CN105799911A - Folding-wing unmanned plane for energy-saving and environment-friendly constructional engineering - Google Patents
Folding-wing unmanned plane for energy-saving and environment-friendly constructional engineering Download PDFInfo
- Publication number
- CN105799911A CN105799911A CN201610305811.1A CN201610305811A CN105799911A CN 105799911 A CN105799911 A CN 105799911A CN 201610305811 A CN201610305811 A CN 201610305811A CN 105799911 A CN105799911 A CN 105799911A
- Authority
- CN
- China
- Prior art keywords
- wing
- slide block
- slide
- hole
- base plate
- 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.)
- Granted
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 10
- 230000000149 penetrating effect Effects 0.000 abstract 1
- 230000015556 catabolic process Effects 0.000 description 2
- 238000006731 degradation reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000001737 promoting effect Effects 0.000 description 2
- 230000001141 propulsive effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- LENZDBCJOHFCAS-UHFFFAOYSA-N tris Chemical compound OCC(N)(CO)CO LENZDBCJOHFCAS-UHFFFAOYSA-N 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
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
-
- 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
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Wind Motors (AREA)
Abstract
The invention discloses a folding-wing unmanned plane for energy-saving and environment-friendly constructional engineering. The folding-wing unmanned plane comprises a plane body, a tail fin and wings, wherein the wings are connected with the plane body through folding mechanisms; each wing comprises a bottom plate, a wing body and a sliding plate; a slide chute is formed in the upper part of each bottom plate; a guide post is arranged in each slide chute; a first spring is arranged on each guide post; a threaded hole is formed in the middle of the bottom plate; a plurality of shallow slots are evenly distributed in the bottom plate with the threaded hole as the center; runners are arranged at two sides of the top part of the sliding plate, respectively; first slide blocks are arranged at two sides of the bottom part of the sliding plate, respectively; a through hole is formed in each first slide block; each first slide block is arranged in the corresponding slide chute in a sliding manner; the through hole of each first slide block is formed in the corresponding guide post in a penetrating manner, so that one side wall of the first slide block abuts on the corresponding first spring. The sweep angle of each wing can be automatically changed along with different flight speeds, so that the flight efficiency is improved, and the wings can be effectively prevented from being damaged in collision.
Description
Technical field
The invention belongs to vehicle technology field, be specifically related to a kind of electric ship.
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.
Additionally the unmanned plane of fixed-wing due to the span longer, storage inconvenience, take up room big.
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 energy-conserving and environment-protective architectural engineering folding wings unmanned plane, and the wing to solve the unmanned plane of prior art is easily damaged, and unmanned plane during flying is inefficient, and take up room big problem.
(2) technical scheme
For solving above-mentioned technical problem, the technical solution adopted in the present invention is: a kind of energy-conserving and environment-protective architectural engineering folding wings unmanned plane, including fuselage, empennage and wing, described wing is connected with fuselage by fold mechanism, and described wing includes base plate, wing-body and slide plate；
Described base plate is arranged over 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 one first slide block, described first slide block is provided with a through hole, described first skid is installed in described chute, and the through hole of described first slide block is arranged on described guide pillar so that described first 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；
Described fold mechanism includes the slide rail and the second slide block that are fixed on described fuselage, described slide rail includes the flat segments at middle part and is located at the segmental arc of flat segments both sides, described flat segments is installed with double end cylinder, the described segmental arc of both sides is slidably installed the second slide block described in respectively, described second slide block connects a jacking block by axis of rotation, the vertical direction of the both sides outfan of described double end cylinder is connected to a jacking block cylinder, the outfan of described jacking block cylinder connects described jacking block, and described second slide block is also fixed the base plate connecting described wing；
Described empennage includes the first motor being located in back body portion and the connection ring extending back body, it is connected to rotating shaft by bearing in described connection ring, described rotating shaft horizontally set, described rotating shaft is fixedly connected with travelling gear, described first motor drives described travelling gear by driving gear, the two ends place of described rotating shaft is respectively provided with one second motor, and the output shaft of described second motor is connected to propeller.
(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；
Owing to being provided with fold mechanism, folding wing can be facilitated, it is simple to deposit, there is practicality；
Owing to empennage can convert the rotational angle of propeller by rotating shaft, thus realizing deceleration, accelerating, having assisted degradation effect.
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 top plan view 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 fold mechanism of the present invention.
Fig. 6 is the schematic diagram of the empennage 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 energy-conserving and environment-protective architectural engineering folding wings unmanned plane, including fuselage 4, empennage 50 and wing, described wing is connected with fuselage 4 by fold mechanism, and described wing includes base plate 1, wing-body 2 and slide plate 3；
Described base plate 1 is arranged over 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 one first slide block 32, described first slide block 32 is provided with a through hole 33, described first slide block 32 is slidably mounted in described chute 11, and the through hole 33 of described first slide block 32 is arranged on described guide pillar 12 so that described first 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 25 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 50 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 the present invention 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.
As shown in Figure 5, described fold mechanism includes the slide rail 80 and the second slide block 81 that are fixed on described fuselage 4, described slide rail 80 includes the flat segments 801 at middle part and is located at the segmental arc 802 of flat segments both sides, described flat segments 801 is installed with double end cylinder 82, the described segmental arc 802 of both sides is slidably installed the second slide block 81 described in respectively, described second slide block 81 is rotationally connected a jacking block 84 by rotating shaft 83, the vertical direction of the both sides outfan of described double end cylinder 82 is connected to a jacking block cylinder 85, the outfan of described jacking block cylinder 85 connects described jacking block 84, described second slide block 81 is also fixed the base plate 1 connecting described wing.
When needs folding or expansion wing, the outfan of double end cylinder stretches or inward collapsible to both sides, and jacking block cylinder and double end cylinder link simultaneously, makes jacking block promote slide block to slide along slide rail, thus driving base plate to rotate.
As shown in Figure 6, described empennage 50 includes the first motor 51 being located in fuselage 4 rearward end and the connection ring 54 extending fuselage 4 rear end, it is connected to rotating shaft 55 by bearing in described connection ring 54, described rotating shaft 55 horizontally set, described rotating shaft 55 is fixedly connected with travelling gear 53, described first motor 51 drives described travelling gear 53 by driving gear 52, the two ends place of described rotating shaft 55 is respectively provided with one second motor 57, and the output shaft of described second motor 57 is connected to propeller 56.First motor 51 drives travelling gear 53 to rotate by driving gear 52, and travelling gear 53 is rotated axle 55 and rotates in connection ring 54, the therefore rotational angle of scalable propeller.
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；
Owing to being provided with fold mechanism, folding wing can be facilitated, it is simple to deposit, there is practicality；
Owing to empennage can convert the rotational angle of propeller by rotating shaft, thus realizing deceleration, accelerating, having assisted degradation effect.
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 (1)
1. an energy-conserving and environment-protective architectural engineering folding wings unmanned plane, including fuselage, empennage and wing, it is characterised in that: described wing is connected with fuselage by fold mechanism, and described wing includes base plate, wing-body and slide plate；
Described base plate is arranged over 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 one first slide block, described first slide block is provided with a through hole, described first skid is installed in described chute, and the through hole of described first slide block is arranged on described guide pillar so that described first 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；
Described fold mechanism includes the slide rail and the second slide block that are fixed on described fuselage, described slide rail includes the flat segments at middle part and is located at the segmental arc of flat segments both sides, described flat segments is installed with double end cylinder, the described segmental arc of both sides is slidably installed the second slide block described in respectively, described second slide block connects a jacking block by axis of rotation, the vertical direction of the both sides outfan of described double end cylinder is connected to a jacking block cylinder, the outfan of described jacking block cylinder connects described jacking block, and described second slide block is also fixed the base plate connecting described wing；
Described empennage includes the first motor being located in back body portion and the connection ring extending back body, it is connected to rotating shaft by bearing in described connection ring, described rotating shaft horizontally set, described rotating shaft is fixedly connected with travelling gear, described first motor drives described travelling gear by driving gear, the two ends place of described rotating shaft is respectively provided with one second motor, and the output shaft of described second motor is connected to propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610305811.1A CN105799911B (en) | 2016-05-10 | 2016-05-10 | A kind of energy-conserving and environment-protective architectural engineering folding wings unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610305811.1A CN105799911B (en) | 2016-05-10 | 2016-05-10 | A kind of energy-conserving and environment-protective architectural engineering folding wings unmanned plane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105799911A true CN105799911A (en) | 2016-07-27 |
| CN105799911B CN105799911B (en) | 2017-11-21 |
Family
ID=56456708
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610305811.1A Active CN105799911B (en) | 2016-05-10 | 2016-05-10 | A kind of energy-conserving and environment-protective architectural engineering folding wings unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105799911B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107471936A (en) * | 2017-09-21 | 2017-12-15 | 张龙 | Hovercar |
| CN108033012A (en) * | 2017-12-13 | 2018-05-15 | 四川宝天智控系统有限公司 | VTOL fixed-wings unmanned plane and its fixed wing structure |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| NO345905B1 (en) * | 2020-01-10 | 2021-10-04 | Griff Aviation As | A foldable propeller assembly |
Citations (5)
| 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 |
| US20130341467A1 (en) * | 2012-06-21 | 2013-12-26 | Seiya Sakurai | Swing tip assembly rotation joint |
| 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 |
-
2016
- 2016-05-10 CN CN201610305811.1A patent/CN105799911B/en active Active
Patent Citations (5)
| 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 |
| US20130341467A1 (en) * | 2012-06-21 | 2013-12-26 | Seiya Sakurai | Swing tip assembly rotation joint |
| 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 |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107471936A (en) * | 2017-09-21 | 2017-12-15 | 张龙 | Hovercar |
| CN108033012A (en) * | 2017-12-13 | 2018-05-15 | 四川宝天智控系统有限公司 | VTOL fixed-wings unmanned plane and its fixed wing structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105799911B (en) | 2017-11-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105905275A (en) | Environment-friendly unmanned aerial vehicle for constructional engineering | |
| CN105923158B (en) | A kind of municipal afforestation folding wings unmanned plane | |
| CN105620720B (en) | One kind is taken photo by plane folding wings unmanned plane | |
| CN105620719B (en) | A kind of municipal gardens folding wings unmanned plane | |
| CN103963958B (en) | Unmanned plane wingfold mechanism | |
| CN103072688B (en) | Can be verted quadrotor | |
| CN105799911A (en) | Folding-wing unmanned plane for energy-saving and environment-friendly constructional engineering | |
| CN105438458A (en) | Double-layer and eight-rotor-wing aircraft | |
| CN110116806B (en) | Device for butt joint of fixed-wing unmanned aerial vehicle and rotor wing launching platform | |
| CN211195749U (en) | Tilt shaftless duct rotor aerocar | |
| CN105197237A (en) | Vertical takeoff and landing unmanned aerial vehicle | |
| CN110654190A (en) | Tilting shaftless ducted rotor aerocar and working method thereof | |
| CN105691593A (en) | Folding-wing unmanned aerial vehicle | |
| CN110753631A (en) | Turnover type propeller device | |
| CN105667763B (en) | A kind of municipal afforestation folding wings unmanned plane | |
| CN105173076A (en) | VTOL (vertical take-off and landing) UAV (unmanned aerial vehicle) | |
| CN105711810B (en) | A kind of municipal afforestation folding wings unmanned plane of improvement | |
| CN105905276A (en) | Folding wing unmanned aerial vehicle for constructional engineering | |
| CN105346725A (en) | Vertical take-off and landing unmanned aerial vehicle | |
| CN105667762A (en) | Unmanned aerial vehicle for municipal gardens | |
| CN205837192U (en) | Can be verted tail-rotor | |
| CN105752318A (en) | Unmanned aerial vehicle with hook lock buffer device | |
| CN204489182U (en) | A kind of collapsible blade of autogiro | |
| CN211711113U (en) | A take-off and landing device for unmanned aerial vehicle aerial emission platform | |
| CN101723088A (en) | Stability control mechanism for dish aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20170810 Address after: 510640 Guangdong City, Tianhe District Province, No. five, road, public education building, unit 371-1, unit 2401 Applicant after: Guangdong Gaohang Intellectual Property Operation Co., Ltd. Address before: Xiangshan County town of 315700 village Shipu Zhejiang province Ningbo City, No. 329 Applicant before: Zhong Songmei |
|
| TA01 | Transfer of patent application right | ||
| CB03 | Change of inventor or designer information |
Inventor after: Lv Qiujun Inventor after: Li Shuqi Inventor after: Li Shuting Inventor after: Zhang Ben Inventor before: Zhong Songmei |
|
| CB03 | Change of inventor or designer information | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20171013 Address after: 150000 F420 room 153, Zhongshan Road 83, Nangang District, Heilongjiang, Harbin Applicant after: Harbin Construction Technology Co., Ltd. Applicant after: Beijing Hong Tour Technology Co., Ltd. Address before: 510640 Guangdong City, Tianhe District Province, No. five, road, public education building, unit 371-1, unit 2401 Applicant before: Guangdong Gaohang Intellectual Property Operation Co., Ltd. |
|
| TA01 | Transfer of patent application right | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |