CN114671005B - Aircraft nose cone structure and preparation method thereof - Google Patents
Aircraft nose cone structure and preparation method thereof Download PDFInfo
- Publication number
- CN114671005B CN114671005B CN202210463690.9A CN202210463690A CN114671005B CN 114671005 B CN114671005 B CN 114671005B CN 202210463690 A CN202210463690 A CN 202210463690A CN 114671005 B CN114671005 B CN 114671005B
- Authority
- CN
- China
- Prior art keywords
- nose cone
- mounting plate
- equipment mounting
- cone cover
- aircraft
- 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
- 238000002360 preparation method Methods 0.000 title abstract description 10
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 31
- 210000001503 joint Anatomy 0.000 claims abstract description 17
- 239000002131 composite material Substances 0.000 claims description 11
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 9
- 239000004917 carbon fiber Substances 0.000 claims description 9
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 9
- 229910052751 metal Inorganic materials 0.000 claims description 8
- 239000002184 metal Substances 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 7
- 239000003822 epoxy resin Substances 0.000 claims description 6
- 229920000647 polyepoxide Polymers 0.000 claims description 6
- 229920001721 polyimide Polymers 0.000 claims description 6
- 239000009719 polyimide resin Substances 0.000 claims description 6
- 239000000853 adhesive Substances 0.000 claims description 5
- 230000001070 adhesive effect Effects 0.000 claims description 5
- 238000005520 cutting process Methods 0.000 claims description 5
- 239000011248 coating agent Substances 0.000 claims description 4
- 238000000576 coating method Methods 0.000 claims description 4
- 238000000034 method Methods 0.000 claims description 4
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 3
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 230000001680 brushing effect Effects 0.000 claims description 3
- 239000003795 chemical substances by application Substances 0.000 claims description 3
- 238000004140 cleaning Methods 0.000 claims description 3
- 239000000835 fiber Substances 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 239000013307 optical fiber Substances 0.000 claims description 3
- 239000010453 quartz Substances 0.000 claims description 3
- 238000000926 separation method Methods 0.000 claims description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 3
- 229920001971 elastomer Polymers 0.000 claims 1
- 239000000806 elastomer Substances 0.000 claims 1
- 230000007797 corrosion Effects 0.000 abstract description 6
- 238000005260 corrosion Methods 0.000 abstract description 6
- 230000035699 permeability Effects 0.000 abstract description 5
- 230000000694 effects Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000001603 reducing effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Classifications
-
- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
- B64C1/0683—Nose cones
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses an aircraft nose cone structure and a preparation method thereof, wherein the aircraft nose cone structure comprises a nose cone cover, a reinforcing frame, a butt joint frame, L-shaped angle bars, T-shaped angle bars, a horizontal equipment mounting plate, an upper equipment mounting plate and a lower equipment mounting plate, and is characterized in that: the nose cone cover maintains pneumatic appearance, has certain rigidity and strength, and part of antennas are arranged on the inner surface of the nose cone cover; the reinforcing frame is positioned at the front half part of the inner space of the nose cone cover and supports the nose cone cover from the inside; the butt joint frame is positioned at the rear part of the nose cone cover and is used for connecting the nose cone with the aircraft projectile body. The invention relates to the technical field of aerospace. The aircraft nose cone structure and the preparation method thereof solve the problems of heavy weight, poor wave permeability, low strength, corrosion environment resistance, rainwater resistance and high temperature resistance of the existing aircraft nose cone structure.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to an aircraft nose cone structure and a preparation method thereof.
Background
With the development of aerospace technology, the flying speed of an aircraft is higher and higher. The surface of the high-speed flying aircraft is not only required to bear aerodynamic pressure load, but also is required to bear aerodynamic heat load generated by high-speed airflow, especially the nose cone, the front edge of the wing, the front edge of the tail wing and the like of the aircraft.
In addition, as an aircraft nose cone for protecting an aircraft guide head, the aircraft nose cone is required to have excellent performances such as light weight, good wave permeability, corrosion resistance, rainwater resistance and the like. Compared with a metal nose cone, the composite material has high specific strength, high specific rigidity, good designability and corrosion resistance, can bear a certain high temperature, and can meet the requirements of the nose cone of an aircraft.
Based on this, the present application is made.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides an aircraft nose cone structure and a preparation method thereof, and solves the problems of heavy weight, poor wave permeability, low strength, corrosion-resistant environment, rain-resistant performance and high temperature-resistant performance of the existing aircraft nose cone structure.
In order to achieve the above purpose, the invention is realized by the following technical scheme: the utility model provides an aircraft nose cone structure and preparation method thereof, includes nose cone cover, reinforcing frame, butt joint frame, L type angle bar, T type angle bar, horizontal equipment mounting panel, upper portion equipment mounting panel and lower part equipment mounting panel constitution, its characterized in that: the nose cone cover maintains pneumatic appearance, has certain rigidity and strength, and part of antennas are arranged on the inner surface of the nose cone cover; the reinforcing frame is positioned at the front half part of the inner space of the nose cone cover and supports the nose cone cover from the inside; the butt joint frame is positioned at the rear part of the nose cone cover and is used for connecting the nose cone with the aircraft projectile body; the L-shaped angle bar is positioned at the junction of the horizontal equipment mounting plate, the upper equipment mounting plate and the lower equipment mounting plate; the T-shaped angle bar is longitudinally arranged on the inner side of the nose cone cover and plays a role in longitudinally reinforcing the nose cone cover, and meanwhile, the T-shaped angle bar is also used for connecting with the equipment mounting plate; the device mounting plate is connected with the nose cone cover through an angle bar, wherein the horizontal device mounting plate is used for mounting laser inertial navigation and optical fiber inertial navigation, the upper device mounting plate is used for mounting a transponder, and the lower device mounting plate is used for mounting a flight control computer.
Preferably, the nose cone cover is made of quartz fiber polyimide resin composite material and is formed by a vacuum bag autoclave.
Preferably, the reinforcing frame is made of carbon fiber polyimide resin composite material and is formed by a vacuum bag autoclave.
Preferably, the butt joint frame is a metal machine added ring frame, and reinforcing ribs are arranged between the ring frame edge strips and the web plates.
Preferably, the horizontal equipment mounting plate, the upper equipment mounting plate and the lower equipment mounting plate are flat plates made of carbon fiber epoxy resin composite materials.
Preferably, the nose cone cover is connected with the T-shaped angle bars, the reinforcing frame and the butt joint frame through structural adhesive and rivets.
Preferably, the T-shaped angle bar is connected with the horizontal equipment mounting plate, the upper equipment mounting plate and the lower equipment mounting plate through rivets, and the L-shaped angle bar is connected with the horizontal equipment mounting plate, the upper equipment mounting plate and the lower equipment mounting plate through rivets.
Preferably, the outer surface of the nose cone cover can be sprayed with a heat-resistant coating, so that the high temperature resistance is further enhanced.
Preferably, the reinforcing frame is a ring frame, so that the reinforcing effect is achieved, the weight can be reduced, and the middle parts of the horizontal equipment mounting plate, the upper equipment mounting plate and the lower equipment mounting plate are provided with lightening holes, so that the weight reduction effect is achieved.
Preferably, the manufacturing process and preparation method thereof are as follows:
step one, cleaning the surface of a metal mold, brushing a release agent, and paving a nose cone cover, a reinforcing frame, L-shaped angle bars and T-shaped angle bars according to a designed paving angle; in the paving process, vacuumizing and compacting are carried out every 3-4 layers; finally laying a separation film and an airfelt, making a vacuum bag, and conveying the die to an autoclave for curing.
And step two, adding the butt joint frame by adopting a TC4 titanium alloy machine.
Thirdly, using a finished carbon fiber epoxy resin plate as a horizontal equipment mounting plate, an upper equipment mounting plate and a lower equipment mounting plate, and cutting the appearance, lightening holes and equipment mounting holes through a wire cutting machine.
Advantageous effects
The invention provides an aircraft nose cone structure and a preparation method thereof. The beneficial effects are as follows:
(1) The nose cone structure of the aircraft has obvious weight reducing effect. Compared with the traditional metal structure, the weight is reduced by more than 30%, the maneuverability and maneuverability of the aircraft can be improved, and the smooth completion of tactical flight tasks is facilitated.
(2) The nose cone structure of the aircraft has good wave permeability, high temperature resistance, corrosion resistance and rainwater resistance. The nose cone cover is made of a composite material with good wave permeability, high temperature resistance, corrosion resistance and rainwater resistance; the integral molding reduces the sealing seam and is favorable for rain protection; the outer surface is provided with a heat-resistant coating, so that the high temperature resistance is further enhanced.
Drawings
FIG. 1 is an isometric view of the present invention;
FIG. 2 is an isometric view of the present invention (nose cone cover not shown);
FIG. 3 is an isometric view of the device mounting platform of the present invention;
in the figure: 1. a nose cone cover; 2. a reinforcing frame; 3. a butt joint frame; 4. l-shaped angle materials; 5. t-shaped angle materials; 6. a horizontal device mounting plate; 7. an upper device mounting plate; 8. a lower device mounting plate;
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.
Referring to fig. 1-3, the present invention provides a technical solution:
embodiment one: the aircraft nose cone structure comprises a nose cone cover 1, a reinforcing frame 2, a butt joint frame 3, L-shaped angle bars 4, T-shaped angle bars 5, a horizontal equipment mounting plate 6, an upper equipment mounting plate 7 and a lower equipment mounting plate 8, wherein the nose cone cover 1 maintains a pneumatic appearance and has certain rigidity and strength, and part of antennas are arranged on the inner surface of the nose cone cover 1; the reinforcing frame 2 is positioned at the front half part of the inner space of the nose cone cover 1 and supports the nose cone cover 1 from the inside; the butt joint frame 3 is positioned at the rear part of the nose cone cover 1 and is used for connecting the nose cone with the aircraft projectile body; the L-shaped angle bar 4 is positioned at the junction of the horizontal equipment mounting plate 6, the upper equipment mounting plate 7 and the lower equipment mounting plate 8; the T-shaped angle bars 5 are longitudinally arranged on the inner side of the nose cone cover 1 and play a role in longitudinally reinforcing the nose cone cover 1, and meanwhile, the T-shaped angle bars 5 are also used for connecting equipment mounting plates; the equipment mounting plate is connected with the nose cone cover 1 through angle bars, wherein the horizontal equipment mounting plate 6 is used for mounting laser inertial navigation and optical fiber inertial navigation, the upper equipment mounting plate 7 is used for mounting a transponder, the lower equipment mounting plate is used for mounting a flight control computer, the nose cone cover 1 is made of quartz fiber polyimide resin composite materials, and is formed through a vacuum bag autoclave.
Embodiment two: the difference between the embodiment and the first embodiment is that the reinforcing frame 2 is made of carbon fiber polyimide resin composite material, the abutting frame 3 is a metal machine added ring frame, reinforcing ribs are arranged between the ring frame edge strips and the web, the horizontal device mounting plate 6, the upper device mounting plate 7 and the lower device mounting plate 8 are made of carbon fiber epoxy resin composite material flat plates, the nose cone cover 1 is connected with the T-shaped angle bar 5, the reinforcing frame 2 and the abutting frame 3 through structural adhesive and rivets, the T-shaped angle bar 5 is connected with the horizontal device mounting plate 6, the upper device mounting plate 7 and the lower device mounting plate 8 through rivets, the L-shaped angle bar 4 is connected with the horizontal device mounting plate 6, the upper device mounting plate 7 and the lower device mounting plate 8 through rivets, the outer surface of the nose cone cover 1 can be sprayed with a heat-resistant coating, the high temperature resistant capability is further enhanced, the reinforcing frame 2 is a ring frame, the reinforcing effect is achieved, the weight is reduced, and the middle parts of the horizontal device mounting plate 6, the upper device mounting plate 7 and the lower device mounting plate 8 are provided with lightening holes, and the weight is reduced.
The manufacturing process and the preparation method are as follows:
firstly, cleaning the surface of a metal mold, brushing a release agent, and paving a nose cone cover 1, a reinforcing frame 2, an L-shaped angle material 4 and a T-shaped angle material 5 according to a designed paving angle; in the paving process, vacuumizing and compacting are carried out every 3-4 layers; finally laying a separation film and an airfelt, making a vacuum bag, and conveying the die to an autoclave for curing.
And step two, adding the butt joint frame 3 by adopting a TC4 titanium alloy machine.
And thirdly, cutting the appearance, lightening holes and equipment mounting holes by using a wire cutting machine by using a finished carbon fiber epoxy resin plate as a horizontal equipment mounting plate 6, an upper equipment mounting plate 7 and a lower equipment mounting plate 8.
When assembled: firstly, positioning the positions of the reinforcing frame 2, the butt joint frame 3 and the T-shaped angle material 5 through an assembly type frame, and connecting the positions by using structural adhesive and rivets; then assembling the horizontal device mounting plate 6, the upper device mounting plate 7, the lower device mounting plate 8 and the L-shaped angle bar 4 using rivets; finally, the nose cone cover 1 is installed by using structural adhesive and rivets, and an antenna installation hole is drilled on the surface of the nose cone cover 1 through a drilling jig.
It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions.
Claims (10)
1. The utility model provides an aircraft nose cone structure, includes nose cone cover (1), reinforcing frame (2), butt joint frame (3), L type angle bar (4), T type angle bar (5), horizontal equipment mounting panel (6), upper portion equipment mounting panel (7) and lower part equipment mounting panel (8), its characterized in that: the nose cone cover (1) maintains a pneumatic shape, has certain rigidity and strength, and a part of antennas are arranged on the inner surface of the nose cone cover (1); the reinforcing frame (2) is positioned at the front half part of the inner space of the nose cone cover (1) and internally supports the nose cone cover (1); the butt joint frame (3) is positioned at the rear part of the nose cone cover (1) and is used for connecting the nose cone with the aircraft elastomer; the L-shaped angle bar (4) is positioned at the junction of the horizontal equipment mounting plate (6), the upper equipment mounting plate (7) and the lower equipment mounting plate (8); the T-shaped angle bar (5) is longitudinally arranged at the inner side of the nose cone cover (1) and plays a role of longitudinally reinforcing the nose cone cover (1), and meanwhile, the T-shaped angle bar (5) is also used for connecting with the equipment mounting plate; the device mounting plate is connected with the nose cone cover (1) through angle bars, wherein the horizontal device mounting plate (6) is used for mounting laser inertial navigation and optical fiber inertial navigation, the upper device mounting plate (7) is used for mounting a transponder, and the lower device mounting plate is used for mounting a flight control computer.
2. An aircraft nose cone structure as claimed in claim 1, wherein: the nose cone cover (1) is made of quartz fiber polyimide resin composite material and is formed by a vacuum bag autoclave.
3. An aircraft nose cone structure as claimed in claim 1, wherein: the reinforcing frame (2) is made of carbon fiber polyimide resin composite material and is formed by a vacuum bag autoclave.
4. An aircraft nose cone structure as claimed in claim 1, wherein: the butt joint frame (3) is a metal machine annular frame, and reinforcing ribs are arranged between annular frame edge strips and webs.
5. An aircraft nose cone structure as claimed in claim 1, wherein: the horizontal equipment mounting plate (6), the upper equipment mounting plate (7) and the lower equipment mounting plate (8) are flat plates made of carbon fiber epoxy resin composite materials.
6. An aircraft nose cone structure as claimed in claim 1, wherein: the nose cone cover (1) is connected with the T-shaped angle bar (5), the reinforcing frame (2) and the butt joint frame (3) through structural adhesive and rivets.
7. An aircraft nose cone structure as claimed in claim 1, wherein: t type angle bar (5) pass through rivet connection horizontal equipment mounting panel (6), upper portion equipment mounting panel (7), lower part equipment mounting panel (8), L type angle bar (4) pass through rivet connection horizontal equipment mounting panel (6), upper portion equipment mounting panel (7), lower part equipment mounting panel (8).
8. An aircraft nose cone structure as claimed in claim 1, wherein: the outer surface of the nose cone cover (1) is sprayed with a heat-proof coating, so that the high temperature resistance is further enhanced.
9. An aircraft nose cone structure as claimed in claim 1, wherein: the reinforcing frame (2) is a ring frame, so that the reinforcing effect is achieved, the weight can be reduced, and the middle parts of the horizontal equipment mounting plate (6), the upper equipment mounting plate (7) and the lower equipment mounting plate (8) are provided with lightening holes, so that the weight is reduced.
10. A method for manufacturing an aircraft nose cone structure, applied to the aircraft nose cone structure according to any one of claims 1-9, comprising the following steps:
(1) cleaning the surface of a metal mold, brushing a release agent, and paving a nose cone cover (1), a reinforcing frame (2), an L-shaped angle material (4) and a T-shaped angle material (5) according to a designed paving angle; in the paving process, vacuumizing and compacting are carried out every 3-4 layers; finally laying a separation film and an airfelt, making a vacuum bag, and conveying the die to an autoclave for curing;
(2) the butt joint frame 3 is formed by adopting a TC4 titanium alloy machine;
(3) the horizontal equipment mounting plate (6), the upper equipment mounting plate (7) and the lower equipment mounting plate (8) use finished carbon fiber epoxy resin plates, and the appearance, the lightening holes and the equipment mounting holes are cut through a wire cutting machine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210463690.9A CN114671005B (en) | 2022-04-28 | 2022-04-28 | Aircraft nose cone structure and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210463690.9A CN114671005B (en) | 2022-04-28 | 2022-04-28 | Aircraft nose cone structure and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114671005A CN114671005A (en) | 2022-06-28 |
| CN114671005B true CN114671005B (en) | 2024-04-12 |
Family
ID=82079851
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210463690.9A Active CN114671005B (en) | 2022-04-28 | 2022-04-28 | Aircraft nose cone structure and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114671005B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103407570A (en) * | 2013-07-12 | 2013-11-27 | 西北工业大学 | Eddy current generating device for controlling lateral force of large-incidence-angle slender body |
| CN109449591A (en) * | 2018-10-25 | 2019-03-08 | 湖北航天技术研究院总体设计所 | Active radar and passive radar seeker antenna cover and aircraft |
| CN110775245A (en) * | 2019-11-01 | 2020-02-11 | 北京航空航天大学 | Be applied to whole reinforcing frame structure of combined material of unmanned vehicles equipment fixing |
| CN217673163U (en) * | 2022-04-28 | 2022-10-28 | 威海光晟航天航空科技有限公司 | Aircraft nose cone structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10344672B2 (en) * | 2016-11-03 | 2019-07-09 | Rolls-Royce Corporation | Low weight nose cone assembly |
-
2022
- 2022-04-28 CN CN202210463690.9A patent/CN114671005B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103407570A (en) * | 2013-07-12 | 2013-11-27 | 西北工业大学 | Eddy current generating device for controlling lateral force of large-incidence-angle slender body |
| CN109449591A (en) * | 2018-10-25 | 2019-03-08 | 湖北航天技术研究院总体设计所 | Active radar and passive radar seeker antenna cover and aircraft |
| CN110775245A (en) * | 2019-11-01 | 2020-02-11 | 北京航空航天大学 | Be applied to whole reinforcing frame structure of combined material of unmanned vehicles equipment fixing |
| CN217673163U (en) * | 2022-04-28 | 2022-10-28 | 威海光晟航天航空科技有限公司 | Aircraft nose cone structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114671005A (en) | 2022-06-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7063763B2 (en) | Tubular members integrated to form a structure | |
| US10836472B2 (en) | One-piece composite bifurcated winglet | |
| US7080805B2 (en) | Stiffened structures and associated methods | |
| US4284443A (en) | Single stage hot bonding method for producing composite honeycomb core structures | |
| EP2669186B1 (en) | Bonded composite airfoil and fabrication method | |
| US8371537B2 (en) | Aircraft structure with hinge rib assembly | |
| EP2886452B1 (en) | Flow body, method for manufacturing a flow body and aircraft having such a flow body | |
| US20030146346A1 (en) | Tubular members integrated to form a structure | |
| EP3406887A1 (en) | Method for manufacturing a thrust reverser cascade and thrust reverser cascade | |
| JP2016175631A (en) | Composite fixed edge of aircraft wing and method for attaching the same | |
| EP3650333B1 (en) | Composite spar for aircraft wing | |
| US4304376A (en) | Composite honeycomb core structures and single stage hot bonding method of producing such structures | |
| JPH05301598A (en) | Withstand load structure and method for manufacturing same | |
| CN107651163B (en) | Fixed wing unmanned aerial vehicle outer wing structure and manufacturing method thereof | |
| US20120119031A1 (en) | Hybrid Frame Co-Mold Manufacture | |
| US20040000613A1 (en) | Preforms for acute structural edges | |
| CN217673163U (en) | Aircraft nose cone structure | |
| CN207346075U (en) | A kind of outer wing structure of fixed-wing unmanned plane | |
| EP2076431B1 (en) | Wing panel structure | |
| CN115837974A (en) | Composite material light truss type wing rib and assembling method | |
| CN114671005B (en) | Aircraft nose cone structure and preparation method thereof | |
| CN210653691U (en) | Fairing and aerospace craft | |
| CN214397196U (en) | Full-height honeycomb control surface structure | |
| US11292578B2 (en) | Composite aerodynamic structure | |
| US20240140588A1 (en) | Aircraft wing structure |
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 |