CN107284643A - The horn fold mechanism and aircraft of a kind of aircraft - Google Patents
The horn fold mechanism and aircraft of a kind of aircraft Download PDFInfo
- Publication number
- CN107284643A CN107284643A CN201610573275.3A CN201610573275A CN107284643A CN 107284643 A CN107284643 A CN 107284643A CN 201610573275 A CN201610573275 A CN 201610573275A CN 107284643 A CN107284643 A CN 107284643A
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- folding rod
- projection
- aircraft
- folding
- hole
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- 230000007246 mechanism Effects 0.000 title claims abstract description 69
- 210000001503 joint Anatomy 0.000 claims description 27
- 238000011084 recovery Methods 0.000 abstract description 3
- 238000010276 construction Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 5
- 230000009471 action Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000000151 deposition Methods 0.000 description 1
- 239000000686 essence Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- 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
- B64C1/063—Folding or collapsing to reduce overall dimensions, e.g. foldable tail booms
-
- 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
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
Abstract
The invention discloses a kind of horn fold mechanism of aircraft, including the first folding rod, the second folding rod and folding rod bindiny mechanism, first folding rod and the second folding rod are connected by folding rod bindiny mechanism；Wherein, it is connected in the folding rod bindiny mechanism by being plugged in the connecting shaft of the first connector and the second connector, and then realizes the folding between the first folding rod and the second folding rod and opening.In addition, the present invention will not also produce twisting so as to ensure that between the first projection and the second projection by the position restriction between the 3rd projection and projection limited block when in open mode.Also the first folding rod is fixed in the present invention using a fixing button set and pushes open position between the second folding rod to, it is ensured that in the on-state, horn fold mechanism will not be bent.The present invention is simple in construction, lightweight, occupy little space, and the expansion and recovery that can meet the horn of aircraft or unmanned plane are used.
Description
Technical field
The present invention relates to the manufacturing technology field of aircraft or unmanned plane, the horn folding machine of more particularly to a kind of aircraft
Structure and the aircraft using the horn fold mechanism.
Background technology
Aircraft or unmanned plane with its lightweight, small volume, using flexibly, can adapt to the advantages such as various adverse circumstances
Through being widely used in terms of scientific research, production, social life.
Because the characteristics of lightweight, small volume, the structure of aircraft or unmanned plane need to carry out it is well-designed, also, just
For the structure of aircraft itself, the mechanical structure of each several part can not take excessive space.And existing mechanical structure should
During for aircraft or unmanned plane, often because volume is big, space-consuming many and has influence on aircraft or unmanned plane type
Design.For example, it is contemplated that to the requirement for using and depositing of aircraft or unmanned plane, it may be desirable to some of aircraft or unmanned plane
Part is folded accordingly, can be deployed aircraft or unmanned plane in time during in order to use, and the storage time
Space-consuming is saved to avoid the foreign impacts being likely to occur from causing damage etc..But existing various fold mechanisms can not be met
Lightweight, small volume the requirement of aircraft or unmanned plane.Therefore, the these requirements of aircraft to be directed to or unmanned plane of still needing are entered
Row is correspondingly improved.
The content of the invention
In view of this, the present invention provides a kind of horn fold mechanism of aircraft and flying using the horn fold mechanism
Row device, occupied little space with meeting aircraft or unmanned plane, it is lightweight require.
The technical proposal of the invention is realized in this way：
A kind of horn fold mechanism of aircraft, the horn fold mechanism include the first folding rod, the second folding rod and
Folding rod bindiny mechanism, first folding rod and the second folding rod are connected by folding rod bindiny mechanism；Wherein, it is described to fold
Bar bindiny mechanism includes：
First butt joint body, first butt joint body is located at first folding rod towards one end of second folding rod；
Second butt joint body, second butt joint body is located at second folding rod towards one end of first folding rod,
And be adapted with the first butt joint body；
First connector, first connector is located at first folding rod towards one end of second folding rod,
And adjacent to first butt joint body, first connector offers the first connecting hole, the axial direction side of first connecting hole
To the axial direction perpendicular to first folding rod and the second folding rod；
Second connector, second connector is located at second folding rod towards one end of first folding rod,
And adjacent to second butt joint body, second connector offers the second connecting hole, the axial direction side of second connecting hole
To the axial direction perpendicular to first folding rod and the second folding rod；And,
Connecting shaft, the connecting shaft is arranged in first connecting hole and the second connecting hole, and then causes described first
Folding rod has the free degree rotated relative to the connecting shaft.
Further, first butt joint body is bulge loop, and the bulge loop is fixed on first folding rod towards described second
One end of folding rod, and protruded to second folding rod；
Second butt joint body is groove, and the groove is opened in second folding rod towards first folding rod
One end, and be adapted with the bulge loop；
First connector is the first projection, and first projection is located at first folding rod towards second folding
One end of folded bar, and adjacent to the bulge loop, first projection offers through hole, and the axial direction of the through hole is perpendicular to institute
State the axial direction of the first folding rod and the second folding rod；
Second connector is the second projection, and second projection is fixed on second folding rod towards described first
One end of folding rod, and adjacent to the groove, second projection offers pilot hole, the axial direction of the pilot hole hangs down
Directly in first folding rod and the axial direction of the second folding rod, the bearing of trend of the pilot hole is parallel to second folding
The axial direction of folded bar；
The connecting shaft is bearing pin, and the bearing pin is arranged in the through hole and pilot hole, and then causes first folding
Folded bar has the free degree rotated relative to the bearing pin, and causes first folding rod has to be moved along the pilot hole
The free degree.
Further, first projection is two, and the distance between two first projections accommodate second projection just.
Further, the folding rod bindiny mechanism also includes：
3rd projection, it is convex that the 3rd projection is laterally away from described first by one of the bulge loop away from first projection
The direction extension of block is formed；
Projection limited block, the projection limited block is located at side of the groove away from the second projection, and the projection is spacing
Block is made up of two pieces of sub- limited blocks, and the distance between two pieces of sub- limited blocks accommodate the 3rd projection just, when described first
Folding rod rotates relative to the bearing pin and causes the axis of first folding rod and the diameter parallel of second folding rod
When, the 3rd projection is located exactly between described two sub- projections.
Further, first folding rod offers external screw thread close to the outer of the side of second folding rod；
The horn fold mechanism also includes：
Fixing button set, the fixing button set is sheathed on second folding rod, and fixing button set is close to described the
The interior edge of one folding rod offers the internal thread being adapted with the external screw thread；
When the fixing button set is screwed in first folding rod, the folding rod bindiny mechanism is closed in the fixation
In button set.
Further, outer of first folding rod away from the second folding rod side offers the first loop bar connecting screw hole,
First folding rod is fixed on the horn connecting rod of aircraft by being arranged in the bolt of the first loop bar connecting screw hole.
Further, outer of second folding rod away from the first folding rod side offers the second loop bar connecting screw hole,
Second folding rod is fixed on the fuselage connecting rod of aircraft by being arranged in the bolt of the second loop bar connecting screw hole.
Further, outer of first folding rod away from the second folding rod side offers the first loop bar connecting screw hole,
First folding rod is fixed on the fuselage connecting rod of aircraft by being arranged in the bolt of the first loop bar connecting screw hole.
Further, outer of second folding rod away from the first folding rod side offers the second loop bar connecting screw hole,
Second folding rod is fixed on the horn connecting rod of aircraft by being arranged in the bolt of the second loop bar connecting screw hole.
A kind of aircraft, the aircraft uses the horn fold mechanism of aircraft as above described in any one.
From such scheme as can be seen that in the horn fold mechanism of the aircraft of the present invention, mainly performing jackknife action
Folding rod bindiny mechanism is significantly less than the first folding rod in the radially shared space of the first folding rod and the second folding rod
With the diameter of the second folding rod, and then cause the horn fold mechanism shared by space it is sufficiently small, small space-consuming is also same
When alleviate the weight of horn fold mechanism.It is real by switching of the bearing pin between the first projection and the second projection in the present invention
Show rotating against between the first folding rod and the second folding rod, and the pilot hole that the second projection is opened up is so that first folds
Movement that can be relative between bar and the second folding rod.When needing to open horn fold mechanism, by using bearing pin as rotating shaft
Rotate the first folding rod and the second folding rod so that the axial direction of the first folding rod and the second folding rod it is axially coincident when, along being oriented to
The bearing of trend in hole pushes the first folding rod to second folding rod and then causes the 3rd projection to enter two pieces of sons of projection limited block
Between limited block, and then the first folding rod can be locked push relative position between the second folding rod to, recycle fixing button set
Push relative position between the second folding rod to fix the first folding rod, you can realize the opening of horn fold mechanism, Gu
Determine button set to ensure that in the on-state, horn fold mechanism will not be bent.When needing to fold horn fold mechanism,
Knob fixing button set to depart from the first folding rod, then along pilot hole bearing of trend by the first folding rod to away from the second folding rod
Direction pull out, then by rotating shaft of bearing pin the first folding rod of rotation and the second folding rod cause the first folding rod be axially displaced from the
The axial direction of two-fold bar, you can realize the folding of horn fold mechanism.The structure of the horn fold mechanism of the aircraft of the present invention
Simply, it is lightweight, occupy little space, the expansion and recovery that can meet the horn of aircraft or unmanned plane are used.
Brief description of the drawings
Figure 1A is the embodiment dimensional structure diagram of the horn fold mechanism of the aircraft of the present invention；
Figure 1B is the embodiment cross section structure diagram of the horn fold mechanism of the aircraft of the present invention；
Fig. 2A is the dimensional structure diagram of the first folding rod in the embodiment of the present invention；
Fig. 2 B are the front view of the first folding rod in the embodiment of the present invention；
Fig. 2 C are the left view of the first folding rod in the embodiment of the present invention；
Fig. 2 D are the upward view of the first folding rod in the embodiment of the present invention；
Fig. 3 A are the dimensional structure diagram of the second folding rod in the embodiment of the present invention；
Fig. 3 B are the front view of the second folding rod in the embodiment of the present invention；
Fig. 3 C are the left view of the second folding rod in the embodiment of the present invention；
Fig. 3 D are the top view of the second folding rod in the embodiment of the present invention；
The dimensional structure diagram that Fig. 4 covers for the fixing button in the embodiment of the present invention.
Embodiment
In order to make the purpose , technical scheme and advantage of the present invention be clearer, develop simultaneously embodiment referring to the drawings,
The present invention is described in further detail.
Figure 1A shows the example structure of the horn fold mechanism of the aircraft of the present invention, and Figure 1B shows the embodiment
Sectional structure, the horn fold mechanism includes the first folding rod 1, the second folding rod 2 and folding rod bindiny mechanism 3, wherein, it is described
First folding rod 1 is connected with the second folding rod 2 by folding rod bindiny mechanism 3.
Fig. 2A, Fig. 2 B, Fig. 2 C and Fig. 2 D respectively illustrate the stereochemical structure, front view structure, left view structure of the first folding rod 1
With look up structure, wherein, Fig. 2 D's looks up structure for structure of first folding rod 1 towards the one end of the second folding rod 2.
Fig. 3 A, Fig. 3 B, Fig. 3 C and Fig. 3 D respectively illustrate the stereochemical structure, front view structure, left view structure of the second folding rod 2
And plan structure, wherein, Fig. 3 D's looks up structure for structure of second folding rod 2 towards the one end of the first folding rod 1.
Referring concurrently to shown in Fig. 2A, Fig. 2 B, Fig. 2 C, Fig. 2 D, Fig. 3 A, Fig. 3 B, Fig. 3 C and Fig. 3 D,
The folding rod bindiny mechanism 3 includes the first butt joint body, and first butt joint body is located at the first folding rod court
To one end of second folding rod；Second butt joint body, second butt joint body is located at second folding rod towards described the
One end of one folding rod, and be adapted with the first butt joint body；First connector, first connector is located at described first and folded
Bar is towards one end of second folding rod, and adjacent to first butt joint body, and first connector offers the first company
Hole is connect, the axial direction of first connecting hole is perpendicular to first folding rod and the axial direction of the second folding rod；Second
Connector, second connector is located at second folding rod towards one end of first folding rod, and adjacent to described
Second butt joint body, second connector offers the second connecting hole, and the axial direction of second connecting hole is perpendicular to described
The axial direction of first folding rod and the second folding rod；And, connecting shaft, the connecting shaft be arranged in first connecting hole and
In second connecting hole, and then cause first folding rod that there is the free degree rotated relative to the connecting shaft.
Specifically, first butt joint body is that bulge loop 31, second butt joint body are that groove 32, first connector are
First projection 33, first connecting hole are that through hole, second connector are the second projection 34, second connecting hole to lead
It is bearing pin 35 to hole 341, the connecting shaft.And then, the folding rod bindiny mechanism 3 includes bulge loop 31, groove 32, the first projection
33rd, the second projection 34 and bearing pin 35.Wherein, the bulge loop 31 is fixed on first folding rod 1 towards second folding rod 2
One end, and protruded to second folding rod 2.The groove 32 is opened in second folding rod 2 towards first folding
One end of folded bar 1, and be adapted with the bulge loop 31.First projection 33 is located at first folding rod 1 towards described the
One end of two-fold bar 2, and adjacent to the bulge loop 31, first projection 33 offers through hole, the axial direction side of the through hole
To the axial direction perpendicular to first folding rod 1 and the axial direction of the second folding rod 2.Second projection 34 is fixed on
Second folding rod 2 is towards one end of first folding rod 1, and second projection 34 is adjacent to the groove 32,
Second projection 34 offers pilot hole 341, and the axial direction of the pilot hole 341 is perpendicular to first folding rod 1
The axial direction of axial direction and the second folding rod 2, the bearing of trend of the pilot hole 341 is parallel to second folding rod 2
Axial direction.The bearing pin 35 is arranged in the through hole and pilot hole 341, and then first folding rod 1 is had
The free degree rotated relative to the bearing pin 35, and cause first folding rod 1 to have what is moved along the pilot hole 341
The free degree.In the embodiment of the present invention, first projection 33 is two, and the distance between two first projections 33 accommodate institute just
State the second projection 34.
With continued reference to shown in Fig. 2A, Fig. 2 B, Fig. 2 C, Fig. 2 D, Fig. 3 A, Fig. 3 B, Fig. 3 C and Fig. 3 D, the folding rod connects machine
Structure also includes the 3rd projection 36 and projection limited block 37.Wherein, the 3rd projection 36 by the bulge loop 31 away from described first
The direction extension that the one of projection 33 is laterally away from first projection 33 is formed.The projection limited block 37 is located at the groove 32
Side away from the second projection 34, the projection limited block 37 is made up of two pieces of sub- limited blocks, between two pieces of sub- limited blocks
Distance accommodates the 3rd projection 36 just, causes described the when first folding rod 1 rotates relative to the bearing pin 35
During the diameter parallel of the axis of one folding rod 1 and second folding rod 2, the 3rd projection 36 is located exactly at the projection limit
Between two sub- projections of position block 37.
As shown in Figure 1A, 2A, 2B, 2C, outer 11 of first folding rod 1 close to the side of second folding rod 2
Offer external screw thread.In the embodiment of the present invention, the horn fold mechanism also includes fixing button set 4.Fig. 4 shows the fixing button
The stereochemical structure of set 4, shown in reference picture 1A, Figure 1B and Fig. 4, the fixing button set 4 is sheathed on second folding rod 2, and
The fixing button set 4 offers the internal thread being adapted with the external screw thread close to the interior edge of first folding rod 1, when described
Fixing button set 4 is screwed when first folding rod 1, and the folding rod bindiny mechanism 3 is closed in the fixing button set 4.By
This can be seen that in the embodiment of the present invention, entirely play folding effect folding rod bindiny mechanism 3 shared by space it is minimum, can
It is contained in fixing button set 4, along with fixing button covers 4 effect so that the first folding rod 1 and the second folding rod 2 are in exhibition
Bend resistance ability is stronger during open state.
In the embodiment of the present invention, as shown in Figure 1A, Fig. 2A, Fig. 2 B, first folding rod 1 is away from the second folding rod 2 one
The outer of side offers the first loop bar connecting screw hole 12.As shown in Figure 1A, Fig. 3 A, Fig. 3 B, second folding rod 2 is away from first
The outer of the side of folding rod 1 offers the second loop bar connecting screw hole 21.
In Figure 1A, Figure 1B illustrated embodiment, in order to which needed for showing, second folding rod 2 is by being arranged in described second
The bolt of loop bar connecting screw hole 21 is fixed on a connecting rod 5, and the first folding rod 1 does not fix corresponding connecting rod, in reality
In use, the first folding rod 1 also needs to fix corresponding connecting rod.For example, in a specific embodiment, first folding rod
1 is fixed on the horn connecting rod of aircraft by being arranged in the bolt of the first loop bar connecting screw hole 12, and second folding
Folded bar 2 is fixed on the fuselage connecting rod of aircraft by being arranged in the bolt of the second loop bar connecting screw hole 21.At another
In specific embodiment, first folding rod 1 is fixed on flight by being arranged in the bolt of the first loop bar connecting screw hole 12
The fuselage connecting rod of device, and second folding rod 2 is fixed on by being arranged in the bolt of the second loop bar connecting screw hole 21
The horn connecting rod of aircraft.
In the embodiment of the present invention, bearing pin 35 can be made of stainless steel material, and then the progress of bending place is strengthened and energy
Enough play a part of preventing abrasion, and other parts all can be made of aluminum alloy materials, and then mitigate overall weight.
The embodiment of the present invention additionally provides a kind of aircraft, and the aircraft is rolled over using the horn of aircraft as described above
Folded mechanism.
In the horn fold mechanism of the aircraft of the present invention, the main folding rod bindiny mechanism for performing jackknife action is first
The radially shared space of folding rod and the second folding rod is significantly less than the diameter of the first folding rod and the second folding rod, enters
And make it that the space shared by the horn fold mechanism is sufficiently small, small space-consuming also alleviates horn fold mechanism simultaneously
Weight.In the present invention, by switching of the bearing pin between the first projection and the second projection, the first folding rod and the second folding are realized
Rotating against between folded bar, and the pilot hole that the second projection is opened up is so that can between the first folding rod and the second folding rod
Relative movement.When needing to open horn fold mechanism, by rotating the first folding rod and the second folding by rotating shaft of bearing pin
Folded bar cause the first folding rod axial direction and the second folding rod it is axially coincident when, along pilot hole bearing of trend by first fold
Bar pushes the second folding rod to and then the 3rd projection is entered between two pieces of sub- limited blocks of projection limited block, and then can lock
First folding rod pushes the relative position between the second folding rod to, recycles fixing button set to fix the first folding rod and pushes the to
Relative position between two-fold bar, you can realize the opening of horn fold mechanism, fixing button set ensure that in the on-state,
Horn fold mechanism will not be bent.When needing to fold horn fold mechanism, knob fixing button set is to depart from the first folding
Folded bar, then pull out the first folding rod to the direction away from the second folding rod along the bearing of trend of pilot hole, then using bearing pin for turn
Axle rotates the first folding rod and the second folding rod causes the axial direction for being axially displaced from the second folding rod of the first folding rod, you can realize
The folding of horn fold mechanism.The present invention aircraft horn fold mechanism it is simple in construction, lightweight, occupy little space,
The expansion and recovery that the horn of aircraft or unmanned plane can be met are used.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
God is with principle, and any modification, equivalent substitution and improvements done etc. should be included within the scope of protection of the invention.
Claims (10)
1. the horn fold mechanism of a kind of aircraft, it is characterised in that the horn fold mechanism includes the first folding rod, second
Folding rod and folding rod bindiny mechanism, first folding rod and the second folding rod are connected by folding rod bindiny mechanism；Wherein,
The folding rod bindiny mechanism includes：
First butt joint body, first butt joint body is located at first folding rod towards one end of second folding rod；
Second butt joint body, second butt joint body is located at second folding rod towards one end of first folding rod, and with
First butt joint body is adapted；
First connector, first connector is located at first folding rod towards one end of second folding rod, and phase
Adjacent to first butt joint body, first connector offers the first connecting hole, and the axial direction of first connecting hole hangs down
Directly in first folding rod and the axial direction of the second folding rod；
Second connector, second connector is located at second folding rod towards one end of first folding rod, and phase
Adjacent to second butt joint body, second connector offers the second connecting hole, and the axial direction of second connecting hole hangs down
Directly in first folding rod and the axial direction of the second folding rod；And,
Connecting shaft, the connecting shaft is arranged in first connecting hole and the second connecting hole, and then causes described first to fold
Bar has the free degree rotated relative to the connecting shaft.
2. the horn fold mechanism of aircraft according to claim 1, it is characterised in that：
First butt joint body is bulge loop, and the bulge loop is fixed on first folding rod towards the one of second folding rod
End, and protruded to second folding rod；
Second butt joint body is groove, and the groove is opened in second folding rod towards the one of first folding rod
End, and be adapted with the bulge loop；
First connector is the first projection, and first connecting hole is through hole, and first projection is located at first folding
Folded bar is towards one end of second folding rod, and adjacent to the bulge loop, and first projection offers through hole, the through hole
Axial direction perpendicular to first folding rod and the axial direction of the second folding rod；
Second connector is the second projection, and second connecting hole is pilot hole, and second projection is fixed on described the
Two-fold bar is towards one end of first folding rod, and adjacent to the groove, and second projection offers pilot hole, institute
The axial direction of pilot hole is stated perpendicular to first folding rod and the axial direction of the second folding rod, the extension of the pilot hole
It is oriented parallel to the axial direction of second folding rod；
The connecting shaft is bearing pin, and the bearing pin is arranged in the through hole and pilot hole, and then causes first folding rod
With the free degree rotated relative to the bearing pin, and cause first folding rod have along the pilot hole move from
By spending.
3. the horn fold mechanism of aircraft according to claim 2, it is characterised in that：
First projection is two, and the distance between two first projections accommodate second projection just.
4. the horn fold mechanism of aircraft according to claim 2, it is characterised in that the folding rod bindiny mechanism is also
Including：
3rd projection, the 3rd projection is laterally away from first projection by one of the bulge loop away from first projection
Direction extension is formed；
Projection limited block, the projection limited block be located at side of the groove away from the second projection, the projection limited block by
Two pieces of sub- limited blocks are constituted, and the distance between two pieces of sub- limited blocks accommodate the 3rd projection just, when the described first folding
When bar rotates relative to the bearing pin and causes the diameter parallel of axis and second folding rod of first folding rod, institute
The 3rd projection is stated to be located exactly between described two sub- projections.
5. the horn fold mechanism of aircraft according to claim 2, it is characterised in that：
First folding rod offers external screw thread close to the outer of the side of second folding rod；
The horn fold mechanism also includes：
Fixing button set, the fixing button set is sheathed on second folding rod, and fixing button set is close to first folding
The interior edge of folded bar offers the internal thread being adapted with the external screw thread；
When the fixing button set is screwed in first folding rod, the folding rod bindiny mechanism is closed in the fixing button set
It is interior.
6. the horn fold mechanism of aircraft according to claim 2, it is characterised in that first folding rod is away from
The outer of two-fold bar side offers the first loop bar connecting screw hole, and first folding rod is by being arranged in first loop bar
The bolt of connecting screw hole is fixed on the horn connecting rod of aircraft.
7. the horn fold mechanism of aircraft according to claim 6, it is characterised in that second folding rod is away from
The outer of one folding rod side offers the second loop bar connecting screw hole, and second folding rod is by being arranged in second loop bar
The bolt of connecting screw hole is fixed on the fuselage connecting rod of aircraft.
8. the horn fold mechanism of aircraft according to claim 2, it is characterised in that first folding rod is away from
The outer of two-fold bar side offers the first loop bar connecting screw hole, and first folding rod is by being arranged in first loop bar
The bolt of connecting screw hole is fixed on the fuselage connecting rod of aircraft.
9. the horn fold mechanism of aircraft according to claim 8, it is characterised in that second folding rod is away from
The outer of one folding rod side offers the second loop bar connecting screw hole, and second folding rod is by being arranged in second loop bar
The bolt of connecting screw hole is fixed on the horn connecting rod of aircraft.
10. a kind of aircraft, it is characterised in that the aircraft is using the aircraft as described in any one of claim 1 to 9
Horn fold mechanism.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620269865 | 2016-04-01 | ||
| CN2016202698652 | 2016-04-01 |
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| Publication Number | Publication Date |
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| CN107284643A true CN107284643A (en) | 2017-10-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610573275.3A Pending CN107284643A (en) | 2016-04-01 | 2016-07-19 | The horn fold mechanism and aircraft of a kind of aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107867389A (en) * | 2017-11-08 | 2018-04-03 | 安徽梦之翼无人机科技有限公司 | A kind of plant protection unmanned plane horn structure |
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| DE19627593A1 (en) * | 1996-07-09 | 1998-01-15 | Happich Fahrzeug & Ind Teile | Bicycle with two frame halves |
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| CN102336243A (en) * | 2011-08-08 | 2012-02-01 | 太仓市车中宝休闲用品有限公司 | Tapered sleeve locking type folding handle vertical pipe |
| CN102514670A (en) * | 2012-01-16 | 2012-06-27 | 太仓市车中宝休闲用品有限公司 | Taper sleeve quick release locking type folding handlebar stem |
| CN202429315U (en) * | 2012-01-16 | 2012-09-12 | 太仓市车中宝休闲用品有限公司 | Conical sleeving quick-release locking type foldable stem |
| CN203032851U (en) * | 2013-01-09 | 2013-07-03 | 深圳市喜德盛自行车有限公司 | Pipe folding device |
| CN204297074U (en) * | 2014-11-13 | 2015-04-29 | 昆山优力电能运动科技有限公司 | Many rotor wing unmanned aerial vehicles |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107867389A (en) * | 2017-11-08 | 2018-04-03 | 安徽梦之翼无人机科技有限公司 | A kind of plant protection unmanned plane horn structure |
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Application publication date: 20171024 |
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