CN105947209B - A kind of energy saving and environment friendly building municipal administration unmanned plane - Google Patents
A kind of energy saving and environment friendly building municipal administration unmanned plane Download PDFInfo
- Publication number
- CN105947209B CN105947209B CN201610309056.4A CN201610309056A CN105947209B CN 105947209 B CN105947209 B CN 105947209B CN 201610309056 A CN201610309056 A CN 201610309056A CN 105947209 B CN105947209 B CN 105947209B
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- Prior art keywords
- wing
- sliding block
- hole
- bottom plate
- rotating cylinder
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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- 239000007921 spray Substances 0.000 description 14
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 7
- 239000007788 liquid Substances 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 3
- 238000004134 energy conservation Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000007613 environmental effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000001141 propulsive effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/16—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting
- B64D1/18—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting by spraying, e.g. insecticides
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Pest Control & Pesticides (AREA)
- Remote Sensing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of energy saving and environment friendly building municipal administration unmanned plane, including fuselage, empennage and wing, it is characterised in that：The wing is connected by fold mechanism with fuselage, and the wing includes bottom plate, wing-body and slide plate；Be equipped with sliding slot above the bottom plate, the sliding slot is interior to be equipped with guide post, is provided with the first spring on the guide post, and the medium position on the bottom plate is equipped with a threaded hole, and multiple shallow slots are evenly equipped with centered on threaded hole on the bottom plate；Both sides are respectively equipped with a runner at the top of the slide plate, the slide plate two bottom sides are respectively equipped with one first sliding block, first sliding block is equipped with a through hole, first sliding block is slidably mounted in the sliding slot, and the through hole of first sliding block is arranged on the guide post so that the first sliding block one side wall is resisted against first spring.The present invention can be achieved, with the different auto-changing wing sweep angles of flying speed, to lift flight efficiency, and can effectively protect wing when colliding from damage.
Description
Technical field
The invention belongs to vehicle technology field, and in particular to a kind of energy saving and environment friendly building municipal administration unmanned plane.
Background technology
Existing fixed-wing unmanned plane, since wing is fixed, so one of component as most rapid wear, and due to machine
The wing is fixed, and flight efficiency is less desirable.
In addition the unmanned plane of fixed-wing due to the span it is longer, storage is inconvenient, and occupied space is big.
The content of the invention
(1) technical problems to be solved
It is existing to solve the technical problem to be solved in the present invention is to provide a kind of energy saving and environment friendly building municipal administration unmanned plane
The problem of wing of the unmanned plane of technology is easily damaged, and unmanned plane during flying is inefficient, and occupied space is big.
(2) technical solution
In order to solve the above technical problems, the technical solution adopted in the present invention is：A kind of energy saving and environment friendly building municipal administration is used
Unmanned plane, including fuselage, empennage and wing, the wing are connected by fold mechanism with fuselage, the wing include bottom plate,
Wing-body and slide plate；
Sliding slot is equipped with above the bottom plate, guide post is equipped with the sliding slot, the first spring is installed on the guide post, it is described
Medium position on bottom plate is equipped with a threaded hole, and multiple shallow slots are evenly equipped with centered on threaded hole on the bottom plate；
Both sides are respectively equipped with a runner at the top of the slide plate, and the slide plate two bottom sides are respectively equipped with one first sliding block, institute
State the first sliding block and be equipped with a through hole, first sliding block is slidably mounted in the sliding slot, and the through hole of first sliding block is worn
In on the guide post so that the first sliding block one side wall is resisted against first spring；
On the wing-body connecting hole, the connecting hole and the screw thread on the bottom plate are equipped with close to the side of fuselage
Hole is coaxially disposed, and a screw is screwed together on the threaded hole after passing through the connecting hole and makes the relatively described bottom of the wing-body
Plate is freely rotated, and has on the wing-body two side equipped with concave-arc part, and the runner on the slide plate is embedded in the concave-arc part,
Multiple blind holes, the multiple blind hole and the multiple shallow slot are evenly equipped with the wing-body bottom centered on the connecting hole
Corresponding and be coaxially disposed, a second spring is equipped with each blind hole, the bottom contact of the second spring has a sphere,
The spherical part is placed in the shallow slot；
The fold mechanism includes the slide and the second sliding block being fixed on the fuselage, and the slide includes middle part
Flat segments and the segmental arc arranged on flat segments both sides, are installed with double end cylinder, the arc of both sides in the flat segments
Shape section is slidably installed second sliding block respectively, and second sliding block passes through shaft and is rotatablely connected a jacking block, the double end gas
A jacking block cylinder is connected in the vertical direction of the both sides output terminal of cylinder, the output terminal of the jacking block cylinder connects the top
Block, the bottom plate of the wing is also fixedly connected with second sliding block.
Wherein, the afterbody of the fuselage is additionally provided with self-rotating nozzle, the self-rotating nozzle include base, rotating cylinder and in
Axis, the base are connected with afterbody, and the base is equipped with limbers, and the rotating cylinder is rotatably connected at institute by axis
State on base, the rotating cylinder is hollow structure, and the rotating cylinder includes the outer rotaring tube for being located at outside and interior turn close to base side
Cylinder, the outer rotaring tube are fastened with interior rotating cylinder by the buckle on periphery wall, and the outer end face of the outer rotaring tube is with its axle center institute
Four outer circle holes are evenly equipped with for the center of circle, the inner face of the interior rotating cylinder is that the center of circle is evenly equipped with four with place where its axle center at place
Circular hole, each outer circle hole are connected with circular hole in wherein one by hose respectively.
Wherein, the base has four support arms being connected on its madial wall, encloses structure between four support arms
Into the limbers, the junction of four support arms is equipped with centre bore, and the centre bore is used to penetrate the axis.
(3) beneficial effect
The present invention is compared to the prior art, has the advantages that：
The present invention can be achieved with the different auto-changing wing sweep angles of flying speed, when flying speed is high, wing
Sweep angle becomes larger, so as to reduce flight resistance, lifts flight efficiency, and wing can be effectively protected when colliding from damage.
Secondly as being equipped with self-rotating nozzle in afterbody, current pass sequentially through limbers and hose spray on base
Spill, since hose is distorted shape, current can be ejected with rotating flow direction from hose, and produce rotating reactive force,
And rotating cylinder is produced rotation relative to base, the current of the larger rotating-spray of spray area are formed, improve operating efficiency, and
It is not required extra motor to drive, energy conservation and environmental protection, alleviates weight of equipment；In addition can as needed spray area size with
And the size of sprinkling water column, by rotating the relative position of outer rotaring tube and interior rotating cylinder, hose is formed different torsion degrees.
Further, since being equipped with fold mechanism, folding wing can be facilitated, easy to store, there is practicality.
Brief description of the drawings
Fig. 1 is the structure diagram of the present invention.
Fig. 2 is the sectional view in A-A directions in Fig. 1.
Fig. 3 is the schematic top plan view of the bottom plate of the present invention.
Fig. 4 is the schematic diagram of the slide plate of the present invention.
Fig. 5 is the sectional view of the self-rotating nozzle of the present invention.
Fig. 6 is the top view of the rotating cylinder of the self-rotating nozzle of the present invention.
Fig. 7 is the stereogram of the base of the self-rotating nozzle of the present invention.
Fig. 8 is the overlooking structure figure of the fold mechanism of the present invention.
Embodiment
With reference to the accompanying drawings and examples, the embodiment of the present invention is described in further detail.Following reality
Apply example to be used to illustrate the present invention, but be not limited to the scope of the present invention.
As shown in Figures 1 to 4, the embodiment provides a kind of energy saving and environment friendly building municipal administration unmanned plane, bag
Fuselage 4, empennage 5 and wing are included, the wing is connected by fold mechanism with fuselage 4, and the wing includes bottom plate 1, wing
Body 2 and slide plate 3；
The top of bottom plate 1 is equipped with sliding slot 11, is equipped with guide post 12 in the sliding slot 11, first is provided with the guide post 12
Spring 13, the medium position on the bottom plate 1 are equipped with a threaded hole 14, are evenly equipped with the bottom plate 1 centered on threaded hole 14
Multiple shallow slots 15；
The 3 top both sides of slide plate are respectively equipped with a runner 31, and 3 two bottom sides of slide plate are respectively equipped with one first sliding block
32, first sliding block 32 is equipped with a through hole 33, and first sliding block 32 is slidably mounted in the sliding slot 11, and described first slides
The through hole 33 of block 32 is arranged on the guide post 12 so that 32 one side wall of the first sliding block is resisted against first spring 13；Institute
State and a postive stop baffle 16 is additionally provided with 1 one side wall of bottom plate, the postive stop baffle 16 is used for the position for limiting slide plate 3, anti-limited slip plate 3
Outside the track that the sliding slot 11 is skidded off in sliding process.
On the wing-body 2 connecting hole 21, the connecting hole 21 and the bottom plate 1 are equipped with close to the side of fuselage 4
On threaded hole 14 be coaxially disposed, a screw 6 is screwed together on the threaded hole 14 after passing through the connecting hole 21 and makes the machine
The relatively described bottom plate 1 of wing body 2 is freely rotated, that is to say, that after screw 6 is screwed together in threaded hole 14, threaded hole is located on screw 6
Length outside 14 is slightly larger than the thickness of wing-body 2 so that screw 6 will not lock wing-body 2 and 1 phase of bottom plate；It is described
Have on 2 two side of wing-body equipped with concave-arc part 22, the runner 31 on the slide plate 3 is embedded in the concave-arc part 22, the machine
Be evenly equipped with multiple blind holes 23 on 2 bottom of wing body centered on the connecting hole 21, the multiple blind hole 23 with it is the multiple shallow
Groove 15 is corresponded and is coaxially disposed, and a second spring 24, the bottom top of the second spring 24 are equipped with each blind hole 23
A sphere 25 is had, 25 part of sphere is placed in the shallow slot 15.
The shallow slot 15 is equipped with 12.Therefore the blind hole 23 is also correspondingly provided with 12.Of course for more accurately making ball
Body 25 is sticked in shallow slot 15, can increase the quantity of shallow slot 15 and the depth of shallow slot 15 in design, specifically how to select to see
Actual demand.
Under original state, wing-body 2 is embedded on the first shallow slot 151 of bottom plate 1 by the sphere 25 in blind hole 23, and
Wing-body 2 is positioned on bottom plate 1 by screw 6, therefore wing-body 2 can keep relative static conditions with bottom plate 1, when it flies
During row, the front of wing-body 2 can be subject to the reaction force of air-flow so that the outer end of wing-body 2 can have moves towards empennage 5
Trend, when the reaction force make it that sphere 25 is sliding out the first shallow slot 151, the outer end of wing-body 2 rotates, at this time wing
Concave-arc part 22 on body 2 can promote runner 31, and the sphere 25 on wing-body 2 can be moved towards the second shallow slot 152, at this moment be slided
Plate 3 is slided along sliding slot 11, so that 13 1 thrusts of the first spring are bestowed, the propulsive thrust of the first spring 13 and the anti-work of air-flow
Firmly offset, at this moment the sphere 25 on wing-body 2 can be embedded in the second shallow slot 152, when the present invention flying speed after
During continuous increase, the sphere 25 on wing-body 2 can be moved towards the 3rd shallow slot 153, it is achieved thereby that can be according to flying speed certainly
The function of dynamic conversion wing sweep angle.When wing-body 2 collides, wing-body 2 can transfer drop with screw 6 for center of circle automatic rotary
The possibility of low damage.When stopping flight, wing-body 2 can be returned to initial position by the propulsive thrust of the first spring 13, i.e.,
So that sphere 25 is located on the first shallow slot 151.
As shown in Figures 5 to 7, the afterbody of the fuselage 4 is additionally provided with self-rotating nozzle 7, and the self-rotating nozzle includes bottom
Seat 71, rotating cylinder 72 and axis 73, the base 71 are connected with 4 afterbody of fuselage, and the base 71 is equipped with limbers 711, described
Rotating cylinder 72 is rotatably connected on the base 71 by axis 73, and the rotating cylinder 72 is hollow structure, and the rotating cylinder 72 wraps
The outer rotaring tube 724 positioned at outside and the interior rotating cylinder 725 close to base side are included, the outer rotaring tube 724 is with interior rotating cylinder 725 by setting
Fastened in the buckle 726 on periphery wall, the outer end face of the outer rotaring tube 724 is evenly equipped with four outside with place where its axle center for the center of circle
Circular hole 721, the inner face of the interior rotating cylinder 725 are each cylindrical to be evenly equipped with four interior circular holes 722 at the place of its axle center for the center of circle
Hole 721 is connected with circular hole 722 in wherein one by hose 74 respectively.Since outer rotaring tube 724 and interior rotating cylinder 725 pass through buckle
726 connections, outer rotaring tube 724 and interior rotating cylinder 725 by relatively rotating, make hose 74 produce torsion, turn round after hose 74 is connected
Carryover degree is determined according to particular condition in use, then passes through the fastening outer rotaring tube 724 of buckle 726 and interior rotating cylinder 725.
The base 71 has four support arms 712 being connected on its madial wall, is enclosed between four support arms 712
The limbers 711 is formed, the junction of four support arms 712 is equipped with centre bore 713, and the centre bore 713 is used to wear
Enter the axis 73.The upper surface and lower face of the rotating cylinder 72 are equipped with central shaft hole 723 and are used for through the axis 73.
Water tank and water pump can be carried during implementation on fuselage, the liquid for needing to spray in water tank is increased by water pump
Pressure, is then connected with base, and liquid passes sequentially through limbers on base and hose sprays away, since hose is distorted shape,
Liquid can be ejected with rotating flow direction from hose, and produce rotating reactive force, and rotating cylinder is produced relative to base and turned
It is dynamic, the current of the larger rotating-spray of spray area are formed, improve operating efficiency, and it is not required extra motor to drive,
Energy conservation and environmental protection, alleviates weight of equipment；In addition can as needed the size of spray area and spray water column size, by turn
Dynamic outer rotaring tube and the relative position of interior rotating cylinder, make hose form different torsion degrees.Certainly the device for providing liquid also can be
On ground, it is connected to by long hose on base.
As shown in figure 8, the fold mechanism includes 80 and second sliding block 81 of slide being fixed on the fuselage 4, institute
Stating slide 80 includes the flat segments 801 at middle part and the segmental arc 802 arranged on flat segments both sides, is fixed in the flat segments 801
Double end cylinder 82 is installed, the segmental arcs 802 of both sides is slidably installed second sliding block 81 respectively, second sliding block
81 are rotatablely connected a jacking block 84 by shaft 83, are connected in the vertical direction of the both sides output terminal of the double end cylinder 82
One jacking block cylinder 85, the output terminal of the jacking block cylinder 85 connect the jacking block 84, are also fixedly connected on second sliding block 81
The bottom plate 1 of the wing.
When needing folding or expansion wing, the output terminal of double end cylinder is stretched to both sides or inwardly collapsed, while jacking block
Cylinder links with double end cylinder, makes jacking block promote sliding block to be slided along slide, so as to drive bottom plate to be rotated.
The present invention is compared to the prior art, has the advantages that：
The present invention can be achieved with the different auto-changing wing sweep angles of flying speed, when flying speed is high, wing
Sweep angle becomes larger, so as to reduce flight resistance, lifts flight efficiency, and wing can be effectively protected when colliding from damage.
Secondly as being equipped with self-rotating nozzle in afterbody, current pass sequentially through limbers and hose spray on base
Spill, since hose is distorted shape, current can be ejected with rotating flow direction from hose, and produce rotating reactive force,
And rotating cylinder is produced rotation relative to base, the current of the larger rotating-spray of spray area are formed, improve operating efficiency, and
It is not required extra motor to drive, energy conservation and environmental protection, alleviates weight of equipment；In addition can as needed spray area size with
And the size of sprinkling water column, by rotating the relative position of outer rotaring tube and interior rotating cylinder, hose is formed different torsion degrees.
Further, since being equipped with fold mechanism, folding wing can be facilitated, easy to store, there is practicality.
Certainly, it the above is only the concrete application example of the present invention, protection scope of the present invention be not limited in any way.Remove
Outside above-described embodiment, the present invention can also have other embodiment.All technical sides formed using equivalent substitution or equivalent transformation
Case, all falls within scope of the present invention.
Claims (3)
1. a kind of energy saving and environment friendly building municipal administration unmanned plane, including fuselage, empennage and wing, it is characterised in that：The machine
The wing is connected by fold mechanism with fuselage, and the wing includes bottom plate, wing-body and slide plate；
Sliding slot is equipped with above the bottom plate, guide post is equipped with the sliding slot, the first spring, the bottom plate is installed on the guide post
On medium position be equipped with a threaded hole, multiple shallow slots are evenly equipped with centered on threaded hole on the bottom plate；
Both sides are respectively equipped with a runner at the top of the slide plate, and the slide plate two bottom sides are respectively equipped with one first sliding block, and described the
One sliding block is equipped with a through hole, and first sliding block is slidably mounted in the sliding slot, and the through hole of first sliding block is arranged in institute
State on guide post so that the first sliding block one side wall is resisted against first spring；
Side on the wing-body close to fuselage is equipped with a connecting hole, and the connecting hole and the threaded hole on the bottom plate are same
Axis is set, and a screw is screwed together on the threaded hole after passing through the connecting hole and makes the relatively described bottom plate of the wing-body certainly
By rotating, have on the wing-body two side equipped with concave-arc part, the runner on the slide plate is embedded in the concave-arc part, described
Multiple blind holes are evenly equipped with wing-body bottom centered on the connecting hole, the multiple blind hole and the multiple shallow slot are one by one
Correspond to and be coaxially disposed, be equipped with a second spring in each blind hole, the bottom contact of the second spring has a sphere, described
Spherical part is placed in the shallow slot；
The fold mechanism includes the slide and the second sliding block being fixed on the fuselage, and the slide includes the straight of middle part
Section and the segmental arc arranged on flat segments both sides, are installed with double end cylinder, the segmental arc of both sides in the flat segments
Be slidably installed second sliding block respectively, and second sliding block is rotatablely connected a jacking block by shaft, the double end cylinder
A jacking block cylinder is connected in the vertical direction of both sides output terminal, the output terminal of the jacking block cylinder connects the jacking block,
The bottom plate of the wing is also fixedly connected with second sliding block.
2. energy saving and environment friendly building municipal administration unmanned plane according to claim 1, it is characterised in that：The afterbody of the fuselage
Self-rotating nozzle is additionally provided with, the self-rotating nozzle includes base, rotating cylinder and axis, and the base is connected with afterbody,
The base is equipped with limbers, and the rotating cylinder is rotatably connected on the base by axis, and the rotating cylinder is hollow knot
Structure, the rotating cylinder include the outer rotaring tube positioned at outside and the interior rotating cylinder close to base side, and the outer rotaring tube passes through with interior rotating cylinder
Buckle fastening on periphery wall, the outer end face of the outer rotaring tube with place where its axle center be the center of circle be evenly equipped with four it is cylindrical
Hole, the inner face of the interior rotating cylinder are that the center of circle is evenly equipped with four interior circular holes with place where its axle center, each outer circle hole respectively with its
In in one circular hole be connected by hose.
3. energy saving and environment friendly building municipal administration unmanned plane according to claim 2, it is characterised in that：The base has four
A support arm being connected on its madial wall, encloses between four support arms and forms the limbers, four support arms
Junction be equipped with centre bore, the centre bore is used to penetrate the axis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610309056.4A CN105947209B (en) | 2016-05-10 | 2016-05-10 | A kind of energy saving and environment friendly building municipal administration unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610309056.4A CN105947209B (en) | 2016-05-10 | 2016-05-10 | A kind of energy saving and environment friendly building municipal administration unmanned plane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105947209A CN105947209A (en) | 2016-09-21 |
| CN105947209B true CN105947209B (en) | 2018-04-17 |
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ID=56912134
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610309056.4A Expired - Fee Related CN105947209B (en) | 2016-05-10 | 2016-05-10 | A kind of energy saving and environment friendly building municipal administration unmanned plane |
Country Status (1)
| Country | Link |
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| CN (1) | CN105947209B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110127032A (en) * | 2019-06-06 | 2019-08-16 | 湖南文理学院 | A kind of collapsible unmanned plane, remote control method for folding and UAV system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU524255B2 (en) * | 1978-12-29 | 1982-09-09 | Commonwealth Of Australia, The | Deployable wing |
| RU2407674C1 (en) * | 2009-08-31 | 2010-12-27 | Юлия Алексеевна Щепочкина | Aircraft |
| CN103963958A (en) * | 2014-04-21 | 2014-08-06 | 西工大常熟研究院有限公司 | Wing folding mechanism for unmanned plane |
| CN104512545A (en) * | 2013-10-06 | 2015-04-15 | 波音公司 | Swing wing tip system, assembly and method with dual load path structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8708286B2 (en) * | 2012-06-21 | 2014-04-29 | The Boeing Company | Swing tip assembly rotation joint |
-
2016
- 2016-05-10 CN CN201610309056.4A patent/CN105947209B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU524255B2 (en) * | 1978-12-29 | 1982-09-09 | Commonwealth Of Australia, The | Deployable wing |
| RU2407674C1 (en) * | 2009-08-31 | 2010-12-27 | Юлия Алексеевна Щепочкина | Aircraft |
| CN104512545A (en) * | 2013-10-06 | 2015-04-15 | 波音公司 | Swing wing tip system, assembly and method with dual load path structure |
| CN103963958A (en) * | 2014-04-21 | 2014-08-06 | 西工大常熟研究院有限公司 | Wing folding mechanism for unmanned plane |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105947209A (en) | 2016-09-21 |
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Inventor after: Feng Xinru Inventor before: Zhong Songmei |
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| TA01 | Transfer of patent application right |
Effective date of registration: 20180309 Address after: Nansha District Fengze road Guangzhou city Guangdong province 511400 No. 106 (self building No. 1) X1301-I1399 (only for office use) (JM) Applicant after: Jing Guo International Education Technology (Guangzhou) Co.,Ltd. Address before: Xiangshan County town of 315700 village Shipu Zhejiang province Ningbo City, No. 329 Applicant before: Zhong Songmei |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180417 |