CN117284516A - Carbon fiber composite aircraft cabin shell and assembly method thereof - Google Patents

Carbon fiber composite aircraft cabin shell and assembly method thereof Download PDF

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Publication number
CN117284516A
CN117284516A CN202311451370.2A CN202311451370A CN117284516A CN 117284516 A CN117284516 A CN 117284516A CN 202311451370 A CN202311451370 A CN 202311451370A CN 117284516 A CN117284516 A CN 117284516A
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CN
China
Prior art keywords
cabin
shell
cabin section
section main
carbon fiber
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.)
Pending
Application number
CN202311451370.2A
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Chinese (zh)
Inventor
李懿
魏秀宾
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Anhui Mengkes Aviation Technology Co ltd
Original Assignee
Anhui Mengkes Aviation Technology Co ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Anhui Mengkes Aviation Technology Co ltd filed Critical Anhui Mengkes Aviation Technology Co ltd
Priority to CN202311451370.2A priority Critical patent/CN117284516A/en
Publication of CN117284516A publication Critical patent/CN117284516A/en
Pending legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/60—UAVs characterised by the material
    • B64U20/65—Composite materials
    • 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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/70—Constructional aspects of the UAV body
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/15—UAVs specially adapted for particular uses or applications for conventional or electronic warfare
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Materials Engineering (AREA)
  • Transportation (AREA)
  • Laminated Bodies (AREA)

Abstract

The invention discloses a cabin section shell of an aircraft made of carbon fiber composite materials and an assembly method thereof, wherein the cabin section shell comprises a cabin section main shell and a shape-like layer frame, and the shape-like layer frame is detachably connected in the cabin section main shell; the both ends of cabin section main casing set up respectively and accept portion and back and accept portion, and the cabin section main casing is close to the one side of preceding portion of accepting and is open structure, and preceding portion of accepting and back are accepted the equal circumference equipartition and are had the portion of accepting mounting hole, and the top of cabin section main casing is equipped with the rectangle and caves, and the bottom symmetry of cabin section main casing is equipped with rectangular shape and caves, the both sides of cabin section main casing are equipped with the mounting hole, the both sides wall of stand-by-stand is provided with the buried nut hole corresponding with the mounting hole. The invention provides a cabin section shell which is light in weight, high in strength, stable in structure, capable of being quickly connected with and detached from an unmanned aerial vehicle and a combat section, free of interference in signal receiving, and convenient in module unit integrated installation and disassembly.

Description

Carbon fiber composite aircraft cabin shell and assembly method thereof
Technical Field
The invention relates to the technical field of aircraft manufacturing, in particular to a carbon fiber composite aircraft cabin shell and an assembly method thereof.
Background
The small and medium-sized unmanned aerial vehicle is widely used in modern warfare, hundreds of unmanned aerial vehicles can be beaten into a combat team by a control system, the combat force is improved by orders of magnitude, and the control system comprises a plurality of core technologies such as an integrated control algorithm, a network communication design, a task and path planning technology, a formation control technology and the like. The system hardware consists of a plurality of intelligent module units and connecting lines which realize corresponding functions, and can be installed in a shell in a centralized way to be used as a control cabin section to be connected with the unmanned aerial vehicle.
At present, a small unmanned aerial vehicle shell is widely made of a light high-strength carbon fiber composite material, but carbon fibers have shielding effects on navigation signals and communication signals, and a common method is to replace the carbon fibers with aramid fiber materials or glass fiber reinforced plastic materials locally, so that the structural design is complex, and the overall rigidity of a cabin section is weakened.
The control cabin section needs to be integrally provided with a plurality of module units, and as an independent cabin section, the control cabin section needs to be capable of being repeatedly and rapidly assembled and disassembled with the unmanned aerial vehicle and the combat section. Each module unit inside is convenient to disassemble, assemble, detect and replace. At present, the interior units of the unmanned cabin section are directly arranged on the cabin section shell, the disassembly and replacement procedures are complicated, and because the specifications of the module units are various, the cost investment of the cabin section shell in the initial stage of development is large, the module units in the later stage are slightly changed, the cabin section shell needs to be changed or newly thrown, and the loss and the waste are serious.
Disclosure of Invention
The invention aims to solve the defects in the prior art, and provides a cabin shell made of a carbon fiber composite material and an assembly method thereof.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
the cabin section shell of the carbon fiber composite aircraft comprises a cabin section main shell and a shape-like layer frame, wherein the shape-like layer frame is detachably connected to the inside of the cabin section main shell;
the both ends of cabin section main casing set up respectively and accept portion and back and accept portion, and the cabin section main casing is close to the one side of preceding portion of accepting and is open structure, and preceding portion of accepting and back are accepted the equal circumference equipartition and are had the portion of accepting mounting hole, and the top of cabin section main casing is equipped with the rectangle sunken, and the bottom symmetry of cabin section main casing is equipped with rectangular shape sunken.
Preferably, the two sides of the cabin main shell are provided with assembly holes, and the two side walls of the annular layer frame are provided with embedded nut holes corresponding to the assembly holes.
Preferably, the end face of the cabin main shell close to the rear bearing part is provided with an end face through hole.
Preferably, a signal antenna assembly hole is formed in the bottom of the strip-shaped recess.
Preferably, the vertical surface of the rectangular recess is of a slope smooth transition structure.
Preferably, a plurality of exhaust holes are formed in the bottom of the cabin main shell, and the exhaust holes are located between the two strip-shaped depressions.
Preferably, the laminate and the side wall of the rectangular shelf are provided with a plurality of through holes.
Preferably, the inner walls of the two sides of the cabin main shell are connected with limit bearing strips for supporting the rectangular shelf.
Preferably, the cabin main shell comprises a solid frame, wherein the side plate of the inner wall of the solid frame is of a sandwich structure, a sandwich layer is arranged in the sandwich structure, and the sandwich layer is a thermal self-expansion adhesive film.
An assembly method of a carbon fiber composite aircraft cabin section shell, which comprises the following steps:
the method comprises the steps of installing a navigation antenna in a rectangular recess on the top surface of a cabin section main shell, installing signal antennas in rectangular recesses on two sides of the bottom surface of the cabin section main shell, installing a module unit a on the upper surface of the top layer of a square-shaped layer frame, installing a module unit b on the upper surface of the middle layer of the square-shaped layer frame, installing a module unit c on the lower surface of the square-shaped layer frame, sliding the square-shaped layer frame into the cabin section main shell, connecting all signal lines, connecting a front bearing part with a fight section, and connecting a rear bearing part with an unmanned aerial vehicle.
Compared with the prior art, the invention has the beneficial effects that: the invention provides a cabin section shell which is light in weight, high in strength, stable in structure, capable of being quickly connected with and detached from an unmanned aerial vehicle and a combat section, free of interference in signal receiving, and convenient in module unit integrated installation and disassembly.
Drawings
In order to more particularly and intuitively illustrate an embodiment of the present invention or a technical solution in the prior art, a brief description of the drawings is provided below, which are required to be used in the description of the embodiment or the prior art.
FIG. 1 is a schematic view of a carbon fiber composite aircraft cabin shell and method of assembling the same according to the present invention;
FIG. 2 is an isometric view of the top surface of a main cabin shell of an aircraft cabin shell of carbon fiber composite and a method of assembling the same in accordance with the present invention;
FIG. 3 is an isometric view of a bottom surface of a main cabin shell of an aircraft cabin shell of carbon fiber composite and a method of assembling the same in accordance with the present invention;
FIG. 4 is a schematic view of a carbon fiber composite aircraft cabin shell and its assembly method;
FIG. 5 is a schematic illustration of a carbon fiber composite aircraft cabin shell and its method of assembly, the drawer-type cradle sliding into the interior of the cabin main shell;
FIG. 6 is a schematic view of a solid frame structure of a carbon fiber composite aircraft cabin shell and a cabin main shell of a method of assembling the same according to the present invention;
fig. 7 is a cross-sectional view of a carbon fiber composite aircraft cabin shell and a cabin main shell of a method of assembling the same according to the present invention.
In the figure: 1: a cabin main housing; 101: a front receiving portion; 102: a rear receiving portion; 103: a receiving portion fitting hole; 104: an end surface through hole; 105: a top rectangular recess; 106: a limit supporting bar; 107: a fitting hole; 108: a bottom elongated recess; 109: a signal antenna assembly hole; 110: an exhaust hole; 111: a physical frame; 112: a sandwich structure; 2: a shape layer rack; 201: the shape of the embedded nut hole; 202: and a through hole.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments.
Example 1
Referring to fig. 1-7, a carbon fiber composite aircraft cabin shell comprises a cabin main shell 1 and a shaped layer frame 2.
The cabin section main body 1 both ends set up to preceding adapting portion 101 and back adapting portion 102, equipartition adapting portion pilot hole 103 all around, and preceding adapting portion 101 is connected with the battle section, and back adapting portion 102 is connected with unmanned aerial vehicle, adopts bolted connection to realize the stable connection that can dismantle fast. The data lines connected with the unmanned aerial vehicle pass through the end face through holes 104.
An external square navigation antenna is arranged in the rectangular recess 105 on the top surface, and signal reception is not affected. Two round bar-shaped signal antennas are externally arranged in the strip-shaped recesses 108 on two sides of the bottom surface through signal antenna assembly holes 109 and are connected with an internal steering engine.
The axial direction of the antenna is vertical to the bottom surface, and the axial direction of the signal antenna is vertical to the bottom surface during flying, so that the received signal is not affected. The vertical surface of the long strip-shaped concave 105 is in smooth transition with an inclined surface, the influence of turbulence of high-speed flight is eliminated according to aerodynamic design, and a plurality of exhaust holes 110 in the middle of the bottom surface are used for heat dissipation of the inner module unit.
The plurality of through holes 202 of all the layers and the side plates of the rectangular layer frame 2 are used for the passage of a screw driver during the installation of the module unit, and simultaneously play roles of weight reduction and heat dissipation, and the bottom is in contact fit with the limit supporting strips 106 of the cabin section main shell 1.
The cabin section main shell 1 and the hollow-shaped layer frame 2 form a drawer structure, the hollow-shaped layer frame 2 slides into the cabin section main shell 1, the embedded nut holes 201 at two sides are aligned with the assembly holes 107 at two sides of the cabin section main shell 1, and the hollow-shaped layer frame is fastened through bolts.
Example two
The embodiment of the invention provides a method for assembling a carbon fiber composite aircraft cabin shell, which comprises the following steps of: the method comprises the steps of installing a navigation antenna in a rectangular recess 105 on the top surface of a cabin section main shell 1, installing signal antennas in rectangular recesses 108 on two sides of the bottom surface of the cabin section main shell 1, installing a module unit on the upper surface of the top layer of a shape-taking layer frame 2, installing a module unit on the upper surface of the middle layer of the shape-taking layer frame 2, installing a module unit on the upper surface of the bottom layer of the shape-taking layer frame 2, sliding the shape-taking layer frame 2 into the cabin section main shell 1, connecting all signal wires, connecting a front bearing part 101 with a fight section, and connecting a rear bearing part 102 with an unmanned aerial vehicle.
Example III
The cabin main shell 1 adopts a structure of a composite material solid frame 111, and the wall plates at other parts inside the frame adopt a sandwich structure 112, which is similar to a sandwich.
The sandwich material is a thermal self-expansion adhesive film, and adopts a thermal self-expansion integrated molding process (HSM). The adhesive film is solidified into a high-strength foam sandwich material after expansion, the density is only 4% of that of the composite material, the light weight effect is obvious, and the weight design requirement is met.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art, who is within the scope of the present invention, should make equivalent substitutions or modifications according to the technical scheme of the present invention and the inventive concept thereof, and should be covered by the scope of the present invention.

Claims (10)

1. The cabin section shell of the carbon fiber composite aircraft comprises a cabin section main shell (1) and a shape-described layer frame (2), and is characterized in that the shape-described layer frame (2) is detachably connected in the cabin section main shell (1);
the both ends of cabin section main body (1) set up preceding adapting portion (101) and back adapting portion (102) respectively, and one side that cabin section main body (1) is close to preceding adapting portion (101) is open structure, and preceding adapting portion (101) and back adapting portion (102) all circumference equipartition have adapting portion pilot hole (103), and the top of cabin section main body (1) is equipped with rectangle recess (105), and the bottom symmetry of cabin section main body (1) is equipped with rectangular recess (108).
2. The carbon fiber composite aircraft cabin section shell according to claim 1, wherein the two sides of the cabin section main shell (1) are provided with assembly holes (107), and the two side walls of the frame (2) are provided with embedded nut holes (201) corresponding to the assembly holes (107).
3. A carbon fibre composite aircraft cabin shell according to claim 2, characterized in that the end face of the cabin main shell (1) adjacent to the rear receptacle (102) is provided with an end face through hole (104).
4. A carbon fibre composite aircraft cabin segment shell according to claim 3, characterized in that the bottom of the elongated recess (108) is provided with a signal antenna assembly hole (109).
5. The carbon fiber composite aircraft cabin segment shell according to claim 4, wherein the vertical surface of the rectangular recess (105) is of a slope smooth transition structure.
6. The carbon fiber composite aircraft cabin shell according to claim 5, wherein the bottom of the cabin main shell (1) is provided with a plurality of exhaust holes (110), and the exhaust holes (110) are located between two elongated depressions (108).
7. The carbon fiber composite aircraft cabin segment shell according to claim 6, wherein the laminate and the side walls of the rectangular layer frame (2) are provided with a plurality of through holes (202).
8. The carbon fiber composite aircraft cabin shell according to claim 7, wherein limiting support strips (106) for supporting the rectangular shelf (2) are connected to the inner walls of the two sides of the cabin main shell (1).
9. The carbon fiber composite aircraft cabin shell according to claim 8, wherein the cabin main shell (1) comprises a solid frame (111), an inner wall side plate of the solid frame (111) is a sandwich structure (112), a sandwich layer is arranged inside the sandwich structure (112), and the sandwich layer is a thermal self-expansion adhesive film.
10. A method of assembling a carbon fiber composite aircraft cabin shell according to claim 9, wherein the method of assembling comprises:
the navigation antenna is arranged in a rectangular recess (105) on the top surface of the cabin section main shell (1), the signal antenna is arranged in rectangular recesses (108) on two sides of the bottom surface of the cabin section main shell (1), the module unit a is arranged on the upper surface of the top layer of the square-shaped layer frame (2), the module unit b is arranged on the upper surface of the middle layer of the square-shaped layer frame (2), the module unit c is arranged on the upper surface of the bottom layer of the square-shaped layer frame (2), the square-shaped layer frame (2) slides into the cabin section main shell (1), all signal lines are connected, the front bearing part (101) is connected with a fight section, and the rear bearing part (102) is connected with an unmanned aerial vehicle.
CN202311451370.2A 2023-10-31 2023-10-31 Carbon fiber composite aircraft cabin shell and assembly method thereof Pending CN117284516A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202311451370.2A CN117284516A (en) 2023-10-31 2023-10-31 Carbon fiber composite aircraft cabin shell and assembly method thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202311451370.2A CN117284516A (en) 2023-10-31 2023-10-31 Carbon fiber composite aircraft cabin shell and assembly method thereof

Publications (1)

Publication Number Publication Date
CN117284516A true CN117284516A (en) 2023-12-26

Family

ID=89239225

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202311451370.2A Pending CN117284516A (en) 2023-10-31 2023-10-31 Carbon fiber composite aircraft cabin shell and assembly method thereof

Country Status (1)

Country Link
CN (1) CN117284516A (en)

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