CN110422319A - A kind of light aerocraft rudder control device - Google Patents
A kind of light aerocraft rudder control device Download PDFInfo
- Publication number
- CN110422319A CN110422319A CN201910822017.8A CN201910822017A CN110422319A CN 110422319 A CN110422319 A CN 110422319A CN 201910822017 A CN201910822017 A CN 201910822017A CN 110422319 A CN110422319 A CN 110422319A
- Authority
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- China
- Prior art keywords
- rudder
- pull rod
- pedal
- main shaft
- sleeve
- 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.)
- Pending
Links
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 4
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- 239000004411 aluminium Substances 0.000 claims description 4
- 238000005096 rolling process Methods 0.000 claims 1
- 239000007787 solid Substances 0.000 claims 1
- 238000012423 maintenance Methods 0.000 abstract description 4
- 241001347978 Major minor Species 0.000 description 8
- 230000005540 biological transmission Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- 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
- B64C13/04—Initiating means actuated personally
- B64C13/044—Initiating means actuated personally operated by feet, e.g. pedals
-
- 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
- B64C13/30—Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Mechanical Control Devices (AREA)
Abstract
The invention discloses a kind of light aerocraft rudder control devices, including footrest component, rudder pull rod, rudder rocker arm, rocker arm support and rudder；The footrest component is connect with the rudder pull rod, the rudder pull rod is provided with several, the junction of the adjacent rudder pull rod is connect with the rudder rocker arm, rudder rocker arm lower end is hinged with rocker arm support, the rocker arm support is fixedly connected with fuselage, and the rudder pull rod connect setting with the rudder.With the advantages of structure simple strength height, repair and maintenance is convenient, high reliablity, good economy performance.
Description
Technical field
The present invention relates to General Aviation technical field more particularly to a kind of light aerocraft rudder control devices.
Background technique
Rudder of aircraft manipulation device is that one kind on the aircraft using non helping hand mechanical transmission-type flight control system is normal
With device, major and minor driver can individually be manipulated.Main function is to control rudder kick to control the transverse and longitudinal movement of aircraft.
Driver is forward and backward to pedal foot pedal, and foot pedal rotates around the spindle, and controls rudder kick, and rudder will be generated by aerodynamic force
One torque for turning Nose Left or right avertence, to change the course of aircraft.Existing ruddered manipulation device uses cable wire
The flexible transmissions such as pulley, flexible deformation and frictional force are larger, and structural strength performance is low, and repair and maintenance difficulty is big, lead to system
The lower economy of global reliability is poor.
Summary of the invention
In view of the above shortcomings of the prior art, present patent application the technical problem to be solved is that: how a kind of knot is provided
Structure simple strength is high, and repair and maintenance is convenient, high reliablity, the light aerocraft rudder control device of good economy performance.
To achieve the goals above, present invention employs following technical solutions:
A kind of light aerocraft rudder control device, including footrest component, rudder pull rod, rudder rocker arm, rocker arm branch
Seat and rudder；The footrest component is connect with the rudder pull rod, and the rudder pull rod is provided with several, adjacent institute
The junction for stating rudder pull rod is connect with the rudder rocker arm, and rudder rocker arm lower end is hinged with rocker arm support, institute
It states rocker arm support to be fixedly connected with fuselage, the rudder pull rod connect setting with the rudder.
In this way, rudder control device uses rigid transmission system, driver tramples footrest component, drives rudder pull rod
Movement, and then rudder kick is driven by rudder pull rod.Specifically, rudder pressure ratio and rocker arm support are used for direction
Rudder pull rod is limited, so that rudder pull rod is only capable of axially movable, improving reliability.
Further, the rudder pull rod includes left lever, right pull rod, intermediate draw bar and several back segment pull rods, institute
State left lever and right pull rod one end be hinged with footrest component respectively, the other end of the left lever and right pull rod respectively with it is described in
Between pull rod both ends it is hinged, described intermediate draw bar one end and back segment pull rod are hinged, and the adjacent back segment pull rod is hinged, and are located at
Last back segment pull rod and the rudder are hinged, and the centre of the intermediate draw bar and fuselage are rotatablely connected；The adjacent back segment
The junction of pull rod is hinged with the rudder rocker arm.
In this way, acting in footrest component, left lever movement is driven, left lever is transferred to back segment pull rod by intermediate draw bar,
Rudder is driven to deflect to side by back segment pull rod.When needing rudder to deflect to the other side, footrest component drives right drawing
Bar movement.Manoeuvrable is easy to grasp, is driven using pull rod, at low cost.
Further, it is connected and is arranged by bearing between the back segment pull rod and the rudder rocker arm.It can be better
It relatively rotates.The bearing is self-aligning ball bearing.
Further, the rudder pull rod is made by aluminium.Light weight, intensity is high, better meets requirement.
Further, between the left lever and intermediate draw bar, between right pull rod and intermediate draw bar and intermediate draw bar with
Pylon line is provided between back segment pull rod.Electrostatic can be preferably prevented, reliability is improved.Specifically, pylon line and complete machine
The connection setting of rudder control system.
Further, the footrest component includes that main shaft, main shaft sleeve, auxiliary spindle, auxiliary spindle sleeve, left master are foot-operated
Plate, left secondary foot pedal, right main pedal and right major-minor pedal；The main shaft is rotatably assorted in the main shaft sleeve, institute
It states auxiliary spindle to be rotatably assorted in the auxiliary spindle sleeve, be rotatably equipped with respectively on the main shaft sleeve and auxiliary spindle sleeve
Pedal support, the pedal support are fixedly connected with fuselage, the main shaft sleeve and auxiliary spindle sleeve pass through respectively slotting ear with
The left lever and right pull rod are hinged；Left secondary foot pedal setting the left main pedal and the right main pedal it
Between, between institute's left secondary foot pedal and the right secondary foot pedal, the main shaft sleeve and pair turn for the right main pedal setting
Shaft is fixedly connected with by connector respectively on shaft sleeve, the shaft upper end is rotatably equipped with axle sleeve, and the left master is foot-operated
Plate, left secondary foot pedal, right main pedal and right secondary pedal two sides are fixedly installed with floor, the left main pedal and right main foot
The floor being arranged on pedal is fixedly connected with the axle sleeve of main shaft sleeve both ends setting respectively, the left secondary foot pedal and right secondary foot
The floor being arranged on pedal is fixedly connected with the axle sleeve of auxiliary spindle sleeve both ends setting respectively.
In this way, awing, driver tramples left main pedal, left secondary foot pedal, right main pedal, right major-minor pedal,
Left main pedal, left secondary foot pedal, right main pedal, right major-minor pedal drive main shaft sleeve or auxiliary spindle sleeve to turn respectively
It is dynamic, and then left lever pulling or right pull rod is driven to pull, so that intermediate draw bar passes through back segment pull rod drive side around rotation point rotation
Deflection to the direction of rudder, to control the rotation of rudder.
Further, the main shaft connect setting, the pair by needle bearing with the end of the main shaft sleeve
Shaft connect setting by needle bearing with the end of the auxiliary spindle sleeve.Friction can be reduced, the service life is extended.
To sum up, in rudder of aircraft manipulation device, using rigid transmission system, overall structure is simple, material selection aluminium
Light weight intensity is high, and repair and maintenance is convenient, high reliablity better economy；Rudder is drawn in this rudder of aircraft manipulation device
Bar, rudder rocker arm and rocker arm support combination limitation rudder pull rod freedom degree, keep rudder pull rod axially straight along pull rod
Line movement, structure are reliable；Control to rudder kick can be completed by only needing to trample before and after driver pedal, make rudder control
Flexibly, it is easy to grasp；Transmission system uses pull rod Linear transmission, cheap, has saved cost.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of light aerocraft rudder control device disclosed by the invention.
Fig. 2 is the connection structure enlarged diagram of rocker arm support, rudder rocker arm and back segment pull rod in Fig. 1.
Fig. 3 is the connection structure enlarged diagram of pedal support and main shaft sleeve and auxiliary spindle sleeve in Fig. 1.
Fig. 4 is the link position enlarged diagram of left lever in Fig. 1, intermediate draw bar, right pull rod and back segment pull rod.
Fig. 5 is the structural schematic diagram of pedal assembly.
Fig. 6 is the structure enlargement diagram in Fig. 5 on rear side of left main pedal.
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.
Referring to Fig.1-6,
A kind of light aerocraft rudder control device, including footrest component, rudder pull rod, rudder rocker arm 101, rocker arm
Support 102 and rudder 103；The footrest component is connect with the rudder pull rod, if the rudder pull rod is provided with
Dry, the junction of the adjacent rudder pull rod is connect with the rudder rocker arm 101,101 lower end of the rudder rocker arm hinge
It is connected to rocker arm support 102, the rocker arm support 102 is fixedly connected with fuselage, and the rudder pull rod and the rudder 103 connect
Connect setting.
In this way, rudder control device uses rigid transmission system, driver tramples footrest component, drives rudder pull rod
Movement, and then rudder kick is driven by rudder pull rod.Specifically, rudder pressure ratio and rocker arm support are used for direction
Rudder pull rod is limited, so that rudder pull rod is only capable of axially movable, improving reliability.
In the present embodiment, the rudder pull rod includes left lever 104, right pull rod 105, intermediate draw bar 106 and several
Back segment pull rod 107, the left lever 104 and 105 one end of right pull rod are hinged with footrest component respectively, the left lever 104 and the right side
The other end of pull rod 105 is hinged with the both ends of the intermediate draw bar 106 respectively, described 106 one end of intermediate draw bar and back segment pull rod
107 is hinged, and the adjacent back segment pull rod 107 is hinged, hinged positioned at last back segment pull rod 107 and the rudder 103,
The centre of the intermediate draw bar 106 and fuselage are rotatablely connected；The junction of the adjacent back segment pull rod 107 is hinged with the direction
Rudder rocker arm 101.
In this way, acting in footrest component, left lever movement is driven, left lever is transferred to back segment pull rod by intermediate draw bar,
Rudder is driven to deflect to side by back segment pull rod.When needing rudder to deflect to the other side, footrest component drives right drawing
Bar movement.Manoeuvrable is easy to grasp, is driven using pull rod, at low cost.
In the present embodiment, is connected and be arranged by bearing between the back segment pull rod 107 and the rudder rocker arm 101.It can
Preferably to relatively rotate.The bearing is self-aligning ball bearing.
In the present embodiment, the rudder pull rod is made by aluminium.Light weight, intensity is high, better meets requirement.
In the present embodiment, between the left lever 104 and intermediate draw bar 106, between right pull rod 105 and intermediate draw bar 106
And pylon line 108 is provided between intermediate draw bar 106 and back segment pull rod 107.Electrostatic can be preferably prevented, is improved reliable
Property.Specifically, pylon line connect setting with complete machine rudder control system.
In the present embodiment, including main shaft 1, main shaft sleeve 11, auxiliary spindle 2, auxiliary spindle sleeve 21, left main pedal 3,
Left secondary foot pedal 4, right main pedal 5 and right major-minor pedal 6；The main shaft 1 is rotatably assorted in the main shaft sleeve 11,
The auxiliary spindle 2 is rotatably assorted in the auxiliary spindle sleeve 21, on the main shaft sleeve 11 and auxiliary spindle sleeve 21 respectively
It is rotatably equipped with pedal support 7, the pedal support 7 is fixedly connected with fuselage, the main shaft sleeve 11 and auxiliary spindle sleeve
21 is hinged by slotting ear 22 and the left lever 104 and right pull rod 105 respectively；The left secondary foot pedal 4 is arranged in the left master
Between foot pedal 2 and the right main pedal 5, the right setting of main pedal 5 is foot-operated in institute's left secondary foot pedal 4 and the right pair
Between plate 6, shaft 8 is fixedly connected with by connector 23 respectively on the main shaft sleeve 11 and auxiliary spindle sleeve 21, it is described
8 upper end of shaft is rotatably equipped with axle sleeve 81, the left main pedal 3, left secondary foot pedal 4, right main pedal 5 and right secondary pedal 6
Two sides are fixedly installed with floor 61, the floor being arranged on the left main pedal 3 and right main pedal 5 respectively with main shaft set
The axle sleeve of 11 both ends of cylinder setting is fixedly connected, and the floor being arranged on the left secondary foot pedal 4 and right secondary foot pedal 6 turns with pair respectively
The axle sleeve of 12 both ends of shaft sleeve setting is fixedly connected.
In this way, awing, driver tramples left main pedal, left secondary foot pedal, right main pedal, right major-minor pedal,
Left main pedal, left secondary foot pedal, right main pedal, right major-minor pedal drive main shaft sleeve or auxiliary spindle sleeve to turn respectively
It is dynamic, and then left lever pulling or right pull rod is driven to pull, so that intermediate draw bar passes through back segment pull rod drive side around rotation point rotation
Deflection to the direction of rudder, to control the rotation of rudder.When driver is completed in deflection decontrols foot pedal, at shaft and machine
The return spring work of body connection, makes pedal return to middle position；
In the present embodiment, the main shaft 1 connect setting, institute by needle bearing with the end of the main shaft sleeve 21
It states auxiliary spindle 2 and setting is connect by needle bearing with the end of the auxiliary spindle sleeve 21.Friction can be reduced, the service life is extended.
Working principle:
Awing, driver tramples left main pedal, left secondary foot pedal, right main pedal, right major-minor pedal, left main foot
Pedal, left secondary foot pedal, right main pedal, right major-minor pedal drive main shaft sleeve or auxiliary spindle sleeve to rotate respectively, in turn
Left lever pulling or right pull rod is driven to pull, so that intermediate draw bar passes through back segment pull rod drive rudder around rotation point rotation
The deflection in direction, to control the rotation of rudder.
The foregoing is only a preferred embodiment of the present invention, but scope of protection of the present invention is not limited thereto,
Anyone skilled in the art in the technical scope disclosed by the present invention, according to the technique and scheme of the present invention and its
Inventive concept is subject to equivalent substitution or change, should be covered by the protection scope of the present invention.
Claims (8)
1. a kind of light aerocraft rudder control device, which is characterized in that shaken including footrest component, rudder pull rod, rudder
Arm, rocker arm support and rudder；The footrest component is connect with the rudder pull rod, if the rudder pull rod is provided with
Dry, the junction of the adjacent rudder pull rod is connect with the rudder rocker arm, and rudder rocker arm lower end, which is hinged with, shakes
Arm support, the rocker arm support are fixedly connected with fuselage, and the rudder pull rod connect setting with the rudder.
2. a kind of light aerocraft rudder control device according to claim 1, which is characterized in that the rudder pull rod
Including left lever, right pull rod, intermediate draw bar and several back segment pull rods, the left lever and right pull rod one end respectively with foot-operated group
Part is hinged, and the other end of the left lever and right pull rod is hinged with the both ends of the intermediate draw bar respectively, the intermediate draw bar one
End is hinged with back segment pull rod, and the adjacent back segment pull rod is hinged, hinged positioned at last back segment pull rod and the rudder,
The centre of the intermediate draw bar and fuselage are rotatablely connected；The junction of the adjacent back segment pull rod is hinged with the rudder and shakes
Arm.
3. a kind of light aerocraft rudder control device according to claim 1, which is characterized in that the back segment pull rod with
It is connected and is arranged by bearing between the rudder rocker arm.
4. a kind of light aerocraft rudder control device according to claim 1, which is characterized in that the bearing is aligning
Ball bearing.
5. a kind of light aerocraft rudder control device according to claim 1, which is characterized in that the rudder pull rod
It is made by aluminium.
6. a kind of light aerocraft rudder control device according to claim 1, which is characterized in that the left lever is in
Between be provided with pylon line between pull rod, between right pull rod and intermediate draw bar and between intermediate draw bar and back segment pull rod.
7. a kind of light aerocraft rudder control device according to claim 1, which is characterized in that the footrest component packet
Include main shaft, main shaft sleeve, auxiliary spindle, auxiliary spindle sleeve, left main pedal, left secondary foot pedal, right main pedal and right master
Secondary pedal；The main shaft is rotatably assorted in the main shaft sleeve, and the auxiliary spindle is rotatably assorted in the auxiliary spindle set
In cylinder, pedal support is rotatably equipped on the main shaft sleeve and auxiliary spindle sleeve respectively, the pedal support and fuselage are solid
Fixed connection, the main shaft sleeve and auxiliary spindle sleeve passes through slotting ear respectively and the left lever and right pull rod are hinged；The left side
Secondary foot pedal is arranged between the left main pedal and the right main pedal, and the right main pedal is arranged in institute's left secondary foot
Between pedal and the right secondary foot pedal, it is fixedly connected with respectively by connector on the main shaft sleeve and auxiliary spindle sleeve
Shaft, the shaft upper end are rotatably equipped with axle sleeve, and the left main pedal, left secondary foot pedal, right main pedal and right pair are stepped on
Plate two sides are fixedly installed with floor, the floor being arranged on the left main pedal and right main pedal respectively with main shaft sleeve
The axle sleeve of both ends setting is fixedly connected, the floor being arranged on the left secondary foot pedal and right secondary foot pedal respectively with auxiliary spindle sleeve
The axle sleeve of both ends setting is fixedly connected.
8. a kind of light aerocraft rudder control device according to claim 7, which is characterized in that the main shaft and institute
The end for stating main shaft sleeve is connected by needle bearing to be arranged, and the end of the auxiliary spindle and the auxiliary spindle sleeve passes through rolling
Needle bearing connection setting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910822017.8A CN110422319A (en) | 2019-09-02 | 2019-09-02 | A kind of light aerocraft rudder control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910822017.8A CN110422319A (en) | 2019-09-02 | 2019-09-02 | A kind of light aerocraft rudder control device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110422319A true CN110422319A (en) | 2019-11-08 |
Family
ID=68418481
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910822017.8A Pending CN110422319A (en) | 2019-09-02 | 2019-09-02 | A kind of light aerocraft rudder control device |
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| Country | Link |
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| CN (1) | CN110422319A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111572757A (en) * | 2020-05-09 | 2020-08-25 | 陕西飞机工业（集团）有限公司 | Method for designing driving mechanism of follow-up control surface of aircraft rudder |
| CN112173068A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Adjustable helicopter side end plate structure |
| CN113148115A (en) * | 2021-03-25 | 2021-07-23 | 中国商用飞机有限责任公司 | Rudder balancing system for aircraft and control method thereof |
| CN117682055A (en) * | 2024-02-02 | 2024-03-12 | 捷中鲨鱼(沧州)飞机制造有限公司 | Pedal control device for rudder of light aircraft |
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| CN208813495U (en) * | 2018-09-03 | 2019-05-03 | 重庆恩斯特龙通用航空技术研究院有限公司 | A kind of aircraft evelvator manipulation device |
| CN109911173A (en) * | 2018-12-29 | 2019-06-21 | 福建野马飞机制造有限公司 | A kind of light-duty sport plane |
| CN210526837U (en) * | 2019-09-02 | 2020-05-15 | 重庆恩斯特龙通用航空技术研究院有限公司 | Light airplane rudder control device |
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| FR820413A (en) * | 1936-07-17 | 1937-11-10 | D Aviat Louis Breguet Atel | Refinements to the elastic control system of the warping ailerons |
| JP2000272591A (en) * | 1999-03-24 | 2000-10-03 | Mitsubishi Heavy Ind Ltd | Piloting pedal for two-seat cockpit |
| CN208813495U (en) * | 2018-09-03 | 2019-05-03 | 重庆恩斯特龙通用航空技术研究院有限公司 | A kind of aircraft evelvator manipulation device |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111572757A (en) * | 2020-05-09 | 2020-08-25 | 陕西飞机工业（集团）有限公司 | Method for designing driving mechanism of follow-up control surface of aircraft rudder |
| CN111572757B (en) * | 2020-05-09 | 2023-03-14 | 陕西飞机工业（集团）有限公司 | Method for designing driving mechanism of follow-up control surface of aircraft rudder |
| CN112173068A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Adjustable helicopter side end plate structure |
| CN113148115A (en) * | 2021-03-25 | 2021-07-23 | 中国商用飞机有限责任公司 | Rudder balancing system for aircraft and control method thereof |
| CN113148115B (en) * | 2021-03-25 | 2024-03-22 | 中国商用飞机有限责任公司 | Rudder trimming system for aircraft and control method thereof |
| CN117682055A (en) * | 2024-02-02 | 2024-03-12 | 捷中鲨鱼(沧州)飞机制造有限公司 | Pedal control device for rudder of light aircraft |
| CN117682055B (en) * | 2024-02-02 | 2024-05-07 | 捷中鲨鱼(沧州)飞机制造有限公司 | Pedal control device for rudder of light aircraft |
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