CN215794400U - Framework type airplane body structure - Google Patents
Framework type airplane body structure Download PDFInfo
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- CN215794400U CN215794400U CN202121890629.XU CN202121890629U CN215794400U CN 215794400 U CN215794400 U CN 215794400U CN 202121890629 U CN202121890629 U CN 202121890629U CN 215794400 U CN215794400 U CN 215794400U
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Abstract
The application provides a framework aircraft fuselage structure, framework aircraft fuselage structure includes fuselage 1, fuselage frame 3, fuselage door 4 and rotatory bolt mechanism 6, front end fuselage 5 is installed to the outside one end of fuselage 1, the inner wall of fuselage 1 sets up the multiunit fuselage frame 3, the top installation of fuselage 1 fuselage door 4, the outside of fuselage 1 is provided with covering 2, the outside of front end fuselage 5 sets up the multiunit rotatory bolt mechanism 6, keep away from in the outside of fuselage 1 the other end of front end fuselage 5 is provided with rear end fuselage 18.
Description
Technical Field
The utility model relates to the technical field of aircrafts, in particular to a framework type airplane fuselage structure.
Background
In the manufacturing process of the aircraft parts, because the types of the aircraft parts are more, the structure is complex, the manufacturing period is long, a large number of various tool equipment are needed to realize the positioning function of the aircraft parts, and the accuracy and precision of the aircraft parts in the machining process are ensured.
The positioning device for machining the aircraft parts in the prior art can only machine and position one specification of one part mostly, and the part can be damaged due to the fact that the clamp for machining the part is fixed to a dead plate, and the problems that the part is not machined completely, errors occur in the machining process and the like can be solved.
Disclosure of Invention
The utility model overcomes the defects in the prior art and provides a framework type airplane fuselage structure.
For realizing above-mentioned purpose, this application provides a framework aircraft fuselage structure, framework aircraft fuselage structure includes fuselage 1, fuselage frame 3, fuselage door 4 and rotatory bolt mechanism 6, front end fuselage 5 is installed to the outside one end of fuselage 1, the inner wall of fuselage 1 sets up the multiunit fuselage frame 3, the top installation of fuselage 1 fuselage door 4, the outside of fuselage 1 is provided with covering 2, the outside of front end fuselage 5 sets up the multiunit rotatory bolt mechanism 6, keep away from in the outside of fuselage 1 the other end of front end fuselage 5 is provided with rear end fuselage 18.
Specifically, fuselage door 4 includes folding mechanism 10, folding ladder mounting panel 11, first ladder frame 14 and second ladder frame 15, folding mechanism 10 is installed the inside of fuselage door 4, folding mechanism 10's bottom is connected folding ladder mounting panel 11, hydraulic stem installation base 13 is installed in folding ladder mounting panel 11's the outside, hydraulic stem installation base 13's top is connected with hydraulic stem 12, hydraulic stem 12 keeps away from hydraulic stem installation base 13's the other end is connected folding mechanism 10.
Specifically, the outer surface of the folding ladder mounting plate 11 is provided with the first ladder frame 14, the bottom end of the first ladder frame 14 is connected with the second ladder frame 15, and a plurality of groups of ladder frame connecting pieces 16 are mounted on the outer sides of the first ladder frame 14 and the second ladder frame 15.
Specifically, a plurality of groups of bolt holes 7 are formed in the rotary bolt mechanism 6, a plurality of groups of bolt heads 17 are arranged on the outer side of the rear end machine body 18, and the bolt heads 17 are connected with the bolt holes 7.
Specifically, the inner wall of the front end machine body 5 is provided with an internal thread 8, and the internal thread 8 is connected with the inner ring of the rear end machine body 18.
Specifically, the outer sides of the machine body 1, the front end machine body 5 and the rear end machine body 18 are all provided with a plurality of groups of machine body mounting holes 9.
Specifically, the folding mechanism 10 is made of aluminum alloy.
Compared with the prior art, the utility model has the beneficial effects that:
1. the integral machine body is divided into the non-airtight detachable front end machine body and the rear end machine body, a plurality of groups of rotary bolt mechanisms are arranged on the outer side of the rear end machine body, a plurality of corresponding groups of bolt heads are arranged on the outer side of the front end machine body, the bolt heads and the bolt holes are correspondingly arranged, and the connection is further strengthened through internal threads, so that the number of connected pieces is reduced compared with the existing machine body mechanism, the machine body butt joint process risk is reduced through butt joint of the non-airtight machine bodies, and the connection reliability is high;
2. according to the utility model, the folding mechanism is arranged at the top of the airplane body, when the airplane body has problems and needs to be maintained, a traditional maintenance worker needs to put up a vehicle for maintenance on the outer side of the airplane for maintenance, and the maintenance worker can enter the top of the airplane body for maintenance through the installed ladder frame by opening the folding mechanism and the airplane body door on the inner wall of the airplane body, so that the airplane body can be maintained at the highest speed, and the space is saved and the escape is facilitated by designing the ladder frame into the folding mechanism.
Drawings
The utility model comprises 3 figures, which are described as follows:
FIG. 1 is a perspective view of a front end fuselage of the present invention;
FIG. 2 is a block diagram of the folding mechanism of the present invention;
fig. 3 is a structural view of the rear end body of the present invention.
In the figure: 1-fuselage, 2-skin, 3-fuselage frame, 4-fuselage door, 5-front-end fuselage, 6-rotary latch mechanism, 7-latch hole, 8-internal thread, 9-fuselage mounting hole, 10-folding mechanism, 11-folding ladder mounting plate, 12-hydraulic rod, 13-hydraulic rod mounting base, 14-first ladder frame, 15-second ladder frame, 16-ladder frame connecting piece, 17-latch head, 18-rear-end fuselage.
Detailed Description
Example one
The utility model aims to provide a framework type airplane body structure, which is characterized in that an integral body is divided into a non-airtight detachable front-end body and a rear-end body, a plurality of groups of rotary bolt mechanisms are arranged on the outer side of the rear-end body, a plurality of corresponding groups of bolt heads are arranged on the outer side of the front-end body, the bolt heads are correspondingly arranged with bolt holes, and the bolt heads are further connected in a reinforced manner through internal threads, so that compared with the existing body mechanism, the number of connected pieces is reduced, the risk of the body butt joint process is reduced through butt joint of the non-airtight body, the connection reliability is high, a folding mechanism is arranged on the top of the body, when the airplane body has problems and needs to be maintained, a traditional maintenance person needs to lap a vehicle for maintenance on the outer side of the airplane for maintenance, and the maintenance person can enter the top of the body through an installed ladder frame for maintenance by opening the folding mechanism and a body door on the inner wall of the body, the advantage of doing so can be so that the fuselage maintains at the fastest speed, design into folding mechanism through the ladder frame in addition, also conveniently flee when saving space, all adopt the segmentation design with the aircraft fuselage among the prior art who proposes in solving above-mentioned background art basically, and with each section fuselage butt joint become complete fuselage, the butt joint between two sections fuselages all adopts permanent connection, can't dismantle, can make the maintenance in later stage very troublesome problem when the fuselage goes wrong like this.
In order to achieve the purpose, the utility model provides the following technical scheme: the utility model provides a framework type aircraft fuselage structure, includes fuselage, fuselage frame, fuselage door and rotatory bolt mechanism, the front end fuselage is installed to the outside one end of fuselage, the inner wall of fuselage sets up the multiunit the fuselage frame, the top installation of fuselage the fuselage door, the outside of fuselage is provided with the covering, the outside of front end fuselage sets up the multiunit rotatory bolt mechanism, keep away from in the outside of fuselage the other end of front end fuselage is provided with the rear end fuselage.
Preferably, the fuselage door includes folding mechanism, folding ladder mounting panel, first ladder frame and second ladder frame, folding mechanism installs the inside of fuselage door, folding mechanism's bottom is connected the folding ladder mounting panel, hydraulic stem installation base is installed in the outside of folding ladder mounting panel, hydraulic stem installation base's top is connected with the hydraulic stem, the hydraulic stem is kept away from the other end of hydraulic stem installation base is connected folding mechanism.
Preferably, the outer surface of the folding ladder mounting plate is provided with the first ladder frame, the bottom end of the first ladder frame is connected with the second ladder frame, and a plurality of groups of ladder frame connecting pieces are arranged on the outer sides of the first ladder frame and the second ladder frame.
Preferably, a plurality of groups of bolt holes are formed in the rotary bolt mechanism, a plurality of groups of bolt heads are arranged on the outer side of the rear end machine body, and the bolt heads are connected with the bolt holes.
Preferably, the inner wall of the front end machine body is provided with internal threads, and the internal threads are connected with the inner ring of the rear end machine body.
Preferably, the outer sides of the machine body, the front end machine body and the rear end machine body are provided with a plurality of groups of machine body mounting holes.
Example two
The technical solution in the embodiment of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiment of the present invention:
the embodiment provided by the utility model comprises the following steps: the utility model provides a framework type aircraft fuselage structure, includes fuselage 1, fuselage frame 3, fuselage door 4 and rotatory bolt mechanism 6, and front end fuselage 5 is installed to the outside one end of fuselage 1, and the inner wall of fuselage 1 sets up multiunit fuselage frame 3, and fuselage door 4 is installed at the top of fuselage 1, and the outside of fuselage 1 is provided with covering 2, and the outside of front end fuselage 5 sets up multiunit rotatory bolt mechanism 6, and the other end that front end fuselage 5 was kept away from in the outside of fuselage 1 is provided with rear end fuselage 18.
Through dividing into non-airtight detachable front end fuselage 5 and rear end fuselage 18 with holistic fuselage, be provided with multiunit rotary latch mechanism 6 through the outside at rear end fuselage 18, set up corresponding multiunit bolt head 17 in the outside of front end fuselage 5, correspond the installation with bolt head 17 and bolt hole 7, reduced the number of connection pieces, connect the reliability height.
In this implementation, fuselage door 4 includes folding mechanism 10, folding ladder mounting panel 11, first ladder frame 14 and second ladder frame 15, and folding mechanism 10 installs in the inside of fuselage door 4, and folding ladder mounting panel 11 is connected to folding mechanism 10's bottom, and hydraulic stem installation base 13 is installed in folding ladder mounting panel 11's the outside, and hydraulic stem installation base 13's top is connected with hydraulic stem 12, and folding mechanism 10 is connected to the other end that hydraulic stem 12 kept away from hydraulic stem installation base 13.
The advantage of allowing maintenance personnel to access the top of the fuselage through the installed ladder by opening the folding mechanism 10 and the fuselage door 4 on the inside wall of the fuselage is that maintenance can be performed at the fastest possible speed.
In this embodiment, the outer surface of the folding ladder mounting plate 11 is provided with a first ladder frame 14, the bottom end of the first ladder frame 14 is connected with a second ladder frame 15, and a plurality of sets of ladder frame connecting pieces 16 are arranged on the outer sides of the first ladder frame 14 and the second ladder frame 15.
By designing the ladder frame as the folding mechanism 10, space is saved and escape is facilitated.
In this embodiment, a plurality of sets of pin holes 7 are formed in the rotary pin mechanism 6, a plurality of sets of pin heads 17 are formed on the outer side of the rear body 18, and the pin heads 17 are connected with the pin holes 7.
Through bolt head 17 and bolt hole 7 interconnect, for current fuselage mechanism, reduced the number of connecting pieces, through the non-airtight fuselage of butt joint, reduced fuselage butt joint technology risk, it is high to connect the reliability.
In this embodiment, the inner wall of the front end body 5 is provided with an internal thread 8, and the internal thread 8 is interconnected with the inner ring of the rear end body 18.
Through the further reinforced connection of internal thread 8, reduced fuselage butt joint technology risk, it is high to connect the reliability.
In the present embodiment, a plurality of sets of body mounting holes 9 are provided on the outer sides of the body 1, the front end body 5, and the rear end body 18.
The front-end machine body 5 and the rear-end machine body 18 can be connected and installed more firmly by arranging a plurality of groups of machine body mounting holes 9 on the outer sides of the machine body 1, the front-end machine body 5 and the rear-end machine body 18.
The working principle is as follows:
step 1: according to the utility model, the integral machine body is divided into the non-airtight detachable front-end machine body 5 and the rear-end machine body 18, a plurality of groups of rotary bolt mechanisms 6 are arranged on the outer side of the rear-end machine body 18, a plurality of corresponding groups of bolt heads 17 are arranged on the outer side of the front-end machine body 5, the bolt heads 17 and the bolt holes 7 are correspondingly arranged, and the connection is further strengthened through the internal threads 8, so that the number of the connected pieces is reduced compared with the existing machine body mechanism, the machine body butt joint process risk is reduced through butt joint of the non-airtight machine bodies, and the connection reliability is high;
step 2: according to the utility model, the folding mechanism 10 is arranged at the top of the airplane body, when the airplane body has problems and needs to be maintained, a traditional maintenance worker needs to put up a vehicle for maintenance on the outer side of the airplane for maintenance, and the maintenance worker can enter the top of the airplane body for maintenance through the installed ladder frame by opening the folding mechanism 10 and the airplane body door 4 on the inner wall of the airplane body, so that the airplane body can be maintained at the highest speed, and the folding mechanism 10 is designed through the ladder frame, so that the space is saved and the escape is facilitated.
The utility model discloses a framework type airplane fuselage structure, which relates to the technical field of aircrafts and comprises a fuselage, a fuselage frame, a fuselage door and a rotary bolt mechanism, wherein the integral fuselage is divided into a front-end fuselage and a rear-end fuselage which are non-airtight and detachable, a bolt head is correspondingly arranged with a bolt hole, the bolt is further connected in a reinforced way through internal threads, compared with the existing fuselage mechanism, the number of connected pieces is reduced, the connection reliability is high by butting the non-airtight fuselage, a folding mechanism is arranged at the top of the fuselage, when the airplane fuselage has problems and needs to be maintained, the traditional maintenance personnel need to put up a vehicle for maintenance on the outer side of the airplane for maintenance, the maintenance personnel can enter the top of the fuselage through an installed ladder frame for maintenance by opening the folding mechanism and the fuselage door on the inner wall of the fuselage, and the maintenance can be carried out at the highest speed, the space is saved and the escape is convenient.
Claims (7)
1. The utility model provides a framework aircraft fuselage structure, its characterized in that, framework aircraft fuselage structure includes fuselage (1), fuselage frame (3), fuselage door (4) and rotatory bolt mechanism (6), front end fuselage (5) are installed to the outside one end of fuselage (1), the inner wall of fuselage (1) sets up the multiunit fuselage frame (3), the top installation of fuselage (1) fuselage door (4), the outside of fuselage (1) is provided with covering (2), the outside of front end fuselage (5) sets up the multiunit rotatory bolt mechanism (6), keep away from in the outside of fuselage (1) the other end of front end fuselage (5) is provided with rear end fuselage (18).
2. A framed aircraft fuselage structure according to claim 1, wherein: fuselage door (4) are including folding mechanism (10), folding ladder mounting panel (11), first ladder frame (14) and second ladder frame (15), folding mechanism (10) are installed the inside of fuselage door (4), the bottom of folding mechanism (10) is connected folding ladder mounting panel (11), hydraulic stem installation base (13) are installed in the outside of folding ladder mounting panel (11), the top of hydraulic stem installation base (13) is connected with hydraulic stem (12), hydraulic stem (12) are kept away from the other end of hydraulic stem installation base (13) is connected folding mechanism (10).
3. A framed aircraft fuselage structure according to claim 2, wherein: the outer surface mounting of folding ladder mounting panel (11) first ladder frame (14), the bottom of first ladder frame (14) is connected second ladder frame (15), first ladder frame (14) with the outside installation multiunit ladder frame connection piece (16) of second ladder frame (15).
4. A framed aircraft fuselage structure according to claim 1, wherein: the novel multifunctional rotary bolt is characterized in that a plurality of groups of bolt holes (7) are formed in the rotary bolt mechanism (6), a plurality of groups of bolt heads (17) are arranged on the outer side of the rear end machine body (18), and the bolt heads (17) are connected with the bolt holes (7) mutually.
5. A framed aircraft fuselage structure according to claim 1, wherein: the inner wall of the front end machine body (5) is provided with internal threads (8), and the internal threads (8) are connected with the inner ring of the rear end machine body (18).
6. A framed aircraft fuselage structure according to claim 1, wherein: the outer sides of the machine body (1), the front end machine body (5) and the rear end machine body (18) are provided with a plurality of groups of machine body mounting holes (9).
7. A framed aircraft fuselage structure according to claim 1, wherein: the folding mechanism (10) is made of aluminum alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121890629.XU CN215794400U (en) | 2021-08-12 | 2021-08-12 | Framework type airplane body structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121890629.XU CN215794400U (en) | 2021-08-12 | 2021-08-12 | Framework type airplane body structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215794400U true CN215794400U (en) | 2022-02-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121890629.XU Active CN215794400U (en) | 2021-08-12 | 2021-08-12 | Framework type airplane body structure |
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|---|---|
| CN (1) | CN215794400U (en) |
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2021
- 2021-08-12 CN CN202121890629.XU patent/CN215794400U/en active Active
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