity is improved, the front edge part is connected with the connecting edge of the bearing beam by a quick-release lock, the disassembly is convenient, and cables, pipelines and the like (pipelines which are not maintained frequently) can be arranged in the front edge part.
The rear edge part of the embodiment of the invention is larger, a sheet metal assembly is usually adopted, a wedge piece is designed at the narrow tail part, higher rigidity can be provided, two side skins are connected, the inner rear edge is provided with a clapboard which is in one-to-one correspondence with the beam rear clapboard on the beam, a system through hole is formed in the rear edge clapboard and is used for a system pipeline to pass through, a reinforced angle material (namely a first angle-shaped reinforcing part 8) is arranged on the system through hole, and two side skins are longitudinally reinforced by a long truss (namely a second angle-shaped reinforcing part 13) to form a sheet metal stress structure.
The embodiment of the invention aims at the problems of pneumatic sensitivity, large bearing capacity and difficult arrangement of the external hanging object, and provides the external hanging object support which has the advantages of simple structure, few elements, light weight and convenient maintenance on the premise of meeting the requirements on structural strength, rigidity and function. The pneumatic flight control device can meet the maintenance and use requirements, and can realize small pneumatic resistance and light weight, thereby ensuring flight safety and normal completion of tasks. The aircraft external hanging support is particularly suitable for a hanging support of an aircraft external hanging nacelle, a missile or a torpedo.
According to the aircraft external hanging object support provided by the embodiment of the invention, the bearing structure is in an open-section integral numerical control machining part adding structure form, so that the force transmission structure is more reasonable, the number of parts of a single-side hanging rack is smaller than that of a conventional sheet metal structure, the number of connecting nails is also small, the production cost and the maintenance difficulty are greatly reduced, and the rigidity of the hanging rack is improved; in addition, the front edge skin shell, the I-shaped bearing beam and the rear edge skin assembly are combined into the airfoil support structure, and the support structure integrally taking the airfoil shape has the advantages of low aerodynamic resistance, high bearing efficiency, light weight, good manufacturability and convenience for system installation and maintenance.
Although the embodiments of the present invention have been described above, the above description is only for the convenience of understanding the present invention, and is not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (8)
1. An aircraft store support, comprising: a leading edge skin shell, a trailing edge skin assembly, an I-beam connected between the leading edge skin shell and the trailing edge skin assembly;
the I-beam comprises beam flanges at two sides, a beam web plate arranged between the beam flanges at the two sides, a beam front connecting edge arranged at the front end of each beam flange, a beam rear connecting edge arranged at the rear end of each beam flange, a plurality of beam front partition plates arranged at the front part of the beam web plate and a plurality of beam rear partition plates arranged at the rear part of the beam web plate;
and the inside of the rear edge skin assembly is provided with rear edge clapboards which are correspondingly connected with the beam rear clapboards one by one.
2. The aircraft pylon of claim 1 wherein the integral shell structure formed by the leading edge skin shell, the trailing edge skin assembly and the i-beam of the pylon is an airfoil structure.
3. The aircraft pylon of claim 1 wherein the leading edge skin shell is a composite, unitary structure with stiffeners disposed on the inside of the leading edge skin shell.
4. An aircraft pylon according to claim 1 wherein the trailing edge skin assembly includes two side trailing edge skins, a wedge disposed aft of the trailing edge skin assembly for connecting the two side trailing edge skins.
5. The aircraft store support according to claim 1, further comprising: the one-to-one sets up in every first angular form reinforcement on the trailing edge baffle face, and run through the second angular form reinforcement of first angular form reinforcement, the two sides of second angular form reinforcement is laminated respectively first angular form reinforcement and trailing edge covering.
6. The aircraft pylon of claim 1 wherein the trailing edge skin assembly has system through holes provided therein for routing system lines of an aircraft.
7. The aircraft pylon of claim 1 wherein the trailing edge skin assembly is connected to the spar trailing connecting edge by a pallet nut and the leading edge skin shell is connected to the spar leading connecting edge by a quick release lock.
8. The aircraft external hanger support according to any one of claims 1 to 7, wherein connecting holes are formed in two ends of the I-beam, a knuckle bearing is installed in each connecting hole, one end of the I-beam is connected to the bottom of an aircraft through the knuckle bearing and a bolt, and the other end of the I-beam is connected to an external hanger through the knuckle bearing and the bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911362780.3A CN111003184A (en) | 2019-12-25 | 2019-12-25 | Aircraft external hanging article support |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911362780.3A CN111003184A (en) | 2019-12-25 | 2019-12-25 | Aircraft external hanging article support |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111003184A true CN111003184A (en) | 2020-04-14 |
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ID=70117989
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911362780.3A Pending CN111003184A (en) | 2019-12-25 | 2019-12-25 | Aircraft external hanging article support |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111003184A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111661349A (en) * | 2020-05-21 | 2020-09-15 | 北京爱思达航天科技有限公司 | Fuel tank for fixed-wing aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB537445A (en) * | 1940-02-29 | 1941-06-23 | Fairey Aviat Co Ltd | Improvements in or relating to the construction of metal skin covered wings for aircraft |
| CN201276209Y (en) * | 2008-08-21 | 2009-07-22 | 马献林 | Once solidified and molded wing type frame and covering |
| US20090217487A1 (en) * | 2008-02-29 | 2009-09-03 | Airbus Uk Limited | Hinge rib |
| CN102849218A (en) * | 2012-09-04 | 2013-01-02 | 西安飞机工业（集团）有限责任公司 | Mounting beam for auxiliary power unit of aircraft |
| CN108100218A (en) * | 2017-11-16 | 2018-06-01 | 中国航空工业集团公司西安飞机设计研究所 | A kind of detachable radome support construction with aerofoil profile |
-
2019
- 2019-12-25 CN CN201911362780.3A patent/CN111003184A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB537445A (en) * | 1940-02-29 | 1941-06-23 | Fairey Aviat Co Ltd | Improvements in or relating to the construction of metal skin covered wings for aircraft |
| US20090217487A1 (en) * | 2008-02-29 | 2009-09-03 | Airbus Uk Limited | Hinge rib |
| CN201276209Y (en) * | 2008-08-21 | 2009-07-22 | 马献林 | Once solidified and molded wing type frame and covering |
| CN102849218A (en) * | 2012-09-04 | 2013-01-02 | 西安飞机工业（集团）有限责任公司 | Mounting beam for auxiliary power unit of aircraft |
| CN108100218A (en) * | 2017-11-16 | 2018-06-01 | 中国航空工业集团公司西安飞机设计研究所 | A kind of detachable radome support construction with aerofoil profile |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111661349A (en) * | 2020-05-21 | 2020-09-15 | 北京爱思达航天科技有限公司 | Fuel tank for fixed-wing aircraft |
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Application publication date: 20200414 |
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