CN105752318A - Unmanned aerial vehicle with hook lock buffer device - Google Patents
Unmanned aerial vehicle with hook lock buffer device Download PDFInfo
- Publication number
- CN105752318A CN105752318A CN201610104090.8A CN201610104090A CN105752318A CN 105752318 A CN105752318 A CN 105752318A CN 201610104090 A CN201610104090 A CN 201610104090A CN 105752318 A CN105752318 A CN 105752318A
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- CN
- China
- Prior art keywords
- wing
- plate
- hole
- sliding
- spring
- 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.)
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Classifications
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- 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
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- 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
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- 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
Abstract
The invention discloses an unmanned aerial vehicle with a hook lock buffer device. The unmanned aerial vehicle comprises an aerial vehicle body, a tail wing and airfoils; the airfoils comprise bottom plates fixed together with the aerial vehicle body, airfoil bodies and sliding plates; the bottom plates are provided with sliding slots; the sliding slots are internally provided with guide pillars; the guide pillars are provided with first springs; the central part of each bottom plate is provided with a threaded hole; multiple shallow slots are uniformly formed in each bottom plate by taking the threaded hole as a center; two sides of the top of each sliding plate are respectively provided with a rotating wheel; two sides of the bottom of each sliding plate are respectively provided with a sliding block; each sliding block is provided with a through hole; the sliding blocks are slidably arranged in the sliding slots; the through holes of the sliding blocks penetrate through the guide pillars so as to ensure that one side wall of each sliding block props against the corresponding first spring. The unmanned aerial vehicle is capable of automatically changing the grazing angles of the airfoils along with the flying speed; when the flying speed is high, the grazing angles of the airfoils increase, so that the flight resistance is reduced, the flight efficiency is improved, and the airfoils are effectively protected from being damaged during collision.
Description
Technical field
The invention belongs to vehicle technology field, be specifically related to a kind of unmanned plane with hook lock buffer unit.
Background technology
Existing fixed-wing unmanned plane, owing to wing is fixing, so one of becoming the parts of most rapid wear, and owing to wing is fixing, flight efficiency is less desirable.After flight speed is too fast, or landing distance is too in short-term, it is difficult to reach, by controlling speed, the effect that safety and stability is landed.
Summary of the invention
(1) to solve the technical problem that
The technical problem to be solved in the present invention is to provide a kind of unmanned plane with hook lock buffer unit, and the wing to solve the fixed-wing unmanned plane of prior art is easily damaged and unmanned plane during flying is inefficient, and unsafe problem of landing.
(2) technical scheme
For solving above-mentioned technical problem, the technical solution adopted in the present invention is: a kind of unmanned plane with hook lock buffer unit, and including fuselage, empennage and wing, described wing includes the base plate, wing-body and the slide plate that fix with described fuselage；
Described base plate is provided with chute, is provided with guide pillar in described chute, and described guide pillar is provided with the first spring, and the medium position on described base plate is provided with a screwed hole, and described base plate is evenly equipped with multiple shallow slot centered by screwed hole；
Described slide plate top is respectively provided on two sides with a runner, described slide plate two bottom sides is respectively equipped with a slide block, described slide block is provided with a through hole, and described skid is installed in described chute, and the through hole of described slide block is arranged on described guide pillar so that described slide block one sidewall is resisted against described first spring；
On described wing-body, the side near fuselage is provided with a connecting hole, described connecting hole is coaxially disposed with the screwed hole on described base plate, one screw is screwed together on described screwed hole and makes the relatively described base plate of described wing-body freely rotatable after described connecting hole, described wing-body two side is provided with concave-arc part, runner on described slide plate is embedded in described concave-arc part, centered by described connecting hole, multiple blind hole it is evenly equipped with on bottom described wing-body, the plurality of blind hole and the plurality of shallow slot one_to_one corresponding are also coaxially disposed, one second spring it is provided with in each blind hole, the bottom contact of described second spring has a spheroid, described spherical part is placed in described shallow slot；
The afterbody of described fuselage is connected with hook lock buffer unit, described hook lock buffer unit includes being located at the slide rail below described afterbody, U-shaped plate and extension spring, the opening direction of described U-shaped plate is towards described fuselage head, described U-shaped plate includes epipleural, lower side panel and connect the connecting plate of described epipleural and lower side panel, described epipleural and slide rail match and are incorporated on slide rail and slide, the rear end of described epipleural has upwardly extended protuberance, described extension spring it is provided with between described protuberance and the end of slide rail, it is provided with jointed shaft in described epipleural, described jointed shaft is rotatably connected to baffle plate by torsion spring, described torsion spring makes the outer end of described baffle plate be resisted against on described lower side panel.
The outer end of described 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 realize the different auto-changing wing sweep angle along with flight speed, and when flight speed height, the sweep angle of wing becomes big, thus reducing flight resistance, promoting flight efficiency, and can effectively protect when colliding wing not damaged.
The hook lock buffer unit of the present invention can play, when landing, the effect that safety and stability is landed, and reduces the length of the required runway that lands, and slide rail and the arranging of extension spring on hook lock buffer unit can effectively cushion the impulsive force landed when slowing down.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention.
Fig. 2 is the sectional view in A-A direction in Fig. 1.
Fig. 3 is the schematic diagram of the base 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.
Detailed description of the invention
Below in conjunction with drawings and Examples, the specific embodiment of the present invention is described in further detail.Following example are used for illustrating the present invention, but are 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, described wing includes the base plate 1, wing-body 2 and the slide plate 3 that fix with described fuselage 4；
Described base plate 1 is provided with chute 11, is provided with guide pillar 12 in described chute 11, and described guide pillar 12 is provided with the first spring 13, and the medium position on described base plate 1 is provided with a screwed hole 14, and described base plate 1 is evenly equipped with multiple shallow slot 15 centered by screwed hole 14；
Described slide plate 3 top is respectively provided on two sides with a runner 31, described slide plate 3 two bottom sides is respectively equipped with a slide block 32, described slide block 32 is provided with a through hole 33, described slide block 32 is slidably mounted in described chute 11, and the through hole 33 of described slide block 32 is arranged on described guide pillar 12 so that described slide block 32 1 sidewall is resisted against described first spring 13；Being additionally provided with a postive stop baffle 16 on described base plate 1 one sidewall, described postive stop baffle 16 is for limiting the position of slide plate 3, it is prevented that slide plate 3 skids off outside the track of described chute 11 in sliding process.
On described wing-body 2, the side near fuselage 4 is provided with a connecting hole 21, described connecting hole 21 is coaxially disposed with the screwed hole 14 on described base plate 1, one screw 6 is screwed together on described screwed hole 14 and makes the relatively described base plate 1 of described wing-body 2 freely rotatable after described connecting hole 21, that is, after screw 6 is screwed together in screwed hole 14, screw 6 is positioned at the length outside screwed hole 14 and is a bit larger tham the thickness of wing-body 2 so that wing-body 2 will not be locked with base plate 1 phase by screw 6；Described wing-body 2 two side is provided with concave-arc part 22, runner 31 on described slide plate 3 is embedded in described concave-arc part 22, centered by described connecting hole 21, multiple blind hole 23 it is evenly equipped with on bottom described wing-body 2, the plurality of blind hole 23 and the plurality of shallow slot 15 one_to_one corresponding are also coaxially disposed, one second spring 24 it is provided with in each blind hole 23, the bottom contact of described second spring 24 has a spheroid 25, and described spheroid 25 part is placed in described shallow slot 15.
Described shallow slot 15 is provided with 12.Therefore described blind hole 23 is also correspondingly provided with 12.It is sticked in shallow slot 15 of course for making spheroid more accurately, it is possible to increase the quantity of shallow slot 15 and the depth of shallow slot 15 in design, specifically how to select to see actual demand.
nullUnder original state，Wing-body 2 is embedded on the first shallow slot 151 of base plate 1 by the spheroid 25 in blind hole 23，And wing-body 2 is positioned on base plate 1 by screw 6，Therefore wing-body 2 and base plate 1 can keep relative static conditions，When its flight，Wing-body 2 front can be subject to the counteracting force of air-flow，The outer end making wing-body 2 can have the trend towards empennage 5 motion，When this counteracting force makes spheroid 25 be sliding out the first shallow slot 151，The outer end of wing-body 2 rotates，Now the concave-arc part 22 on wing-body 2 can promote runner 31，Spheroid 25 on wing-body 2 can move towards the second shallow slot 152，At this moment slide plate 3 slides along chute 11，Thus bestowing 12 1 thrusts of the first spring，The propulsive thrust of the first spring 12 offsets with the counteracting force of air-flow，At this moment the spheroid 25 on wing-body 2 can be embedded in the second shallow slot 152，When the flight speed of unmanned plane continues to increase，Spheroid 25 on wing-body 2 can move towards the 3rd shallow slot 153，It is achieved thereby that can according to the function of flight speed auto-changing wing sweep angle.When wing-body 2 collides, wing-body 2 can transfer, with screw 6, the probability reducing damage for center of circle automatic rotary.When stopping flight, wing-body 2 can be returned to initial position by the propulsive thrust of the first spring 12, namely makes spheroid 25 be positioned on the first shallow slot 151.
nullAs shown in Figure 5，The afterbody of described fuselage 4 is connected with hook lock buffer unit，Described hook lock buffer unit includes being located at the slide rail 41 below described fuselage 4 afterbody、U-shaped plate and extension spring 42，The opening direction of described U-shaped plate is towards described fuselage 4 head，Described U-shaped plate includes epipleural 43、Lower side panel 44 and connect the connecting plate 45 of described epipleural 43 and lower side panel 44，Described epipleural 43 matches with slide rail 41 and is incorporated on slide rail 41 and slides，The rear end of described epipleural 43 has upwardly extended protuberance 46，Described extension spring 42 it is provided with between described protuberance 46 and the end of slide rail 41，It is provided with jointed shaft 47 in described epipleural 43，Described jointed shaft 47 is rotatably connected to baffle plate 49 by torsion spring 48，Described torsion spring 48 makes the outer end of described baffle plate 49 be resisted against on described lower side panel 44.The outer end of described lower side panel 44 has guide ramp 50.
When aircraft prepares to land, after earth surface, ground landing rope can back down baffle plate, enter in the groove of U-shaped plate, after U-shaped plate is subject to resistance, thus connected fuselage is slowed down, owing to U-shaped plate is connected with slide rail by extension spring, extension spring elongation after stress, thus the impulsive force of landing rope can be reduced.
The present invention is compared to prior art, has the advantages that
The present invention can realize the different auto-changing wing sweep angle along with flight speed, and when flight speed height, the sweep angle of wing becomes big, thus reducing flight resistance, promoting flight efficiency, and can effectively protect when colliding wing not damaged.
The hook lock buffer unit of the present invention can play, when landing, the effect that safety and stability is landed, and reduces the length of the required runway that lands, and slide rail and the arranging of extension spring on hook lock buffer unit can effectively cushion the impulsive force landed when slowing down.
Certainly, above is only the concrete exemplary applications of the present invention, and protection scope of the present invention is not constituted any limitation.In addition to the implementation, the present invention can also have other embodiment.All employings are equal to replacement or the technical scheme of equivalent transformation formation, all fall within present invention scope required for protection.
Claims (2)
1. there is a unmanned plane for hook lock buffer unit, including fuselage, empennage and wing, it is characterised in that: described wing includes the base plate, wing-body and the slide plate that fix with described fuselage；
Described base plate is provided with chute, is provided with guide pillar in described chute, and described guide pillar is provided with the first spring, and the medium position on described base plate is provided with a screwed hole, and described base plate is evenly equipped with multiple shallow slot centered by screwed hole；
Described slide plate top is respectively provided on two sides with a runner, described slide plate two bottom sides is respectively equipped with a slide block, described slide block is provided with a through hole, and described skid is installed in described chute, and the through hole of described slide block is arranged on described guide pillar so that described slide block one sidewall is resisted against described first spring；
On described wing-body, the side near fuselage is provided with a connecting hole, described connecting hole is coaxially disposed with the screwed hole on described base plate, one screw is screwed together on described screwed hole and makes the relatively described base plate of described wing-body freely rotatable after described connecting hole, described wing-body two side is provided with concave-arc part, runner on described slide plate is embedded in described concave-arc part, centered by described connecting hole, multiple blind hole it is evenly equipped with on bottom described wing-body, the plurality of blind hole and the plurality of shallow slot one_to_one corresponding are also coaxially disposed, one second spring it is provided with in each blind hole, the bottom contact of described second spring has a spheroid, described spherical part is placed in described shallow slot；
The afterbody of described fuselage is connected with hook lock buffer unit, described hook lock buffer unit includes being located at the slide rail below described afterbody, U-shaped plate and extension spring, the opening direction of described U-shaped plate is towards described fuselage head, described U-shaped plate includes epipleural, lower side panel and connect the connecting plate of described epipleural and lower side panel, described epipleural and slide rail match and are incorporated on slide rail and slide, the rear end of described epipleural has upwardly extended protuberance, described extension spring it is provided with between described protuberance and the end of slide rail, it is provided with jointed shaft in described epipleural, described jointed shaft is rotatably connected to baffle plate by torsion spring, described torsion spring makes the outer end of described baffle plate be resisted against on described lower side panel.
2. lower side panel according to claim 1, it is characterised in that: the outer end of described lower side panel 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 true CN105752318A (en) | 2016-07-13 |
| CN105752318B CN105752318B (en) | 2017-09-29 |
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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 |
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| Country | Link |
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| CN (1) | CN105752318B (en) |
Cited By (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 |
Cited By (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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105752318B (en) | 2017-09-29 |
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| 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 |
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| 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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