CN111114757B - Fly-by-wire aircraft operating force generating device - Google Patents
Fly-by-wire aircraft operating force generating device Download PDFInfo
- Publication number
- CN111114757B CN111114757B CN201911265448.5A CN201911265448A CN111114757B CN 111114757 B CN111114757 B CN 111114757B CN 201911265448 A CN201911265448 A CN 201911265448A CN 111114757 B CN111114757 B CN 111114757B
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- CN
- China
- Prior art keywords
- torsional deformation
- elastic piece
- force
- fly
- deformation elastic
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- B64C13/02—Initiating means
- B64C13/04—Initiating means actuated personally
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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
- B64C13/02—Initiating means
- B64C13/04—Initiating means actuated personally
- B64C13/042—Initiating means actuated personally operated by hand
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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
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
- B64C13/507—Transmitting means with power amplification using electrical energy with artificial feel
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention belongs to the design technology of flight control systems, and particularly relates to an fly-by-wire aircraft control force generating device. The steering force in steady state flight is properly eliminated or lightened, so that a reasonable steering force generation and elimination mode is an important link of the fly-by-wire aircraft. The fly-by-wire aircraft operating force generating device comprises an electric actuator and force sensing devices arranged at two synchronous output ends of the electric actuator, wherein a torsional deformation elastic piece is arranged; and a rocker arm is coaxially connected to the outer side of the force sensing device, the rocker arm is hinged to one end of a connecting rod at the free end, and the other end of the connecting rod is hinged to the main steering rod and the auxiliary steering rod. The integrated level is high, the space is reduced, the weight is reduced, and the spare parts and the maintenance cost are reduced. The main and auxiliary driving has high bilateral synchronism and good consistency. The pilot is provided with visual control feeling, the flight quality is improved, and the flight safety is ensured.
Description
Technical Field
The invention belongs to the design technology of flight control systems, and particularly relates to an fly-by-wire aircraft control force generating device.
Background
The fly-by-wire aircraft control surface load cannot be reversely transmitted to the aircraft control system, so that the pilot can intuitively feel the state of the aircraft in order to restore the actual control feeling of the aircraft, the situation that the safety of the aircraft is influenced by incorrect control is avoided, and meanwhile, the physical strength of the pilot is considered, so that the control force in steady-state flight is properly eliminated or lightened. Therefore, a reasonable operating force generation and elimination mode is an important link of the fly-by-wire aircraft.
Disclosure of Invention
The purpose of the invention is that: an fly-by-wire aircraft steering force generating apparatus is presented. And simultaneously provides artificial force sense for the two sides of the main and auxiliary drivers and provides maneuvering force for the pilot. And according to pilot instructions in the operation process, the manual force sense is changed, pilot operating force is lightened or eliminated, and pilot physical burden is lightened.
The technical scheme of the invention is as follows: an fly-by-wire aircraft operating force generating device is used for providing synchronous equivalent force feedback for a main steering column and a secondary steering column, and comprises an electric actuator and a force sensing device arranged at two synchronous output ends of the electric actuator, wherein the force sensing device is provided with a torsional deformation elastic piece; and a rocker arm is coaxially connected to the outer side of the force sensing device, the rocker arm is hinged to one end of a connecting rod at the free end, and the other end of the connecting rod is hinged to the main steering rod and the auxiliary steering rod.
Further, the torsionally deformed elastic member has rotation shafts at both ends thereof rotatably installed in the force sensing device.
Further, the torsional deformation elastic piece adopts a torsion spring.
Further, the electric actuator comprises a motor and two sets of worm and worm wheel assemblies, wherein the worm is meshed with an output shaft of the motor, and a rotating shaft of the worm wheel is connected with a rotating shaft of the torsional deformation elastic piece and outputs the torsional deformation elastic piece in the same transmission ratio.
Further, the worm and worm wheel component has a self-locking function.
Further, torque is also transferred between the electric actuator and the force sensing device through the torsion tube.
Further, the force sensing device comprises a main frame side force sensing device and a secondary driving side force sensing device; the torsional deformation elastic piece comprises a main frame side torsional deformation elastic piece and a secondary driving side torsional deformation elastic piece; the rocker arm comprises a main frame side rocker arm and an auxiliary driving side rocker arm; the connecting rod comprises a main frame side connecting rod and a secondary driving side connecting rod.
Further, when the main steering rod or the auxiliary steering rod is operated, the rocker arm is driven to rotate through the connecting rod, so that the torsional deformation elastic piece generates torsional deformation to provide an operating force.
Further, when a force cancellation command is issued, torsional deformation of the torsional deformation elastic member is cancelled by controlling the electric actuator.
Further, when a force eliminating instruction is sent, the electric actuator is controlled to drive the worm and worm wheel assembly to synchronously move, so that torsional deformation of the torsional deformation elastic piece is eliminated.
The invention has the advantages that: an electric actuator has anchoring and balancing functions, high integration level, space reduction, weight reduction and spare part and maintenance cost reduction. The main and auxiliary driving has high bilateral synchronism and good consistency. The pilot is provided with visual control feeling, the flight quality is improved, and the flight safety is ensured.
Drawings
FIG. 1 is a schematic perspective view of an fly-by-wire aircraft steering force generating apparatus of the present invention;
fig. 2 is a schematic transmission diagram of an fly-by-wire aircraft steering force generating apparatus of the present invention.
Detailed Description
An fly-by-wire aircraft steering force generation, see fig. 1, is used for providing synchronous equivalent force feedback to a main steering rod 9a and a secondary steering rod 9b, and the device comprises an electric actuator 1 and a force sensing device 4 arranged at two synchronous output ends of the electric actuator 1, wherein a torsional deformation elastic piece 5 is arranged; a rocker arm 7 is coaxially connected to the outside of the force sensing device 4, and the rocker arm 7 is hinged to one end of a link 8 at a free end, and the other end of the link 8 is hinged to the main and auxiliary levers 9a, 9 b.
The torsionally deformable elastic member 5 has rotation shafts at both ends and is rotatably installed in the force sensing device 4. The torsional deformation elastic piece 5 adopts a torsion spring.
The electric actuator 1 comprises a motor 2 and two sets of worm and worm wheel assemblies 3a and 3b, wherein the worm is meshed with an output shaft of the motor 2, and a rotating shaft of the worm wheel is connected with a rotating shaft of the torsional deformation elastic piece 5 and outputs the torsional deformation elastic piece with the same transmission ratio. The worm and worm wheel assemblies 3a, 3b have a self-locking function.
Torque is also transmitted between the electric actuator 1 and the force sensing device 4 via the torsion tube 6.
The force sensing device 4 comprises a main frame side force sensing device 4a and a secondary driving side force sensing device 4b; the torsional deformation elastic member 5 includes a main frame side torsional deformation elastic member 5a and a secondary driving side torsional deformation elastic member 5b; the rocker arm 7 includes a main frame side rocker arm 7a and a sub-drive side rocker arm 7b; the link 8 includes a main frame side link 8a and a sub-drive side link 8b.
When the main steering rod 9a or the auxiliary steering rod 9b is operated, the rocker arm 7 is rotated by the connecting rod 8, so that the torsional deformation elastic member 5 is subjected to torsional deformation to provide an operating force. When a force cancellation command is issued, torsional deformation of the torsional deformation elastic member 5 is cancelled by controlling the electric actuator 1. When a force eliminating command is sent, the electric actuator 1 is controlled to drive the worm and worm wheel assemblies 3a and 3b to synchronously move, so that the torsional deformation of the torsional deformation elastic piece 5 is eliminated.
When the steering column is operated, the load mechanism deforms to generate an operating force, and when the pilot sends out a trimming instruction, the motor in the actuator moves and drives the worm and worm wheel assembly to move, so that the double-side anchoring supporting points are changed, the working stroke of the load mechanism is reduced or eliminated, namely, the artificial force sense is changed, and the pilot operating force is reduced or eliminated.
Claims (4)
1. An fly-by-wire aircraft steering force generating device for providing synchronous equivalent force feedback to primary and secondary steering levers (9 a, 9 b), characterized by: the device comprises an electric actuator (1) and a force sensing device (4) arranged at two synchronous output ends of the electric actuator (1), wherein a torsional deformation elastic piece (5) is arranged; the force sensing device (4) comprises a main driving side force sensing device (4 a) and a secondary driving side force sensing device (4 b); the torsional deformation elastic piece (5) comprises a main driving side torsional deformation elastic piece (5 a) and a secondary driving side torsional deformation elastic piece (5 b); the rocker arm (7) comprises a main driving side rocker arm (7 a) and an auxiliary driving side rocker arm (7 b); the connecting rod (8) comprises a main driving side connecting rod (8 a) and a secondary driving side connecting rod (8 b); a rocker arm (7) is coaxially connected to the outer side of the force sensing device (4), the rocker arm (7) is hinged with one end of a connecting rod (8) at the free end, and the other end of the connecting rod (8) is hinged with main and auxiliary driving rods (9 a, 9 b); the torsion deformation elastic piece (5) is provided with rotating shafts at two ends and is rotatably arranged in the force sensing device (4); the torsional deformation elastic piece (5) adopts a torsion spring; the electric actuator (1) comprises a motor (2) and two groups of worm and worm wheel assemblies (3 a, 3 b), wherein a worm is meshed with an output shaft of the motor (2), and a rotating shaft of the worm wheel is connected with a rotating shaft of the torsional deformation elastic piece (5) and outputs the torsional deformation elastic piece in the same transmission ratio; when a force elimination instruction is sent, torsional deformation of the torsional deformation elastic piece (5) is eliminated by controlling the electric actuator (1), and the worm and worm wheel assemblies (3 a and 3 b) are driven to synchronously move by controlling the electric actuator (1), so that torsional deformation of the torsional deformation elastic piece (5) is eliminated.
2. Fly-by-wire aircraft steering force generating device according to claim 1, wherein: the worm and worm wheel assemblies (3 a, 3 b) have a self-locking function.
3. Fly-by-wire aircraft steering force generating device according to claim 2, wherein: torque is also transmitted between the electric actuator (1) and the force sensing device (4) via the torsion tube (6).
4. A fly-by-wire aircraft steering force generating device according to any one of claims 1-3, wherein: when the main steering rod (9 a) or the auxiliary steering rod (9 b) is operated, the rocker arm (7) is driven to rotate through the connecting rod (8), so that the torsional deformation elastic piece (5) generates torsional deformation to provide an operating force.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911265448.5A CN111114757B (en) | 2019-12-11 | 2019-12-11 | Fly-by-wire aircraft operating force generating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911265448.5A CN111114757B (en) | 2019-12-11 | 2019-12-11 | Fly-by-wire aircraft operating force generating device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111114757A CN111114757A (en) | 2020-05-08 |
| CN111114757B true CN111114757B (en) | 2023-07-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911265448.5A Active CN111114757B (en) | 2019-12-11 | 2019-12-11 | Fly-by-wire aircraft operating force generating device |
Country Status (1)
| Country | Link |
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| CN (1) | CN111114757B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112727902A (en) * | 2020-12-25 | 2021-04-30 | 兰州飞行控制有限责任公司 | Balancing mechanism and method for flexible connecting assembly transmission |
| CN112918660A (en) * | 2021-03-26 | 2021-06-08 | 陕西飞机工业有限责任公司 | Device is imitated to elevator |
| CN113086171B (en) * | 2021-04-11 | 2022-07-19 | 燕山大学 | Coaxial double-cone rotor parallel manual device of helicopter |
| CN115447761A (en) * | 2022-10-12 | 2022-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Variable transmission ratio aircraft control system |
| CN116882208B (en) * | 2023-09-06 | 2023-11-07 | 天津华翼蓝天科技股份有限公司 | Disengageable function simulation system and method for load control system |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2558136B1 (en) * | 1984-01-12 | 1986-04-25 | Aerospatiale | CONTROL DEVICE HAVING TWO JOINED HANDLES AND ACTUATED RESPECTIVELY BY A LEFT HAND AND A RIGHT HAND |
| US7108232B2 (en) * | 2004-02-05 | 2006-09-19 | Hoh Roger H | Helicopter force-feel and stability augmentation system with parallel servo-actuator |
| WO2005124500A1 (en) * | 2004-06-21 | 2005-12-29 | Hitachi, Ltd. | Operation input device |
| FR3033767B1 (en) * | 2015-03-16 | 2017-03-10 | Sagem Defense Securite | DEVICE FOR CONTROLLING FLIGHT OF AN AIRCRAFT |
| US10106245B2 (en) * | 2015-10-19 | 2018-10-23 | Honeywell International Inc. | Automatic flight control actuator systems |
| EP3403926B1 (en) * | 2017-05-18 | 2019-07-03 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A method of controlling an artificial force feel generating device for generation of an artificial feeling of force on an inceptor of a vehicle control system |
| CN209388518U (en) * | 2018-04-24 | 2019-09-13 | 中航大（天津）模拟机工程技术有限公司 | Simple load simulation device based on airplane steering column control |
| CN109466752A (en) * | 2018-12-05 | 2019-03-15 | 兰州飞行控制有限责任公司 | A kind of device of stable aircraft handling lever operation |
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2019
- 2019-12-11 CN CN201911265448.5A patent/CN111114757B/en active Active
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| Publication number | Publication date |
|---|---|
| CN111114757A (en) | 2020-05-08 |
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