CN112478126B - Unmanned aerial vehicle fuselage cabin section - Google Patents
Unmanned aerial vehicle fuselage cabin section Download PDFInfo
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- CN112478126B CN112478126B CN202011388878.9A CN202011388878A CN112478126B CN 112478126 B CN112478126 B CN 112478126B CN 202011388878 A CN202011388878 A CN 202011388878A CN 112478126 B CN112478126 B CN 112478126B
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- ring frame
- aerial vehicle
- unmanned aerial
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- honeycomb
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- 230000002787 reinforcement Effects 0.000 claims description 12
- 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 17
- 229920000049 Carbon (fiber) Polymers 0.000 description 15
- 239000004917 carbon fiber Substances 0.000 description 15
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 15
- 238000004519 manufacturing process Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 230000001413 cellular effect Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 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
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
-
- 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 unmanned aerial vehicle fuselage cabin section design technical field, concretely relates to unmanned aerial vehicle fuselage cabin section, include: the front ring frame, the middle ring frame and the rear ring frame are sequentially arranged; 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 wall plate is arranged between the middle ring frame and the rear ring frame, one end of the grid wall plate is connected with the middle ring frame, and the other end of the grid wall plate is connected with the rear ring frame; the honeycomb skin, one side edge is connected with one side edge of the honeycomb bottom plate and one side edge of the grid wall plate, and the other side edge is connected with the other side edge of the honeycomb bottom plate and the other side edge of the grid wall plate and covers the front ring frame, the middle ring frame and the rear ring frame.
Description
Technical Field
The application belongs to unmanned aerial vehicle fuselage cabin section design technical field, concretely relates to unmanned aerial vehicle fuselage cabin section.
Background
The unmanned aerial vehicle fuselage cabin section bears surface pressure load in the unmanned aerial vehicle flight process, and is connected with the undercarriage, takes off, the landing in-process at the unmanned aerial vehicle, bears the impact load of undercarriage transmission, is the last important bearing structure of unmanned aerial vehicle.
Currently, in order to meet the bearing requirement, the cabin section of the multi-design unmanned aerial vehicle has larger quality and does not meet the current weight reduction requirement of the unmanned aerial vehicle.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present invention, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an unmanned aerial vehicle fuselage section that overcomes or alleviates the technical drawbacks of at least one aspect of the known existence.
The technical scheme of the application is as follows:
an unmanned aerial vehicle fuselage section comprising:
the front ring frame, the middle ring frame and the rear ring frame are sequentially arranged;
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 wall plate is arranged between the middle ring frame and the rear ring frame, one end of the grid wall plate is connected with the middle ring frame, and the other end of the grid wall plate is connected with the rear ring frame;
the honeycomb skin, one side edge is connected with one side edge of the honeycomb bottom plate and one side edge of the grid wall plate, and the other side edge is connected with the other side edge of the honeycomb bottom plate and the other side edge of the grid wall plate and covers the front ring frame, the middle ring frame and the rear ring frame.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage 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 present application, in the above-mentioned unmanned aerial vehicle fuselage section, the cross sections of the front ring frame, the middle ring frame, and the rear ring frame are i-shaped.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage section, the front ring frame, the middle ring frame, and the rear ring frame are substantially horseshoe-shaped.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage section, the honeycomb bottom plate is manufactured by adopting an internal and external carbon fiber composite material skin+middle honeycomb body co-curing manufacturing scheme.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage section, the mesh wall plate is made of a carbon fiber composite material.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage section, the honeycomb skin is manufactured by adopting an internal and external carbon fiber composite material skin+middle honeycomb co-curing manufacturing scheme.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage section, the honeycomb skin is substantially U-shaped.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage section, further includes:
the 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 one side edge of the honeycomb bottom plate and is connected with the edge of the corresponding side of the honeycomb skin;
the two rear stringers 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; each rear stringer is connected to an edge of one side of the grid panel, and to an edge of the corresponding side of the honeycomb skin.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage 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 present application, in the above-mentioned unmanned aerial vehicle fuselage section, each of the front stringers and the rear stringers has an L-shaped cross section.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage section, further includes:
the 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 stiffening beam is connected with the middle ring frame, and the other end of each stiffening beam is connected with the back ring frame and the grid wallboard.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage section, each of the front reinforcement beam and the rear reinforcement beam is made of a carbon fiber composite material.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage 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 present application, in the above-mentioned unmanned aerial vehicle fuselage section, the cellular bottom plate is provided with a landing gear retraction opening;
unmanned aerial vehicle fuselage 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 present application, in the above-mentioned unmanned aerial vehicle fuselage section, the landing gear door is manufactured by adopting an inner and outer carbon fiber composite material skin+middle honeycomb co-curing manufacturing scheme.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage cell, the landing gear front joint and the landing gear rear joint are made of aluminum alloy materials.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage section, each landing gear rear joint is correspondingly connected to one end of one front reinforcement beam facing the middle ring frame.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage section, further includes:
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 stiffening beam.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage section, each support beam is made of a carbon fiber composite material.
According to at least one embodiment of the present application, in the above-mentioned unmanned aerial vehicle fuselage section, each support beam has a C-shaped cross section.
Drawings
Fig. 1 is an outline view of a fuselage section of an unmanned aerial vehicle provided in 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 part of a cabin section structure of an unmanned aerial vehicle according to an embodiment of the present application;
FIG. 4 is a schematic view of another angle of FIG. 3;
wherein:
1-a front ring frame; 2-a middle ring frame; 3-a rear ring frame; 4-honeycomb floor; 5-grid wall panels; 6-honeycomb
A skin; 7-front stringers; 8-a rear stringer; 9-a front stiffening beam; 10-a rear reinforcement beam; 11-landing gear door;
12-landing gear nose-piece; 13-landing gear aft joint; 14-supporting beams.
For the purpose of better illustrating the embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions; further, the drawings are for illustrative purposes, wherein the terms describing the positional relationship are limited to the illustrative description only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like, are intended to cover an element or article that appears before the term and that is recited after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The present application is described in further detail below with reference to fig. 1-4.
An unmanned aerial vehicle fuselage section comprising:
the front ring frame 1, the middle ring frame 2 and the rear ring frame 3 are sequentially arranged;
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;
the honeycomb skin 6, one side edge 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 is connected with the other side edge of the honeycomb bottom plate 4 and the other side edge of the grid wall plate 5, and covers the front ring frame 1, the middle ring frame 2 and the rear ring frame 3.
For the unmanned aerial vehicle fuselage section disclosed in the above embodiment, it will be understood by those skilled in the art that the honeycomb bottom plate 4 between the front ring frame 1 and the middle ring frame 2 is designed to be made of composite materials, and the honeycomb skin designed to cover the front ring frame 1, the middle ring frame 2 and the rear ring frame 3 is made of compliant materials, so that the unmanned aerial vehicle fuselage section has relatively light weight while meeting the surface pressure load bearing requirement and meets the current weight reduction requirement of the unmanned aerial vehicle.
In some alternative embodiments, in the above-mentioned unmanned aerial vehicle fuselage section, 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 mass is light and the rigidity is high.
In some alternative embodiments, in the above-mentioned unmanned aerial vehicle fuselage section, 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 alternative embodiments, in the above-mentioned unmanned aerial vehicle fuselage section, the front ring frame 1, the middle ring frame 2, and the rear ring frame 3 are substantially horseshoe-shaped.
In some alternative embodiments, the above-described unmanned aerial vehicle fuselage section, the honeycomb floor 4 is manufactured using an inner and outer carbon fiber composite skin+intermediate honeycomb co-curing manufacturing scheme, so that the honeycomb floor 4 has a relatively light weight, high rigidity, and meets the surface pressure load bearing requirements.
In some alternative embodiments, the mesh panel 5 is made of carbon fiber composite material in the unmanned plane cabin section, so that the overall weight is light, the rigidity is high, and the requirement of bearing surface pressure load is met.
In some alternative embodiments, the above-described unmanned aerial vehicle fuselage section, the honeycomb skin 6 is manufactured using an inner and outer carbon fiber composite skin+intermediate honeycomb co-cure manufacturing scheme, so that the honeycomb skin 6 has a relatively light weight, high stiffness, and meets the surface pressure load bearing requirements.
In some alternative embodiments, the honeycomb skin 6 is generally U-shaped in the above-described unmanned aircraft fuselage section.
In some optional embodiments, the above-mentioned unmanned aerial vehicle fuselage section further includes:
two front stringers 7 arranged between the front ring frame 1 and the middle ring frame 2, 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 connected with the edge of one side of the honeycomb bottom plate 4 and with 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 is connected with the middle ring frame 2, and the other end of each rear stringer is connected with the rear ring frame 3; each rear stringer 8 is connected to an edge of one side of the grid panel 5, and to an edge of the corresponding side of the honeycomb skin 6.
For the unmanned aerial vehicle fuselage section disclosed in the above embodiment, it will be understood by those skilled in the art that the arrangement of the front stringers 7 can, on the one hand, locate the front ring frame 1, the middle ring frame 2 and, on the other hand, provide a connection point for the connection between the honeycomb floor 4 and the honeycomb skin 6.
For the unmanned plane fuselage section disclosed in the above embodiment, it will be further understood by those skilled in the art that the arrangement of the rear stringers 8 can, on the one hand, perform a positioning function on the middle ring frame 2 and the rear ring frame 3, and, on the other hand, can provide a connection site for the connection between the mesh panel 5 and the honeycomb skin 6.
In some alternative embodiments, each of the front and rear stringers 7, 8 in the unmanned aircraft fuselage section described above is made of carbon fibre composite material to have a relatively low mass, a high stiffness, and to meet load carrying requirements.
In some alternative embodiments, in the above-mentioned unmanned aerial vehicle fuselage section, each of the front stringers 7, the rear stringers 8 has an L-shaped cross section.
In some optional embodiments, the above-mentioned unmanned aerial vehicle fuselage section further includes:
two front stiffening beams 9 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, the other end of each front stiffening beam is connected with the middle ring frame 2, and each front stiffening beam is connected with the honeycomb bottom plate 4;
two back stiffening beams 10 are arranged between the middle ring frame 2 and the back ring frame 3, one end of each back stiffening beam is connected with the middle ring frame 2, and the other end of each back stiffening beam is connected with the back ring frame 3 and the grid wall plate 5.
For the unmanned aerial vehicle fuselage cabin section disclosed in the above embodiment, those skilled in the art can understand that the setting of the front stiffening beam 9 can play a role in positioning the front ring frame 1 and the middle ring frame 2 on one hand, and can enhance the rigidity of the honeycomb bottom plate 4 on the other hand, so as to meet the load-bearing requirement.
For the unmanned aerial vehicle fuselage cabin section disclosed in the above embodiment, those skilled in the art can also understand that the setting of the rear stiffening beam 10 can play a role in positioning the middle ring frame 2 and the rear ring frame 3 on one hand, and can enhance the rigidity of the grid wallboard 5 on the other hand, so as to meet the load-bearing requirement.
In some alternative embodiments, in the above-mentioned unmanned aerial vehicle fuselage section, each of the front reinforcement beam 9 and the rear reinforcement beam 10 is made of a carbon fiber composite material, so as to have relatively light weight, high rigidity, and meet the load-bearing requirements.
In some alternative embodiments, in the above-mentioned unmanned aerial vehicle fuselage section, each of the front reinforcement beam 9 and the rear reinforcement beam 10 has a C-shaped cross section.
In some alternative embodiments, in the above-mentioned unmanned aerial vehicle fuselage section, the cellular bottom plate 4 is provided with a landing gear retraction opening;
unmanned aerial vehicle fuselage section still includes:
a landing gear door 11 provided at the landing gear retraction opening and openable and closable;
the landing gear front joint 12 is connected with the front ring frame 1;
and the landing gear rear joint 13 is connected with the middle ring frame 2.
For the unmanned aerial vehicle fuselage section disclosed in the above embodiment, it will be understood by those skilled in the art that the landing gear front joint 12 and the landing gear rear joint 13 thereof may be connected to the landing gear of the unmanned aerial vehicle, and the landing gear may be retracted when the landing gear door 11 is opened.
In some alternative embodiments, the landing gear door 11 is manufactured using an inner and outer carbon fiber composite skin + intermediate honeycomb co-cure manufacturing scheme in the unmanned aerial vehicle fuselage cell described above to provide a landing gear door 11 of relatively low mass, high stiffness, and to meet the surface pressure load requirements. .
In some alternative embodiments, in the above-mentioned unmanned aerial vehicle fuselage section, the landing gear front joint 12 and the landing gear rear joint 13 are made of aluminum alloy materials.
For the unmanned aerial vehicle fuselage section disclosed in the above embodiment, it can be understood by those skilled in the art that the landing gear front joint 12 and the landing gear rear joint 13 are directly connected with the landing gear, and directly bear the impact load transferred by the landing gear in the process of taking off and landing of the unmanned aerial vehicle, and the landing gear front joint 12 and the landing gear rear joint 13 are designed into aluminum alloy structures, so that the unmanned aerial vehicle fuselage section can have higher bearing capacity and can effectively bear the impact load transferred by the landing gear.
In some alternative embodiments, in the above-mentioned unmanned aerial vehicle fuselage section, each landing gear rear joint 13 is connected to one end of one front reinforcement beam 9 facing the middle ring frame 2.
For the unmanned aerial vehicle fuselage section disclosed in the above embodiment, it can be understood by those skilled in the art that the landing gear rear joint 13 for being directly connected with the landing gear 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 that the direct connection on the honeycomb bottom plate 4 is avoided, and the centralized load generated in the take-off and landing processes of the unmanned aerial vehicle on the honeycomb bottom plate 4 can be avoided, and the unmanned aerial vehicle is damaged.
In some optional embodiments, the above-mentioned unmanned aerial vehicle fuselage section further includes:
and two support beams 14, wherein one end of each support beam 14 is connected with the front ring frame 1, and the other end is correspondingly connected with one front reinforcement beam 9.
For the unmanned aerial vehicle fuselage section disclosed in the above embodiment, it can be understood by those skilled in the art that the landing gear front connector 12 for being directly connected with the landing gear is arranged on the front ring frame 1, so as to avoid being directly connected with the honeycomb bottom plate 4, thereby being capable of avoiding the centralized load generated in the process of taking off and landing of the unmanned aerial vehicle on the honeycomb bottom plate 4 and being damaged, and in addition, the support beam 14 is designed to be supported on the front ring frame 1 and the front reinforcement beam 9, so that a stable triangular support structure can be formed, and the unmanned aerial vehicle fuselage section has higher deformation resistance and bearing capacity.
In some alternative embodiments, each support beam 14 is made of carbon fiber composite material in the above-described unmanned aircraft fuselage section to have a relatively light weight, high stiffness, and to meet load bearing requirements.
In some alternative embodiments, each support beam 14 is C-shaped in cross-section in the above-described unmanned aircraft fuselage section.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (6)
1. An unmanned aerial vehicle fuselage section, comprising:
the front ring frame (1), the middle ring frame (2) and the rear ring frame (3) are sequentially arranged;
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);
a honeycomb skin (6), wherein one side edge is connected with one side edge of the honeycomb bottom plate (4) and one side edge of the grid wallboard (5), and the other side edge is connected with the other side edge of the honeycomb bottom plate (4) and the other side edge of the grid wallboard (5) to cover the front ring frame (1), the middle ring frame (2) and the rear ring frame (3);
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);
two rear stiffening beams (10) are arranged between the middle ring frame (2) and the rear ring frame (3), one end of each rear stiffening beam is connected with the middle ring frame (2), and the other end of each rear stiffening beam is connected with the rear ring frame (3) and the grid wallboard (5);
and one end of each supporting beam (14) is connected with the front ring frame (1), and the other end of each supporting beam is correspondingly connected with one front stiffening beam (9).
2. The unmanned aerial vehicle fuselage section of claim 1 wherein,
further comprises:
the two front stringers (7) are arranged between the front ring frame (1) and the middle ring frame (2), 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 one side edge of the honeycomb bottom plate (4) and is connected with the edge of the corresponding side of the honeycomb skin (6);
the two rear stringers (8) are arranged between the middle ring frame (2) and the rear ring frame (3), one end of each rear stringer is connected with the middle ring frame (2), and the other end of each rear stringer is connected with the rear ring frame (3); each rear stringer (8) is connected to an edge of one side of the grid panel (5) and to an edge of the corresponding side of the honeycomb skin (6).
3. The unmanned aerial vehicle fuselage section of claim 2, wherein,
the cross section of each front stringer (7) and each rear stringer (8) is L-shaped.
4. The unmanned aerial vehicle fuselage section of claim 1 wherein,
the honeycomb bottom plate (4) is provided with a landing gear retraction opening;
the unmanned aerial vehicle fuselage section further includes:
a landing gear cabin door (11) which is arranged at the landing gear retraction opening and can be opened and closed;
a landing gear front joint (12) connected with the front ring frame (1);
and the landing gear rear joint (13) is connected with the middle ring frame (2).
5. The unmanned aerial vehicle fuselage section of claim 4, wherein,
the landing gear front joint (12) and the landing gear rear joint (13) are made of aluminum alloy materials.
6. The unmanned aerial vehicle fuselage section of claim 4, wherein,
each landing gear rear joint (13) is correspondingly connected with one end of one front reinforcement beam (9) facing the middle ring frame (2).
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 |
|---|---|---|---|
| CN202011388878.9A CN112478126B (en) | 2020-12-02 | 2020-12-02 | Unmanned aerial vehicle fuselage cabin section |
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| CN112478126A CN112478126A (en) | 2021-03-12 |
| CN112478126B true CN112478126B (en) | 2024-01-02 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106507751B (en) * | 2007-11-03 | 2011-11-23 | 成都飞机工业（集团）有限责任公司 | SUAV fuselage |
| 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 |
| CN107891965A (en) * | 2017-10-08 | 2018-04-10 | 成都飞机工业（集团）有限责任公司 | A kind of unmanned plane nose-gear bay section based on catapult-assisted take-off |
| CN108109507A (en) * | 2018-01-29 | 2018-06-01 | 天津中德应用技术大学 | Undercarriage folding and unfolding process demonstrator |
| KR101878681B1 (en) * | 2017-07-28 | 2018-08-16 | 주식회사 샘코 | Battery pack structure for unmanned aerial vehicle |
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| FR2893588B1 (en) * | 2005-11-21 | 2008-02-01 | Airbus France Sas | TRAIN BOX WITH HOUSING STRUCTURE |
| EP2889212B1 (en) * | 2013-12-30 | 2016-01-06 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Subfloor structure with an integral hull for a rotary wing aircraft |
| US10793285B2 (en) * | 2018-02-13 | 2020-10-06 | Bell Helicopter Textron Inc. | Fuselage embedded fuel tank |
| FR3089946B1 (en) * | 2018-12-18 | 2021-01-08 | Airbus Operations Sas | structure of a FUSELAGE OF AN aircraft presenting a panel reinforced by a trellis |
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|---|---|---|---|---|
| CN106507751B (en) * | 2007-11-03 | 2011-11-23 | 成都飞机工业（集团）有限责任公司 | SUAV fuselage |
| KR101878681B1 (en) * | 2017-07-28 | 2018-08-16 | 주식회사 샘코 | Battery pack structure for unmanned aerial vehicle |
| CN107891965A (en) * | 2017-10-08 | 2018-04-10 | 成都飞机工业（集团）有限责任公司 | A kind of unmanned plane nose-gear bay section based on catapult-assisted take-off |
| 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 |
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