CN109720550B - Side lever mechanism for purely mechanical flight control system - Google Patents
Side lever mechanism for purely mechanical flight control system Download PDFInfo
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- CN109720550B CN109720550B CN201811340177.0A CN201811340177A CN109720550B CN 109720550 B CN109720550 B CN 109720550B CN 201811340177 A CN201811340177 A CN 201811340177A CN 109720550 B CN109720550 B CN 109720550B
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- rotating shaft
- rocker arm
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- groove
- side lever
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Abstract
The invention relates to a side lever mechanism for a purely mechanical flight control system, which comprises a side lever handle (1), a support (2), a transverse output rocker arm (3), a bolt (6), a nut (5), a longitudinal output rocker arm (7), a support (9) and a groove-type rotating shaft (10); the side lever handle (1) and the longitudinal output rocker arm (7) are fixedly connected together through a bolt (6) and a nut (5) penetrating through the groove-shaped rotating shaft (10), when the side lever handle (1) rotates around the axis a-a during pushing or pulling a rod, the longitudinal transmission rod (8) is driven to move through the longitudinal output rocker arm (7), the movement is transmitted to the elevator control system, and at the moment, the transverse output rocker arm (3) cannot move, namely, the aileron control system cannot move. The rotating shaft line of the longitudinal output rocker arm and the rotating shaft line of the transverse output are intersected at one point, so that the longitudinal output motion and the transverse output motion are ensured not to be affected.
Description
Technical Field
The invention belongs to the field of flight control systems, and relates to a cabin control form and a transmission mechanism in a flight control system.
Background
The sidestick is a cockpit steering device in a fixed wing aircraft flight control system that receives and transmits pilot forces and displacement commands that are transmitted to the elevator or aileron via mechanical lines or cables to control deflection of the elevator or aileron. The side lever control technology is firstly applied to an fly-by-wire control system of an air-passenger aircraft, and after receiving the instructions of a pilot, the side lever device converts the instructions into electric signals and transmits the electric signals to corresponding actuators through buses, and the actuators push elevators or ailerons to deflect.
The maximum emission force of a pilot on a large-scale aircraft can not overcome the huge hinge moment of a control surface, so that the flight control systems of the large-scale aircraft are all power control systems of telex or booster; all the general aircraft, particularly the small aircraft, adopt the flying operation of a pure machine, in the flying operation system of the pure machine, the steering wheel and the central control rod are adopted, the steering wheel operation can occupy the precious instrument installation position on the instrument panel, and particularly the application of the multifunctional display screen on the general aircraft in recent years is very mature, and the position of the multifunctional display screen occupying the instrument panel promotes the steering wheel operation to change. Although the center stick can solve the above problems, the arrangement of the stick limits the movement space of the pilot and severely hinders the pilot from getting in and out of the cockpit of the general-purpose aircraft because the cockpit space of the general-purpose aircraft is limited and the arrangement is very compact. The steering wheel is arranged on the instrument panel to prevent the pilot from observing the sight of the instrument on the instrument panel to a certain extent; the push-pull rod connected with the steering wheel can penetrate through the instrument board, the control rods of the drivers and the copiers are connected on the back of the instrument board to form a transmission mechanism, and the transmission mechanism can be blocked by movement due to the fact that a large number of cables are arranged on the back of the instrument board. In addition, the pilot overcomes the hinge moment of the control surface by manipulating the steering wheel or the central lever, and according to the statistical data of human factors, the pilot can control the maximum limit acting force emitted by the steering wheel, and the limit acting force emitted by the central lever is controlled to be secondary, and the limit acting force emitted by the lateral lever is controlled to be minimum. It is therefore desirable to select the appropriate sidebar effective arm length and motion range to achieve the pilot's satisfactory lever force and stick displacement.
Disclosure of Invention
The invention aims to improve a hand control mechanism in cabin control of a purely mechanical flight control system, and applies a side lever to the purely mechanical flight control system of a general aircraft, particularly a small aircraft, wherein a longitudinal output rocker arm and a transverse output rocker arm are arranged in two mutually perpendicular planes so as to ensure mutual independence between longitudinal control and transverse control and avoid transverse and longitudinal coupling control.
In order to solve the technical problems, the technical scheme adopted by the invention for solving the technical problems is as follows: the side lever mechanism comprises a side lever handle, a longitudinal output rocker arm, a longitudinal transmission rod, a groove-shaped rotating shaft, a transverse output rocker arm, a transverse transmission rod, a support, a bolt and a nut, wherein the side lever handle and the longitudinal output rocker arm are fixedly connected into a whole, two sections of the groove-shaped rotating shaft are cylindrical, the middle part of the groove-shaped rotating shaft is in a groove shape, a small hole is formed in the middle groove shape, the bolt and the nut penetrate through the small hole in the middle of the groove-shaped rotating shaft and are hinged with the longitudinal output rocker arm together, the longitudinal output rocker arm rotates around the axis of the bolt to serve as longitudinal output, the longitudinal output rocker arm is hinged with the longitudinal transmission rod to transmit a motion instruction to an elevator control system, the transverse output rocker arm is fixedly connected with the groove-shaped rotating shaft into a whole, the groove-shaped rotating shaft is connected with the connecting body of the transverse output rocker arm around the axis of the support, and the transverse transmission rod is hinged with the transverse output rocker arm to transmit the motion instruction to the aileron control system, and the small hole is used for being connected with a structure on an airplane.
As a modification to the technical solution of the invention, the use of the sidesticks replaces the traditional steering wheel or central stick on a general aircraft, in particular a small aircraft, and the sidesticks are mounted on the sides of the pilot.
As an improvement on the independent mechanism of longitudinal and transverse output movement, the longitudinal output rocker arm and the transverse output rocker arm move in two mutually perpendicular planes, and meanwhile, the longitudinal output rocker arm is hinged with the groove-shaped rotating shaft and the fixing body of the transverse output rocker arm through the bolts and the nuts, so that the rotating shaft line of the longitudinal output rocker arm and the rotating shaft line of the transverse output rocker arm intersect at one point, and the side rod can be ensured to output movements in two directions without mutual interference. The specific scheme is as follows:
a side lever mechanism for a purely mechanical flight control system, which comprises a side lever handle 1, a support 2, a transverse output rocker arm 3, a bolt 6, a nut 5, a longitudinal output rocker arm 7, a support 9 and a groove-shaped rotating shaft 10; the side lever handle 1 and the longitudinal output rocker arm 7 are fixedly connected together through a bolt 6 and a nut 5 penetrating through the groove-shaped rotating shaft 10, when the side lever handle 1 is pushed or pulled, the side lever handle rotates around the transverse axis a-a of the groove-shaped rotating shaft 10, the longitudinal transmission rod 8 is driven to move through the longitudinal output rocker arm 7, the movement is transmitted to the elevator control system, and at the moment, the transverse output rocker arm 3 does not move, namely the aileron control system does not move.
Preferably, the lateral output rocker arm 3 is integrated with the groove-shaped rotating shaft 10, and is fixed on the machine body structure through the support 2 and the support 9.
Preferably, when the side lever is transversely operated, the side lever handle 1 rotates around the longitudinal axis b-b of the groove-shaped rotating shaft 10, the groove-shaped rotating shaft 10 is driven to rotate around the longitudinal axis b-b of the groove-shaped rotating shaft 10 together, the transverse transmission rod 4 is driven to move through the transverse output rocker arm 3, and the movement is transmitted to the aileron operation system; when the side lever handle 1 is controlled leftwards and rightwards, the longitudinal output rocker arm 7 at the lower end is driven to swing leftwards and rightwards in addition to the rotation of the groove-shaped rotating shaft 10.
Preferably, the bolt 6 and the nut 5 pass through a circular hole on the transverse axis a-a of the groove type rotating shaft 10
Preferably, in order to avoid coupling in the longitudinal and transverse directions, the output point of the longitudinal transmission rod 8 is on the longitudinal axis b-b of the grooved spindle 10.
The invention has the beneficial effects that: the difficulty of cabin arrangement caused by a traditional steering wheel or a central rod on a general aircraft, particularly a small aircraft is solved; the pilot can obtain more activity space, and a wider cockpit view is provided for the pilot; the arrangement of the side bars meets the requirements of human engineering, so that the pilot can control the pitching and rolling of the airplane more comfortably; meanwhile, the possibility that the transmission mechanism is blocked at the back of the instrument board is avoided, and the safety of the flight control system is improved.
Drawings
FIG. 1 is a schematic illustration of an arrangement of a sidebar mechanism on an aircraft for a purely mechanical flight control system of the present invention.
FIG. 2 is a schematic illustration of a side bar mechanism single side (side-to-side symmetrical arrangement) for a purely mechanical flight control system of the present invention.
In FIG. 2, the side lever handle, 2, the support, 3, the lateral output rocker, 4, the lateral drive rod, 5, the nut, 6, the bolt, 7, the longitudinal output rocker, 8, the longitudinal drive rod, 9, the support, 10, the grooved shaft.
Detailed Description
Specific embodiments of the present invention will be further described below with reference to the accompanying drawings. The invention relates to a side lever mechanism for a purely mechanical flight control system, which comprises a side lever handle 1, a support 2, a transverse output rocker arm 3, a bolt 6, a nut 5, a longitudinal output rocker arm 7, a support 9 and a groove-shaped rotating shaft 10. The side lever handle 1 and the longitudinal output rocker arm 7 are fixedly connected together through a bolt 6 and a nut 5 which pass through a groove-shaped rotating shaft 10 (the bolt and the nut pass through a round hole of a transverse axis a-a of the groove-shaped rotating shaft 10), when in pushing or pulling, the side lever handle 1 rotates around the axis a-a, the longitudinal transmission rod 8 is driven to move through the longitudinal rocker output arm 7, the movement is transmitted to an elevator control system, and at the moment, the transverse output rocker arm 3 does not move, namely, an auxiliary wing control system does not move; the transverse output rocker arm 3 and the groove-shaped rotating shaft 10 are integrated, the transverse output rocker arm 3 and the groove-shaped rotating shaft 10 are fixed on a machine body structure through the support 2 and the support 9, when the side lever is transversely operated, the side lever handle 1 rotates around the longitudinal axis b-b of the groove-shaped rotating shaft 10, the groove-shaped rotating shaft 10 is driven to rotate around the longitudinal axis b-b of the groove-shaped rotating shaft 10, the transverse transmission rod 4 is driven to move through the transverse output rocker arm 3, and the movement is transmitted to the aileron operation system. When the side lever handle 1 is operated left and right, the lower end of the longitudinal output rocker 7 is driven to swing left and right in addition to the rotation of the groove-shaped rotating shaft 10, and in order to avoid the coupling between the longitudinal direction and the transverse direction, the output point of the longitudinal transmission rod 8 is required to be positioned on the longitudinal axis b-b of the groove-shaped rotating shaft 10.
Claims (3)
1. A side lever mechanism for a purely mechanical flight control system comprises a side lever handle (1), a first support (2), a transverse output rocker arm (3), a bolt (6), a nut (5), a longitudinal output rocker arm (7), a second support (9) and a groove-type rotating shaft (10); the transverse output rocker arm (3) and the groove-shaped rotating shaft (10) are integrated, and are fixed on a machine body structure through a first support (2) and a second support (9); the side lever handle (1) and the longitudinal output rocker arm (7) are fixedly connected together through a bolt (6) and a nut (5) penetrating through the groove-shaped rotating shaft (10), when the side lever handle (1) rotates around the transverse axis a-a of the groove-shaped rotating shaft (10) during pushing or pulling of the rod, the longitudinal output rocker arm (7) drives the longitudinal transmission rod (8) to move, and the movement is transmitted to the elevator control system, so that the transverse output rocker arm (3) does not move, namely the aileron control system does not move; when the side lever is transversely operated, the side lever handle (1) rotates around the longitudinal axis b-b of the groove-shaped rotating shaft (10), the groove-shaped rotating shaft (10) is driven to rotate around the longitudinal axis b-b of the groove-shaped rotating shaft (10), and the transverse transmission rod (4) is driven to move through the transverse output rocker arm (3) to transmit the movement to the aileron operation system; when the side lever handle (1) is controlled leftwards and rightwards, the longitudinal output rocker arm (7) at the lower end is driven to swing leftwards and rightwards besides the rotation of the groove-shaped rotating shaft (10).
2. The sidebar mechanism of claim 1, wherein: the bolt (6) and the nut (5) pass through a round hole on the transverse axis a-a of the groove type rotating shaft (10).
3. The sidebar mechanism of claim 1, wherein: in order to avoid coupling in the longitudinal and transverse directions, the output point of the longitudinal transmission rod (8) is located on the longitudinal axis b-b of the groove-shaped rotating shaft (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811340177.0A CN109720550B (en) | 2018-11-12 | 2018-11-12 | Side lever mechanism for purely mechanical flight control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811340177.0A CN109720550B (en) | 2018-11-12 | 2018-11-12 | Side lever mechanism for purely mechanical flight control system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109720550A CN109720550A (en) | 2019-05-07 |
| CN109720550B true CN109720550B (en) | 2023-09-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811340177.0A Active CN109720550B (en) | 2018-11-12 | 2018-11-12 | Side lever mechanism for purely mechanical flight control system |
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| CN (1) | CN109720550B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112278146A (en) * | 2020-09-27 | 2021-01-29 | 郑州海王实业有限公司 | Gear type wing-in-ground effect ship aileron control system with smaller idle stroke |
| CN114937391A (en) * | 2022-05-18 | 2022-08-23 | 中电科芜湖钻石飞机制造有限公司 | Teaching aid for airplane transmission system |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2825975A1 (en) * | 2001-06-13 | 2002-12-20 | Aeronix | Joystick control for aircraft has swiveling mounting allowing fore-and-aft motion and side-to-side motion for control in pitch and roll axes |
| CN102765482A (en) * | 2011-05-03 | 2012-11-07 | 昊翔电能运动科技(昆山)有限公司 | Integrated control system for aircraft with V-shaped empennage |
| CN206476096U (en) * | 2017-01-17 | 2017-09-08 | 湖南山河科技股份有限公司 | A kind of light aerocraft Aileron control system |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB605642A (en) * | 1943-05-15 | 1948-07-28 | Roger Aime Robert | Improvements in control means for aircraft |
| US8469317B2 (en) * | 2010-10-22 | 2013-06-25 | Woodward Mpc, Inc. | Line replaceable, fly-by-wire control columns with push-pull interconnect rods |
| US9004411B2 (en) * | 2010-11-15 | 2015-04-14 | Michael Lam | Mechanical control mixer and method therefor |
-
2018
- 2018-11-12 CN CN201811340177.0A patent/CN109720550B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2825975A1 (en) * | 2001-06-13 | 2002-12-20 | Aeronix | Joystick control for aircraft has swiveling mounting allowing fore-and-aft motion and side-to-side motion for control in pitch and roll axes |
| CN102765482A (en) * | 2011-05-03 | 2012-11-07 | 昊翔电能运动科技(昆山)有限公司 | Integrated control system for aircraft with V-shaped empennage |
| CN206476096U (en) * | 2017-01-17 | 2017-09-08 | 湖南山河科技股份有限公司 | A kind of light aerocraft Aileron control system |
Non-Patent Citations (1)
| Title |
|---|
| 飞机飞行操纵系统卡阻问题研究;刘国庆等;《科学技术创新》(第第15期期);第9-10页 * |
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Address after: 519000 1st floor, headquarters base office building, 1519 Yinwan Road, Wanchai, Xiangzhou District, Zhuhai City, Guangdong Province Applicant after: R&D INSTITUTE OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. Address before: 519040 AVIC Tongfei industrial base, aviation industrial park, Jinwan District, Zhuhai City, Guangdong Province Applicant before: R&D INSTITUTE OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. |
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