CN112478126A - Unmanned aerial vehicle fuselage cabin section - Google Patents
Unmanned aerial vehicle fuselage cabin section Download PDFInfo
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- CN112478126A CN112478126A CN202011388878.9A CN202011388878A CN112478126A CN 112478126 A CN112478126 A CN 112478126A CN 202011388878 A CN202011388878 A CN 202011388878A CN 112478126 A CN112478126 A CN 112478126A
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- 230000003014 reinforcing effect Effects 0.000 claims description 19
- 239000002775 capsule Substances 0.000 claims description 14
- 229910000838 Al alloy Inorganic materials 0.000 claims description 4
- 239000000956 alloy Substances 0.000 claims description 3
- 239000002131 composite material Substances 0.000 description 19
- 229920000049 Carbon (fiber) Polymers 0.000 description 17
- 239000004917 carbon fiber Substances 0.000 description 17
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 17
- 238000004519 manufacturing process Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000006378 damage Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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Classifications
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- 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
- B64C1/061—Frames
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- 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
- B64C1/10—Bulkheads
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- 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
- B64C1/12—Construction or attachment of skin panels
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- 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
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1407—Doors; surrounding frames
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The application belongs to the technical field of unmanned aerial vehicle fuselage cabin section design, concretely relates to unmanned aerial vehicle fuselage cabin section, include: the front ring frame, the middle ring frame and the rear ring frame are arranged in sequence; the honeycomb bottom plate is arranged between the front ring frame and the middle ring frame, one end of the honeycomb bottom plate is connected with the front ring frame, and the other end of the honeycomb bottom plate is connected with the middle ring frame; the grid wallboard is arranged between the middle ring frame and the rear ring frame, one end of the grid wallboard is connected with the middle ring frame, and the other end of the grid wallboard is connected with the rear ring frame; one side edge of the honeycomb skin is connected with one side edge of the honeycomb bottom plate and one side edge of the grid wall plate, the other side edge of the honeycomb skin is connected with the other side edge of the honeycomb bottom plate and the other side edge of the grid wall plate, and the honeycomb skin covers the front ring frame, the middle ring frame and the rear ring frame.
Description
Technical Field
The application belongs to the technical field of unmanned aerial vehicle fuselage cabin section design, concretely relates to unmanned aerial vehicle fuselage cabin section.
Background
The unmanned aerial vehicle fuselage cabin section bears the surface pressure load at unmanned aerial vehicle flight in-process, and is connected with the undercarriage, takes off at unmanned aerial vehicle, descends the in-process, bears the impact load of undercarriage transmission, is the last important bearing structure of unmanned aerial vehicle.
At present, for satisfying the needs of bearing the weight of, the many designs unmanned aerial vehicle fuselage cabin section has great quality, is not conform to the requirement that unmanned aerial vehicle subtracts the weight now.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present patent application.
Disclosure of Invention
It is an object of the present application to provide a fuselage capsule section of a drone to overcome or mitigate the technical drawbacks of at least one aspect known to exist.
The technical scheme of the application is as follows:
an unmanned aerial vehicle fuselage cabin segment, comprising:
the front ring frame, the middle ring frame and the rear ring frame are arranged in sequence;
the honeycomb bottom plate is arranged between the front ring frame and the middle ring frame, one end of the honeycomb bottom plate is connected with the front ring frame, and the other end of the honeycomb bottom plate is connected with the middle ring frame;
the grid wallboard is arranged between the middle ring frame and the rear ring frame, one end of the grid wallboard is connected with the middle ring frame, and the other end of the grid wallboard is connected with the rear ring frame;
one side edge of the honeycomb skin is connected with one side edge of the honeycomb bottom plate and one side edge of the grid wall plate, the other side edge of the honeycomb skin is connected with the other side edge of the honeycomb bottom plate and the other side edge of the grid wall plate, and the honeycomb skin covers the front ring frame, the middle ring frame and the rear ring frame.
According to at least one embodiment of the application, in the above-mentioned unmanned aerial vehicle fuselage cabin section, the front ring frame, the middle ring frame and the rear ring frame are made of carbon fiber composite materials.
According to at least one embodiment of the application, in the fuselage cabin section of the unmanned aerial vehicle, the cross sections of the front ring frame, the middle ring frame and the rear ring frame are in an I shape.
According to at least one embodiment of the application, in the above-mentioned unmanned aerial vehicle fuselage cabin section, the front ring frame, the middle ring frame and the rear ring frame are roughly shaped like a horseshoe.
According to at least one embodiment of the application, in the above-mentioned unmanned aerial vehicle fuselage cabin section, the honeycomb bottom plate is manufactured by adopting an inner and outer carbon fiber composite skin + intermediate honeycomb body co-curing manufacturing scheme.
According to at least one embodiment of this application, among the foretell unmanned aerial vehicle fuselage cabin section, the net wallboard adopts carbon-fibre composite to make.
According to at least one embodiment of the application, in the unmanned aerial vehicle fuselage cabin section, the honeycomb skin is manufactured by adopting an inner carbon fiber composite material skin and an outer carbon fiber composite material skin plus an intermediate honeycomb body co-curing manufacturing scheme.
According to at least one embodiment of the application, in the unmanned aerial vehicle fuselage cabin section, the honeycomb skin is approximately U-shaped.
According to at least one embodiment of this application, among the foretell unmanned aerial vehicle fuselage cabin section, still include:
two front stringers are arranged between the front ring frame and the middle ring frame, one end of each front stringer is connected with the front ring frame, and the other end of each front stringer is connected with the middle ring frame; each front stringer is correspondingly connected with the edge of one side of the honeycomb bottom plate and connected with the edge of the corresponding side of the honeycomb skin;
two rear stringers, which are arranged between the middle ring frame and the rear ring frame, one end of each rear stringer is connected with the middle ring frame, and the other end of each rear stringer is connected with the rear ring frame; and each rear stringer is correspondingly connected with the edge of one side of the grid wall plate and the edge of the corresponding side of the honeycomb skin.
According to at least one embodiment of the application, in the above-mentioned unmanned aerial vehicle fuselage cabin section, each of the front stringers and the rear stringers is made of a carbon fiber composite material.
According to at least one embodiment of the application, in the unmanned aerial vehicle fuselage cabin section, the cross section of each of the front stringers and the rear stringers is L-shaped.
According to at least one embodiment of this application, among the foretell unmanned aerial vehicle fuselage cabin section, still include:
two front stiffening beams are arranged between the front ring frame and the middle ring frame, one end of each front stiffening beam is connected with the front ring frame, and the other end of each front stiffening beam is connected with the middle ring frame and the honeycomb bottom plate;
two back stiffening beams are arranged between the middle ring frame and the back ring frame, one end of each back stiffening beam is connected with the middle ring frame, and the other end of each back stiffening beam is connected with the back ring frame and the grid wall plate.
According to at least one embodiment of the application, in the above-mentioned unmanned aerial vehicle fuselage cabin section, each of the front stiffening beam and the rear stiffening beam is made of a carbon fiber composite material.
According to at least one embodiment of the application, in the above-mentioned unmanned aerial vehicle fuselage cabin section, the cross section of each front stiffening beam and each rear stiffening beam is C-shaped.
According to at least one embodiment of the application, in the fuselage cabin section of the unmanned aerial vehicle, the honeycomb bottom plate is provided with an undercarriage retracting opening;
unmanned aerial vehicle fuselage cabin section still includes:
the landing gear cabin door is arranged at the landing gear retraction opening and can be opened and closed;
the landing gear front joint is connected with the front ring frame;
and the landing gear rear joint is connected with the middle ring frame.
According to at least one embodiment of the application, in the unmanned aerial vehicle fuselage cabin section, the landing gear doors are manufactured by adopting an inner carbon fiber composite skin and an outer carbon fiber composite skin plus an intermediate honeycomb body co-curing manufacturing scheme.
According to at least one embodiment of the application, in the unmanned aerial vehicle fuselage cabin section, the undercarriage front joint and the undercarriage rear joint are made of aluminum alloy materials.
According to at least one embodiment of the application, in the unmanned aerial vehicle fuselage cabin section, each undercarriage rear joint is connected with one end, facing the middle ring frame, of the front reinforcing beam.
According to at least one embodiment of this application, among the foretell unmanned aerial vehicle fuselage cabin section, still include:
and one end of each supporting beam is connected with the front ring frame, and the other end of each supporting beam is correspondingly connected with one front reinforcing beam.
According to at least one embodiment of the application, in the above-mentioned unmanned aerial vehicle fuselage cabin section, each support beam is made of carbon fiber composite.
According to at least one embodiment of this application, in foretell unmanned aerial vehicle fuselage cabin section, the cross-section of each supporting beam is the C type.
Drawings
Fig. 1 is an external view of a fuselage capsule section of an unmanned aerial vehicle provided by an embodiment of the present application;
FIG. 2 is a schematic view of another angle of FIG. 1;
fig. 3 is a schematic view of a structure of a cabin section part of a fuselage of the unmanned aerial vehicle provided by an embodiment of the application;
FIG. 4 is a schematic view of another angle of FIG. 3;
wherein:
1-front ring frame; 2-middle ring frame; 3-rear ring frame; 4-a honeycomb substrate; 5-grid wall plates; 6-honeycomb
Covering a skin; 7-front stringer; 8-rear stringer; 9-a front stiffening beam; 10-a rear stiffening beam; 11-landing gear bay doors;
12-landing gear nose joint; 13-landing gear rear joint; 14-supporting beam.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The use of the terms "comprising" or "including" and the like in the description of the present application is intended to indicate that the element or item preceding the term covers the element or item listed after the term and its equivalents, without excluding other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1 to 4.
An unmanned aerial vehicle fuselage cabin segment, comprising:
the front ring frame 1, the middle ring frame 2 and the rear ring frame 3 are arranged in sequence;
the honeycomb bottom plate 4 is arranged between the front ring frame 1 and the middle ring frame 2, one end of the honeycomb bottom plate is connected with the front ring frame 1, and the other end of the honeycomb bottom plate is connected with the middle ring frame 2;
a grid wall plate 5 arranged between the middle ring frame 2 and the rear ring frame 3, wherein one end of the grid wall plate is connected with the middle ring frame 2, and the other end of the grid wall plate is connected with the rear ring frame 3;
one side edge of the honeycomb skin 6 is connected with one side edge of the honeycomb bottom plate 4 and one side edge of the grid wall plate 5, and the other side edge of the honeycomb skin is connected with the other side edge of the honeycomb bottom plate 4 and the other side edge of the grid wall plate 5 to cover the front ring frame 1, the middle ring frame 2 and the rear ring frame 3.
For the fuselage cabin section of the unmanned aerial vehicle disclosed in the above embodiment, those skilled in the art can understand that the honeycomb bottom plate 4 between the front ring frame 1 and the middle ring frame 2 is made of a composite material, and the honeycomb skin covering the front ring frame 1, the middle ring frame 2 and the rear ring frame 3 is made of a material, so that the fuselage cabin section has relatively light weight while bearing surface pressure load, and meets the weight reduction requirement of the existing unmanned aerial vehicle.
In some optional embodiments, in the above-mentioned fuselage cabin section of the unmanned aerial vehicle, the front ring frame 1, the middle ring frame 2, and the rear ring frame 3 are made of carbon fiber composite materials, so that the overall weight is light, and the rigidity is high.
In some optional embodiments, in the above-mentioned fuselage cabin section of the unmanned aerial vehicle, the cross sections of the front ring frame 1, the middle ring frame 2 and the rear ring frame 3 are i-shaped.
In some optional embodiments, in the above-mentioned fuselage cabin section of the unmanned aerial vehicle, the front ring frame 1, the middle ring frame 2 and the rear ring frame 3 are substantially horseshoe-shaped.
In some alternative embodiments, in the above-mentioned fuselage cell section of the unmanned aerial vehicle, the honeycomb floor 4 is manufactured by using a co-curing manufacturing scheme of inner and outer carbon fiber composite skins and an intermediate honeycomb body, so that the honeycomb floor 4 has relatively light mass, high rigidity, and meets the requirement of bearing surface pressure load.
In some optional embodiments, in the above-mentioned fuselage cabin section of the unmanned aerial vehicle, the grid wall panels 5 are made of carbon fiber composite materials, so that the whole weight is light, the rigidity is high, and the requirement of bearing surface pressure load is met.
In some alternative embodiments, in the above-mentioned fuselage capsule section of the unmanned aerial vehicle, the honeycomb skin 6 is manufactured by using a co-curing manufacturing scheme of inner and outer carbon fiber composite skins and an intermediate honeycomb body, so that the honeycomb skin 6 has relatively light mass, high rigidity, and meets the requirement of bearing surface pressure load.
In some alternative embodiments, in the above-described fuselage cell section of the drone, the honeycomb skin 6 is substantially U-shaped.
In some optional embodiments, in the above-mentioned fuselage capsule section of the unmanned aerial vehicle, further comprising:
two front stringers 7 arranged between the front ring frame 1 and the middle ring frame 2, one end of each front stringer being connected with the front ring frame 1, and the other end of each front stringer being connected with the middle ring frame 2; each front stringer 7 is correspondingly connected with the edge of one side of the honeycomb bottom plate 4 and the edge of the corresponding side of the honeycomb skin 6;
two rear stringers 8, which are provided between the middle ring frame 2 and the rear ring frame 3, and one end of which is connected with the middle ring frame 2 and the other end of which is connected with the rear ring frame 3; each rear stringer 8 is connected to the edge of one side of the grid wall panel 5 and to the edge of the corresponding side of the honeycomb skin 6.
For the unmanned aerial vehicle fuselage cabin section disclosed in the above embodiment, it can be understood by those skilled in the art that the arrangement of the front stringer 7 can position the front ring frame 1 and the middle ring frame 2, and can provide a connection portion for the connection between the honeycomb base plate 4 and the honeycomb skin 6.
To the unmanned aerial vehicle fuselage cabin section disclosed in the above embodiment, those skilled in the art can also understand that the arrangement of the rear stringer 8 can position the middle ring frame 2 and the rear ring frame 3, and provide a connection portion for the connection between the grid wall plate 5 and the honeycomb skin 6.
In some alternative embodiments, in the above-mentioned fuselage cabin section of the unmanned aerial vehicle, each of the front and rear stringers 7, 8 is made of a carbon fiber composite material so as to have relatively light weight, high rigidity, and meet the load bearing requirement.
In some alternative embodiments, in the above-mentioned fuselage cell section of the unmanned aerial vehicle, the cross section of each of the front and rear stringers 7, 8 is L-shaped.
In some optional embodiments, in the above-mentioned fuselage capsule section of the unmanned aerial vehicle, further comprising:
two front stiffening beams 9 are arranged between the front ring frame 1 and the middle ring frame 2, one end of each front stiffening beam is connected with the front ring frame 1, and the other end of each front stiffening beam is connected with the middle ring frame 2 and the honeycomb bottom plate 4;
and two rear reinforcing beams 10 are arranged between the middle ring frame 2 and the rear ring frame 3, one end of each rear reinforcing beam is connected with the middle ring frame 2, and the other end of each rear reinforcing beam is connected with the rear ring frame 3 and the grid wall plate 5.
To the unmanned aerial vehicle fuselage cabin section disclosed to above-mentioned embodiment, technical personnel in the field can understand that, the setting of preceding stiffening beam 9 can play the positioning action to preceding ring frame 1, well ring frame 2 on the one hand, and on the other hand can strengthen honeycomb floor 4's rigidity, satisfies the demand that bears.
To the unmanned aerial vehicle fuselage cabin section disclosed to above-mentioned embodiment, technical personnel can also understand in the field that the setting of back stiffening beam 10 can play the positioning action to center ring frame 2, back ring frame 3 on the one hand, and on the other hand can strengthen the rigidity of net wallboard 5, satisfies the demand that bears.
In some optional embodiments, in the above-mentioned fuselage cabin section of the unmanned aerial vehicle, each of the front reinforcing beam 9 and the rear reinforcing beam 10 is made of carbon fiber composite material so as to have relatively light weight, high rigidity, and meet the requirement of load bearing.
In some optional embodiments, in the above-mentioned fuselage cabin section of the unmanned aerial vehicle, each of the front reinforcing beam 9 and the rear reinforcing beam 10 has a C-shaped cross section.
In some optional embodiments, in the above-mentioned fuselage cabin section of the unmanned aerial vehicle, the honeycomb bottom plate 4 is provided with a landing gear retraction opening;
unmanned aerial vehicle fuselage cabin section still includes:
a landing gear bay door 11 which is provided at the landing gear retraction/extension opening and can be opened and closed;
a landing gear front joint 12 connected with the front ring frame 1;
and a landing gear rear joint 13 connected with the middle ring frame 2.
To the unmanned aerial vehicle fuselage cabin section disclosed in the above embodiments, it can be understood by those skilled in the art that the undercarriage front joint 12 and the undercarriage rear joint 13 thereof may be connected to the undercarriage of the unmanned aerial vehicle, and when the undercarriage door 11 is opened, the undercarriage may be retracted and extended.
In some alternative embodiments, in the above-mentioned fuselage capsule section of the unmanned aerial vehicle, the landing gear door 11 is manufactured by using an inner and outer carbon fiber composite skin plus an intermediate honeycomb co-curing manufacturing scheme so as to provide the landing gear door 11 with relatively light mass, high rigidity, and meet the requirement of bearing the surface pressure load. .
In some optional embodiments, in the above-mentioned fuselage cabin section of the unmanned aerial vehicle, the landing gear front joint 12 and the landing gear rear joint 13 are made of aluminum alloy materials.
To the unmanned aerial vehicle fuselage cabin section disclosed to above-mentioned embodiment, technical personnel in the field can understand that undercarriage front joint 12, undercarriage rear joint 13 are direct to be connected with the undercarriage, directly bear the impact load of undercarriage transmission in unmanned aerial vehicle take-off, landing process, design undercarriage front joint 12, undercarriage rear joint 13 for the aluminum alloy structure, can have higher bearing capacity, can effectively bear the impact load of undercarriage transmission.
In some alternative embodiments, in the above-mentioned fuselage section of the unmanned aerial vehicle, each rear landing gear joint 13 is connected to an end of one of the front reinforcing beams 9 facing the middle ring frame 2.
To the unmanned aerial vehicle fuselage cabin section disclosed in the above embodiment, a person skilled in the art can understand that the undercarriage rear joint 13 for directly connecting with the undercarriage is arranged between the front stiffening beam 9 and the middle ring frame 2, and is connected with the front stiffening beam 9 and the middle ring frame 2, so as to avoid direct connection on the honeycomb bottom plate 4, thereby avoiding concentrated load generated in the take-off and landing processes of the unmanned aerial vehicle on the honeycomb bottom plate 4 from being damaged.
In some optional embodiments, in the above-mentioned fuselage capsule section of the unmanned aerial vehicle, further comprising:
two support beams 14, each support beam 14 having one end connected to the front ring frame 1 and the other end connected to a corresponding one of the front reinforcing beams 9.
To the unmanned aerial vehicle fuselage cabin section disclosed to above-mentioned embodiment, technical personnel in the field can understand that, it will be used for setting up on the ring frame 1 with undercarriage lug connection's undercarriage front joint 12, avoid lug connection on honeycomb bottom plate 4, with this, can avoid taking off at unmanned aerial vehicle on the honeycomb bottom plate 4, the landing in-process produces concentrated load, suffer destruction, in addition, design supporting beam 14 supports at ring frame 1 in the front, preceding stiffening beam 9 can form firm triangle-shaped bearing structure, have higher resistance to deformation, bearing capacity.
In some alternative embodiments, each support beam 14 in the above-described fuselage cabin section of the drone is made of carbon fiber composite material to have relatively light mass, high stiffness, and to meet load bearing requirements.
In some alternative embodiments, in the above-described fuselage cell section of the drone, each support beam 14 is C-shaped in cross-section.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (8)
1. An unmanned aerial vehicle fuselage cabin section, comprising:
the front ring frame (1), the middle ring frame (2) and the rear ring frame (3) are arranged in sequence;
the honeycomb bottom plate (4) is arranged between the front ring frame (1) and the middle ring frame (2), one end of the honeycomb bottom plate is connected with the front ring frame (1), and the other end of the honeycomb bottom plate is connected with the middle ring frame (2);
the grid wall plate (5) is arranged between the middle ring frame (2) and the rear ring frame (3), one end of the grid wall plate is connected with the middle ring frame (2), and the other end of the grid wall plate is connected with the rear ring frame (3);
honeycomb covering (6), one side edge with honeycomb bottom plate (4) one side edge, net wallboard (5) one side edge is connected, the opposite side edge with honeycomb bottom plate (4) the opposite side edge of net wallboard (5) opposite side edge is connected, covers preceding ring frame (1) well ring frame (2) back ring frame (3).
2. The UAV fuselage capsule section of claim 1,
further comprising:
two front stringers (7) arranged between the front ring frame (1) and the middle ring frame (2), wherein one end of each front stringer is connected with the front ring frame (1), and the other end of each front stringer is connected with the middle ring frame (2); each front stringer (7) is correspondingly connected with the edge of one side of the honeycomb bottom plate (4) and the edge of the corresponding side of the honeycomb skin (6);
two rear stringers (8) arranged between the middle ring frame (2) and the rear ring frame (3), one end of each rear stringer being connected with the middle ring frame (2), and the other end of each rear stringer being connected with the rear ring frame (3); each rear stringer (8) is correspondingly connected with one side edge of the grid wall plate (5) and the edge of the corresponding side of the honeycomb skin (6).
3. The UAV fuselage capsule section of claim 2,
the cross section of each front stringer (7) and each rear stringer (8) is L-shaped.
4. The UAV fuselage capsule section of claim 1,
further comprising:
two front reinforcing beams (9) are arranged between the front ring frame (1) and the middle ring frame (2), one end of each front reinforcing beam is connected with the front ring frame (1), and the other end of each front reinforcing beam is connected with the middle ring frame (2) and the honeycomb bottom plate (4);
two rear reinforcing beams (10) are arranged between the middle ring frame (2) and the rear ring frame (3), one end of each rear reinforcing beam is connected with the middle ring frame (2), and the other end of each rear reinforcing beam is connected with the rear ring frame (3) and the grid wall plate (5).
5. The UAV fuselage capsule section of claim 4,
the honeycomb bottom plate (4) is provided with a landing gear retraction opening;
unmanned aerial vehicle fuselage cabin section still includes:
a landing gear compartment door (11) which is provided at the landing gear retraction opening and can be opened and closed;
a landing gear nose joint (12) connected to the nose ring frame (1);
and the landing gear rear joint (13) is connected with the middle ring frame (2).
6. The UAV fuselage capsule section of claim 5,
the undercarriage front joint (12) and the undercarriage rear joint (13) are made of aluminum alloy materials.
7. The UAV fuselage capsule section of claim 5,
each landing gear rear joint (13) is connected with one end, facing the middle ring frame (2), of the front reinforcing beam (9).
8. The UAV fuselage capsule section of claim 5,
further comprising:
and one end of each support beam (14) is connected with the front ring frame (1), and the other end of each support beam (14) is correspondingly connected with one front reinforcing beam (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011388878.9A CN112478126B (en) | 2020-12-02 | 2020-12-02 | Unmanned aerial vehicle fuselage cabin section |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011388878.9A CN112478126B (en) | 2020-12-02 | 2020-12-02 | Unmanned aerial vehicle fuselage cabin section |
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| CN112478126A true CN112478126A (en) | 2021-03-12 |
| CN112478126B CN112478126B (en) | 2024-01-02 |
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100072319A1 (en) * | 2005-11-21 | 2010-03-25 | Airbus France | Landing gear casing provided with a box structure |
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| US20100072319A1 (en) * | 2005-11-21 | 2010-03-25 | Airbus France | Landing gear casing provided with a box structure |
| CN106507751B (en) * | 2007-11-03 | 2011-11-23 | 成都飞机工业（集团）有限责任公司 | SUAV fuselage |
| US20150183505A1 (en) * | 2013-12-30 | 2015-07-02 | Airbus Helicopters Deutschland GmbH | Subfloor structure with an integral hull for a rotary wing aircraft |
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| CN107672778A (en) * | 2017-11-10 | 2018-02-09 | 江苏美龙航空部件有限公司 | A kind of unmanned plane forebody structure |
| CN108109507A (en) * | 2018-01-29 | 2018-06-01 | 天津中德应用技术大学 | Undercarriage folding and unfolding process demonstrator |
| US20200156803A1 (en) * | 2018-02-13 | 2020-05-21 | Bell Helicopter Textron Inc. | Fuselage embedded fuel tank |
| US20200189711A1 (en) * | 2018-12-18 | 2020-06-18 | Airbus Operations Sas | Aircraft fuselage structure having a grid-stiffened panel |
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| CN112478126B (en) | 2024-01-02 |
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