CN109018303A - A kind of aircraft horizontal tail wing that can quickly face upward with nutation - Google Patents
A kind of aircraft horizontal tail wing that can quickly face upward with nutation Download PDFInfo
- Publication number
- CN109018303A CN109018303A CN201810924644.8A CN201810924644A CN109018303A CN 109018303 A CN109018303 A CN 109018303A CN 201810924644 A CN201810924644 A CN 201810924644A CN 109018303 A CN109018303 A CN 109018303A
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- CN
- China
- Prior art keywords
- fixedly connected
- tailplane
- groove
- nutation
- horizontal tail
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- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/26—Transmitting means without power amplification or where power amplification is irrelevant
- B64C13/28—Transmitting means without power amplification or where power amplification is irrelevant mechanical
- B64C13/34—Transmitting means without power amplification or where power amplification is irrelevant mechanical using toothed gearing
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Automation & Control Theory (AREA)
- Toys (AREA)
Abstract
The invention discloses the aircraft horizontal tail wings that one kind can quickly face upward with nutation, it is related to tailplane technical field, it includes body, the upper surface of the body and the lower surface of pedestal overlap, the left and right sides of the pedestal are opened up there are two the second through-hole, the first disposed thread is provided in second through-hole, the first disposed thread internal screw thread is connected with rotating device, and the rotating device is threaded in the second disposed thread.The aircraft horizontal tail wing that can quickly face upward with nutation, pass through setting electric pushrod, slide plate, sliding slot, the second tailplane, first through hole and the first groove, so that slide plate drives the second tailplane to be moved to the left, staff's two, control right side electric pushrod work in an identical manner again, two the second tailplanes are unfolded, the contact area for improving air and first level empennage and the second tailplane, to play the effect for allowing aircraft to carry out flight adjustment in a short time.
Description
Technical field
The present invention relates to tailplane technical field, specially a kind of aircraft horizontal tail wing that can quickly face upward with nutation.
Background technique
Tailplane, also known as " horizontal tail " refer to the aerofoil for keeping aircraft portrait (pitching) to stablize and manipulate, in most aircrafts
On, symmetrically device becomes a part of empennage in tail portion for it, has a small number of aircrafts that it is arranged in front of wing.
It can all be provided with tailplane on most aircraft, when aircraft needs to carry out urgent avoidance, promptly face upward and dive
When, tailplane, which can not achieve to spread apart, pushes empennage to be extended, and the contact area of air and empennage cannot be improved, so that flying
Machine cannot carry out the effect of flight adjustment in a short time.
Summary of the invention
In view of the deficiencies of the prior art, the present invention provides the aircraft horizontal tail wings that one kind can quickly face upward with nutation, solve
When aircraft needs to carry out urgent avoidance, when promptly facing upward and diving, tailplane, which can not achieve to spread apart, pushes empennage progress
Extend, the contact area of air and empennage cannot be improved, prevent aircraft is from a short time carrying out the effect of flight adjustment
Problem.
To achieve the above objectives, the technical solution adopted by the present invention is that: the aircraft horizontal tail that can quickly face upward with nutation of one kind
The wing, including body, the upper surface of the body and the lower surface of pedestal overlap, and the left and right sides of the pedestal offer two
A second through-hole is provided with the first disposed thread in second through-hole, and the first disposed thread internal screw thread is connected with rotation
Device, the rotating device are threaded in the second disposed thread, and second disposed thread is arranged in third groove, institute
The left side that third groove is provided with body is stated, the upper surface of the pedestal is fixedly connected with the lower surface of baffle, the baffle
Left and right sides be fixedly connected to first level empennage, the right side of the first level empennage offers the first groove.
The second tailplane is provided in first groove, the right side of second tailplane is fixedly connected with cunning
Plate, the slide plate slides are connected in two sliding slots, and two sliding slots are provided with the upper surface of the first groove inner wall under respectively
The right side on surface, the slide plate is fixedly connected by electric pushrod with the left side of baffle, and second tailplane is located at
In first through hole, the first through hole is provided with the left side of the first groove inner wall, the left side of the first level empennage inner wall
Face is connected with second bearing, is socketed with shaft in the second bearing.
The outer surface of the shaft is socketed with first bearing, and the first bearing is connected to the right side of tailplane inner wall
Face, the outer surface of the shaft are fixedly connected with elevator, and the lower surface of the elevator offers the second groove, and described second
Transmission device is provided in groove, the transmission device is connected to the outer surface of shaft, the right side of the transmission device and drive
The left end of dynamic device is fixedly connected, and the lower surface of the driving device is fixedly connected to the upper surface of the base.
Preferably, the transmission device includes driven gear, and the driven gear is connected to the outer surface of shaft, it is described from
Moving gear is meshed with driving gear, and the right side of the driving gear is fixedly connected with the left end of driving device.
Preferably, the driving device includes dual-axle motor, two output shafts of the dual-axle motor respectively with two masters
The left and right sides of moving gear are fixedly connected, and the lower surface of the dual-axle motor fuselage is solid by the upper surface of fixed plate and pedestal
Fixed connection.
Preferably, the rotating device includes screw head, and the lower surface of the screw head is fixedly connected with threaded rod, the screw thread
Bar is threaded in the first disposed thread and the second disposed thread.
Preferably, the first level empennage is shaped to concave shape, and the quantity of the electric pushrod is two.
Preferably, the width of second groove is greater than the width of driven gear, and the first through hole is shaped to
Rectangle.
The beneficial effects of the present invention are:
1, of the invention, by the way that electric pushrod, slide plate, sliding slot, the second tailplane, first through hole and the first groove is arranged,
When need to extend the second tailplane when, the work of two electric pushrods is controlled, so that electric pushrod elongation drives slide plate to moving to left
Dynamic, so that slide plate drives the second tailplane to be moved to the left, two, control right side is electronic in an identical manner again pushes away by staff
Bar work, is unfolded two the second tailplanes, improves connecing for air and first level empennage and the second tailplane
Contacting surface product, to play the effect for allowing aircraft to carry out flight adjustment in a short time.
2, of the invention, by setting dual-axle motor, driving gear, driven gear, shaft and elevator, risen when needing to adjust
When dropping the angle of rudder, control dual-axle motor work, so that two output shafts of dual-axle motor drive two driving gear rotations respectively
Turn, so that two driving gears drive two driven gear rotations respectively, so that two driven gears drive two shafts respectively
Rotation, so that two shafts drive two elevator rotations respectively, so that the more convenient angle for adjusting elevator of staff.
3, the present invention passes through setting screw head, threaded rod, body and pedestal, when needing to remove first level empennage, work
Personnel unscrew four threaded rods by tool, so that four threaded rods are detached from spiral shell built in four the second disposed threads and first respectively
Line so that staff remove it is more convenient when first level empennage.
Detailed description of the invention
Fig. 1 is the schematic diagram of the section structure that the present invention faces；
Fig. 2 is the structural schematic diagram that the present invention overlooks；
Fig. 3 is the structural schematic diagram that the present invention faces；
Fig. 4 is the structural schematic diagram of first level empennage left view of the present invention；
Fig. 5 is the structural schematic diagram amplified at A of the present invention；
Fig. 6 is the structural schematic diagram amplified at B of the present invention.
In figure: the second tailplane of 1-, 2- first level empennage, 3- sliding slot, 4- slide plate, 5- electric pushrod, 6- first are recessed
Slot, 7- transmission device, 71- driven gear, 72- driving gear, 8- driving device, 81- dual-axle motor, 82- fixed plate, 9- first
Bearing, 10- baffle, 11- pedestal, 12- body, 13- second bearing, 14- shaft, 15- elevator, the second groove of 16-, 17- turn
Dynamic device, 171- screw head, 172- threaded rod, 18- first through hole, the second through-hole of 19-, the first disposed thread of 20-, in 21- second
Set screw thread, 22- third groove.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
As shown in figures 1 to 6, the present invention provides a kind of technical solution: the aircraft horizontal tail wing that one kind can quickly face upward with nutation,
Including body 12, the upper surface of body 12 and the lower surface of pedestal 11 are overlapped, there are two the left and right sides of pedestal 11 open up
Second through-hole 19, the first disposed thread 20 is provided in the second through-hole 19, and 20 internal screw thread of the first disposed thread is connected with rotation dress
17 are set, by setting 20 column of the first disposed thread and the second disposed thread 21, when needing for pedestal 11 to be mounted on body 12,
Staff tightens threaded rod 172 using tool, so that threaded rod 172 is threaded in built in the first disposed thread 20 and second
In screw thread 21, so that pedestal 11 is effectively fixed on body 12, rotating device 17 includes screw head 171, the lower surface of screw head 171
It is fixedly connected with threaded rod 172, threaded rod 172 is threaded in the first disposed thread 20 and the second disposed thread 21, rotation
Device 17 is threaded in the second disposed thread 21, and the second disposed thread 21 is arranged in third groove 22, third groove 22
It is provided with the left side of body 12, the upper surface of pedestal 11 is fixedly connected with the lower surface of baffle 10, the left and right sides of baffle 10
Face is fixedly connected to first level empennage 2, and first level empennage 2 is shaped to concave shape, and the quantity of electric pushrod 5 is
Two, by the way that electric pushrod 5 is arranged, so that the elongation of electric pushrod 5 drives slide plate 4 to be moved to the left, so that slide plate 4 drives the second water
The horizontal tail wing 1 is moved to the left, and two, right side of control electric pushrod 5 works staff in an identical manner again, so that two second
Tailplane 1 can be unfolded, and improve the contact area of air and first level empennage 2 and the second tailplane 1, first level tail
The right side of the wing 2 offers the first groove 6.
The second tailplane 1 is provided in first groove 6, the right side of the second tailplane 1 is fixedly connected with slide plate 4,
Slide plate 4 is slidably connected in two sliding slots 3, by setting slide plate 4 and sliding slot 3, when electric pushrod 5 elongates or shortens drive slide plate
4 when moving left and right, so that slide plate 4 will not shake and more laborsaving when moving left and right in two sliding slots 3 respectively, and two sliding slots
3 are provided with the upper and lower surfaces of 6 inner wall of the first groove respectively, and the right side of slide plate 4 passes through electric pushrod 5 and baffle 10
Left side is fixedly connected, and the second tailplane 1 is located in first through hole 18, and first through hole 18 is provided with 6 inner wall of the first groove
The left side of left side, 2 inner wall of first level empennage is connected with second bearing 13, passes through setting first bearing 9 and second bearing
13, so that two driven gears 71 drive two shafts 14 to rotate respectively, so that two shafts 14 drive two elevators respectively
15 rotations, so that shaft 14 will not shake and more stable when first bearing 9 and second bearing 13 rotate, in second bearing 13
It is socketed with shaft 14.
The outer surface of shaft 14 is socketed with first bearing 9, and first bearing 9 is connected to the right side of tailplane inner wall, turns
The outer surface of axis 14 is fixedly connected with elevator 15, and the lower surface of elevator 15 offers the second groove 16, by the way that twin shaft is arranged
Motor 81, when needing to adjust the angle of elevator 15, so that two shafts 14 drive two elevators 15 to rotate respectively, so that
The more convenient angle for adjusting elevator 15 of staff, the width of the second groove 16 are greater than the width of driven gear 71, and first
Through-hole 18 is shaped to rectangle, and transmission device 7 is provided in the second groove 16, and transmission device 7 includes driven gear 71, from
Moving gear 71 is connected to the outer surface of shaft 14, and driven gear 71 is meshed with driving gear 72, the right side of driving gear 72
It is fixedly connected with the left end of driving device 8, by setting driving gear 72 and driven gear 71, so that two driving gears 72 divide
Not Dai Dong two driven gears 71 it is more efficient when rotating, and the transmission connection of driving gear 72 and driven gear 71 have it is constant
Transmission ratio, transmission efficiency is high, reliable operation and benefit with long service life, transmission device 7 are connected to the outer surface of shaft 14,
The right side of transmission device 7 is fixedly connected with the left end of driving device 8, and driving device 8 includes dual-axle motor 81, dual-axle motor 81
Two output shafts be fixedly connected respectively with the left and right sides of two driving gears 72, the lower surface of 81 fuselage of dual-axle motor is logical
Fixed plate 82 is crossed to be fixedly connected with the upper surface of pedestal 11, by the way that pedestal 11 is arranged, when needing to remove first level empennage 2,
Staff unscrews four threaded rods 172 by tool, so that four threaded rods 172 are detached from four the second disposed threads 21 respectively
With the first disposed thread 20 so that staff remove it is more convenient when first level empennage 2, the lower surface of driving device 8 with
The upper surface of pedestal 11 is fixedly connected.
The principle of the invention is,
S1, when need to extend the second tailplane 1 when, control two electric pushrods 5 and work, so that electric pushrod 5 extends
Slide plate 4 is driven to be moved to the left, so that slide plate 4 drives the second tailplane 1 to be moved to the left, staff is controlled in an identical manner again
Two, right side of system electric pushrod 5 works, and two the second tailplanes 1 are unfolded, air and first level empennage 2 are improved
With the contact area of the second tailplane 1；
S2, when needing to adjust the angle of elevator 15, control dual-axle motor 81 work so that two of dual-axle motor 81
Output shaft drives two driving gears 72 to rotate respectively, so that two driving gears 72 drive two driven gears 71 to revolve respectively
Turn, so that two driven gears 71 drive two shafts 14 to rotate respectively, so that two shafts 14 drive two elevators respectively
15 rotations；
S3, when needing to remove first level empennage 2, staff unscrews four threaded rods 172 by tool, so that four
A threaded rod 172 is detached from four the second disposed threads 21 and the first disposed thread 20 respectively, and staff is allowed to remove
One tailplane 2.
Above-described specific embodiment has carried out further the purpose of the present invention, technical scheme and beneficial effects
It is described in detail, it should be understood that being not limited to this hair the foregoing is merely a specific embodiment of the invention
Bright, all within the spirits and principles of the present invention, any modification, equivalent substitution, improvement and etc. done should be included in the present invention
Protection scope within.
Claims (6)
- The aircraft horizontal tail wing with nutation 1. one kind can quickly face upward, including body (12), it is characterised in that: the body (12) The lower surface of upper surface and pedestal (11) overlaps, and the left and right sides of the pedestal (11) open up that there are two the second through-holes (19), it is provided with the first disposed thread (20) in second through-hole (19), first disposed thread (20) is threaded with Rotating device (17), the rotating device (17) are threaded in the second disposed thread (21), second disposed thread (21) in third groove (22), the third groove (22) is provided with the left side of body (12), the pedestal (11) for setting Upper surface be fixedly connected with the lower surface of baffle (10), the left and right sides of the baffle (10) are fixedly connected to the first water The right side of the horizontal tail wing (2), the first level empennage (2) offers the first groove (6).
- The aircraft horizontal tail wing with nutation 2. one kind according to claim 1 can quickly face upward, it is characterised in that: the transmission Device (7) includes driven gear (71), and the driven gear (71) is connected to the outer surface of shaft (14), the driven gear (71) it is meshed with driving gear (72), the right side of the driving gear (72) is fixedly connected with the left end of driving device (8).
- The aircraft horizontal tail wing with nutation 3. one kind according to claim 1 can quickly face upward, it is characterised in that: the driving Device (8) includes dual-axle motor (81), two output shafts of the dual-axle motor (81) respectively with two driving gears (72) Left and right sides are fixedly connected, and the lower surface of dual-axle motor (81) fuselage passes through the upper table of fixed plate (82) and pedestal (11) Face is fixedly connected；It is provided with the second tailplane (1) in first groove (6), the right side of second tailplane (1) It is fixedly connected with slide plate (4), the slide plate (4) is slidably connected in two sliding slots (3), and two sliding slots (3) are provided with respectively The right side of the upper and lower surfaces of the first groove (6) inner wall, the slide plate (4) passes through electric pushrod (5) and baffle (10) Left side be fixedly connected, second tailplane (1) is located in first through hole (18), and the first through hole (18) is provided with The left side of the left side of the first groove (6) inner wall, first level empennage (2) inner wall is connected with second bearing (13), institute It states in second bearing (13) and is socketed with shaft (14).
- The aircraft horizontal tail wing with nutation 4. one kind according to claim 1 can quickly face upward, it is characterised in that: the rotation Device (17) includes screw head (171), and the lower surface of the screw head (171) is fixedly connected with threaded rod (172), the threaded rod (172) it is threaded in the first disposed thread (20) and the second disposed thread (21)；The outer surface of the shaft (14) is socketed Have first bearing (9), the first bearing (9) is connected to the right side of tailplane inner wall, the outer surface of the shaft (14) It is fixedly connected with elevator (15), the lower surface of the elevator (15) offers the second groove (16), second groove (16) it is provided with transmission device (7) in, the transmission device (7) is connected to the outer surface of shaft (14), the transmission device (7) Right side be fixedly connected with the left end of driving device (8), the upper surface of the lower surface of the driving device (8) and pedestal (11) It is fixedly connected.
- The aircraft horizontal tail wing with nutation 5. one kind according to claim 1 can quickly face upward, it is characterised in that: described first Tailplane (2) is shaped to concave shape, and the quantity of the electric pushrod (5) is two.
- The aircraft horizontal tail wing with nutation 6. one kind according to claim 1 can quickly face upward, it is characterised in that: described second The width of groove (16) is greater than the width of driven gear (71), and the first through hole (18) is shaped to rectangle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810924644.8A CN109018303B (en) | 2018-08-14 | 2018-08-14 | Plane flat tail wing capable of quickly pitching up and down |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810924644.8A CN109018303B (en) | 2018-08-14 | 2018-08-14 | Plane flat tail wing capable of quickly pitching up and down |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109018303A true CN109018303A (en) | 2018-12-18 |
| CN109018303B CN109018303B (en) | 2020-05-19 |
Family
ID=64631015
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810924644.8A Active CN109018303B (en) | 2018-08-14 | 2018-08-14 | Plane flat tail wing capable of quickly pitching up and down |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109018303B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115946843A (en) * | 2023-03-14 | 2023-04-11 | 中国民用航空飞行学院 | Airplane tail wing and elevator jamming adjusting method |
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| DE3412371A1 (en) * | 1984-04-03 | 1985-11-07 | Franz Albert 3012 Langenhagen Agethen | Boundary-layer suction without motor-driven units for winged aircraft |
| CN102239083A (en) * | 2008-12-04 | 2011-11-09 | 空中客车运作有限公司 | Aircraft directional control and stabilizing surface |
| WO2014029972A1 (en) * | 2012-08-22 | 2014-02-27 | Moog Wolverhampton Limited | Control surface actuation assembly |
| CN104943850A (en) * | 2014-03-27 | 2015-09-30 | 杨文建 | Main wing retractable type fixed wing airplane |
| CN205366052U (en) * | 2016-02-02 | 2016-07-06 | 张大伟 | Retractable wing |
| CN106167089A (en) * | 2016-07-19 | 2016-11-30 | 深圳市创翼睿翔天空科技有限公司 | Tail structure and there is its unmanned plane |
| CN207450221U (en) * | 2017-10-27 | 2018-06-05 | 华南农业大学 | A kind of unmanned plane of variable aerodynamic arrangement |
| CN108275259A (en) * | 2017-12-22 | 2018-07-13 | 兰州空间技术物理研究所 | A kind of flat aileron steering engine mechanism |
| CN207683769U (en) * | 2017-11-21 | 2018-08-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of spanwise length variable geometry and the aircraft with it |
| CN207683770U (en) * | 2017-12-25 | 2018-08-03 | 宝鸡特种飞行器工程研究院有限公司 | Retractable wing for folding wings unmanned plane |
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2018
- 2018-08-14 CN CN201810924644.8A patent/CN109018303B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3412371A1 (en) * | 1984-04-03 | 1985-11-07 | Franz Albert 3012 Langenhagen Agethen | Boundary-layer suction without motor-driven units for winged aircraft |
| CN102239083A (en) * | 2008-12-04 | 2011-11-09 | 空中客车运作有限公司 | Aircraft directional control and stabilizing surface |
| WO2014029972A1 (en) * | 2012-08-22 | 2014-02-27 | Moog Wolverhampton Limited | Control surface actuation assembly |
| CN104943850A (en) * | 2014-03-27 | 2015-09-30 | 杨文建 | Main wing retractable type fixed wing airplane |
| CN205366052U (en) * | 2016-02-02 | 2016-07-06 | 张大伟 | Retractable wing |
| CN106167089A (en) * | 2016-07-19 | 2016-11-30 | 深圳市创翼睿翔天空科技有限公司 | Tail structure and there is its unmanned plane |
| CN207450221U (en) * | 2017-10-27 | 2018-06-05 | 华南农业大学 | A kind of unmanned plane of variable aerodynamic arrangement |
| CN207683769U (en) * | 2017-11-21 | 2018-08-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of spanwise length variable geometry and the aircraft with it |
| CN108275259A (en) * | 2017-12-22 | 2018-07-13 | 兰州空间技术物理研究所 | A kind of flat aileron steering engine mechanism |
| CN207683770U (en) * | 2017-12-25 | 2018-08-03 | 宝鸡特种飞行器工程研究院有限公司 | Retractable wing for folding wings unmanned plane |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115946843A (en) * | 2023-03-14 | 2023-04-11 | 中国民用航空飞行学院 | Airplane tail wing and elevator jamming adjusting method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109018303B (en) | 2020-05-19 |
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