CN105667762A - Unmanned aerial vehicle for municipal gardens - Google Patents
Unmanned aerial vehicle for municipal gardens Download PDFInfo
- Publication number
- CN105667762A CN105667762A CN201610192241.XA CN201610192241A CN105667762A CN 105667762 A CN105667762 A CN 105667762A CN 201610192241 A CN201610192241 A CN 201610192241A CN 105667762 A CN105667762 A CN 105667762A
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- China
- Prior art keywords
- wing
- base plate
- hole
- shallow slot
- spring
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- 238000009304 pastoral farming Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 3
- 230000015556 catabolic process Effects 0.000 description 2
- 238000006731 degradation reaction Methods 0.000 description 2
- 230000000694 effects 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
- 230000001737 promoting effect Effects 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
- 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
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
Abstract
The invention discloses an unmanned aerial vehicle for municipal gardens. The unmanned aerial vehicle comprises a vehicle body, a tail wing and wings, wherein each wing comprises a base plate, a wing body and a sliding plate, and the base plate is fixed together with the vehicle body; chutes are formed in the base plates, guide pillars are arranged in the chutes, first springs are mounted on the guide pillars, a threaded hole is formed in the middle of each base plate, and a plurality of shallow grooves are uniformly formed in each base plate by taking the threaded hole as a center; a rotating wheel is arranged on each of two sides of the top of each sliding plate, a sliding block is arranged on each of two sides of the bottom of the sliding plate, a through hole is formed in each sliding block, each sliding block is slidably mounted in the corresponding chute, and the through hole of each sliding block penetrates through the corresponding pillar to enable one side wall of the sliding block to prop against the first spring. According to the unmanned aerial vehicle, grazing angles of the wings can be automatically converted according to different flight speeds, and the wings can be effectively prevented from being damaged during collision.
Description
Technical field
The invention belongs to vehicle technology field, be specifically related to a kind of municipal administration gardens unmanned plane.
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 and empennage are fixing, flight efficiency is less desirable.
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 municipal administration gardens unmanned plane, to solve the problem that wing is easily damaged and unmanned plane during flying is inefficient of the fixed-wing unmanned plane of prior art.
(2) technical scheme
For solving above-mentioned technical problem, the technical solution adopted in the present invention is: a kind of municipal administration gardens unmanned plane, 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,
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.
Described shallow slot is provided with 12.
(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 empennage of the present invention converts the rotational angle of propeller by rotating shaft, it may be achieved slows down, accelerate, 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 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 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 municipal administration gardens unmanned plane, including fuselage 4, empennage 5 and wing, unmanned plane can drive it to fly by the electromotor being placed in below fuselage head or wing, and 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.
Under 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.
As shown in Figure 5, described empennage 5 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 municipal gardens unmanned plane of the present invention can realize the different auto-changing wing sweep angle along with flight speed; when flight speed height, the sweep angle of wing becomes big, thus reducing flight resistance; promote flight efficiency, and can effectively protect when colliding wing not damaged.
The empennage of the present invention converts the rotational angle of propeller by rotating shaft, it may be achieved slows down, accelerate, 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 (2)
1. a municipal gardens unmanned plane, 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,
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.
2. shallow slot according to claim 1, it is characterised in that: described shallow slot is provided with 12.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610192241.XA CN105667762B (en) | 2016-03-30 | 2016-03-30 | A kind of municipal gardens unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610192241.XA CN105667762B (en) | 2016-03-30 | 2016-03-30 | A kind of municipal gardens unmanned plane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105667762A true CN105667762A (en) | 2016-06-15 |
| CN105667762B CN105667762B (en) | 2018-01-05 |
Family
ID=56224679
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610192241.XA Active CN105667762B (en) | 2016-03-30 | 2016-03-30 | A kind of municipal gardens unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105667762B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109552619A (en) * | 2018-12-01 | 2019-04-02 | 江苏鸿鹄无人机应用科技有限公司 | A kind of unmanned plane propeller |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3565369A (en) * | 1968-04-18 | 1971-02-23 | British Aircraft Corp Ltd | Aircraft having variable sweep-back wings |
| US4022403A (en) * | 1976-01-28 | 1977-05-10 | Louis Francois Chiquet | Convertible aircraft |
| US5671899A (en) * | 1996-02-26 | 1997-09-30 | Lockheed Martin Corporation | Airborne vehicle with wing extension and roll control |
| US7185847B1 (en) * | 2004-05-13 | 2007-03-06 | Raytheon Company | Winged vehicle with variable-sweep cantilevered wing mounted on a translating wing-support body |
| CN200995782Y (en) * | 2007-01-17 | 2007-12-26 | 赵文志 | Airplane |
| CN104925247A (en) * | 2015-05-26 | 2015-09-23 | 李宏生 | Helicopter with multiple propellers inclining forwards |
| CN105366033A (en) * | 2015-11-10 | 2016-03-02 | 中国空气动力研究与发展中心高速空气动力研究所 | Wing dissymmetric backswept rolling control method for gliding aircrafts |
-
2016
- 2016-03-30 CN CN201610192241.XA patent/CN105667762B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3565369A (en) * | 1968-04-18 | 1971-02-23 | British Aircraft Corp Ltd | Aircraft having variable sweep-back wings |
| US4022403A (en) * | 1976-01-28 | 1977-05-10 | Louis Francois Chiquet | Convertible aircraft |
| US5671899A (en) * | 1996-02-26 | 1997-09-30 | Lockheed Martin Corporation | Airborne vehicle with wing extension and roll control |
| US7185847B1 (en) * | 2004-05-13 | 2007-03-06 | Raytheon Company | Winged vehicle with variable-sweep cantilevered wing mounted on a translating wing-support body |
| CN200995782Y (en) * | 2007-01-17 | 2007-12-26 | 赵文志 | Airplane |
| CN104925247A (en) * | 2015-05-26 | 2015-09-23 | 李宏生 | Helicopter with multiple propellers inclining forwards |
| CN105366033A (en) * | 2015-11-10 | 2016-03-02 | 中国空气动力研究与发展中心高速空气动力研究所 | Wing dissymmetric backswept rolling control method for gliding aircrafts |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109552619A (en) * | 2018-12-01 | 2019-04-02 | 江苏鸿鹄无人机应用科技有限公司 | A kind of unmanned plane propeller |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105667762B (en) | 2018-01-05 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20171113 Address after: 100088 Beijing City, Haidian District Zhichun Road Jinqiu International Building No. 6 room 508 building A Applicant after: Beijing fortune Intellectual Property Consulting Co., Ltd. Address before: Xiangshan County, Zhejiang province 315700 Ningbo Zhen Tang Ao Cun Tu Ci Applicant before: Zhong Xianhui |
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| TA01 | Transfer of patent application right | ||
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Effective date of registration: 20171201 Address after: 710003 Shaanxi province Xi'an national civil aerospace industry base Shenzhou four road set up the international square C seat 3 floor 302 room Applicant after: Xi'an Jingdong Tianhong science and Technology Co., Ltd. Address before: 100088 Beijing City, Haidian District Zhichun Road Jinqiu International Building No. 6 room 508 building A Applicant before: Beijing fortune Intellectual Property Consulting Co., Ltd. |
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