CN105752318B - A kind of unmanned plane with hook lock buffer unit - Google Patents
A kind of unmanned plane with hook lock buffer unit Download PDFInfo
- Publication number
- CN105752318B CN105752318B CN201610104090.8A CN201610104090A CN105752318B CN 105752318 B CN105752318 B CN 105752318B CN 201610104090 A CN201610104090 A CN 201610104090A CN 105752318 B CN105752318 B CN 105752318B
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- Prior art keywords
- wing
- plate
- sliding block
- hole
- bottom plate
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/40—Varying angle of sweep
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/68—Arrester hooks
-
- 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
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/60—Take-off or landing of UAVs from a runway using their own power
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Vibration Dampers (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of unmanned plane with hook lock buffer unit, including fuselage, empennage and wing, the wing includes bottom plate, wing-body and the slide plate mutually fixed with the fuselage；The bottom plate, which is provided with chute, the chute, is provided with guide pillar, and the medium position being provided with the guide pillar on the first spring, the bottom plate is provided with a screwed hole, the bottom plate and multiple shallow slots are evenly equipped with centered on screwed hole；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 a sliding block, the sliding block is provided with a through hole, and the sliding block is slidably mounted in the chute, and the through hole of the sliding block is arranged on the guide pillar so that sliding block side wall is resisted against first spring.The present invention can be achieved with the different auto-changing wing sweep angles of flying speed, when flying speed is high, and the sweep angle of wing becomes big, so as to reduce flight resistance, lifts flight efficiency, and effectively wing can be protected not damaged when colliding.
Description
Technical field
The invention belongs to vehicle technology field, and in particular to a kind of unmanned plane with hook lock buffer unit.
Background technology
Existing fixed-wing unmanned plane, because wing is fixed, so one of part as most rapid wear, and due to machine
The wing is fixed, and flight efficiency is less desirable.After flying speed is too fast, or landing distance is too in short-term, it is difficult to pass through control
Speed processed reaches the effect that safety and stability is landed.
The content of the invention
(1) technical problem to be solved
The technical problem to be solved in the present invention is to provide a kind of unmanned plane with hook lock buffer unit, to solve existing skill
The wing of the fixed-wing unmanned plane of art is easily damaged and unmanned plane during flying is inefficient, and unsafe problem of landing.
(2) technical scheme
In order to solve the above technical problems, the technical solution adopted in the present invention is：A kind of nothing with hook lock buffer unit
Man-machine, including fuselage, empennage and wing, the wing includes bottom plate, wing-body and the cunning mutually fixed with the fuselage
Plate；
The bottom plate, which is provided with chute, the chute, is provided with guide pillar, and the first spring, the bottom are provided with the guide pillar
Medium position on plate is provided with a screwed hole, the bottom plate and multiple shallow slots is evenly equipped with centered on screwed hole；
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 a sliding block, the cunning
Block is provided with a through hole, and the sliding block is slidably mounted in the chute, the through hole of the sliding block be arranged on the guide pillar so that
Sliding block 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 provided with close to the side of fuselage
Hole is coaxially disposed, and a screw, which is passed through, to be screwed together on the screwed hole after the connecting hole and make the relatively described bottom of the wing-body
Plate is freely rotated, and the runner that the wing-body two side is provided with concave-arc part, the slide plate is embedded in the concave-arc part, institute
State and be evenly equipped with multiple blind holes on wing-body bottom centered on the connecting hole, the multiple blind hole and the multiple shallow slot one
One correspondence is simultaneously coaxially disposed, and a second spring is provided with each blind hole, the bottom contact of the second spring has a spheroid, institute
Spherical part is stated to be placed in the shallow slot；
Hook lock buffer unit is provided with below the afterbody of the fuselage, the hook lock buffer unit includes being located at the fuselage tail
Slide rail, U-shaped plate and extension spring below portion, the opening direction of the U-shaped plate is towards the fuselage head, and the U-shaped plate includes
The connecting plate of epipleural, lower side panel and the connection epipleural and lower side panel, the epipleural matches with slide rail and merged in cunning
Slided on rail, the rear end of the epipleural has upwardly extended convex portion, the extension spring be provided between the convex portion and the end of slide rail,
It is provided with the epipleural on jointed shaft, the jointed shaft and baffle plate is rotatably connected to by torsion spring, the torsion spring makes the baffle plate
Outer end be resisted against on the lower side panel.
The outer end of the lower side panel has guide ramp.
(3) beneficial effect
The present invention is compared to 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 big, so as to reduce flight resistance, lifts flight efficiency, and effectively wing can be protected not damaged when colliding.
The hook lock buffer unit of the present invention can play the effect of safety and stability landing in landing, reduce and run needed for landing
The setting of slide rail and extension spring in the length in road, and hook lock buffer unit can effectively buffer the impulsive force landed when slowing down.
Brief description of the drawings
Fig. 1 is structural representation of the invention.
Fig. 2 is the sectional view in A-A directions in Fig. 1.
Fig. 3 is the schematic diagram 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 structure chart of the latch hook buffer unit of the present invention.
Embodiment
With reference to the accompanying drawings and examples, the embodiment to the present invention is described in further detail.Following reality
Applying example is used to illustrate the present invention, but is not limited to the scope of the present invention.
As shown in Figures 1 to 4, The embodiment provides a kind of unmanned plane with hook lock buffer unit, including
Fuselage 4, empennage 5 and wing, the wing include bottom plate 1, wing-body 2 and the slide plate 3 mutually fixed with the fuselage 4；
The bottom plate 1, which is provided with chute 11, the chute 11, is provided with guide pillar 12, and the first bullet is provided with the guide pillar 12
Medium position on spring 13, the bottom plate 1 be provided with a screwed hole 14, the bottom plate 1 be evenly equipped with centered on screwed hole 14 it is many
Individual shallow slot 15；
The top both sides of slide plate 3 are respectively equipped with a runner 31, and the two bottom sides of slide plate 3 are respectively equipped with a sliding block 32,
The sliding block 32 is provided with a through hole 33, and the sliding block 32 is slidably mounted in the chute 11, and the through hole 33 of the sliding block 32 is worn
So that the side wall of the sliding block 32 is resisted against first spring 13 on the guide pillar 12；On the side wall of bottom plate 1 also
Provided with a postive stop baffle 16, the postive stop baffle 16 is used for the position for limiting slide plate 3, and anti-limited slip plate 3 is skidded off in sliding process
Outside the track of the chute 11.
On the wing-body 2 connecting hole 21, the connecting hole 21 and the bottom plate 1 are provided with close to the side of fuselage 4
On screwed hole 14 be coaxially disposed, a screw 6 is screwed together on the screwed hole 14 after passing through the connecting hole 21 and makes the machine
Wing body 2 is freely rotated relative to the bottom plate 1, that is to say, that screw 6 is screwed together in after screwed hole 14, and screwed 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 mutually lock wing-body 2 with bottom plate 1；It is described
The runner 31 that the two side of wing-body 2 is provided with concave-arc part 22, the slide plate 3 is embedded in the concave-arc part 22, the wing
Multiple blind holes 23, the multiple blind hole 23 and the multiple shallow slot are evenly equipped with the bottom of body 2 centered on the connecting hole 21
15 are corresponded and are coaxially disposed, and a second spring 24, the bottom contact of the second spring 24 are provided with each blind hole 23
There is a spheroid 25, the part of spheroid 25 is placed in the shallow slot 15.
The shallow slot 15 is provided with 12.Therefore the blind hole 23 is also correspondingly provided with 12.Of course for more accurately making ball
Body 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 reality
Border demand.
Under original state, wing-body 2 is embedded on the first shallow slot 151 of bottom plate 1 by the spheroid 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, reaction force of the front of wing-body 2 meeting by 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 spheroid 25 is sliding out the first shallow slot 151, the outer end of wing-body 2 is rotated, now wing
Concave-arc part 22 on body 2 can promote the spheroid 25 on runner 31, wing-body 2 to be moved towards the second shallow slot 152, at this moment slide
Plate 3 is slided along chute 11, so as to bestow 13 1 thrusts of the first spring, the propulsive thrust of the first spring 13 and the anti-work of air-flow
Firmly offset, at this moment the spheroid 25 on wing-body 2 can be embedded in the second shallow slot 152, when unmanned plane flying speed after
During continuous increase, the spheroid 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 be that center of circle automatic rotary transfers drop with screw 6
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 spheroid 25 is located on the first shallow slot 151.
As shown in figure 5, being provided with hook lock buffer unit below the afterbody of the fuselage 4, the hook lock buffer unit includes setting
Slide rail 41, U-shaped plate and extension spring 42 below the afterbody of fuselage 4, the opening direction of the U-shaped plate is towards the fuselage 4
Head, the U-shaped plate includes the connecting plate 45 of epipleural 43, lower side panel 44 and the connection epipleural 43 and lower side panel 44,
The epipleural 43 matches to merge with slide rail 41 to be slided on slide rail 41, and the rear end of the epipleural 43 has upwardly extended convex portion
46, it is provided between the convex portion 46 and the end of slide rail 41 in the extension spring 42, the epipleural 43 and is provided with jointed shaft 47, it is described
Baffle plate 49 is rotatably connected to by torsion spring 48 on jointed shaft 47, it is described that the torsion spring 48 is resisted against the outer end of the baffle plate 49
On lower side panel 44.The outer end of the lower side panel 44 has guide ramp 50.
When aircraft prepares to land, after being contacted with ground, the landing rope on ground, which can be pushed up, holds baffle plate, enters U-shaped plate
Groove in, U-shaped plate is by after resistance, so as to slow down to connected fuselage, because U-shaped plate passes through extension spring and slide rail phase
Even, extension spring extends after stress, so as to reduce the impulsive force of landing rope.
The present invention is compared to 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 big, so as to reduce flight resistance, lifts flight efficiency, and effectively wing can be protected not damaged when colliding.
The hook lock buffer unit of the present invention can play the effect of safety and stability landing in landing, reduce and run needed for landing
The setting of slide rail and extension spring in the length in road, and hook lock buffer unit can effectively buffer the impulsive force landed when slowing down.
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 use equivalent substitutions or the technical side of equivalent transformation formation
Case, all falls within scope of the present invention.
Claims (2)
1. a kind of unmanned plane with hook lock buffer unit, including fuselage, empennage and wing, it is characterised in that：The wing
Including the bottom plate, wing-body and slide plate mutually fixed with the fuselage；
The bottom plate, which is provided with chute, the chute, is provided with guide pillar, is provided with the guide pillar on the first spring, the bottom plate
Medium position be provided with a screwed hole, multiple shallow slots are evenly equipped with centered on screwed 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 a sliding block, and the sliding block is set
There is a through hole, the sliding block is slidably mounted in the chute, the through hole of the sliding block is arranged on the guide pillar so that described
Sliding block side wall is resisted against first spring；
A connecting hole is provided with close to the side of fuselage on the wing-body, the connecting hole and screwed hole on the bottom plate are same
Axle is set, and a screw, which is passed through, to be screwed together on the screwed hole after the connecting hole and make the relatively described bottom plate of the wing-body certainly
By rotating, the runner that the wing-body two side is provided with concave-arc part, the slide plate is embedded in the concave-arc part, the machine
It is evenly equipped with multiple blind holes on wing body bottom portion centered on the connecting hole, a pair of the multiple blind hole and the multiple shallow slot 1
It and should be coaxially disposed, a second spring be provided with each blind hole, the bottom contact of the second spring has a spheroid, the ball
Body portion is placed in the shallow slot；
Hook lock buffer unit is provided with below the afterbody of the fuselage, the hook lock buffer unit includes being located under the afterbody
Slide rail, U-shaped plate and the extension spring of side, the opening direction of the U-shaped plate is towards the fuselage head, and the U-shaped plate includes upside
The connecting plate of plate, lower side panel and the connection epipleural and lower side panel, the epipleural matches with slide rail and merged on slide rail
Slide, the rear end of the epipleural has upwardly extended convex portion, the extension spring is provided between the convex portion and the end of slide rail, it is described
It is provided with epipleural on jointed shaft, the jointed shaft and baffle plate is rotatably connected to by torsion spring, the torsion spring makes the outer of the baffle plate
End is resisted against on the lower side panel.
2. the unmanned plane according to claim 1 with hook lock buffer unit, it is characterised in that：The outer end of the lower side panel
Portion has guide ramp.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610104090.8A CN105752318B (en) | 2016-02-25 | 2016-02-25 | A kind of unmanned plane with hook lock buffer unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610104090.8A CN105752318B (en) | 2016-02-25 | 2016-02-25 | A kind of unmanned plane with hook lock buffer unit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105752318A CN105752318A (en) | 2016-07-13 |
| CN105752318B true CN105752318B (en) | 2017-09-29 |
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ID=56331285
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610104090.8A Active CN105752318B (en) | 2016-02-25 | 2016-02-25 | A kind of unmanned plane with hook lock buffer unit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105752318B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107651167A (en) * | 2017-09-21 | 2018-02-02 | 应夏英 | A kind of gardens unmanned plane of taking photo by plane |
| CN107745800A (en) * | 2017-10-18 | 2018-03-02 | 单林祥 | One kind builds municipal gardens unmanned plane |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4212441A (en) * | 1978-05-11 | 1980-07-15 | The United States Of America As Represented By The Secretary Of The Air Force | Wing pivot assembly for variable sweep wing aircraft |
| CN102849206A (en) * | 2012-10-30 | 2013-01-02 | 河北科技大学 | Wing folding-unfolding mechanism for small unmanned aerial vehicle with folding wings |
| CN103434651A (en) * | 2013-09-05 | 2013-12-11 | 中国航天时代电子公司 | Novel hook lock buffering device of ejection system |
| CN204750553U (en) * | 2015-07-09 | 2015-11-11 | 武汉智能鸟无人机有限公司 | Collapsible wing of unmanned aerial vehicle |
| CN105173061A (en) * | 2015-08-13 | 2015-12-23 | 中国航空工业集团公司西安飞机设计研究所 | Plane in supersonic speed plane layout |
-
2016
- 2016-02-25 CN CN201610104090.8A patent/CN105752318B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4212441A (en) * | 1978-05-11 | 1980-07-15 | The United States Of America As Represented By The Secretary Of The Air Force | Wing pivot assembly for variable sweep wing aircraft |
| CN102849206A (en) * | 2012-10-30 | 2013-01-02 | 河北科技大学 | Wing folding-unfolding mechanism for small unmanned aerial vehicle with folding wings |
| CN103434651A (en) * | 2013-09-05 | 2013-12-11 | 中国航天时代电子公司 | Novel hook lock buffering device of ejection system |
| CN204750553U (en) * | 2015-07-09 | 2015-11-11 | 武汉智能鸟无人机有限公司 | Collapsible wing of unmanned aerial vehicle |
| CN105173061A (en) * | 2015-08-13 | 2015-12-23 | 中国航空工业集团公司西安飞机设计研究所 | Plane in supersonic speed plane layout |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105752318A (en) | 2016-07-13 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information |
Inventor after: Yu Zhilu Inventor after: Shi Guohu Inventor after: Cui Tao Inventor after: Li Xinfeng Inventor after: Zhu Yun Inventor before: Hu Zenghao |
|
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20170809 Address after: 264000 517 Aerospace Road, hi tech Zone, Shandong, Yantai Applicant after: SHANDONG ZHENG-YUAN DIGITAL CITY CONSTRUCTION CO., LTD. Address before: Jin Shan Shipu town of Xiangshan County of Zhejiang Province in 315700 in Ningbo City Applicant before: Hu Zenghao |
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| GR01 | Patent grant | ||
| GR01 | Patent grant |