CN207510703U - A kind of adjustable unmanned plane wing - Google Patents
A kind of adjustable unmanned plane wing Download PDFInfo
- Publication number
- CN207510703U CN207510703U CN201721454611.9U CN201721454611U CN207510703U CN 207510703 U CN207510703 U CN 207510703U CN 201721454611 U CN201721454611 U CN 201721454611U CN 207510703 U CN207510703 U CN 207510703U
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- CN
- China
- Prior art keywords
- adjusting block
- fuselage
- unmanned plane
- motor
- block
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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- 229910000831 Steel Inorganic materials 0.000 claims abstract description 12
- 239000010959 steel Substances 0.000 claims abstract description 12
- 238000003466 welding Methods 0.000 claims abstract description 7
- 239000000203 mixture Substances 0.000 claims 1
- 238000011889 obduction Methods 0.000 abstract description 7
- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model discloses a kind of adjustable unmanned plane wings, including fuselage, the both sides of the fuselage are installed with main wing, the bottom interior wall of the fuselage is installed with the first motor, the output shaft of first motor is fixedly connected with adjusting block, connecting rod is hinged in adjusting block, there is empennage in one end of the connecting rod through the outside weldings that adjusting block extends to adjusting block, supporting block is equipped in the fuselage, mounting groove is offered in supporting block, adjusting block is located in mounting groove, first motor is located in supporting block, track groove is offered on mounting groove, it is rolled on track groove and steel ball is installed, steel ball is rolled with adjusting block and is connected, horizontally disposed reversed screw is rotatablely equipped in adjusting block, pulley is installed at the top of the reversed screw.The novel adjusting by empennage of the utility model realizes the control in the direction of unmanned plane underriding or obduction and left and right flight, simplifies structure, reduce cost, and stabilized structure is firm, easy to spread.
Description
Technical field
The utility model is related to unmanned air vehicle technique field more particularly to a kind of adjustable unmanned plane wings.
Background technology
Unmanned plane wing includes main wing and empennage, and empennage is particularly important for the control in direction, dives, obduction, and left and right becomes
To flight, depend on empennage to complete, existing empennage adjusts excessively complicated, and empennage support is not secured enough, easily by
Damage, in order to solve problem above, needs, and a kind of adjustable unmanned plane wing meets more than demand.
Utility model content
The purpose of this utility model is and a kind of adjustable nothing proposed in order to solve shortcoming in the prior art
Man-machine wing.
To achieve these goals, the utility model employs following technical solution：
A kind of adjustable unmanned plane wing, including fuselage, the both sides of the fuselage are installed with main wing, the fuselage
Bottom interior wall be installed with the first motor, the output shaft of first motor is fixedly connected with adjusting block, the adjusting block
Connecting rod is inside hinged with, there are empennage, the machine in one end of the connecting rod through the outside weldings that adjusting block extends to adjusting block
Supporting block is equipped in body, offers mounting groove in the supporting block, adjusting block is located in mounting groove, and the first motor is located at supporting block
It is interior, track groove is offered on the mounting groove, is rolled on track groove and steel ball is installed, steel ball is rolled with adjusting block and connected, described
Horizontally disposed reversed screw is rotatablely equipped in adjusting block, is installed with pulley at the top of the reversed screw, pulley with
Supporting block rolls connection, and screw thread is equipped with moving mass on the reversed screw, and the bottom interior wall of the fuselage is installed with the
Two motors are arranged with first bevel gear on the output shaft of the second motor, are arranged with second bevel gear on the reversed screw, and second
Bevel gear engages with first bevel gear, and interlocking bar is hinged on the moving mass, and one end of interlocking bar is cut with scissors through fuselage and empennage
It connects.
Preferably, the reversed screw is made of the first threaded rod, the second threaded rod and cylindrical bar, the both ends point of cylindrical bar
It is not welded with the first threaded rod and the second threaded rod, the hand of spiral of the first threaded rod and the welding of the second threaded rod is on the contrary, adjust
Block is equipped with rectangular through-hole, and cylindrical bar is located in rectangular through-hole.
Preferably, the both sides inner wall of the fuselage is installed with bearing, the both ends of reversed screw respectively in bearing
Circle is fixedly connected, and bearing holder (housing, cover) is set on reversed screw.
Preferably, annular groove is offered at the top of the supporting block, annular groove is connect with pulley rolling.
Preferably, circular open is offered at the top of the fuselage, adjusting block is located in circular open.
Preferably, the steel ball is four, and is respectively uniformly distributed on track groove.
The beneficial effects of the utility model are：First bevel gear and second bevel gear is driven to rotate by the second motor, from
And the movement of interlocking bar is driven, change support angle of the interlocking bar to empennage, realize underriding or the adjusting of obduction, pass through the first electricity
Machine drives the rotation of adjusting block, drives empennage rotation, realizes the angular adjustment of horizontal direction, fly so as to fulfill the left and right of unmanned plane
Capable adjusting.The utility model realizes the direction of unmanned plane underriding or obduction and left and right flight by the adjusting of empennage
Control simplifies structure, reduces cost, and stabilized structure is firm, easy to spread.
Description of the drawings
Fig. 1 be the utility model proposes a kind of adjustable unmanned plane wing structure diagram；
Fig. 2 is the overlooking the structure diagram of supporting block.
In figure：1 fuselage, 2 main wings, 3 first motors, 4 adjusting blocks, 5 connecting rods, 6 empennages, 7 supporting blocks, 8 mounting grooves, 9 rails
Road slot, 10 steel balls, 11 reversed screws, 12 pulleys, 13 moving mass, 14 second motors, 15 first bevel gears, 16 second bevel gears,
17 interlocking bar.
Specific embodiment
The following is a combination of the drawings in the embodiments of the present utility model, and the technical scheme in the embodiment of the utility model is carried out
It clearly and completely describes, it is clear that the described embodiments are only a part of the embodiments of the utility model rather than whole
Embodiment.
With reference to Fig. 1-2, a kind of adjustable unmanned plane wing, including fuselage 1, the both sides of fuselage 1 are installed with main wing
2, the bottom interior wall of fuselage 1 is installed with the first motor 3, and the output shaft of the first motor 3 is fixedly connected with adjusting block 4, adjusts
Connecting rod 5 is hinged in block 4, there are empennage 6, machine in one end of connecting rod 5 through the outside weldings that adjusting block 4 extends to adjusting block 4
Supporting block 7 is equipped in body 1, mounting groove 8 is offered in supporting block 7, adjusting block 4 is located in mounting groove 8, and the first motor 3 is located at branch
In bracer 7, track groove 9 is offered on mounting groove 8, is rolled on track groove 9 and steel ball 10 is installed, steel ball 10 is rolled with adjusting block 4
It connects, is rotatablely equipped with horizontally disposed reversed screw 11 in adjusting block 4, the top of reversed screw 11 is installed with pulley
12, pulley 12 is rolled with supporting block 7 and is connected, and screw thread is equipped with moving mass 13 on reversed screw 11, and the bottom interior wall of fuselage 1 is fixed
Second motor 14 is installed, first bevel gear 15 is arranged on the output shaft of the second motor 14, is arranged on reversed screw 11
Two bevel gears 16, second bevel gear 16 are engaged with first bevel gear 15, and interlocking bar 17 is hinged on moving mass 13, interlocking bar 17
One end is hinged with empennage 6 through fuselage 1.
In the present embodiment, reversed screw 11 is made of the first threaded rod, the second threaded rod and cylindrical bar, the both ends of cylindrical bar
It is welded respectively with the first threaded rod and the second threaded rod, the hand of spiral of the first threaded rod and the welding of the second threaded rod is on the contrary, adjust
Locking nub 4 is equipped with rectangular through-hole, and cylindrical bar is located in rectangular through-hole, and the both sides inner wall of fuselage 1 is installed with bearing, reverse silk
The both ends of bar 11 are fixedly connected respectively with the inner ring of bearing, and bearing holder (housing, cover) is set on reversed screw 11, and the top of supporting block 7 offers
Annular groove, annular groove are rolled with pulley 12 and are connected, and the top of fuselage 1 offers circular open, and adjusting block 4 is opened positioned at circle
In mouthful, steel ball 10 is four, and is respectively uniformly distributed on track groove 9, and 15 He of first bevel gear is driven by the second motor 14
Second bevel gear 16 rotates, and so as to drive the movement of interlocking bar 17, changes support angle of the interlocking bar 17 to empennage 6, realization is bowed
Punching or the adjusting of obduction, the rotation of adjusting block 4 is driven by the first motor 3, and empennage 6 is driven to rotate, realizes the angle of horizontal direction
Degree is adjusted, so as to fulfill the adjusting of the left and right flight of unmanned plane.The utility model realizes unmanned plane by the adjusting of empennage 6
The control in the direction of underriding or obduction and left and right flight, simplifies structure, reduces cost, and stabilized structure is firm, easily
In popularization.
In the present embodiment, first bevel gear 15 is driven to rotate by the second motor 14, first bevel gear 15 drives the second cone
Gear 16 rotates, and so as to drive the movement of interlocking bar 17, interlocking bar 17 drives two moving mass 13 to move toward one another or backwards to fortune
Dynamic, the mobile change interlocking bar 17 of moving mass 13 realizes underriding or the adjusting of obduction, passes through first to the support angle of empennage 6
Motor 3 drives the rotation of adjusting block 4, and empennage 6 is driven to rotate, the angular adjustment of horizontal direction is realized, so as to fulfill unmanned plane
The adjusting of left and right flight, it is simple in structure, cost is reduced, optimizes existing structure, realizes the control of heading.
The preferable specific embodiment of the above, only the utility model, but the scope of protection of the utility model is not
This is confined to, in the technical scope that any one skilled in the art discloses in the utility model, according to this practicality
Novel technical solution and its utility model design are subject to equivalent substitution or change, should all cover the protection model in the utility model
Within enclosing.
Claims (6)
1. a kind of adjustable unmanned plane wing, including fuselage (1), which is characterized in that the both sides of the fuselage (1) are fixedly mounted
There is main wing (2), the bottom interior wall of the fuselage (1) is installed with the first motor (3), the output shaft of first motor (3)
Adjusting block (4) is fixedly connected with, connecting rod (5) is hinged in the adjusting block (4), one end of the connecting rod (5) is through tune
The outside weldings that locking nub (4) extends to adjusting block (4) have empennage (6), and supporting block (7), the support are equipped in the fuselage (1)
Mounting groove (8) is offered on block (7), adjusting block (4) is in mounting groove (8), and the first motor (3) is in supporting block (7), institute
It states and track groove (9) is offered on mounting groove (8), rolled on track groove (9) and steel ball (10), steel ball (10) and adjusting block are installed
(4) connection is rolled, horizontally disposed reversed screw (11), the reversed screw (11) are rotatablely equipped in the adjusting block (4)
Top be installed with pulley (12), pulley (12) is rolled with supporting block (7) and is connected, screw thread peace on the reversed screw (11)
Equipped with moving mass (13), the bottom interior wall of the fuselage (1) is installed with the second motor (14), the output of the second motor (14)
First bevel gear (15) is arranged on axis, second bevel gear (16), second bevel gear are arranged on the reversed screw (11)
(16) it is engaged with first bevel gear (15), interlocking bar (17) is hinged on the moving mass (13), one end of interlocking bar (17) is passed through
It is hinged with empennage (6) to wear fuselage (1).
2. a kind of adjustable unmanned plane wing according to claim 1, which is characterized in that the reversed screw (11) by
First threaded rod, the second threaded rod and cylindrical bar composition, the both ends of cylindrical bar are welded respectively with the first threaded rod and the second threaded rod
It connects, the hand of spiral of the first threaded rod and the welding of the second threaded rod is on the contrary, adjusting block (4) is equipped with rectangular through-hole, cylindrical bar position
In in rectangular through-hole.
A kind of 3. adjustable unmanned plane wing according to claim 1, which is characterized in that the both sides of the fuselage (1)
Inner wall is installed with bearing, and the both ends of reversed screw (11) are fixedly connected respectively with the inner ring of bearing, and bearing holder (housing, cover) is set on reversed
On screw (11).
A kind of 4. adjustable unmanned plane wing according to claim 1, which is characterized in that the top of the supporting block (7)
Portion offers annular groove, and annular groove is rolled with pulley (12) and connected.
A kind of 5. adjustable unmanned plane wing according to claim 1, which is characterized in that the top of the fuselage (1)
Circular open is offered, adjusting block (4) is in circular open.
6. a kind of adjustable unmanned plane wing according to claim 1, which is characterized in that the steel ball (10) is four
It is a, and be respectively uniformly distributed on track groove (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721454611.9U CN207510703U (en) | 2017-11-03 | 2017-11-03 | A kind of adjustable unmanned plane wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721454611.9U CN207510703U (en) | 2017-11-03 | 2017-11-03 | A kind of adjustable unmanned plane wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207510703U true CN207510703U (en) | 2018-06-19 |
Family
ID=62536832
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721454611.9U Expired - Fee Related CN207510703U (en) | 2017-11-03 | 2017-11-03 | A kind of adjustable unmanned plane wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207510703U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108974908A (en) * | 2018-07-27 | 2018-12-11 | 东莞市联洲知识产权运营管理有限公司 | A kind of protective cover structure for conveying on relay packing device |
| CN109823514A (en) * | 2019-02-02 | 2019-05-31 | 北京航空航天大学 | A kind of quick detachable tail structure of adjustable established angle |
-
2017
- 2017-11-03 CN CN201721454611.9U patent/CN207510703U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108974908A (en) * | 2018-07-27 | 2018-12-11 | 东莞市联洲知识产权运营管理有限公司 | A kind of protective cover structure for conveying on relay packing device |
| CN109823514A (en) * | 2019-02-02 | 2019-05-31 | 北京航空航天大学 | A kind of quick detachable tail structure of adjustable established angle |
| CN109823514B (en) * | 2019-02-02 | 2021-01-12 | 北京航空航天大学 | Quick detachable fin structure of adjustable installation angle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180619 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |