CN116101476A - Airplane steering column force sensing balancing system - Google Patents
Airplane steering column force sensing balancing system Download PDFInfo
- Publication number
- CN116101476A CN116101476A CN202310012111.3A CN202310012111A CN116101476A CN 116101476 A CN116101476 A CN 116101476A CN 202310012111 A CN202310012111 A CN 202310012111A CN 116101476 A CN116101476 A CN 116101476A
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- trim
- steering column
- steering
- flight control
- force
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 53
- 238000009966 trimming Methods 0.000 claims abstract description 33
- 238000000034 method Methods 0.000 claims description 8
- 238000006073 displacement reaction Methods 0.000 claims description 5
- 238000012546 transfer Methods 0.000 claims description 2
- 230000006835 compression Effects 0.000 claims 1
- 238000007906 compression Methods 0.000 claims 1
- 230000005540 biological transmission Effects 0.000 abstract description 7
- 230000009347 mechanical transmission Effects 0.000 abstract description 5
- 238000012423 maintenance Methods 0.000 description 3
- 238000011022 operating instruction Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- BCCGKQFZUUQSEX-WBPXWQEISA-N (2r,3r)-2,3-dihydroxybutanedioic acid;3,4-dimethyl-2-phenylmorpholine Chemical compound OC(=O)[C@H](O)[C@@H](O)C(O)=O.OC(=O)[C@H](O)[C@@H](O)C(O)=O.O1CCN(C)C(C)C1C1=CC=CC=C1 BCCGKQFZUUQSEX-WBPXWQEISA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000004132 cross linking Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000007935 neutral 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
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/30—Balancing hinged surfaces, e.g. dynamically
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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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Control Devices (AREA)
- Toys (AREA)
Abstract
The application discloses aircraft steering column force sense trimming system, including left steering column, right steering column, left trim switch, right trim switch, flight control computer, flight control steering wheel, trim steering wheel, force sense mechanism and trim amplifier, flight control computer and flight control steering wheel cross-link, left trim switch and right trim switch and flight control steering wheel cross-link fly control steering wheel cross-link through trim amplifier and trim steering wheel, flight control steering wheel pass through steering wheel output rocking arm and left steering column and right steering column mechanical connection, trim steering wheel passes through switching rocking arm and force sense mechanism mechanical connection, force sense mechanism and left steering column and right steering column mechanical connection. The utility model provides a replace mechanical transmission through the force sense mechanism, save adjustment piece structure and complicated mechanical control mechanism, transmission spare part, the simple structure of this application, light in weight.
Description
Technical Field
The invention relates to the technical field of aviation flight control, in particular to an aircraft steering column force sensing balancing system.
Background
The aircraft balancing system is mainly used for compensating moment unbalance caused by changes of speed, gravity center, aerodynamic shape and the like when an aircraft flies. In the traditional balancing system, a driver manually operates the balancing mechanism through devices such as a balancing hand wheel and the like, and the balancing mechanism is driven manually or electrically to reversely deflect the balancing adjusting piece relative to the control surface, so that the hinge moment of the control surface can be effectively reduced. Trim tabs are deflectable winglets at the trailing edge of the control surface, driven by steering devices inside the cabin via a mechanical transmission system or actuators mounted inside the control surface, with limitations in use, the main drawbacks being: 1. the design and the installation of the trimming adjusting sheet are needed to be considered structurally, and a transmission mechanism for driving the trimming adjusting sheet is arranged in the control surface, so that the design is complex; 2. the trimming adjusting plate is far away from the operating device, the transmission line of the system is long, the middle installation links are more, the weight is heavy, and the maintenance is complex.
Disclosure of Invention
The invention aims at the problems and provides an aircraft steering column force sensing balancing system.
The technical scheme adopted by the invention is as follows:
the utility model provides an aircraft steering column force sense trimming system, including left steering column, right steering column, left trim switch, right trim switch, flight control computer, flight control steering wheel, trim steering wheel, force sense mechanism and trim amplifier, the flight control computer is through cable and flight control steering wheel cross-link, left trim switch is through cable and flight control steering wheel cross-link, the flight control steering wheel is through trim amplifier and trim steering wheel cross-link, left trim switch is installed on left steering column, right trim switch is installed on right steering column, the flight control steering wheel is through steering wheel output rocking arm and left steering column and right steering column mechanical connection, the trim steering wheel is through switching rocking arm and force sense mechanism mechanical connection, force sense mechanism and left steering column and right steering column mechanical connection;
when a driver manipulates the left steering rod to deflect the control surface, the force sensing mechanism and the steering engine output rocker arm of the flight control steering engine follow the left steering rod; when a driver manipulates the right steering rod to deflect the control surface, the force sensing mechanism and a steering engine output rocker arm of the flight control steering engine follow the right steering rod;
during balancing, the balancing steering engine works, the power sensing mechanism is driven by the switching rocker arm to work, the spring in the power sensing mechanism compresses or stretches, and the spring force generated by the power sensing mechanism is used as auxiliary control force, so that the pneumatic hinge moment of the balancing control surface is generated.
The utility model provides a replace mechanical transmission through the force sense mechanism, pilot's operating part is changed into the trimming switch by mechanical hand wheel, and pilot operating switch is the signal of telecommunication to trimming steering wheel between, saves adjustment sheet structure and complicated mechanical operating mechanism, transmission spare part, the simple structure of this application, light in weight.
During practical application, the steering engine and the force sensing mechanism can be integrated in the cabin of the aircraft, so that centralized maintenance is facilitated.
In one embodiment of the invention, the aircraft steering column force sensing trimming system is provided with a manual trimming mode, and in the manual trimming mode, a left trimming switch or a right trimming switch is operated to send a manual trimming command to a trimming amplifier, the trimming amplifier processes the received manual trimming command to form an operation command and transmits the operation command to a trimming steering engine, the trimming steering engine works according to the operation command and works by switching a rocker arm to drive a force sensing mechanism, a spring in the force sensing mechanism is compressed or stretched, and the spring force generated by the force sensing mechanism is used as auxiliary operation force to generate a pneumatic hinge moment for balancing a steering surface, so that the required driver operation force is reduced or eliminated.
In the manual balancing mode, the steering rod is not operated in the process, the control surface is kept at the balancing position, and the force sensing mechanism works without changing the original displacement corresponding relation between the steering rod and the control surface or changing the deflection range of the control surface.
In one embodiment of the invention, the aircraft steering column force sensing balancing system is provided with an automatic balancing mode, when the aircraft is in an automatic flight state in the automatic balancing mode, during the period that the flight control steering engine continuously generates a supporting balance moment through a steering engine output rocker arm, the flight control computer processes additional force on the received flight control steering engine, the additional force is sent to the balancing amplifier through a cable and the flight control steering engine, the balancing amplifier operates the received additional force, an operating command is sent to the balancing steering engine, the balancing steering engine works according to the operating command and works through a power sensing mechanism of a switching rocker arm, and the spring force generated by the power sensing mechanism is used as an auxiliary operating force to generate a pneumatic hinge moment for balancing a control surface, so that the additional force on the flight control steering engine is reduced or eliminated, and the aim of automatic balancing is achieved.
By cross-linking with the autopilot system, an automatic trim function is achieved. The transmission line is greatly shortened without designing a trimming adjusting piece, and the complexity and maintainability of the system are reduced.
When the aircraft automatically flies, the additional force on the flying control steering engine 6 needs to be eliminated or reduced, compared with a set threshold value,
in one embodiment of the invention, the trim steering engine converts the steering command output by the trim amplifier into a linear displacement.
In one embodiment of the present invention, the left trim switch is operated in a direction consistent with the left steering column, and the right trim switch is operated in a direction consistent with the right steering column.
That is, to eliminate the pull rod force, the trim switch is pressed backward, to eliminate the push rod force, the trim switch is pressed forward, to eliminate the left rod force, the trim switch is pressed left, to eliminate the right rod force, and the trim switch is pressed right. After the hands are loosened, the balancing switch can automatically return to the middle, and the balancing steering engine is powered off and kept at the current balancing position.
The beneficial effects of the invention are as follows: the utility model provides a replace mechanical transmission through the force sense mechanism, pilot's operating part is changed into the trimming switch by mechanical hand wheel, and pilot operating switch is the signal of telecommunication to trimming steering wheel between, saves adjustment sheet structure and complicated mechanical operating mechanism, transmission spare part, the simple structure of this application, light in weight.
Drawings
FIG. 1 is a system schematic block diagram of an aircraft steering column force sensing trim system.
The reference numerals in the drawings are as follows:
1. a left trim switch; 2. a left steering column; 3. a right trim switch; 4. a right steering column; 5. a flight control computer; 6. a flight control steering engine; 7. balancing a steering engine; 8. a force sensing mechanism; 9. a trim amplifier; 10. switching a rocker arm; 11. a cable; 14. the steering engine outputs a rocker arm; 15. control surface.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It will be apparent that the embodiments described are some, but not all, of the embodiments of the present application. The components of the embodiments of the present application, which are generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.
In the description of the present application, it should be noted that, the azimuth or positional relationship indicated by the terms "inner", "outer", etc. are based on the azimuth or positional relationship shown in the drawings, or the azimuth or positional relationship that is commonly put when the product of the application is used, are merely for convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element to be referred to must have a specific azimuth, be configured and operated in a specific azimuth, and therefore should not be construed as limiting the present application. Furthermore, the terms "first," "second," and the like, are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
In the description of the present application, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art in a specific context.
The present invention will be described in detail with reference to the accompanying drawings.
As shown in fig. 1, the aircraft steering rod force sensing balancing system comprises a left steering rod 2, a right steering rod 4, a left balancing switch 1, a right balancing switch 3, a flight control computer 5, a flight control steering wheel 6, a balancing steering wheel 7, a force sensing mechanism 8 and a balancing amplifier 9, wherein the flight control computer 5 is crosslinked with the flight control steering wheel 6 through a cable 11, the left balancing switch 1 is crosslinked with the flight control steering wheel 6 through the cable 11, the right balancing switch 3 is crosslinked with the flight control steering wheel 6 through the cable 11, the flight control steering wheel 6 is crosslinked with the balancing steering wheel 7 through the balancing amplifier 9, the left balancing switch 1 is arranged on the left steering rod 2, the right balancing switch 3 is arranged on the right steering rod 4, the flight control steering wheel 6 is mechanically connected with the left steering rod 2 and the right steering rod 4 through a steering wheel output rocker arm 14, the balancing steering wheel 7 is mechanically connected with the force sensing mechanism 8 through a transfer rocker arm 10, and the force sensing mechanism 8 is mechanically connected with the left steering rod 2 and the right steering rod 4;
when the left balancing switch 1 and the right balancing switch 3 are at neutral positions, the balancing steering gear 7 does not act, and when a driver manipulates the left steering rod 2 to deflect the control surface 15, the force sensing mechanism 8 and the steering gear output rocker arm 14 of the flight control steering gear 6 follow the left steering rod 2; when a driver manipulates the right steering rod 4 to deflect the control surface 15, the force sensing mechanism 8 and the steering engine output rocker arm 14 of the flight control steering engine 6 follow the right steering rod 4;
when the balancing steering engine 7 works, the power sensing mechanism 8 is driven to work through the switching rocker arm 10, the spring in the power sensing mechanism 8 compresses or stretches, and the spring force generated by the power sensing mechanism 8 is used as auxiliary control force, so that the pneumatic hinge moment of the balancing control surface 15 is generated.
The utility model provides a replace mechanical transmission through force sense mechanism 8, pilot's operating part is changed the balancing switch by mechanical hand wheel, and pilot operating switch is the electrical signal to balancing steering wheel 7 between, saves adjustment piece structure and complicated mechanical operating mechanism, transmission spare part, and this application simple structure, light in weight.
During practical application, the steering engine and the force sensing mechanism 8 can be integrated in the cabin of the airplane, so that centralized maintenance is facilitated.
In this embodiment, the trim steering engine 7 converts the manipulation instruction output from the trim amplifier 9 into a linear displacement.
In this embodiment, the aircraft steering column force sensing trim system has a manual trim mode and an automatic trim mode.
In the manual balancing mode, a manual balancing instruction is sent to the balancing amplifier 9 by operating the left balancing switch 1 or the right balancing switch 3, the balancing amplifier 9 processes the received manual balancing instruction to form an operating instruction and transmits the operating instruction to the balancing steering engine 7, the balancing steering engine 7 works according to the operating instruction and works through the switching rocker arm 10 with the power sensing mechanism 8, a spring in the power sensing mechanism 8 compresses or stretches, and the spring force generated by the power sensing mechanism 8 is used as auxiliary operating force to generate pneumatic hinge moment for balancing the control surface 15, so that the required driver operating force is reduced or eliminated. In the manual balancing mode, the steering lever is not operated in the process, the control surface 15 is kept at the balancing position, and the force sensing mechanism 8 works without changing the original displacement corresponding relation between the steering lever and the control surface 15 or changing the deflection range of the control surface 15.
In the automatic balancing mode, the aircraft is in an automatic flight state, during the period that the flight control steering engine 6 continuously generates a supporting balance moment through the steering engine output rocker arm 14, the flight control computer 5 processes the received additional force on the flight control steering engine 6, the additional force is transmitted to the balancing amplifier 9 through the cable 11 and the flight control steering engine 6, the balancing amplifier 9 operates the received additional force, an operating command is transmitted to the balancing steering engine 7, the balancing steering engine 7 works according to the operating command and works through the switching rocker arm 10 with the power sensing mechanism 8, the spring in the power sensing mechanism 8 compresses or stretches, and the spring force generated by the power sensing mechanism 8 is used as an auxiliary operating force to generate a pneumatic hinge moment of the balance control surface 15, so that the additional force on the flight control steering engine 6 is reduced or eliminated, and the aim of automatic balancing is achieved.
In the present embodiment, the left trim switch 1 is operated in the same manner as the left steering column 2, and the right trim switch 3 is operated in the same manner as the right steering column 4. That is, to eliminate the pull rod force, the corresponding trim switch is pressed backward, to eliminate the push rod force, the corresponding trim switch is pressed forward, to eliminate the left rod force, the corresponding trim switch is pressed left, to eliminate the right rod force, the corresponding trim switch is pressed right. The balancing switch corresponding to the loose hand can automatically return to the middle, and the balancing steering engine 7 is powered off and kept at the current balancing position.
The foregoing description is only of the preferred embodiments of the present invention, and is not intended to limit the scope of the invention, but rather is intended to cover all equivalent structures as modifications within the scope of the invention, either directly or indirectly, as may be contemplated by the present invention.
Claims (5)
1. The aircraft steering column force sensing trimming system is characterized by comprising a left steering column, a right steering column, a left trimming switch, a right trimming switch, a flight control computer, a flight control steering column, a trimming steering column, a force sensing mechanism and a trimming amplifier, wherein the flight control computer is crosslinked with the flight control steering column through a cable, the left trimming switch is crosslinked with the flight control steering column through the cable, the right trimming switch is crosslinked with the flight control steering column through the cable, the flight control steering column is crosslinked with the trimming steering column through the trimming amplifier, the left trimming switch is arranged on the left steering column, the right trimming switch is arranged on the right steering column, the flight control steering column is mechanically connected with the left steering column and the right steering column through a steering column output rocker, the trimming steering column is mechanically connected with the force sensing mechanism through a transfer rocker, and the force sensing mechanism is mechanically connected with the left steering column and the right steering column;
when a driver manipulates the left steering rod to deflect the control surface, the force sensing mechanism and the steering engine output rocker arm of the flight control steering engine follow the left steering rod; when a driver manipulates the right steering rod to deflect the control surface, the force sensing mechanism and a steering engine output rocker arm of the flight control steering engine follow the right steering rod;
during balancing, the balancing steering engine works, the power sensing mechanism is driven by the switching rocker arm to work, the spring in the power sensing mechanism compresses or stretches, and the spring force generated by the power sensing mechanism is used as auxiliary control force, so that the pneumatic hinge moment of the balancing control surface is generated.
2. The aircraft steering column force sensing trim system of claim 1, wherein the aircraft steering column force sensing trim system has a manual trim mode, and wherein in the manual trim mode, a manual trim command is issued to the trim amplifier by operating the left trim switch or the right trim switch, the trim amplifier processes the received manual trim command to form an operating command, the operating command is transmitted to the trim steering engine, the trim steering engine operates according to the operating command and operates by switching the rocker arm to operate the force sensing mechanism, a spring in the force sensing mechanism compresses or stretches, and a spring force generated by the force sensing mechanism acts as an auxiliary operating force to generate a pneumatic hinge moment for balancing the steering surface, thereby reducing or eliminating a required driver operating force.
3. The aircraft steering column force sensing trim system of claim 1, wherein the aircraft steering column force sensing trim system has an automatic trim mode in which the aircraft is in an automatic flight state, during the period in which the flight control steering engine continuously generates a supporting balance moment through the steering engine output rocker arm, the flight control computer processes additional force on the received flight control steering engine, the additional force is transmitted to the trim amplifier via the cable and the flight control steering engine, the trim amplifier operates the received additional force, the operation command is transmitted to the trim steering engine, the trim steering engine operates according to the operation command and operates by switching the rocker arm to carry out compression or stretching on the power sensing mechanism, and the spring force generated by the force sensing mechanism is used as an auxiliary operation force to generate a pneumatic hinge moment of a balance steering surface, so that the additional force on the flight control steering engine is reduced or eliminated, and the purpose of automatic trim is achieved.
4. An aircraft steering column force sensing trim system according to claim 2 or claim 3, wherein the trim steering engine converts steering commands output by the trim amplifier into linear displacements.
5. The aircraft steering column force sensing trim system of claim 1, wherein the left trim switch is operated in a manner consistent with the direction of operation of the left steering column and the right trim switch is operated in a manner consistent with the direction of operation of the right steering column.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310012111.3A CN116101476A (en) | 2023-01-05 | 2023-01-05 | Airplane steering column force sensing balancing system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310012111.3A CN116101476A (en) | 2023-01-05 | 2023-01-05 | Airplane steering column force sensing balancing system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116101476A true CN116101476A (en) | 2023-05-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310012111.3A Pending CN116101476A (en) | 2023-01-05 | 2023-01-05 | Airplane steering column force sensing balancing system |
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| CN (1) | CN116101476A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117799824A (en) * | 2024-02-29 | 2024-04-02 | 中国商用飞机有限责任公司上海飞机设计研究院 | Force sensing balancing mechanism and aircraft |
-
2023
- 2023-01-05 CN CN202310012111.3A patent/CN116101476A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117799824A (en) * | 2024-02-29 | 2024-04-02 | 中国商用飞机有限责任公司上海飞机设计研究院 | Force sensing balancing mechanism and aircraft |
| CN117799824B (en) * | 2024-02-29 | 2024-06-11 | 中国商用飞机有限责任公司上海飞机设计研究院 | Force sensing balancing mechanism and aircraft |
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