CN112078777A - Fuselage skeleton structure, fuselage and aircraft - Google Patents
Fuselage skeleton structure, fuselage and aircraft Download PDFInfo
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- CN112078777A CN112078777A CN201910508553.0A CN201910508553A CN112078777A CN 112078777 A CN112078777 A CN 112078777A CN 201910508553 A CN201910508553 A CN 201910508553A CN 112078777 A CN112078777 A CN 112078777A
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- 238000005192 partition Methods 0.000 claims description 18
- 230000004308 accommodation Effects 0.000 claims description 4
- 238000012545 processing Methods 0.000 description 7
- 125000006850 spacer group Chemical group 0.000 description 5
- 238000010276 construction Methods 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000012271 agricultural production Methods 0.000 description 1
- 238000013473 artificial intelligence Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009776 industrial production Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000010899 nucleation Methods 0.000 description 1
- 239000000575 pesticide Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 239000002023 wood Substances 0.000 description 1
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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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Abstract
The present disclosure provides a fuselage skeleton structure, including: a plurality of annular support members (210), the plurality of annular support members (210) being arranged in sequence along a length direction of a fuselage for forming an outline of the fuselage; and a connection member (220), the connection member (220) sequentially passing through the plurality of ring-shaped support members (210) and being connected to the plurality of ring-shaped support members (210). Another aspect of the disclosure also provides a fuselage and an aircraft.
Description
Technical Field
The present disclosure relates to the field of warehouse logistics, and more particularly, to a fuselage skeleton structure, a fuselage, and an aircraft.
Background
With the rapid development of artificial intelligence, automatic control, communication and computer technologies, aircraft are increasingly used in many fields such as industrial and agricultural production, building, logistics, and daily life.
In the course of implementing the disclosed concept, the inventors found that there are at least the following problems in the prior art: the existing fuselage skeleton structure is complex, so that the weight of the fuselage is large, and the processing steps are complicated.
Disclosure of Invention
In view of the above, the present disclosure provides a fuselage skeleton structure, a fuselage and an aircraft.
One aspect of the present disclosure provides a fuselage skeleton structure, comprising: the annular support components are sequentially arranged along the length direction of the machine body and are used for forming the outline of the machine body; and a connection member sequentially passing through the plurality of annular support members and connected to the plurality of annular support members.
According to an embodiment of the present disclosure, the connection member is snap-fitted with the plurality of annular support members.
According to an embodiment of the present disclosure, the connection member includes: at least one connecting plate, each connecting plate sequentially penetrates through the plurality of annular supporting parts to be connected with the plurality of annular supporting parts; and a bottom plate positioned above each of the connection plates and connected to a portion of the ring-shaped support members arranged in series.
According to the embodiment of the disclosure, the connecting plate is clamped with the plurality of annular supporting components, and the bottom plate is clamped with the at least one annular supporting component.
According to an embodiment of the present disclosure, each annular support member comprises at least one snap groove into which the connection plate is snapped.
According to an embodiment of the present disclosure, the base plate includes at least one slot, and the ring support member includes a boss that is fitted into the slot.
According to the embodiment of the disclosure, the fuselage skeleton further comprises a partition plate connected with the connecting part and forming an accommodating space with the connecting part for accommodating the avionic device.
According to an embodiment of the present disclosure, a part of the plurality of annular support members arranged in series is an arc support member having an opening above, the arc support member including a first end and a second end, the airframe skeleton structure further includes: and the annular plate is sequentially connected with the first ends and the second ends of the plurality of arc supporting parts.
According to the embodiment of the disclosure, the annular plate is clamped with the first end and the second end of the plurality of arc supporting parts in sequence.
Another aspect of the present disclosure provides a fuselage comprising a housing; and the fuselage skeleton structure is positioned in the accommodating space formed by the shell and is connected with the shell.
Another aspect of the present disclosure provides an aircraft comprising: the fuselage comprises the fuselage skeleton structure; and the wing is connected with the fuselage.
According to the embodiment of the disclosure, the problems that the weight of the machine body is large and the processing steps are complicated can be at least partially solved, and therefore the technical effects of simplifying the framework structure of the machine body, reducing the weight of the machine body and being easy to process can be achieved.
Drawings
The above and other objects, features and advantages of the present disclosure will become more apparent from the following description of embodiments of the present disclosure with reference to the accompanying drawings, in which:
fig. 1 schematically illustrates an application scenario of a fuselage skeleton structure according to an embodiment of the present disclosure;
FIG. 2A schematically illustrates a structural schematic of a fuselage skeleton according to an embodiment of the disclosure;
FIG. 2B schematically illustrates a structural schematic of a fuselage skeleton according to another embodiment of the present disclosure;
fig. 3 schematically illustrates a bottom structural view of a fuselage skeleton according to an embodiment of the disclosure;
FIG. 4 schematically illustrates a top view of a fuselage skeleton according to an embodiment of the disclosure; and
fig. 5 schematically illustrates a bottom view of a fuselage skeleton according to an embodiment of the disclosure.
Detailed Description
Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. It should be understood that the description is illustrative only and is not intended to limit the scope of the present disclosure. In the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the disclosure. It may be evident, however, that one or more embodiments may be practiced without these specific details. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present disclosure.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. The terms "comprises," "comprising," and the like, as used herein, specify the presence of stated features, steps, operations, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, or components.
All terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art unless otherwise defined. It is noted that the terms used herein should be interpreted as having a meaning that is consistent with the context of this specification and should not be interpreted in an idealized or overly formal sense.
Where a convention analogous to "at least one of A, B and C, etc." is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., "a system having at least one of A, B and C" would include but not be limited to systems that have a alone, B alone, C alone, a and B together, a and C together, B and C together, and/or A, B, C together, etc.). Where a convention analogous to "A, B or at least one of C, etc." is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., "a system having at least one of A, B or C" would include but not be limited to systems that have a alone, B alone, C alone, a and B together, a and C together, B and C together, and/or A, B, C together, etc.).
The embodiment of the present disclosure provides a fuselage skeleton structure, which is characterized by including: the annular support components are sequentially arranged along the length direction of the machine body and are used for forming the outline of the machine body; and a connection member sequentially passing through the plurality of annular support members and connected to the plurality of annular support members.
Fig. 1 schematically illustrates an exemplary application scenario of a fuselage skeleton structure according to an embodiment of the present disclosure. It should be noted that fig. 1 is only an example of an application scenario in which the embodiments of the present disclosure may be applied to help those skilled in the art understand the technical content of the present disclosure, but does not mean that the embodiments of the present disclosure may not be applied to other devices, systems, environments or scenarios.
As shown in fig. 1, the fuselage skeleton structure may be applied to a drone 100, for example. The drone 100 is capable of flying, hovering in the air to perform specific tasks, such as flying, tracking, monitoring, delivering, exploring, searching for, seeding, spraying pesticides, extinguishing fires, taking photographs, etc. The drone 100 may carry predetermined functional modules, such as sensors, photographing devices, warehouses, and the like, to implement specific functions.
According to this disclosed embodiment's fuselage skeleton texture can be applied to unmanned aerial vehicle 100 for unmanned aerial vehicle 100's skeleton texture is simpler on firm basis. The fuselage skeleton according to an embodiment of the present disclosure includes: the annular support components are sequentially arranged along the length direction of the machine body and are used for forming the outline of the machine body; and a connection member sequentially passing through the plurality of annular support members and connected to the plurality of annular support members. The fuselage skeleton structure is simple, the self weight of the aircraft is reduced, the processing steps are simple, and the processing cost is low.
The fuselage skeleton structure according to embodiments of the present disclosure is described below with reference to fig. 2A, 2B, and 3-5.
Fig. 2A schematically illustrates a schematic view of a fuselage skeleton 200 according to an embodiment of the disclosure.
As shown in fig. 2A, the airframe 200 includes a plurality of annular support members 210 and connecting members 220.
A plurality of annular support members 210 are sequentially arranged along the length of the body to form the contour of the body. The connection member 220 sequentially passes through the plurality of ring-shaped support members 210 and is connected to the plurality of ring-shaped support members 210.
According to the embodiment of the present disclosure, the fuselage skeleton structure 200 forms a fuselage outline by a plurality of annular support members 210, and the connection member 220 connects the plurality of annular support members 210, thereby achieving a simplified fuselage skeleton structure, reduced weight of the fuselage, and ease of processing.
According to the embodiment of the present disclosure, the plurality of annular support members 210 may be arranged at equal intervals, or may be arranged at unequal intervals, for example.
According to an embodiment of the present disclosure, the central axes of the plurality of annular support members 210 may be located on the same line, for example.
According to embodiments of the present disclosure, for example, the spacing between the annular support members 210 at locations of greater fuselage weight bearing may be less than the spacing between the annular support members 210 at locations of lesser weight bearing. According to the embodiment of the disclosure, the layout of the plurality of annular supporting parts 210 in the fuselage skeleton structure is more reasonable, more annular supporting parts 210 are arranged at positions with larger bearing capacity so as to increase the stability of the fuselage, and less annular supporting parts 210 are arranged at positions with smaller bearing capacity so as to save the processing cost and reduce the processing steps.
According to embodiments of the present disclosure, the plurality of annular support members 210 may be sized to match the receiving space formed by the fuselage contours, for example. According to an embodiment of the present disclosure, the accommodation space of the fuselage nose and the fuselage tail may be smaller than the accommodation space of the fuselage middle, for example, and accordingly, the diameter of the fuselage nose and the fuselage tail annular support member 210 may be smaller than the diameter of the fuselage middle annular support member 210.
According to an embodiment of the present disclosure, the number of the ring-shaped support members 210 may be set according to the length of the fuselage, for example.
According to an embodiment of the present disclosure, the connection member 220 may be connected with the plurality of annular support members 210 by a locking member, for example. Or the connection member 220 is welded to the plurality of ring-shaped support members 210.
According to other embodiments of the present disclosure, the connection part 220 may sequentially pass through the plurality of ring-shaped support parts 210 and be clamped with the plurality of ring-shaped support parts 210, respectively.
According to the embodiment of the disclosure, the connecting part 220 is clamped with the plurality of annular supporting parts 210, so that the connecting part 220 and the annular supporting parts 220 are easy to mount and dismount, and the flexibility of adaptability adjustment of the fuselage skeleton is improved.
Fig. 2B schematically illustrates a schematic view of a fuselage skeleton 200 according to another embodiment of the present disclosure.
Fig. 3 schematically illustrates a schematic view of a connection part 220 according to an embodiment of the present disclosure. Fig. 4 schematically illustrates a bottom view of the fuselage skeleton 200 according to an embodiment of the disclosure.
As shown in fig. 2B, 3 and 4, the connection member 220 may include at least one connection plate 221 and a bottom plate 222. Wherein each connection plate 221 sequentially passes through the plurality of annular support members 210 and is connected to the plurality of annular support members 210; and a bottom plate positioned above each connection plate 221 and connected to the partially annular support members 210 arranged in series.
According to the embodiment of the present disclosure, the at least one connection plate 221 can increase the supporting strength of the airframe.
According to an embodiment of the present disclosure, the connection plate 221 may, for example, extend through the entire fuselage, the bottom plate 222 may, for example, extend through the fuselage nose and mid-fuselage, and the fuselage tail may, for example, be provided without a bottom plate.
According to an embodiment of the present disclosure, the at least one connection plate 221 may be connected with a plurality of annular support plates, for example, in parallel with each other.
According to an embodiment of the present disclosure, the at least one connection plate 221 may be arranged at equal intervals, for example, or may be arranged at unequal intervals.
According to an embodiment of the present disclosure, the connection plate 221 may be, for example, snapped with the plurality of annular support members 210.
According to the embodiment of the present disclosure, the connection plate 221 is clamped with the plurality of ring-shaped support members 210, for example, at least one clamping slot is included on the ring-shaped support member 210, and the plurality of connection plates 221 are clamped into the corresponding clamping slots.
As shown in fig. 3, the airframe frame 200 may include, for example, 3 connecting plates 221, each annular support member 210 includes 3 slots, and each connecting plate 221 is respectively clipped into the slots of the plurality of annular support members 210, such that each connecting plate 221 respectively penetrates through the plurality of annular support members 210.
According to the embodiment of the present disclosure, the connection plate 221 is clamped with the plurality of ring-shaped support members 210, for example, the position where the connection plate 221 contacts with the ring-shaped support members 210 includes a clamping groove, and correspondingly, the position where the ring-shaped support members 210 contact with the connection plate 221 includes a clamping groove, and the clamping groove of the connection plate 221 is clamped into the clamping groove of the ring-shaped support members 210.
According to an embodiment of the present disclosure, in this embodiment, the height of the connection plate 221 may be, for example, not greater than the depth of the clamping groove of the ring-shaped support member 210, so that the portion of the connection plate 221 clamped into the clamping groove can be completely clamped, thereby enabling the bottom plate 222 to be in contact with the ring-shaped support member 210 and connected with the ring-shaped support member 210.
The base plate 222 and the ring support member 210 may, for example, be snap fit according to embodiments of the present disclosure. As shown in fig. 2B, for example, a plurality of slots 2221 may be disposed on the bottom plate 222, and a boss is disposed on the ring-shaped support component 210, and the boss is inserted into the slot 2221, so as to achieve the clamping connection between the bottom plate 222 and the ring-shaped support component 210.
According to other embodiments of the present disclosure, the bottom plate 222 may be, for example, snapped with the connection plate 221. For example, the connection board 221 includes a boss, the bottom board 222 includes a slot matching with the boss on the connection board 221, and the boss on the connection board 221 is inserted into the slot on the bottom board 222 to realize the clamping connection between the bottom board 222 and the connection board 221.
According to an embodiment of the present disclosure, as shown in fig. 2B, the body frame 200 may further include, for example, a partition 230 connected to the connection member 220 and forming an accommodation space with the connection member 220 for accommodating the avionics device.
According to the embodiment of the disclosure, the partition plate 230 can isolate the avionics device from other devices which influence the operation of the avionics device, and the operation of the avionics device is prevented from being influenced.
According to the embodiment of the present disclosure, the partition 230 may be disposed, for example, at a position where the weight of the fuselage is large, for example, at a position where the distance from the head of the fuselage is one third of the length of the fuselage. According to the embodiment of the present disclosure, the partition plate 230 is disposed at a position where the load bearing of the fuselage is large, so that the partition plate 230 not only can play a role in isolation, but also can increase the load bearing of the fuselage, and further improve the stability of the fuselage.
According to an embodiment of the present disclosure, the spacer 230 may be connected with the ring-shaped support member 210, and/or may be connected with the connection member 220, for example.
According to embodiments of the present disclosure, the partition 230 may be welded, snapped, or otherwise attached to the annular support member 210, for example.
According to the embodiment of the present disclosure, the partition 230 is clamped with the annular support component 210, for example, a position of one annular support component 210 connected with the partition 230 for forming the side wall of the body may include a clamping groove, and two ends of the partition 230 are respectively clamped into the clamping grooves.
According to other embodiments of the present disclosure, the partition 230 is connected to the connection member 220, for example, the partition 230 is clamped to the connection plate 221 and the bottom plate 222. For example, the backplane 222 may include backplane card slots, the spacer 230 may include spacer card slots, and the spacer 230 may be inserted through the backplane card slots such that the connection boards 221 are snapped into the spacer card slots.
According to other embodiments of the present disclosure, the partition 230 is connected to the connecting member 220, for example, the partition 230 is welded to the bottom plate 222, or the partition 230 is connected to the bottom plate 222 via a locking member, etc.
According to an embodiment of the present disclosure, some of the plurality of annular support members 210 arranged in series are arc support members including a first end and a second end, the airframe skeleton structure further includes: and the annular plate 240 is sequentially connected with the first end and the second end of the circular arc supporting parts.
The connection of the annular plate 240 to the annular support member 210 is described below with reference to fig. 2B and 5.
Fig. 5 schematically illustrates a top view of a fuselage skeleton according to an embodiment of the disclosure.
As shown in fig. 2B and 5, the plurality of serially arranged annular support members 210 includes a first end and a second end, and the annular plate 240 is sequentially connected to the first end and the second end of the plurality of serially arranged annular support members 210 to form a nacelle opening.
According to an embodiment of the present disclosure, the annular plate 240 is sequentially engaged with the first and second ends of the plurality of arc support members. For example, the annular plate 240 may include a plurality of slots into which the first and second ends of the arc support members are respectively snapped.
According to the embodiment of the disclosure, the cabin opening of the aircraft is formed by connecting the annular plate 240 with the first end and the second end of the annular support part 210, and the structure is simple and easy to realize.
According to an embodiment of the present disclosure, as shown in fig. 2B and 5, the airframe 200 may further include at least one first connecting rod 250 for connecting the annular plate 240 with the partial annular support plate 210 located at a first side of the annular plate, wherein the first side is a side near an aft portion of the airframe. According to an embodiment of the present disclosure, the fuselage skeleton 200 may include, for example, two first connecting rods 250 respectively distributed on both sides of the fuselage.
According to the embodiment of the disclosure, the structure can increase the bearing capacity of the tail part of the fuselage, so that the fuselage skeleton is firmer.
According to an embodiment of the present disclosure, the first connecting rod 250 may be, for example, snapped with the ring plate 240 and the ring support member 210, respectively. For example, the end of the annular plate 240 close to the tail of the fuselage may include a slot, the side wall of the annular support component 210 includes a slot, and the first connecting rod 250 is respectively clamped into the slot of the annular plate 240 close to the tail of the fuselage and the slot of the side wall of the annular support component 210.
According to an embodiment of the present disclosure, as shown in fig. 2B, the plurality of annular support members 210 includes at least one middle annular support member, and the airframe structure 200 further includes at least one second connecting rod 260, the second connecting rod 260 being for connecting the at least one middle annular support member. According to an embodiment of the present disclosure, the second connecting rod 260 may be, for example, a rod connecting the top portions of the plurality of middle ring-shaped supporting members, thereby enhancing the stability of the top portion of the fuselage skeleton.
According to an embodiment of the present disclosure, the second connecting rod 260 may be, for example, snapped, welded, or connected by a locking member with the middle annular support.
According to the embodiment of the present disclosure, the second connecting rod 260 is clamped with the middle annular support portion, for example, the top of the middle annular support portion includes a clamping groove, and the second connecting rod 260 is clamped into the clamping groove of the top.
According to an embodiment of the present disclosure, the fuselage skeleton 200 may further include a third connecting rod 270, the third connecting rod 270 being used to connect the annular support component 210 at the head of the fuselage with the support 280 of the head of the fuselage for enhancing the stability of the head of the fuselage.
According to embodiments of the present disclosure, the third connecting rod 270 may be snapped, welded, or connected by a retaining member with the annular support member 210, for example.
According to the embodiment of the present disclosure, the third connecting rod 270 is clamped with the annular supporting component 210, for example, the top of the annular supporting component 210 includes a clamping groove, and the third connecting rod 270 is clamped into the clamping groove on the top.
According to the embodiment of the present disclosure, the plurality of ring-shaped support members 210 and the connection members 220 of the body frame 200 may be made of, for example, wood, or may be made of steel or the like.
Another aspect of the present disclosure provides a fuselage comprising: a housing; and the fuselage skeleton structure is positioned in the accommodating space formed by the shell and is connected with the shell. Wherein, fuselage skeleton texture includes: the annular support components are sequentially arranged along the length direction of the machine body and are used for forming the outline of the machine body; and a connection member sequentially passing through the plurality of annular support members and connected to the plurality of annular support members.
According to an embodiment of the present disclosure, the connection member is snap-fitted with the plurality of annular support members.
According to an embodiment of the present disclosure, the connection member includes: at least one connecting plate, each connecting plate passing through the plurality of annular support members in sequence and a first side of each connecting plate being connected to the plurality of annular support members; and a bottom plate disposed at a second side of each of the connection plates and connected with a portion of the ring-shaped support member.
According to the embodiment of the disclosure, the connecting plate is clamped with the plurality of annular supporting components, and the bottom plate is clamped with the at least one annular supporting component.
According to an embodiment of the present disclosure, each annular support member comprises at least one snap groove into which the connection plate is snapped.
According to an embodiment of the present disclosure, the bottom plate includes at least one slot, and the connection plate includes a boss that is fitted with the slot, the boss being inserted into the slot.
According to the embodiment of the disclosure, the fuselage skeleton further comprises a partition board connected with the connecting component to form an accommodating space for accommodating avionic equipment.
According to an embodiment of the present disclosure, some of the plurality of annular support members arranged in series are circular arc support members, the circular arc support members include a first end and a second end, the airframe skeleton structure further includes: and the annular plate is sequentially connected with the first ends and the second ends of the plurality of arc supporting parts.
According to the embodiment of the disclosure, the annular plate is clamped with the first end and the second end of the plurality of arc supporting parts in sequence.
Another aspect of the present disclosure provides an aircraft comprising: the fuselage comprises the fuselage skeleton structure; and the wings are connected with the fuselage main body.
According to embodiments of the present disclosure, a fuselage skeleton structure on an aircraft may include a plurality of annular support members arranged in sequence along a length of a fuselage for forming a contour of the fuselage; and a connection member sequentially passing through the plurality of annular support members and connected to the plurality of annular support members.
According to an embodiment of the present disclosure, the connection member is snap-fitted with the plurality of annular support members.
According to an embodiment of the present disclosure, the connection member includes: at least one connecting plate, each connecting plate passing through the plurality of annular support members in sequence and a first side of each connecting plate being connected to the plurality of annular support members; and a bottom plate disposed at a second side of each of the connection plates and connected with a portion of the ring-shaped support member.
According to the embodiment of the disclosure, the connecting plate is clamped with the plurality of annular supporting components, and the bottom plate is clamped with the at least one annular supporting component.
According to an embodiment of the present disclosure, each annular support member comprises at least one snap groove into which the connection plate is snapped.
According to an embodiment of the present disclosure, the bottom plate includes at least one slot, and the connection plate includes a boss that is fitted with the slot, the boss being inserted into the slot.
According to the embodiment of the disclosure, the fuselage skeleton further comprises a partition board connected with the connecting component to form an accommodating space for accommodating avionic equipment.
According to an embodiment of the present disclosure, some of the plurality of annular support members arranged in series are circular arc support members, the circular arc support members include a first end and a second end, the airframe skeleton structure further includes: and the annular plate is sequentially connected with the first ends and the second ends of the plurality of arc supporting parts.
According to the embodiment of the disclosure, the annular plate is clamped with the first end and the second end of the plurality of arc supporting parts in sequence.
Those skilled in the art will appreciate that various combinations and/or combinations of features recited in the various embodiments and/or claims of the present disclosure can be made, even if such combinations or combinations are not expressly recited in the present disclosure. In particular, various combinations and/or combinations of the features recited in the various embodiments and/or claims of the present disclosure may be made without departing from the spirit or teaching of the present disclosure. All such combinations and/or associations are within the scope of the present disclosure.
The embodiments of the present disclosure have been described above. However, these examples are for illustrative purposes only and are not intended to limit the scope of the present disclosure. Although the embodiments are described separately above, this does not mean that the measures in the embodiments cannot be used in advantageous combination. The scope of the disclosure is defined by the appended claims and equivalents thereof. Various alternatives and modifications can be devised by those skilled in the art without departing from the scope of the present disclosure, and such alternatives and modifications are intended to be within the scope of the present disclosure.
Claims (11)
1. An airframe frame structure, comprising:
a plurality of annular support members (210), the plurality of annular support members (210) being arranged in sequence along a length direction of a fuselage for forming an outline of the fuselage; and
a connection member (220), the connection member (220) sequentially passing through the plurality of ring-shaped support members (210) and being connected to the plurality of ring-shaped support members (210).
2. The airframe frame structure as defined in claim 1, wherein said attachment member (220) is snap-fit to said plurality of ring-shaped support members (210).
3. The airframe frame structure as recited in claim 1, wherein said connecting member (220) comprises:
at least one connecting plate (221), each connecting plate (221) sequentially penetrates through the plurality of annular support members (210) and is connected with the plurality of annular support members (210); and
a bottom plate (222) located above each of the connection plates (221) and connected to a portion of the ring-shaped support members (210) arranged in series.
4. The airframe frame structure as defined in claim 3, wherein said connecting plate (221) is snap-fitted to said plurality of ring-shaped support members (210), and said bottom plate (222) is snap-fitted to said at least one ring-shaped support member (210).
5. The airframe skeleton structure of claim 4, wherein each annular support member (210) includes at least one slot into which the connecting plate (221) snaps.
6. The airframe skeleton structure as recited in claim 4, wherein said base plate (222) includes at least one slot (2221), and said annular support member (210) includes a projection that mates with said slot (2221), said projection (2221) being inserted into said slot (2221).
7. The airframe frame structure as defined in claim 1, further comprising:
and the partition plate (230) is connected with the connecting part (220) and forms an accommodating space with the connecting part (220) for accommodating avionic equipment.
8. The airframe frame structure as defined in claim 7, wherein some of the plurality of ring-shaped support members (210) arranged in series are arc support members having openings formed therein, the arc support members including first and second ends, the airframe frame structure further comprising:
an annular plate (240), the annular plate (240) being connected to the first and second ends of the plurality of arc support members in sequence.
9. The airframe frame structure as defined in claim 8, wherein said annular plate (240) is clamped to a plurality of said arcuate support members at first and second ends thereof in sequence.
10. A fuselage, comprising:
a housing; and
the fuselage skeleton structure of any one of claims 1 to 9, which is located in an accommodation space formed by the housing and connected to the housing.
11. An aircraft, comprising:
the fuselage of claim 10; and
the wing is connected with the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201910508553.0A CN112078777A (en) | 2019-06-12 | 2019-06-12 | Fuselage skeleton structure, fuselage and aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910508553.0A CN112078777A (en) | 2019-06-12 | 2019-06-12 | Fuselage skeleton structure, fuselage and aircraft |
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2019
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| CN101421154A (en) * | 2006-04-10 | 2009-04-29 | 空中客车德国有限公司 | Aircraft door with oversizing |
| CN101472794A (en) * | 2006-06-28 | 2009-07-01 | 空中客车德国有限公司 | Assembling principle for aerial vehicle airframe |
| CN102427997A (en) * | 2009-04-16 | 2012-04-25 | Facc股份公司 | Frame and method for producing such a frame |
| EP3031711A1 (en) * | 2014-12-10 | 2016-06-15 | The Boeing Company | Aircraft frame for tailstrike angle enhancement |
| CN104608915A (en) * | 2015-01-30 | 2015-05-13 | 中国人民解放军国防科学技术大学 | Multilayer grating bearing cylinder and preparation method thereof |
| CN207120868U (en) * | 2017-07-20 | 2018-03-20 | 北京理工大学珠海学院 | The fuselage and unmanned vehicle of unmanned vehicle |
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