CN102815394A - Light aircraft rudder spring centering positioning mechanism - Google Patents
Light aircraft rudder spring centering positioning mechanism Download PDFInfo
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- CN102815394A CN102815394A CN2012102867271A CN201210286727A CN102815394A CN 102815394 A CN102815394 A CN 102815394A CN 2012102867271 A CN2012102867271 A CN 2012102867271A CN 201210286727 A CN201210286727 A CN 201210286727A CN 102815394 A CN102815394 A CN 102815394A
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- yaw rudder
- transmission shaft
- fuselage
- spring
- rudder
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- 230000007246 mechanism Effects 0.000 title claims abstract description 17
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 15
- 239000010959 steel Substances 0.000 claims abstract description 15
- 230000005540 biological transmission Effects 0.000 claims description 32
- 238000009434 installation Methods 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 2
- 229910001315 Tool steel Inorganic materials 0.000 description 1
- 238000002788 crimping Methods 0.000 description 1
- IWEDIXLBFLAXBO-UHFFFAOYSA-N dicamba Chemical compound COC1=C(Cl)C=CC(Cl)=C1C(O)=O IWEDIXLBFLAXBO-UHFFFAOYSA-N 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000003472 neutralizing effect Effects 0.000 description 1
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Abstract
The present invention discloses a light aircraft rudder spring centering positioning mechanism. According to the mechanism, both ends of a drive shaft (8) are rotatably arranged on an aircraft body; one end of the drive shaft (8) is fixedly connected with a rudder (1); the drive shaft (8) is provided with a rocker arm (9); a part between the end part of the rocker arm (9) and the aircraft body is connected with a spring (10) and a steel wire rope (11), wherein the spring and the steel wire rope are provided for keeping the rudder (1) in a center position when the rudder (1) is at a free state. The light aircraft rudder spring centering positioning mechanism of the present invention has advantages of simple structure, large centering force, easy adjustment, adaptability for installation on aircraft tail, and the like. With the light aircraft rudder spring centering positioning mechanism of the present invention, centering and position limitation of the rudder can be concurrently achieved.
Description
Technical field
The present invention relates to a kind of yaw rudder centering detent mechanism, especially relate to a kind of aviette yaw rudder spring centering detent mechanism.
Background technology
In aircraft, yaw rudder is used to control the driftage of aircraft, and its basic role is to guarantee the stability in aircraft path.Normal flat flying in the state,, then cause flight unstable if yaw rudder is not in meta.Therefore, improve the controller performance of yaw rudder, significant to the handling and the safety of aircraft.Simultaneously, when aircraft turns, empennage possibly bear relatively large power. in order to limit the power on the empennage, need the angle of inclination of restriction yaw rudder.The control of yaw rudder is generally handled with pin and is realized; Its serviceability is difficult to visual; Because foot-controlled fine degree is low, make the aviator in driving, can obtain a correct feedback to have important and practical meanings so design good yaw rudder centering body, a stop gear.
Summary of the invention
Technical matters to be solved by this invention provides a kind of aviette yaw rudder spring centering detent mechanism that makes the automatic centering of rudder of aircraft ability.
In order to solve the problems of the technologies described above; Aviette yaw rudder spring centering detent mechanism provided by the invention; The transmission shaft two ends are rotatably installed on the fuselage; Described transmission shaft one end is captiveed joint with yaw rudder, and described transmission shaft is provided with rocking arm, is connected with the spring and the steel rope that make described yaw rudder when free state, be in meta between the end of described rocking arm and the fuselage.
The yaw rudder stop block is installed on the described transmission shaft, spacing collision block is installed on the fuselage, the angle range of the stroke limitation yaw rudder of the described relatively spacing collision block of described yaw rudder stop block.
Adapter sleeve is enclosed within outside the described transmission shaft, and described yaw rudder stop block is enclosed within outside the described adapter sleeve, and the three is drilled with pin-and-hole together, and with the fastening location of three, described adapter sleeve and described yaw rudder are fastenedly connected through bolt and nut by bearing pin or bolt and nut.
The middle part of described rocking arm is fixed on the described transmission shaft; And the two ends of described rocking arm are the both sides that the symmetric line symmetry is in described transmission shaft with the line of centers of described transmission shaft, and the two ends of described rocking arm all and between the fuselage are connected with spring and the steel rope that makes described yaw rudder when free state, be in meta.
The connection mode of described spring and steel rope and fuselage is: described steel rope is fixed on an end of described adjust bar; The other end of described adjust bar is provided with outside thread and outside thread is provided with by two setting nuts, and described adjust bar is locked each other through two setting nuts and is installed on the fuselage.
Described transmission shaft is rotatably installed on the fuselage through bearing; The outer ring of described bearing is by bearing cap shim and fuselage mounting hole location; Described bearing cap shim is fastening by bolt, nut and fuselage; Described bearing cone is located by locating bush, and it is outer and be drilled with pin-and-hole together that described locating bush is enclosed within described transmission shaft, by bearing pin or bolt and nut with described locating bush and the fastening location of described transmission shaft.
Adopt the aviette yaw rudder spring centering detent mechanism of technique scheme, act on rocking arm by spring and steel rope and make yaw rudder be in meta when the free state.The yaw rudder stop block is installed on the transmission shaft, spacing collision block is installed on the fuselage, the angle range of the stroke limitation yaw rudder of yaw rudder stop block relative limit collision block.
In sum, centering positioning systems provided by the invention has simple in structure, can realize the spacing to neutralizing of yaw rudder simultaneously.Also have centering force greatly, regulate, be suitable for advantages such as afterbody installation easily.
Description of drawings
Fig. 1 is a structural representation of the present invention.
Fig. 2 is a cutaway view of the present invention.
Fig. 3 is an adjust bar structural representation of the present invention.
The specific embodiment
Below in conjunction with the accompanying drawing and the specific embodiment the present invention is described further.
Referring to Fig. 1 and Fig. 2, the two ends of transmission shaft 8 are installed on the fuselage through two bearings 6, and fuselage rotates relatively.Bearing 6 outer rings are by bearing cap shim 5 and fuselage mounting hole location, and bearing cap shim 5 is fastening by bolt, nut and fuselage, and bearing 6 inner rings are by locating bush 7 location.It is outer and be drilled with pin-and-holes together that locating bush 7 is enclosed within transmission shaft 8, by bearing pin or bolt and nut with locating bush 7 and transmission shaft 8 fastening location.Adapter sleeve 2 is enclosed within outside the transmission shaft 8; Adapter sleeve 2 and yaw rudder 1 are fastenedly connected through bolt and nut; Transmission shaft 8 drives yaw rudders 1 through adapter sleeve 2 and rotates; the middle part of rocking arm 9 is fixed on the transmission shaft 8, and the two ends of rocking arm 9 are the both sides that the symmetric line symmetry is in transmission shaft 8 with the line of centers of transmission shaft 8, and the two ends of rocking arm 9 are all and be connected with the spring 10 and steel rope 11 that makes yaw rudder 1 when free state, be in meta between the fuselage; by spring 10 tractions, each spring 10 1 end is connected with rocking arm 9 through steel rope respectively at the two ends of the rocking arm 9 of transmission shaft 8; The other end of spring 10 is connected with an end of adjust bar 12 through steel rope 11, and connection mode is in the hole of an end of steel rope 11 insertion adjusts bar 12, and with crimping tool steel rope 11 is pressed in the hole; The other end of adjust bar 12 is provided with outside thread and outside thread is provided with by two setting nuts 13, and adjust bar 12 is locked each other through two setting nuts 13 and is installed on the fuselage.After adjust bar 12 is strained by spring 10; Through the externally threaded position of adjusting setting nut 13 on adjust bar 12, and the position of adjustment adjust bar 12 guarantees that yaw rudder 1 is in meta when free state; Meta makes two setting nuts, 13 mutual locking positionings after regulating and accomplishing.
As a kind of improvement of the present invention; Referring to Fig. 1 and Fig. 2, spacing collision block 4 is installed on the fuselage, yaw rudder stop block 3 is enclosed within on the adapter sleeve 2; The three is drilled with pin-and-hole together; With the fastening location of three, adapter sleeve 2 and yaw rudder 1 are fastenedly connected the angle range of the movement travel restriction yaw rudder 1 of yaw rudder stop block 3 relative limit collision blocks 4 through bolt and nut by bearing pin or bolt and nut.
Claims (6)
1. aviette yaw rudder spring centering detent mechanism; It is characterized in that: transmission shaft (8) two ends are rotatably installed on the fuselage; Described transmission shaft (8) one ends are captiveed joint with yaw rudder (1); Described transmission shaft (8) is provided with rocking arm (9), is connected with the spring (10) and the steel rope (11) that make described yaw rudder (1) when free state, be in meta between the end of described rocking arm (9) and the fuselage.
2. aviette yaw rudder spring centering detent mechanism according to claim 1; It is characterized in that: yaw rudder stop block (3) is installed on the described transmission shaft (8); Spacing collision block (4) is installed, the angle range of the stroke limitation yaw rudder (1) of the described relatively spacing collision block of described yaw rudder stop block (3) (4) on the fuselage.
3. according to right 2 described aviette yaw rudder spring centering detent mechanisms; It is characterized in that: adapter sleeve (2) is enclosed within outside the described transmission shaft (8); Described yaw rudder stop block (3) is enclosed within outside the described adapter sleeve (2); The three is drilled with pin-and-hole together, and with the fastening location of three, described adapter sleeve (2) is fastenedly connected through bolt and nut with described yaw rudder (1) by bearing pin or bolt and nut.
4. according to right 1 or 2 described aviette yaw rudder spring centering detent mechanisms; It is characterized in that: the middle part of described rocking arm (9) is fixed on the described transmission shaft (8); And the two ends of described rocking arm (9) are the both sides that the symmetric line symmetry is in described transmission shaft (8) with the line of centers of described transmission shaft (8), and the two ends of described rocking arm (9) all and between the fuselage are connected with spring (10) and the steel rope (11) that makes described yaw rudder (1) when free state, be in meta.
5. according to right 1 or 2 described aviette yaw rudder spring centering detent mechanisms; It is characterized in that: described spring (10) and steel rope (11) with the connection mode of fuselage are: described steel rope (11) is fixed on an end of described adjust bar (12); The other end of described adjust bar (12) is provided with outside thread and outside thread is provided with by two setting nuts (13), and described adjust bar (12) is locked each other through two setting nuts (13) and is installed on the fuselage.
6. according to right 1 or 2 described aviette yaw rudder spring centering detent mechanisms; It is characterized in that: described transmission shaft (8) is rotatably installed on the fuselage through bearing (6); The outer ring of described bearing (6) is by bearing cap shim (5) and fuselage mounting hole location; Described bearing cap shim (5) is fastening by bolt, nut and fuselage; The inner ring of described bearing (6) is by locating bush (7) location, and it is outer and be drilled with pin-and-hole together that described locating bush (7) is enclosed within described transmission shaft (8), by bearing pin or bolt and nut with described locating bush (7) and the fastening location of described transmission shaft (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102867271A CN102815394A (en) | 2012-08-13 | 2012-08-13 | Light aircraft rudder spring centering positioning mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102867271A CN102815394A (en) | 2012-08-13 | 2012-08-13 | Light aircraft rudder spring centering positioning mechanism |
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| CN102815394A true CN102815394A (en) | 2012-12-12 |
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| CN2012102867271A Pending CN102815394A (en) | 2012-08-13 | 2012-08-13 | Light aircraft rudder spring centering positioning mechanism |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443355A (en) * | 2014-11-13 | 2015-03-25 | 中航沈飞民用飞机有限责任公司 | Light bionic aircraft tail wing |
| CN105523170A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft control system with terminal neutral-position-pulling-back mechanism |
| CN109592013A (en) * | 2018-11-02 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of restraint method of general-purpose aircraft rudder rudder face |
| CN109592014A (en) * | 2018-11-02 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of general-purpose aircraft rudder pivot structure and method of operating |
| CN112550668A (en) * | 2021-03-01 | 2021-03-26 | 北京清航紫荆装备科技有限公司 | Cross double-rotor helicopter and horizontal tail control system |
| CN112700993A (en) * | 2020-12-09 | 2021-04-23 | 河南平高电气股份有限公司 | Spring operating mechanism and plunger latch assembly device |
| CN112874761A (en) * | 2021-02-26 | 2021-06-01 | 北京卫星制造厂有限公司 | High-bearing thin control surface structure |
| CN114194379A (en) * | 2021-11-22 | 2022-03-18 | 北京机电工程研究所 | Combined rudder method for improving control ability of X-type aerodynamic layout |
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| US2857120A (en) * | 1955-02-25 | 1958-10-21 | Northrop Aircraft Inc | Force producer and centering mechanism |
| US4470570A (en) * | 1982-09-29 | 1984-09-11 | The Boeing Company | Control assembly for aircraft |
| EP0590294A1 (en) * | 1992-08-26 | 1994-04-06 | DaimlerChrysler Aerospace Airbus Gesellschaft mit beschränkter Haftung | Centering unit for an aircraft control surface |
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| CN101314409A (en) * | 2008-07-10 | 2008-12-03 | 周武双 | Swallow type inclined rotation rotorcraft |
| US20100044500A1 (en) * | 2008-03-31 | 2010-02-25 | Honda Motor Co., Ltd. | Pedal operated apparatus for controlling an aircraft nose wheel steering system |
| CN202783776U (en) * | 2012-08-13 | 2013-03-13 | 湖南山河科技股份有限公司 | Spring centering and positioning mechanism for rudder of light aircraft |
-
2012
- 2012-08-13 CN CN2012102867271A patent/CN102815394A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2857120A (en) * | 1955-02-25 | 1958-10-21 | Northrop Aircraft Inc | Force producer and centering mechanism |
| US4470570A (en) * | 1982-09-29 | 1984-09-11 | The Boeing Company | Control assembly for aircraft |
| EP0590294A1 (en) * | 1992-08-26 | 1994-04-06 | DaimlerChrysler Aerospace Airbus Gesellschaft mit beschränkter Haftung | Centering unit for an aircraft control surface |
| CN2676989Y (en) * | 2004-02-27 | 2005-02-09 | 蔡东青 | Rudder control mechanism for model airplane |
| CN101297250A (en) * | 2005-10-27 | 2008-10-29 | 空中客车法国公司 | Method and system for limiting an aircraft control surface steering angle |
| US20100044500A1 (en) * | 2008-03-31 | 2010-02-25 | Honda Motor Co., Ltd. | Pedal operated apparatus for controlling an aircraft nose wheel steering system |
| CN101314409A (en) * | 2008-07-10 | 2008-12-03 | 周武双 | Swallow type inclined rotation rotorcraft |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105523170A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft control system with terminal neutral-position-pulling-back mechanism |
| CN105523170B (en) * | 2014-09-28 | 2018-04-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of flight control system of end of tape return to neutral mechanism |
| CN104443355A (en) * | 2014-11-13 | 2015-03-25 | 中航沈飞民用飞机有限责任公司 | Light bionic aircraft tail wing |
| CN109592013A (en) * | 2018-11-02 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of restraint method of general-purpose aircraft rudder rudder face |
| CN109592014A (en) * | 2018-11-02 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of general-purpose aircraft rudder pivot structure and method of operating |
| CN112700993A (en) * | 2020-12-09 | 2021-04-23 | 河南平高电气股份有限公司 | Spring operating mechanism and plunger latch assembly device |
| CN112700993B (en) * | 2020-12-09 | 2024-04-19 | 河南平高电气股份有限公司 | Spring operating mechanism and latch assembly device |
| CN112874761A (en) * | 2021-02-26 | 2021-06-01 | 北京卫星制造厂有限公司 | High-bearing thin control surface structure |
| CN112550668A (en) * | 2021-03-01 | 2021-03-26 | 北京清航紫荆装备科技有限公司 | Cross double-rotor helicopter and horizontal tail control system |
| CN112550668B (en) * | 2021-03-01 | 2021-06-15 | 北京清航紫荆装备科技有限公司 | Cross double-rotor helicopter and horizontal tail control system |
| EP4053015A1 (en) * | 2021-03-01 | 2022-09-07 | Beijing Tsingaero Armanment Technology Co., Ltd | Intermeshing dual-rotor helicopter and horizontal tail control system |
| CN114194379A (en) * | 2021-11-22 | 2022-03-18 | 北京机电工程研究所 | Combined rudder method for improving control ability of X-type aerodynamic layout |
| CN114194379B (en) * | 2021-11-22 | 2023-10-13 | 北京机电工程研究所 | Combined rudder method for improving control capacity of X-type pneumatic layout |
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Application publication date: 20121212 |