CN108408026A - A kind of general-purpose aircraft tailspin changes device - Google Patents
A kind of general-purpose aircraft tailspin changes device Download PDFInfo
- Publication number
- CN108408026A CN108408026A CN201810469167.0A CN201810469167A CN108408026A CN 108408026 A CN108408026 A CN 108408026A CN 201810469167 A CN201810469167 A CN 201810469167A CN 108408026 A CN108408026 A CN 108408026A
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- China
- Prior art keywords
- support bar
- piston
- pillar
- tailspin
- panel
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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.)
- Pending
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- 239000007787 solid Substances 0.000 claims 1
- 230000008859 change Effects 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 4
- 230000004044 response Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
Abstract
The invention discloses a kind of general-purpose aircraft tailspins to change device, including panel, further includes having pillar, first support bar, second support bar, slide lock and piston；The inside of the panel is equipped with the pillar, and the pillar is connected in one end close to head by pivoting support with the panel, and the rocker bar bearing is fixed on fuselage；The pivoting support is fixed in one end of the first support bar, and the other end of the first support bar is rotatablely connected with the slide lock；The slide lock is also rotatably connected to the pull rod of the piston and the second support bar respectively, and the other end of the piston is connected with piston shoe, and the other end of the second support bar is fixed on the middle part of the pillar；The piston shoe is connected with button by circuit, and the button can control the piston by the piston shoe and be moved on the piston shoe；The configuration of the present invention is simple can reduce the probability of maloperation, improve speed and success rate that tailspin changes.
Description
Technical field
The invention belongs to cubpiston fields, and in particular to a kind of general-purpose aircraft tailspin changes device.
Background technology
Cubpiston can intentionally or accidentally be absorbed in stall spin when driving, and traditional changing ways are the disadvantage is that pilot
It is difficult to judge push rod opportunity and make a response rapidly, it is easy to cause rudder and elevator out of control, and use antispin parachute
The disadvantage is that antispin parachute system structure is complicated, pilot need to observe umbrella state, prevent winding aircraft, prevent from influencing nozzle,
It needs to throw after aircraft state back to normal and put, there are certain defects for both of which, for this purpose, it is proposed that a kind of general-purpose aircraft tail
Rotation changes device.
Invention content
The main purpose of the present invention is to provide a kind of general-purpose aircraft tailspins to change device, can effectively solve background technology
The problems in.
To achieve the above object, the technical solution that the present invention takes is：
A kind of general-purpose aircraft tailspin changes device, including panel, further include have pillar, first support bar, second support bar,
Slide lock and piston；The inside of the panel is equipped with the pillar, and the pillar is with the panel logical close to one end of head
It crosses pivoting support to be connected, the rocker bar bearing is fixed on fuselage；The pivoting support is fixed in one end of the first support bar,
The other end of the first support bar is rotatablely connected with the slide lock；The slide lock is also rotatably connected to the piston respectively
Pull rod and the second support bar, the other end of the piston be connected with piston shoe, the other end of the second support bar
It is fixed on the middle part of the pillar；The piston shoe is connected with button by circuit, and the button can be slided by the piston
Rail controls the piston and is moved on the piston shoe.
Preferably, the pillar connects the panel in the other end of the pivoting support by cross-brace, convenient for keeping
The streamline shape of panel is unified with nose-ring.
Preferably, the slide lock includes outline border and mobile lock core；The mobile lock core is separately connected the piston
Pull rod, the first support bar and the second support bar；The pull rod of the piston drives the mobile lock core in the outline border
Interior movement, the mobile lock core are lockked in the both ends extreme position of the outline border.
Preferably, the first support bar connects the mobile lock core with the second support bar.
Preferably, the pivoting support is fixed on the inside of nose-ring.
Advantageous effect：
The configuration of the present invention is simple is arranged below head, is not interfered by other flow-disturbings, will not generate shadow to rudder
It rings.Opening device when needed, when not needed holding meanss closing will not have an impact aircraft state, the panel in device
For a part for nose-ring, it can be used repeatedly, and the operation of device and functional independence can replace, and can also assist increasing
The deflecting action of strong elevator, and rudder is not influenced, maximum anti-tailspin yawing is remained until tailspin changes
Go out, tailspin, which changes device, can ensure that pilot need not must make a response in two seconds, reduce the probability of maloperation, improve tail
Revolve the speed and success rate changed.In the present invention, it is simple that entire general-purpose aircraft tailspin changes apparatus structure, easy to operate, uses
Effect it is more preferable relative to traditional approach.
Description of the drawings
Fig. 1 uses position view for the present invention's；
Fig. 2 is the structural schematic diagram of the normally off of the present invention；
Fig. 3 is the structural schematic diagram of the starting state of the present invention；
Fig. 4 is the side structure schematic view of the pivoting support and hound and panel of the present invention.
In figure：1, panel；2, pivoting support；3, piston；4, piston shoe；5, slide lock；51, outline border；52, mobile lock
Core；6, pillar；7, cross-brace；8, first support bar；9, second support bar.
Specific implementation mode
The embodiment of the present invention is further illustrated below.
As shown in Figures 1 to 4, a kind of general-purpose aircraft tailspin in the present embodiment changes device, including panel (1), pillar
6, first support bar 8, second support bar 9, slide lock 5 and piston 3；The inside of the panel 1 is equipped with the pillar 6, the branch
Column 6 is connected in one end close to head by pivoting support 2 with the panel 1, and the rocker bar bearing 2 is fixed on fuselage；It is described
The pivoting support 2 is fixed in one end of first support bar 8, and the other end of the first support bar 8 is rotated with the slide lock 5
Connection；The slide lock 5 is also rotatably connected to the pull rod and the second support bar 9 of the piston 3 respectively, the piston 3
The other end is connected with piston shoe 4, and the other end of the second support bar 9 is fixed on the middle part of the pillar 6；The piston is slided
Rail 4 is connected with button by circuit, and the button can control the piston 3 in the piston shoe 4 by the piston shoe 4
Upper movement.
In the present embodiment, the pillar connects the panel 1 in the other end of the pivoting support 2 by cross-brace 7, just
It is unified in the streamline shape and nose-ring for keeping panel 1；The slide lock 5 includes outline border 51 and mobile lock core 52；Institute
State pull rod, the first support bar 8 and the second support bar 9 that mobile lock core 52 is separately connected the piston 3；The piston
3 pull rod drives the mobile lock core 52 to be moved in the outline border 51, and the mobile lock core 52 is at the both ends of the outline border 51
It is lockked when extreme position, the first support bar 8 and the second support bar 9 connect the mobile lock core 52；The hinged branch
Seat 2 is fixed on the inside of nose-ring.
The present invention operation principle be：When panel 1 is in normally off, piston 3 is in the upper end of piston shoe 4, living
The mobile lock core 52 of the pull rod control slide lock 5 of plug 3 is set to the top of outline border 51, is in the locked position so that panel 1 passes through
Slide lock 5 is fixed, and is closed；Button is set on the instrument board of aircraft, by button device for opening, controls piston
3 move down at piston shoe 4 so that tailspin changes device startup, and under the effect of piston 3, mobile lock core 52 is moved to outer
The bottom of frame 51 locks, and hound 7 is under the driving of mobile lock core 52, by panel 1 by the drive of pillar 6 around pivoting support
2 rotations make air-flow flow into head along nose-ring to open the notch of head bottom, increase head pressure difference up and down, generate
Pitching moment achievees the effect that elevator deflects down, and without worrying that control elevator too early, rudder face flow-disturbing influence rudder
And reduce anti-tailspin yawing, and then aircraft is made to reach normal dive status, subsequent start-up piston 3 restores 1 position of panel.This
A kind of invention general-purpose aircraft tailspin changes device, and the panel 1 in device is a part for nose-ring, can be repeatedly
It using, the operation of device and functional independence can assist the deflecting action of enhancing elevator, and not influenced on rudder,
Maximum anti-tailspin yawing is remained until tailspin changes, tailspin, which changes device, can ensure that pilot need not be in two seconds
It must make a response, reduce the probability of maloperation.
Specific embodiments of the present invention are described in detail above, but it is intended only as example, the present invention is simultaneously unlimited
It is formed on above description specific embodiment.To those skilled in the art, any to the equivalent modifications that carry out of the present invention and to replace
In generation, is also all among scope of the invention.Therefore, without departing from the spirit and scope of the invention made by impartial conversion and repair
Change, all covers within the scope of the present invention.
Claims (5)
1. a kind of general-purpose aircraft tailspin changes device, including panel (1), it is characterised in that：
Further include having pillar (6), first support bar (8), second support bar (9), slide lock (5) and piston (3)；
The inside of the panel (1) is equipped with the pillar (6), and the pillar (6) is with the panel (1) close to one end of head
It is connected by pivoting support (2), the rocker bar bearing (2) is fixed on fuselage；
The pivoting support (2) is fixed in one end of the first support bar (8), the other end of the first support bar (8) with
Slide lock (5) rotation connection；The slide lock (5) is also rotatably connected to the pull rod and described of the piston (3) respectively
The other end of two supporting rods (9), the piston (3) is connected with piston shoe (4), and the other end of the second support bar (9) is solid
Due to the middle part of the pillar (6)；
The piston shoe (4) is connected with button by circuit, and the button can control the work by the piston shoe (4)
Plug (3) moves on the piston shoe (4).
2. a kind of general-purpose aircraft tailspin according to claim 1 changes device, it is characterised in that：
The pillar connects the panel (1) in the other end of the pivoting support (2) by cross-brace (7), convenient for keeping embedding
The streamline shape of plate (1) is unified with nose-ring.
3. a kind of general-purpose aircraft tailspin according to claim 1 changes device, it is characterised in that：
The slide lock (5) includes outline border (51) and mobile lock core (52)；The mobile lock core (52) is separately connected the work
Fill in pull rod, the first support bar (8) and the second support bar (9) of (3)；The pull rod of the piston (3) drives the shifting
Movable lock core (52) moves in the outline border (51), and the mobile lock core (52) is in the both ends extreme position of the outline border (51)
It locks.
4. a kind of general-purpose aircraft tailspin according to claim 3 changes device, it is characterised in that：
The first support bar (8) and the second support bar (9) connect the mobile lock core (52).
5. a kind of general-purpose aircraft tailspin described in any one according to claims 1 to 4 changes device, it is characterised in that：
The pivoting support (2) is fixed on the inside of nose-ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810469167.0A CN108408026A (en) | 2018-05-16 | 2018-05-16 | A kind of general-purpose aircraft tailspin changes device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810469167.0A CN108408026A (en) | 2018-05-16 | 2018-05-16 | A kind of general-purpose aircraft tailspin changes device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108408026A true CN108408026A (en) | 2018-08-17 |
Family
ID=63139659
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810469167.0A Pending CN108408026A (en) | 2018-05-16 | 2018-05-16 | A kind of general-purpose aircraft tailspin changes device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108408026A (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB558006A (en) * | 1942-04-09 | 1943-12-15 | Fairey Aviat Co Ltd | Improvements in or relating to the control surfaces of aircraft |
| US2563453A (en) * | 1951-08-07 | Device fob controlling the trailing | ||
| US5538202A (en) * | 1993-11-02 | 1996-07-23 | Northrop Grumman Corporation | Hydraulic actuation system for aircraft control surfaces |
| CN101267980A (en) * | 2005-09-23 | 2008-09-17 | 空中客车德国有限公司 | Advanced trailing edge control surface on the wing of an aircraft |
| CN201597752U (en) * | 2010-02-08 | 2010-10-06 | 哈尔滨飞机工业集团有限责任公司 | Follower of aircraft elevator tab |
| CN101959754A (en) * | 2007-08-06 | 2011-01-26 | 空中客车营运有限公司 | High lift system for an aircraft |
| CN102574574A (en) * | 2009-09-03 | 2012-07-11 | 空中客车运营有限公司 | Adjusting mechanism for kinematically guiding an adjusting body during displacement on a supporting structural part, adjusting mechanism for kinematically adjusting a vertically lifting body and vertical lift system comprising said type of adjusting |
| US9038943B1 (en) * | 2014-04-11 | 2015-05-26 | Ralph F. Morris | Safety aileron system |
| CN204674816U (en) * | 2015-05-21 | 2015-09-30 | 江西洪都航空工业集团有限责任公司 | Automatic deviation correction tab mechanism |
| CN105015762A (en) * | 2014-04-21 | 2015-11-04 | 哈尔滨飞机工业集团有限责任公司 | Aircraft geared trim tab mechanism with variable transmission ratio |
-
2018
- 2018-05-16 CN CN201810469167.0A patent/CN108408026A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2563453A (en) * | 1951-08-07 | Device fob controlling the trailing | ||
| GB558006A (en) * | 1942-04-09 | 1943-12-15 | Fairey Aviat Co Ltd | Improvements in or relating to the control surfaces of aircraft |
| US5538202A (en) * | 1993-11-02 | 1996-07-23 | Northrop Grumman Corporation | Hydraulic actuation system for aircraft control surfaces |
| CN101267980A (en) * | 2005-09-23 | 2008-09-17 | 空中客车德国有限公司 | Advanced trailing edge control surface on the wing of an aircraft |
| CN101959754A (en) * | 2007-08-06 | 2011-01-26 | 空中客车营运有限公司 | High lift system for an aircraft |
| CN102574574A (en) * | 2009-09-03 | 2012-07-11 | 空中客车运营有限公司 | Adjusting mechanism for kinematically guiding an adjusting body during displacement on a supporting structural part, adjusting mechanism for kinematically adjusting a vertically lifting body and vertical lift system comprising said type of adjusting |
| CN201597752U (en) * | 2010-02-08 | 2010-10-06 | 哈尔滨飞机工业集团有限责任公司 | Follower of aircraft elevator tab |
| US9038943B1 (en) * | 2014-04-11 | 2015-05-26 | Ralph F. Morris | Safety aileron system |
| CN105015762A (en) * | 2014-04-21 | 2015-11-04 | 哈尔滨飞机工业集团有限责任公司 | Aircraft geared trim tab mechanism with variable transmission ratio |
| CN204674816U (en) * | 2015-05-21 | 2015-09-30 | 江西洪都航空工业集团有限责任公司 | Automatic deviation correction tab mechanism |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for 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: 20200414 Address after: 330000, 18, hi tech Pioneer Park, two hi tech Road, Nanchang hi tech Industrial Development Zone, Jiangxi, China, room 506 Applicant after: JIANGXI GUANYI AVIATION Co.,Ltd. Applicant after: Shanghai Guanyi general aircraft Co., Ltd Address before: 330000, Jiangxi two high tech Industrial Development Zone, Nanchang, Nanchang hi tech Road, 18, high-tech pioneer park building, room 506 Applicant before: JIANGXI GUANYI AVIATION Co.,Ltd. |