CN207120868U - The fuselage and unmanned vehicle of unmanned vehicle - Google Patents
The fuselage and unmanned vehicle of unmanned vehicle Download PDFInfo
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- CN207120868U CN207120868U CN201720887685.5U CN201720887685U CN207120868U CN 207120868 U CN207120868 U CN 207120868U CN 201720887685 U CN201720887685 U CN 201720887685U CN 207120868 U CN207120868 U CN 207120868U
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Abstract
The utility model provides a kind of fuselage and unmanned vehicle of unmanned vehicle, wherein, the fuselage of unmanned vehicle includes multiple bulkheads, stringer group, covering and the first fastener, multiple first necks are provided with the perisporium of each bulkhead, stringer group includes a plurality of stringer, bearing of trend of each stringer along itself is provided with multiple second necks, stringer is fastened on the first neck by the second neck, and bearing of trend arrangement of multiple bulkheads along stringer, a plurality of stringer is along the circumferentially distributed of bulkhead, covering is wrapped circumferentially around on a plurality of stringer along bulkhead, first fastener is fixedly connected between covering and stringer, or, first fastener is connected between bulkhead and covering.And the unmanned vehicle with the fuselage.The fuselage be respectively provided with unmanned vehicle it is simple in construction, it is easy to disassemble, assemble and be easy to maintenance the advantages of.
Description
Technical field
Unmanned vehicle technical field is the utility model is related to, is to be related to a kind of fuselage of unmanned vehicle specifically
And the unmanned vehicle with the fuselage.
Background technology
With the fast development of unmanned vehicle industry, unmanned vehicle is from initial maximization gradually to miniaturization, light
Quantify and portable etc. development.At present, the primary structure of small-sized unmanned vehicle includes following several types：
First, using EPP（Polypropylene plastics expanded material）Or EPO（Expanded polystyrene (EPS) polyethylene mixture）Deng foam
Material is made, and its advantage is：The unmanned vehicle being made of a foam material has good structural strength, and can reduce
The weight of unmanned vehicle.But have the drawback that：The connection of all parts of unmanned vehicle is mainly to be to be glued
It is main, cause when unmanned vehicle damages, it is difficult to which all parts are changed so that unmanned vehicle is repaired difficult
Or it can not repair.In addition, allowing to be repaired, the mechanical property of the breakage after reparation can not also return back to initial shape
State.
Second, made using Ba Sha cork woods plate or linden laminate, will Ba Sha cork woods plate or linden laminate cut into
Each parts of unmanned vehicle, these parts are attached by glue, it is assembled.Its advantage is：Unmanned flight
Device can have mellow and full curved surface so that unmanned vehicle can have an excellent aerodynamic quality, and with foamed material system
Into unmanned vehicle compare, unmanned vehicle has more preferable mechanical property made of Ba Sha cork woods plate or linden laminate.
But have the drawback that：Largely manually come to each, it is necessary to spend when all parts to unmanned vehicle are attached
Individual part is spliced, is bonded so that Production Time is grown.Further, since connection between all parts of unmanned vehicle with
Based on splicing, making it difficult to all parts are dismantled, when unmanned vehicle damages, easily cause a large amount of timber to break
Damage, it is difficult to changed to part, repair difficulty height.
3rd, made using glass fibre, its advantage is：The mechanical property of unmanned vehicle is good, disclosure satisfy that big
Load-carrying or high pneumatic requirement.But have the drawback that：Make it is expensive, and to unmanned vehicle occur it is damaged when, it is difficult to
Repair.
It can be seen that the structure of existing unmanned vehicle is present when unmanned vehicle damages, it is difficult to which nobody is flown
Row device is repaired, maintenance effect difference and maintenance cost height.
The content of the invention
In order to solve the above problems, main purpose of the present utility model is to provide a kind of simple in construction, easy to disassemble, assembling
And it is easy to the fuselage of the unmanned vehicle of maintenance.
Another object of the present utility model is to provide a kind of simple in construction, nothing that is easy to disassemble, assembling and be easy to maintenance
People's aircraft.
In order to realize main purpose of the present utility model, the utility model provides a kind of fuselage of unmanned vehicle, wherein,
Including multiple bulkheads, stringer group, covering and the first fastener, multiple first necks, purlin are provided with the perisporium of each bulkhead
Bar group includes a plurality of stringer, and bearing of trend of each stringer along itself is provided with multiple second necks, and stringer passes through the second card
Groove is fastened on the first neck, and bearing of trend arrangement of multiple bulkheads along stringer, a plurality of stringer cover along the circumferentially distributed of bulkhead
Skin is wrapped circumferentially around on a plurality of stringer along bulkhead, and the first fastener is fixedly connected between covering and stringer, or, first is tight
Firmware is connected between bulkhead and covering.
Further scheme is the first side wall of the first neck and the setting at an acute angle of the angle of second sidewall, the first side wall
Limited block is provided with, stringer is abutted with the first side wall, and limited block is mutually clamped with corresponding second neck.
Further scheme is that on the axially symmetric face of bulkhead, the center of gravity of bulkhead is located on the extended line of the first side wall.
Further scheme is that the bottom bending of the first neck is set.
Further scheme is that fuselage also includes the second fastener, and the second fastener is connected between stringer and bulkhead.
Therefore between all parts of the fuselage of unmanned vehicle be attached by mechanical structure, specifically,
Bulkhead is circumferentially provided with multiple first necks, and bearing of trend of the stringer along stringer is provided with the second neck, and stringer passes through
First neck of two draw-in groove and bulkhead is connected, and then is realized to the mechanical connection between stringer and bulkhead, and is formed
The skeleton of fuselage.In addition, by the way that covering is wrapped on a plurality of stringer, and stringer and covering are consolidated by the first fastener
Fixed connection, can either realize and covering is fixed on the skeleton of fuselage, and can enough prevents the connection between stringer and bulkhead from occurring
Loosen, and can prevent from relatively moving between stringer and bulkhead.Also, between all parts of fuselage of the present utility model
Connection be that traditional adhesive bonding technique is replaced using mechanical structure, and then improve the fastening of the connection between fuselage all parts
Property.Meanwhile all parts are attached by mechanical structure, by increasing capacitance it is possible to increase the maintainability of unmanned vehicle so that when nobody flies
When some part of row device damages, the part can be carry out demolition and replacement at any time.Similarly, covering is by first
Fastener is detachably connected on the skeleton of bulkhead and stringer composition so that when covering damages, can be realized to covering
The quick-replaceable of skin, and then enable fuselage to keep mellow and full surface, ensure the aerodynamic performance of fuselage.Furthermore by
It can be dismounted at any time in the fuselage so that, can be by first to machine when needing additionally to add other devices in fuselage
After some parts of body are dismantled, after the device to be added is arranged in fuselage, then the part dismantled installed back
Go so that there is fuselage stronger repacking performance and equipment to install compatible performance.It can be seen that the utility model passes through to unmanned flight
The setting of the fuselage of device and structure design so that fuselage have it is simple in construction, it is easy to disassemble, assemble and be easy to maintenance it is excellent
Point.
In order to realize another object of the present utility model, the utility model provides a kind of unmanned vehicle, including fuselage, the
One wing, the second wing and empennage, the first wing, the second wing and empennage are fixedly connected with fuselage, and the first wing and
Two wings are located at the both sides of fuselage, and empennage is located at the rear of fuselage, wherein, fuselage includes multiple bulkheads, stringer group, covering and the
One fastener, multiple first necks is provided with the perisporium of each bulkhead, stringer group includes a plurality of stringer, each stringer edge
The bearing of trend of itself is provided with multiple second necks, and stringer is fastened on the first neck by the second neck, and multiple bulkheads
Arranged along the bearing of trend of stringer, a plurality of stringer is wrapped circumferentially around in a plurality of stringer along the circumferentially distributed of bulkhead, covering along bulkhead
On, the first fastener is fixedly connected between covering and stringer, or, the first fastener is connected between bulkhead and covering.
Further scheme is the first side wall of the first neck and the setting at an acute angle of the angle of second sidewall, the first side wall
Limited block is provided with, stringer is abutted with the first side wall, and limited block is mutually clamped with corresponding second neck.
Further scheme is that on the axially symmetric face of bulkhead, the center of gravity of bulkhead is located on the extended line of the first side wall.
Further scheme is that the bottom bending of the first neck is set.
Further scheme is that fuselage also includes the second fastener, and the second fastener is connected between stringer and bulkhead.
Therefore between all parts of fuselage be attached by mechanical structure, specifically, the circumference of bulkhead is set
Multiple first necks are equipped with, and bearing of trend of the stringer along stringer is provided with the second neck, stringer passes through the second neck and bulkhead
The first neck be connected, and then realize to the mechanical connection between stringer and bulkhead, and form the skeleton of fuselage.This
Outside, by the way that covering is wrapped on a plurality of stringer, and stringer and covering are fixedly connected by the first fastener, can either
Covering is fixed on the skeleton of fuselage by realization, and and can enough prevents that connection loosens between stringer and bulkhead, and can prevent
Only relatively moved between stringer and bulkhead.Also, the connection between all parts of the fuselage of unmanned vehicle is to use
Mechanical structure replaces traditional adhesive bonding technique, and then improves the tightness of the connection between fuselage all parts.It is meanwhile each
Part is attached by mechanical structure, by increasing capacitance it is possible to increase the maintainability of unmanned vehicle so that when some portion of unmanned vehicle
When part damages, the part can be carry out demolition and replacement at any time.Similarly, covering is detachable by the first fastener
Ground is connected on the skeleton of bulkhead and stringer composition so that when covering damages, the quick-replaceable to covering can be realized,
And then enable fuselage to keep mellow and full surface, ensure the aerodynamic performance of fuselage.Furthermore because the fuselage can be with
Shi Jinhang is dismounted so that, can be by first entering to some parts of fuselage when needing additionally to add other devices in fuselage
After row dismounting, after the device to be added is arranged in fuselage, then the part dismantled is installed and gone back so that unmanned flight
Utensil has stronger repacking performance and equipment to install compatible performance.It can be seen that the utility model passes through the setting to unmanned vehicle
And structure design so that fuselage have it is simple in construction, it is easy to disassemble, assemble and be easy to maintenance the advantages of.
Brief description of the drawings
Fig. 1 is the structure chart of the utility model unmanned vehicle first embodiment.
Fig. 2 is the structure chart of the fuselage of the utility model unmanned vehicle first embodiment.
Fig. 3 is the structure chart of the skeleton of the fuselage of the utility model unmanned vehicle first embodiment.
Fig. 4 is the enlarged drawing at A in Fig. 2.
Fig. 5 is exploded view of the bulkhead with stringer junction of the utility model unmanned vehicle first embodiment.
Fig. 6 is connection structure diagram of the bulkhead with stringer junction of the utility model unmanned vehicle second embodiment.
Fig. 7 is exploded view of the bulkhead with stringer junction of the utility model unmanned vehicle second embodiment.
Fig. 8 is the structure chart of the bulkhead of the utility model unmanned vehicle second embodiment.
Fig. 9 is connection structure diagram of the bulkhead with stringer junction of the utility model unmanned vehicle 3rd embodiment.
Figure 10 is exploded view of the bulkhead with stringer junction of the utility model unmanned vehicle 3rd embodiment.
Figure 11 is the structure chart of the bulkhead of the utility model unmanned vehicle 3rd embodiment.
Below in conjunction with drawings and Examples, the utility model is described in further detail.
Embodiment
Unmanned vehicle first embodiment：
Referring to figs. 1 to Fig. 4, unmanned vehicle 100 includes fuselage 101, the first wing, the second wing, empennage 102 and power
System 103, wherein, the first wing, the second wing, empennage 102 are fixedly connected with fuselage 101, and the first wing and the second machine
The wing is located at the both sides of fuselage 101 respectively, and the rear for being located at fuselage 101 positioned at 104, dynamical system 103 is connected with fuselage 101, and
Dynamical system 103 is used to provide flight for unmanned vehicle or slides power.
Fuselage 101 includes multiple bulkheads 1, stringer group 2, covering 3, the first fastener 4 and the second fastener 5.Wherein, it is each
Multiple first necks 11 are provided with the perisporium of individual bulkhead 1, it is preferable that circumference of multiple first necks 11 along bulkhead 1 is equably
Distribution.
Stringer group 2 includes a plurality of stringer 21, and bearing of trend of each stringer 21 along itself is provided with multiple second necks
211, stringer 21 is fastened on the first neck 11 by the second neck 211, specifically, as shown in figure 3, stringer 21 is positioned at the first card
In groove 11, and second neck 211 on stringer 21 is mutually clamped with first neck 11 on bulkhead 1, so as to realize
Between one stringer 21 and a bulkhead 1 be relatively fixed with it is spacing.
In addition, bearing of trend arrangement of multiple bulkheads 1 along stringer 21, a plurality of stringer 21 is along the circumferentially distributed of bulkhead 11.That is,
Engaging has a bulkhead 1 in one the second neck 211 of each stringer 21；Similarly, one first card of each bulkhead 1
Engaging has a stringer 21 in groove 21 so that multiple bulkheads 1 and stringer group collectively constitute the skeleton of fuselage 101.
Preferably, the second fastener 5 is connected between stringer 21 and bulkhead 1.Specifically, it is additionally provided with bulkhead 1 multiple
First through hole 12, and a first through hole 12 is accordingly set with first neck 11；Multiple are provided with stringer 21
Two through holes 212, and second through hole 212 is accordingly set with second neck 211.Second fastener 5 is arranged on
The junction of one neck 11 and the second neck 211, and the both ends of the second fastener 5 respectively with first through hole 12, the second through hole 212
It is fixedly connected, so as to which further bulkhead 1 and stringer 21 be fixed.
As shown in figure 1, circumference of the covering 3 along bulkhead 1 is included on a plurality of stringer 21, also, the first fastener 4 is connected to
Between stringer 21 and covering 3, covering 3 and stringer 21 are fixed so that covering 3 can either be fixed on the skeleton of fuselage,
And can enough prevents the connection between stringer 21 and bulkhead 1 from loosening, and can prevent stringer 21 and bulkhead 1 from relative move occurs
It is dynamic.Certainly, the first fastener 4 can also be connected between bulkhead 1 and covering 3.
When needing the fuselage 101 to unmanned vehicle 100 to install, first, multiple bulkheads 1 are arranged on one successively
On bar stringer 21, and make one in multiple first necks 11 of each bulkhead 1 and second neck 211 on stringer 21
It is mutually clamped, meanwhile, ensure that multiple bulkheads 1 are set in coaxial line.Then, with reference to above-mentioned connected mode by remaining a plurality of stringer
21 are attached with multiple bulkheads 1, so as to complete the installation of the skeleton of fuselage 101.Then, using the first fastener 5 to stringer
Group 2 and multiple bulkheads 1 are fixed.Then, being wrapped circumferentially around on a plurality of stringer 21 around bulkhead 1 of covering 3 is made.Finally, use
Stringer 21 and covering 3 are fixed first fastener 4；Or bulkhead 1 and covering 3 are consolidated using the first fastener 4
It is fixed.
Unmanned vehicle second embodiment：
Reference picture 6 is to Fig. 8, using the inventive concept of unmanned vehicle first embodiment, unmanned vehicle second embodiment
It is to be provided with multiple first necks on the perisporium of each bulkhead 6 of second embodiment with the difference of first embodiment
61, it is preferable that circumference of multiple first necks 61 along bulkhead 6 is evenly distributed.
As shown in figure 8, the angle setting at an acute angle of the first side wall 611 and second sidewall 612 of the first neck 61.In addition,
The bottom bending of first neck 61 is set, and the bending side 613 of the first neck 61 is perpendicular to the first side wall 611.In addition, the first card
The first side wall 611 of groove 61 is provided with limited block 614, and limited block 614 is located at the middle part of the first side wall 611.
Stringer group includes a plurality of stringer 71, and bearing of trend of each stringer 71 along itself is provided with multiple second necks
711, stringer 71 is fastened on the first neck 61 by the second neck 711.Specifically, as shown in fig. 6, stringer 71 is positioned at the first card
In groove 61, and the first side wall 611 with the first neck 61, bending side 613 abut stringer 71 respectively, and limited block 614 is inserted into
In two draw-in groove 711, it is relatively fixed so as to realize between a stringer 71 and a bulkhead 6.
Preferably, as shown in figure 8, two mirror images of the first neck 61 adjacent on bulkhead 6 are set, in addition, in the axle of bulkhead 6
To on the plane of symmetry, the center of gravity of bulkhead 6 is located on the extended line R of the first side wall 611.
When needing the fuselage to unmanned vehicle to install, first, multiple bulkheads 6 are sequentially arranged at a stringer
On 71, and one in multiple first necks 61 of each bulkhead 6 is set to engage with second neck 711 on stringer 71,
Ensure that multiple bulkheads 6 are set in coaxial line simultaneously.Specifically, stringer 71 is placed in the first neck 61 of bulkhead 6, and by stringer
71 turn at the first side wall 611 around the axis of bulkhead 6 from second sidewall 612, make stringer 71 respectively with the first side wall 611, curved
Folding face 613 abuts, and limited block 614 is inserted into the second neck 711.
Then, remaining a plurality of stringer 71 is attached with multiple bulkheads 6 with reference to above-mentioned connected mode, so as to complete machine
The installation of the skeleton of body.
Then, covering being wrapped circumferentially around on a plurality of stringer 71 around bulkhead 6 is made.
Finally, stringer 71 and covering are fixed using the first fastener；Or using the first fastener to bulkhead 6
It is fixed with covering.
Preferably, the second fastener can be connected between stringer 71 and bulkhead 6, further stringer 71 and bulkhead 6 are entered
Row is fixed.Certainly, can still ensure to be fixedly connected even if being not connected to the second fastener, between stringer 71 and bulkhead 6, because,
The advantages of connected mode of above-mentioned stringer 71 and bulkhead 6, is：Stringer 71 is positioned in a transverse direction with bulkhead 6, i.e.,
Positioned on the direction parallel to bending side 613 so that if stringer 71 will depart from bulkhead 6, it is necessary to after being rotated
Translational motion could be realized.And actual no matter the tangible ground of unmanned vehicle or controlling, the institute of stringer 71 of unmanned vehicle
The equal very little of tangential force and torsion received, moreover, stringer 71 can be interfixed by the first fastener with covering, and then avoid
Stringer 71 receives tangential force and rotates, comes off.
Unmanned vehicle 3rd embodiment：
Reference picture 9 is to Figure 11, using the inventive concept of unmanned vehicle second embodiment, unmanned vehicle 3rd embodiment
It is to be provided with multiple first necks on the perisporium of each bulkhead 8 of 3rd embodiment with the difference of second embodiment
81, it is preferable that circumference of multiple first necks 81 along bulkhead 8 is evenly distributed.
As shown in figure 11, the angle setting at an acute angle of the first side wall 811 and second sidewall 812 of the first neck 81.In addition,
The bottom bending of first neck 81 is set, and the bending side 813 of the first neck 81 is perpendicular to the first side wall 811.In addition, the first card
The first side wall 811 of groove 81 is provided with limited block 814, and limited block 814 is located at the opening of the first neck 81.
Stringer group 9 includes a plurality of stringer 91, and bearing of trend of each stringer 91 along itself is provided with multiple second necks
911, stringer 91 is fastened on the first neck 81 by the second neck 911, specifically, as shown in figure 9, stringer 91 is positioned at the first card
In groove 81, the second neck 911 is located in two side walls being oppositely arranged of stringer 91, the second neck 911 respectively with the first neck
81 the first side wall 811, bending side 813 abut, and the body with bulkhead 8, limited block 814 engage the second neck 911 respectively, from
And realize and be relatively fixed between a stringer 91 and a bulkhead 8.
Preferably, as shown in figure 11, the mirror image of the first neck of adjacent two 81 on bulkhead 8 is set, in addition, in bulkhead 8
On axially symmetric face, the center of gravity of bulkhead 8 is located on the extended line R1 of the first side wall 811.
When needing the fuselage to unmanned vehicle to install, first, multiple bulkheads 8 are sequentially arranged at a stringer
On 91, and one in multiple first necks 81 of each bulkhead 8 is set to engage with second neck 911 on stringer 91,
Ensure that multiple bulkheads 8 are set in coaxial line simultaneously.Specifically, stringer 91 is placed in the first neck 81 of bulkhead 8, and by stringer
91 turn at the first side wall 811 around the axis of bulkhead 8 from second sidewall 812, and make stringer 91 respectively with the first side wall 811,
Bending side 813 abuts, and the second neck 911 is engaged respectively with bulkhead 8, limited block 814.
Then, remaining a plurality of stringer 91 is attached with multiple bulkheads 8 with reference to above-mentioned connected mode, so as to complete machine
The installation of the skeleton of body.
Then, it is covering being wrapped circumferentially around on a plurality of stringer 91 around bulkhead 6.
Finally, stringer 91 is fixed with covering using the first fastener；Or using the first fastener to bulkhead 8
It is fixed with covering.
Preferably, the second fastener can be connected between stringer 91 and bulkhead 8, further stringer 91 and bulkhead 8 are entered
Row is fixed.Certainly, can still ensure to be fixedly connected even if being not connected to the second fastener, between stringer 91 and bulkhead 8, because,
The advantages of connected mode of above-mentioned stringer 91 and bulkhead 8, is：Stringer 91 is positioned in a transverse direction with bulkhead 8, i.e.,
Positioned on the direction parallel to bending side 813 so that if stringer 91 will depart from bulkhead 8, it is necessary to after being rotated
Translational motion could be realized.And actual no matter the tangible ground of unmanned vehicle or controlling, the institute of stringer 91 of unmanned vehicle
The equal very little of tangential force and torsion received, moreover, stringer 91 can be interfixed by the first fastener with covering, and then avoid
Stringer 91 receives tangential force and rotates, comes off.
From such scheme, the connection between all parts of the fuselage of unmanned vehicle is come generation using mechanical structure
For traditional adhesive bonding technique, and then improve the tightness of the connection between fuselage all parts.Meanwhile all parts pass through machinery
Structure is attached, by increasing capacitance it is possible to increase the maintainability of unmanned vehicle so that when some part of unmanned vehicle damages,
The part can be carry out demolition and replacement at any time.In addition, covering be by the first fastener be detachably connected to bulkhead and
On the skeleton of stringer composition so that when covering damages, the quick-replaceable to covering can be realized, and then enable fuselage
Mellow and full surface is enough kept, ensures the aerodynamic performance of fuselage.Furthermore because the fuselage can be dismounted at any time, make
Proper needs are in fuselage when additionally adding other devices, can be by first being dismantled to some parts of fuselage after, by institute
After the device to be added is arranged in fuselage, then the part dismantled is installed and gone back so that unmanned vehicle has stronger
Reequip performance and equipment installs compatible performance.It can be seen that the utility model is made by the setting to unmanned vehicle and structure design
Fuselage have it is simple in construction, it is easy to disassemble, assemble and be easy to maintenance the advantages of.
Finally it is emphasized that the foregoing is only preferred embodiment of the present utility model, this reality is not limited to
With new, for those skilled in the art, the utility model can have various change and change, all in the utility model
Spirit and principle within, any modification, equivalent substitution and improvements done etc., should be included in protection model of the present utility model
Within enclosing.
Claims (10)
1. the fuselage of unmanned vehicle, it is characterised in that including：
Multiple bulkheads, multiple first necks are provided with the perisporium of each bulkhead；
Stringer group, the stringer group include a plurality of stringer, and bearing of trend of each article of stringer along itself is provided with multiple
Two draw-in groove, the stringer are fastened on first neck by second neck, and multiple bulkheads are along the stringer
Bearing of trend arrangement, a plurality of stringer is along the circumferentially distributed of the bulkhead；
Covering, the covering are wrapped circumferentially around on a plurality of stringer along the bulkhead；
First fastener, first fastener are fixedly connected between the covering and the stringer；Or
First fastener is connected between the bulkhead and the covering.
2. fuselage according to claim 1, it is characterised in that：
The angle setting at an acute angle of the first side wall and second sidewall of first neck；
The first side wall is provided with limited block, and the stringer abuts with the first side wall, and the limited block with it is corresponding
Second neck be mutually clamped.
3. fuselage according to claim 2, it is characterised in that：
On the axially symmetric face of the bulkhead, the center of gravity of the bulkhead is located on the extended line of the first side wall.
4. fuselage according to claim 3, it is characterised in that：
The bottom bending of first neck is set.
5. according to the fuselage described in any one of Claims 1-4, it is characterised in that：
The fuselage also includes the second fastener, and second fastener is connected between the stringer and the bulkhead.
6. unmanned vehicle, including fuselage, the first wing, the second wing and empennage, first wing, the second wing and described
Empennage is fixedly connected with the fuselage, and first wing and second wing are located at the both sides of the fuselage respectively,
The empennage is located at the rear of the fuselage, it is characterised in that：
The fuselage includes：
Multiple bulkheads, multiple first necks are provided with the perisporium of each bulkhead；
Stringer group, the stringer group include a plurality of stringer, and bearing of trend of each article of stringer along itself is provided with multiple
Two draw-in groove, the stringer are fastened on first neck by second neck, and multiple bulkheads are along the stringer
Bearing of trend arrangement, a plurality of stringer is along the circumferentially distributed of the bulkhead；
Covering, the covering are wrapped circumferentially around on a plurality of stringer along the bulkhead；
First fastener, first fastener are fixedly connected between the covering and the stringer；Or
First fastener is connected between the bulkhead and the covering.
7. unmanned vehicle according to claim 6, it is characterised in that：
The angle setting at an acute angle of the first side wall and second sidewall of first neck；
The first side wall is provided with limited block, and the stringer abuts with the first side wall, and the limited block with it is corresponding
Second neck be mutually clamped.
8. unmanned vehicle according to claim 7, it is characterised in that：
On the axially symmetric face of the bulkhead, the center of gravity of the bulkhead is located on the extended line of the first side wall.
9. unmanned vehicle according to claim 8, it is characterised in that：
The bottom bending of first neck is set.
10. according to the unmanned vehicle described in any one of claim 6 to 9, it is characterised in that：
The fuselage also includes the second fastener, and second fastener is connected between the stringer and the bulkhead.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720887685.5U CN207120868U (en) | 2017-07-20 | 2017-07-20 | The fuselage and unmanned vehicle of unmanned vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720887685.5U CN207120868U (en) | 2017-07-20 | 2017-07-20 | The fuselage and unmanned vehicle of unmanned vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN207120868U true CN207120868U (en) | 2018-03-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720887685.5U Expired - Fee Related CN207120868U (en) | 2017-07-20 | 2017-07-20 | The fuselage and unmanned vehicle of unmanned vehicle |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109927878A (en) * | 2019-04-25 | 2019-06-25 | 西安航空学院 | Diamond wing mounting structure and aircraft with the mounting structure |
| CN112078777A (en) * | 2019-06-12 | 2020-12-15 | 北京京东尚科信息技术有限公司 | Fuselage skeleton structure, fuselage and aircraft |
| CN113200149A (en) * | 2021-05-18 | 2021-08-03 | 中国空气动力研究与发展中心空天技术研究所 | Fixed wing unmanned aerial vehicle load structure based on intake duct |
-
2017
- 2017-07-20 CN CN201720887685.5U patent/CN207120868U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109927878A (en) * | 2019-04-25 | 2019-06-25 | 西安航空学院 | Diamond wing mounting structure and aircraft with the mounting structure |
| CN109927878B (en) * | 2019-04-25 | 2024-02-02 | 西安航空学院 | Diamond wing mounting structure and aircraft with same |
| CN112078777A (en) * | 2019-06-12 | 2020-12-15 | 北京京东尚科信息技术有限公司 | Fuselage skeleton structure, fuselage and aircraft |
| CN113200149A (en) * | 2021-05-18 | 2021-08-03 | 中国空气动力研究与发展中心空天技术研究所 | Fixed wing unmanned aerial vehicle load structure based on intake duct |
| CN113200149B (en) * | 2021-05-18 | 2023-04-11 | 中国空气动力研究与发展中心空天技术研究所 | Fixed wing unmanned aerial vehicle load structure based on intake duct |
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