CN115123521A - Flap control system of light airplane - Google Patents
Flap control system of light airplane Download PDFInfo
- Publication number
- CN115123521A CN115123521A CN202210807159.9A CN202210807159A CN115123521A CN 115123521 A CN115123521 A CN 115123521A CN 202210807159 A CN202210807159 A CN 202210807159A CN 115123521 A CN115123521 A CN 115123521A
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- control
- cable
- flap
- wing
- swing
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- 230000005540 biological transmission Effects 0.000 abstract description 13
- 230000007246 mechanism Effects 0.000 description 7
- 229910000831 Steel Inorganic materials 0.000 description 5
- 239000010959 steel Substances 0.000 description 5
- 101001017827 Mus musculus Leucine-rich repeat flightless-interacting protein 1 Proteins 0.000 description 3
- 230000001174 ascending effect Effects 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
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010899 nucleation Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
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Classifications
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- 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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Automation & Control Theory (AREA)
- Mechanical Control Devices (AREA)
Abstract
The invention discloses a light airplane flap control system.A right flap is hinged with a right wing swing connecting rod, the other end of the right wing swing connecting rod is hinged with a right wing swing arm, a right wing swing lever is also fixedly installed on a right wing swing shaft, and a right rear stay cable and a right front stay cable are respectively fixedly buckled at two extending ends of the right wing swing lever; a left wing swing connecting rod is hinged on the left wing flap, a left wing swing arm is fixedly arranged on a swingable left wing swing shaft, a left wing swing lever is also fixedly arranged on the left wing swing shaft, and a left rear pull rope and a left front pull rope are fixedly fastened at two extending ends of the left wing swing lever respectively; the control swing shaft is fixedly connected with a control swing arm, a control rear cable tied to the control swing arm is connected with the right rear cable and the left rear cable, and a control front cable tied to the control swing arm bypasses the control pulley and is connected with the right front cable and the left front cable. The control system can realize remote control of the flap, and has good control transmission rigidity and high control reliability.
Description
Technical Field
The invention relates to a flight control system of a light aircraft, in particular to a soft control mechanism of a flap of the light aircraft.
Background
The light airplane has the characteristics of portability, safety and low use requirement, and is widely applied to various fields of private flight, air browsing, geological exploration, emergency rescue, seeding and fertilizing, fire extinguishing, ore prospecting and the like. The light aircraft control system is a system for controlling the flight attitude by a pilot to control a control surface and a corresponding mechanism of the aircraft, and comprises a flap control system, an aileron control system, an elevator control system and the like.
The flap is a wing surface arranged on the inner side of the trailing edge of the wing, the flap control system is a mechanism for controlling the flap to deflect around the axial direction and the downward direction, the deflection angle of the flap is mainly controlled to increase the camber of the wing so as to increase the lift force, when the airplane takes off, the extension angle of the flap is smaller, the effect of increasing the lift force day is mainly played to accelerate the take off of the airplane, when the airplane lands, the extension angle of the flap is larger, so that the lift force and the drag force of the airplane are increased at the same time, and the landing speed is favorably reduced. At present, most flap control mechanisms mainly comprise rigid elements such as pull rods, rocker arms and the like, the transmission rigidity is good, the requirement on space is relatively low, but the transmission links and the transmission distance of the control mechanism are limited, the control surface control synchronism of the left flap and the right flap is insufficient, especially the manual control is relatively complex, and the requirement on drivers is relatively high.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a light aircraft flap control system, which not only can realize remote control of a flap and is convenient to control, but also has good control transmission rigidity and high control reliability.
In order to solve the technical problem, the light aircraft flap control system comprises a right flap, a left flap, a control swing shaft and a control handle, wherein the control swing shaft and the control handle are fixedly connected with each other; the left flap is hinged with a left flap swing connecting rod, the other end of the left flap swing connecting rod is hinged with a left flap swing arm, the left flap swing arm is fixedly arranged on a swing shaft of the swing left flap, a left flap swing lever is also fixedly arranged on the swing shaft of the swing left flap, and a left rear pull rope and a left front pull rope are fixedly buckled at two extending ends of the left flap swing lever respectively; the control swing shaft is fixedly connected with a control swing arm, a control rear pull rope tied to the control swing arm is connected with a right rear pull rope and a left rear pull rope, and a control front pull rope tied to the control swing arm bypasses a control pulley to be connected with a right front pull rope and a left front pull rope.
In the structure, the right flap and the left flap are respectively controlled to deflect by the corresponding steel wire inhaul cables, so that the remote control of the flaps can be realized, the control transmission structure is simplified, the reasonable design and arrangement of a control console and a control handle are facilitated by the inhaul cable control, and the space occupied by the control transmission mechanism is saved; the inhaul cable only bears the pulling force, and the instability problem caused by the transmission and the operation of the pressure lever is also avoided. And because the left and right flaps are respectively fixed with the two extending ends of the swing lever and are respectively fastened with the corresponding front guy cable and rear guy cable, and these front and rear guys of the flaps are respectively connected with the operation front guy cable and the operation rear guy cable, so that a double guy cable structure is formed, and the front guy cable and the rear guy cable are always in opposite tensioning and stretching directions, so that the transmission rigidity of the operation guy cable is greatly enhanced, and the safety and reliability of flap operation are effectively improved, in particular, the right front guy cable for operating the right flap and the left front guy cable for operating the left flap are connected with the operation front guy cable after being connected in parallel, and the right rear guy cable for operating the right flap and the left rear guy cable for operating the left and right flaps after being connected in parallel, so that the operation of the left and right flaps can be realized by operating a handle, the operation becomes more convenient, and the operation synchronism of the left and right flaps can be effectively ensured by the mutual connection of the corresponding guy cables, the control performance and the control safety of the mechanism are enhanced.
In a further embodiment of the invention, the right inhaul cable is connected with the rear control inhaul cable by sequentially passing through the right rear inhaul cable pulley, the right inhaul cable pulley block and the inhaul cable pulley block; the right front stay cable is connected with the control front stay cable by sequentially bypassing the right stay cable pulley block and the stay cable pulley block. The left rear stay cable is connected with the control rear stay cable by sequentially bypassing the left rear stay cable pulley, the left stay cable pulley block and the stay cable pulley block, and the left front stay cable is connected with the control front stay cable by sequentially bypassing the left stay cable pulley block and the stay cable pulley block. The arrangement path of the inhaul cable can be flexibly arranged, the pulling direction of the inhaul cable can be flexibly changed, the space arrangement of the inhaul cable is more convenient, and the structure is more compact.
In a further embodiment of the present invention, the control pendulum shaft is arranged on the control pendulum shaft seat in a swinging manner, and a shift adjusting groove is arranged on the control pendulum shaft seat. The multi-gear regulation and control of the deflection angle of the front flap can be realized so as to meet the requirements of the airplane on ascending, flying and landing.
In a further embodiment of the invention, the control cable pulley is located on the front side of the control rocker arm and the control rocker shaft. The synchronous control of the double guys can be realized, and the control stability and the transmission rigidity are improved.
In a further embodiment of the present invention, the right cable pulley block and the left cable pulley block are both composed of two coaxial pulley discs capable of rotating relatively, and the cable pulley block is composed of four coaxial pulley discs capable of rotating relatively. The independent guide of two cables can be realized, the mutual transmission interference of adjacent cables is avoided, and the reliability of transmission is improved.
In a preferred embodiment of the present invention, the right wing swing link is hinged to the right flap through a right wing link seat, and the right wing swing shaft is swingably supported on the right wing swing shaft seat. The left wing swing connecting rod is hinged with the left wing flap through a left wing connecting rod seat, and the left wing swing shaft can be supported on the left wing swing shaft seat in a swinging mode. The structure is simple and reasonable.
In a further embodiment of the present invention, a right wing hinge support is fixedly disposed on the right flap, and a left wing hinge support is fixedly disposed on the left flap. Deflection control of the flap is facilitated.
Drawings
The flap control system for a lightweight aircraft according to the invention is described in more detail below with reference to the drawings and the description.
FIG. 1 is a schematic structural view of one embodiment of a lightweight aircraft flap control system of the present invention;
FIG. 2 is a schematic view of a right flap yaw drive configuration of the embodiment shown in FIG. 1;
FIG. 3 is a schematic view of a left flap yaw drive configuration of the embodiment of FIG. 1;
FIG. 4 is a schematic diagram of the manual actuation of the transmission of the embodiment of FIG. 1;
fig. 5 is a schematic view of the structure of fig. 4 from another view angle.
In the figure, 1-right flap, 101-right flap link base, 102-right flap swing link, 103-right flap swing arm, 104-right flap swing shaft, 105-right flap swing shaft base, 106-right flap hinge base, 107-right flap swing lever, 2-left flap, 201-left flap link base, 202-left flap swing link, 203-left flap swing arm, 204-left flap swing shaft, 205-left flap swing shaft base, 206-left flap hinge base, 207-left flap swing lever, 3-right rear cable, 301-right rear cable pulley, 4-right front cable, 5-left rear cable, 501-left rear cable pulley, 6-left front cable, 7-right cable pulley block, 8-left cable pulley block, 9-cable pulley block, 10-operation rear cable, 11-operation front cable, 12-operation swing arm, 13-operation swing shaft, 14-operation pendulum, 15-shift groove, 16-operation handle, 17-operation pulley block.
Detailed Description
In the flap control system of the light airplane shown in fig. 1, a right flap 1 is positioned at the rear part of the right wing of the airplane and close to the right side of the airplane, and a left flap 2 is positioned at the rear part of the left wing of the airplane and close to the left side of the airplane. The right flap 1 is hinged on the cross beam of the right wing by the right wing hinged supports 106 below the two sides of the right flap, and the left flap 2 is hinged on the cross beam of the left wing by the left wing hinged supports 206 below the two sides of the left flap. The control system also comprises a control swing shaft 13, the control swing shaft 13 is rotatably supported on the airplane body beam through a control swing shaft seat 14 corresponding to the position of the control swing shaft 13, the control swing shaft 13 is also fixedly welded with a control swing arm 12 extending downwards and a control handle 16 extending forwards for manual control, an arc-shaped gear shifting groove 15 is arranged on a side plate of the control swing shaft seat 14, and three gear openings are arranged on the gear shifting groove 15 so as to enable the control handle 16 to be positioned at three positions which respectively correspond to the ascending stage, the flying stage and the descending stage of the airplane. The operating swing arm 12 is fixedly buckled with an operating rear cable 10 and an operating front cable 11, and the operating front cable 11 and the operating rear cable 10 are aviation steel cables.
As shown in fig. 2, one end of the right wing swing link 102 is hinged to the right wing link seat 101, the right wing link seat 101 is fixed to a rib plate of the right flap 1, the other end of the right wing swing link 102 is hinged to the right wing swing arm 103, the right wing swing arm 103 is fixedly mounted on the right wing swing shaft 104, the right wing swing shaft 104 is swingably supported on the right wing swing shaft seat 105, and the right wing swing shaft seat 105 is fixedly mounted on a cross beam of the aircraft wing. A right wing swing lever 107 is also fixedly installed at the inner end position of the right wing swing shaft 104, and the right wing swing lever 107 is perpendicular to the axis line of the right wing swing shaft 104. The two extending ends of the right wing swing lever 107 are respectively fixed and buckled with a right rear cable 3 and a right front cable 4, and the buckling points of the right rear cable 3 and the right front cable 4 are symmetrically positioned at two sides of the axial lead of the right wing shaft 104. The right rear stay 3 and the right front stay 4 also adopt aviation steel wire ropes.
As shown in fig. 3, one end of the left wing swing link 202 is hinged to the left wing link base 202, the left wing link base 202 is fixed to a rib plate of the left flap 2, the other end of the left wing swing link 202 is hinged to the left wing swing arm 203, the left wing swing arm 203 is fixedly mounted to the left wing swing shaft 204, the left wing swing shaft 204 is swingably supported to the left wing swing shaft base 205, and the left wing swing shaft base 205 is fixedly mounted to a cross beam of the aircraft wing. A left wing swing lever 207 is also fixedly installed at the inner end position of the left wing swing shaft 204, and the left wing swing lever 207 is perpendicular to the axis line of the left wing swing shaft 204. The left wing swing lever 207 is fixedly buckled with a left rear cable 5 and a left front cable 6 at two extending ends thereof, and the buckling points of the left rear cable 5 and the left front cable 6 are symmetrically located at two sides of the axial line of the left wing swing shaft 204. The left rear stay 5 and the left front stay 6 also adopt aviation steel wire ropes.
As shown in fig. 1, 4 and 5, the right rear cable 3 fastened to the rear end of the right wing swing lever 107 is connected to the rear steering cable 10 by passing through the right rear cable pulley 301, the right cable pulley block 7 and the cable pulley block 9 in sequence. The right front cable 4 which is fixedly fastened at the front end of the right wing swing lever 107 sequentially bypasses the right cable pulley block 7 and the cable pulley block 9 to be connected with the front control cable 11.
The left rear stay 5 at the rear end of the left wing swing lever 207 of the fixing buckle is connected with the operation rear stay 10 by sequentially passing through the left rear stay pulley 501, the left stay pulley block 8 and the stay pulley block 9. The left front cable 6 tied at the front end of the left wing swing lever 207 of the fixing buckle is connected with the front control cable 11 by sequentially bypassing the left cable pulley block 8 and the cable pulley block 9.
The right rear cable pulley 301 and the left rear cable pulley 501 are single-piece cable pulley sheaves, and the right rear cable pulley 301 and the left rear cable pulley 501 are rotatably supported by the body frame of the aircraft via their corresponding pulley support shafts. The right cable pulley block 7 comprises two coaxially-rotating and superposed pulley discs which are rotatably supported on the frame body of the airplane body through corresponding pulley fulcrum shafts, and the two pulley discs respectively correspond to the right rear cable 3 and the right front cable 4. The left cable pulley block 8 also comprises two coaxially and rotatably superposed pulley discs which are rotatably supported on the frame body of the airplane body through corresponding pulley fulcrum shafts, and the two pulley discs respectively correspond to the left rear cable 5 and the left front cable 6.
The cable pulley 9 comprises four pulley discs coaxially rotating and overlapping, the four pulley discs are rotatably supported on the frame body of the airplane body through corresponding pulley fulcrum shafts, and the four pulley discs respectively correspond to the right rear cable 3, the right front cable 4, the left rear cable 5 and the left front cable 6. The right rear cable 3 and the left rear cable 5 are connected with the control rear cable 10 after bypassing the cable pulley block 9 and connected in parallel, and the other end of the control rear cable 10 is fixedly buckled on the control swing arm 12. The right front cable 4 and the left front cable 6 are also connected with one end of the front control cable 11 after passing through the cable pulley block 9 and are connected with each other, the other end of the front control cable 11 passes through the control cable pulley 17 and is fixedly fastened on the control swing arm 12, and the control cable pulley 17 is positioned at the front side position of the control swing arm 12 and the control swing shaft 13. The cable pulley 17 is also a single-piece cable pulley disc which is rotatably supported on the aircraft fuselage carrier by means of a corresponding pulley pivot. The rear cable 10 and the front cable 11 are also operated by aviation steel cables.
Claims (9)
1. A flap control system of a light aircraft, comprising a right flap (1) and a left flap (2), and a control swing shaft (13) and a control handle (16) which are fixedly connected with each other, characterized in that: a right wing swing connecting rod (102) is hinged to the right flap (1), the other end of the right wing swing connecting rod (102) is hinged to a right wing swing arm (103), the right wing swing arm (103) is fixedly mounted on a right wing swing shaft (104) capable of swinging, a right wing swing lever (107) is further fixedly mounted on the right wing swing shaft (104), and a right rear pull rope (3) and a right front pull rope (4) are respectively fixedly buckled at two extending ends of the right wing swing lever (107); a left wing swing connecting rod (202) is hinged on the left wing flap (2), the other end of the left wing swing connecting rod (202) is hinged with a left wing swing arm (203), the left wing swing arm (203) is fixedly arranged on a left wing swing shaft (204) which can swing, a left wing swing lever (207) is also fixedly arranged on the left wing swing shaft (204), and a left rear pull rope (5) and a left front pull rope (6) are fixedly buckled at two extending ends of the left wing swing lever (207) respectively; the control swing shaft (13) is fixedly connected with a control swing arm (12), a control rear inhaul cable (10) tied to the control swing arm (12) is connected with the right rear inhaul cable (3) and the left rear inhaul cable (5), and a control front inhaul cable (11) tied to the control swing arm (12) is connected with the right front inhaul cable (4) and the left front inhaul cable (6) by bypassing the control pulley (17).
2. The light aircraft flap actuation system of claim 1, wherein: the right cable (3) sequentially bypasses a right rear cable pulley (301), a right cable pulley block (7) and a cable pulley block (9) to be connected with a control rear cable (10); the right front cable (4) is connected with the control front cable (11) by sequentially bypassing the right cable pulley block (7) and the cable pulley block (9).
3. The flap manipulation system for a light weight aircraft of claim 1, wherein: the left rear stay cable (5) is connected with the control rear stay cable (10) by sequentially bypassing the left rear stay cable pulley block (501), the left stay cable pulley block (8) and the stay cable pulley block (9), and the left front stay cable (6) is connected with the control front stay cable (11) by sequentially bypassing the left stay cable pulley block (8) and the stay cable pulley block (9).
4. The light aircraft flap actuation system of claim 1, wherein: the control pendulum shaft (13) is arranged on the control pendulum shaft seat (14) in a swinging mode, and a gear shifting groove (15) is formed in the control pendulum shaft seat (14).
5. The flap manipulation system for a light weight aircraft of claim 1, wherein: the control cable pulley (17) is positioned at the front side of the control swing arm (12) and the control swing shaft (13).
6. The light aircraft flap actuation system of claim 1, wherein: the right guy cable pulley block (7) and the left guy cable pulley block (8) are both composed of two coaxial pulley discs capable of rotating relatively, and the guy cable pulley block (9) is composed of four coaxial pulley discs capable of rotating relatively.
7. The light aircraft flap actuation system of claim 1, wherein: the right wing swing connecting rod (102) is hinged with the right flap (1) through a right wing connecting rod seat (101), and the right wing swing shaft (104) is supported on the right wing swing shaft seat (105) in a swinging mode.
8. The light aircraft flap actuation system of claim 1, wherein: the left wing swing connecting rod (202) is hinged with the left wing flap (2) through a left wing connecting rod seat (201), and the left wing swing shaft (204) is supported on a left wing swing shaft seat (205) in a swinging mode.
9. The light aircraft flap actuation system of claim 1, wherein: the right flap (1) is fixedly provided with a right wing hinged support (106), and the left flap (2) is fixedly provided with a left wing hinged support (206).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210807159.9A CN115123521A (en) | 2022-07-11 | 2022-07-11 | Flap control system of light airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210807159.9A CN115123521A (en) | 2022-07-11 | 2022-07-11 | Flap control system of light airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115123521A true CN115123521A (en) | 2022-09-30 |
Family
ID=83380964
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210807159.9A Pending CN115123521A (en) | 2022-07-11 | 2022-07-11 | Flap control system of light airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115123521A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428529A (en) * | 2016-09-23 | 2017-02-22 | 江西洪都航空工业集团有限责任公司 | Control mechanism for trailing edge flap of agriculture light airplane |
| CN108313268A (en) * | 2017-01-17 | 2018-07-24 | 湖南山河科技股份有限公司 | A kind of light aerocraft Aileron control system |
| CN109911180A (en) * | 2019-04-15 | 2019-06-21 | 重庆恩斯特龙通用航空技术研究院有限公司 | A kind of light aerocraft flap runners |
| US20210316840A1 (en) * | 2018-08-20 | 2021-10-14 | Airbus Defence and Space GmbH | Flap support for supporting a flap of a wing for an aircraft |
| CN217805242U (en) * | 2022-07-11 | 2022-11-15 | 湖南翔龙飞机有限公司 | Light aircraft flap control system |
-
2022
- 2022-07-11 CN CN202210807159.9A patent/CN115123521A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428529A (en) * | 2016-09-23 | 2017-02-22 | 江西洪都航空工业集团有限责任公司 | Control mechanism for trailing edge flap of agriculture light airplane |
| CN108313268A (en) * | 2017-01-17 | 2018-07-24 | 湖南山河科技股份有限公司 | A kind of light aerocraft Aileron control system |
| US20210316840A1 (en) * | 2018-08-20 | 2021-10-14 | Airbus Defence and Space GmbH | Flap support for supporting a flap of a wing for an aircraft |
| CN109911180A (en) * | 2019-04-15 | 2019-06-21 | 重庆恩斯特龙通用航空技术研究院有限公司 | A kind of light aerocraft flap runners |
| CN217805242U (en) * | 2022-07-11 | 2022-11-15 | 湖南翔龙飞机有限公司 | Light aircraft flap control system |
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