CN203111496U - High lifting force control system combining synchronous technology and asynchronous technology - Google Patents
High lifting force control system combining synchronous technology and asynchronous technology Download PDFInfo
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- CN203111496U CN203111496U CN 201320049625 CN201320049625U CN203111496U CN 203111496 U CN203111496 U CN 203111496U CN 201320049625 CN201320049625 CN 201320049625 CN 201320049625 U CN201320049625 U CN 201320049625U CN 203111496 U CN203111496 U CN 203111496U
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Abstract
The utility model belongs to the technical field of flight control systems and relates to a high lifting force control system combining the synchronous technology and the asynchronous technology. The control system comprises a control handle (1) with electrical four redundancies, a first controller (2), a second controller (3), a first slits motor (4), a second slits motor (5), a slits differential gear device (6), a slit mechanical transmission linear system (7), leading edge slats (8), a left slat position sensor (9), a right slat position sensor (10), a first flap motor (11), a second flap motor (12), a flap differential gear device (13), a flap mechanical transmission linear system (14), trailing edge flaps (15), a left flap position sensor (16) and a right flap position sensor (17). Since the high lifting force control system adopts the controllers with self-monitoring functions, the monitoring voting function among the controllers is removed.
Description
Technical field
The utility model belongs to the flight control system technical field, relates to the high lift control system that a kind of combination reaches asynchronous technique synchronously.
Background technology
All kinds of aircrafts are many to comprise wing flap, slat at all kinds of high lift devices of its wing installation, move to change the wing geometric configuration increasing lift to control it when the aircraft low-speed operations, this class changes the system that wing configuration improves lift and is called as the high lift control system.
As a rule, when taking off, slat and/or wing flap reach a midway location and increase lift, so aircraft can take off than under the low velocity.Therefore otherwise aircraft must reach a higher takeoff speed, will need the airstrip more grown, greatly increases the airport construction cost.Aloft, the slight drag that need seek a kind of aerodynamic during high-performance cruise is wing, and wing flap and slat pack up to reduce resistance under this kind flight mode, thereby reduce fuel oil consumption.When airfield approach landed, aircraft needed very fast its speed of reduction and improves the low speed lift of getting off the plane, and therefore must take lift-rising to increase the resistance measure in this stage, also namely usually wing flap and slat is reached bigger position.With take off similarly, if there is not the high-lift device of extensile wing flap and slat, aircraft will land with higher speed, with regard to the longer runway of needs aircraft kinetic energy is transformed into to reach stopped status in the friction of air, tire and brake.
Widespread use along with fly-by-wire flight control system; be that the transport plane of new generation of representative begins to adopt based on microprocessor with B777 be the redundance fax control system of core, microprocessor is that slat and wing flap drive and self-checking function is surveyed and safeguarded in offe telex flight control, protection, System self-test of actuating system.
Concerning present redundance fax control system, all adopted simultaneous techniques basically.Simultaneous techniques can almost be sampled simultaneously to the remaining sensor, handled, balanced, voting, and all computing machines are all selected colleague's technology.Therefore the advantage of simultaneous techniques is: tracking error fault, reduction fault detection threshold value little, that be convenient to detecting sensor and computing machine is (synchronous fully as if computing machine, and adopt identical input, then threshold value is answered trail bit level), reduce false-alarm and mistake is cut, reduced time delay, prevents that passage from dispersing, making the development process of software simple, particularly the software test difficulty reduces.But synchronizing function must carefully design, and avoids introducing Single Point of Faliure (synchronizing function inefficacy) and makes all computer failures.Synchronization Design is not fault-tolerant in itself.
The utility model content
Technical problem to be solved in the utility model is: eliminate the high lift control system reliability bottleneck that synchronizing function causes, improve system's antijamming capability, thereby improve the fax high lift control system reliability of operation based on microprocessor.
The technical solution of the utility model is: a kind of combination reaches the high lift control system of asynchronous technique synchronously, comprise the bar handle 1 with electric 4 remainings, first controller 2, second controller 3, the first slat motor 4, the second slat motor 5, slat compensating gear 6, slat mechanical drive linear system 7, leading edge slat 8, left side slat position transduser 9, right slat position transduser 10, the first wing flap motor 11, the second wing flap motor 12, wing flap compensating gear 13, wing flap mechanical drive linear system 14, trailing edge flap 15, port flap position transduser 16 and right flap position transducer 17, wherein, described four sensors all are two remaining sensors that electric remaining A and electric remaining B form, bar handle 1 each electric remaining connects the control channel CON of first controller 2 respectively, the monitor channel MON of first controller 2, the monitor channel MON of the control channel CON of second controller 3 and second controller 3, the first slat motor 4 connects the control channel CON of first controller 2, the second slat motor 5 connects the control channel of second controller 3, the first slat motor 4, the output shaft of the second slat motor 5 connects slat compensating gear 6, the output shaft of slat compensating gear 6 connects slat mechanical drive linear system 7, slat transmission linear system 7 connects leading edge slat 8, left side slat position transduser 9 is installed on slat mechanical drive linear system 7 left distal end, the A channel of left side slat position transduser 9 is connected to the control channel CON of first controller 2, the B passage of left side slat position transduser 9 is connected to the monitor channel MON of second controller 3, right slat position transduser 10 is installed on slat mechanical drive linear system 7 right end, the A channel of right slat position transduser 10 is connected to the control channel CON of second controller 3, the B passage of right slat position transduser 10 is connected to the monitor channel MON of first controller 2, the first wing flap motor 11 connects the control channel CON of first controller 2, the second wing flap motor 12 connects the control channel of second controller 3, the first wing flap motor 11, the output shaft of slat motor 12 connects wing flap compensating gear 13, the output shaft of wing flap compensating gear 13 connects wing flap mechanical drive linear system 14, wing flap transmission linear system connects 14 trailing edge flaps 15, port flap position transduser 16 is installed on wing flap mechanical drive linear system 15 left distal end, the A channel of port flap position transduser 16 is connected to the control channel CON of first controller 2, the B passage of port flap position transduser 16 is connected to the monitor channel MON of second controller 3, right flap position transducer 17 is installed on wing flap mechanical drive linear system 15 right end, the A channel of right flap position transducer 17 is connected to the control channel CON of second controller 3, and the B passage of right flap position transducer 17 is connected to the monitor channel MON of first controller 2.
The beneficial effects of the utility model are: the utility model has adopted the controller that has from monitoring function, has removed monitoring voting function between controller; The utility model has adopted compensating gear that the output of different motors is carried out comprehensively simultaneously, solved the power dispute problem that the difference of whole different electric machine control circuits is brought, and then condition is provided for the loose association of controller, providing to asynchronous working between controller may.The application of asynchronous technique, reduced the connection of cable between controller, reduced the difficulty of system margin management simultaneously, between controller loose operational relation increase anti-electromagnetic interference, thunderbolt ability, insensitive to electromagnetic interference in short-term, introduce the Single Point of Faliure probability little, do not require accurate unanimity, fault freedom is good.The utility model can be applied to airplane in transportation category to the control of its wing flap and/or slat.
Description of drawings
Fig. 1 reaches the high lift control system system architecture scheme drawing of asynchronous technique synchronously for a kind of combination of the utility model;
Fig. 2 reaches the high lift control system slat control fundamental diagram of asynchronous technique synchronously for a kind of combination of the utility model;
A, B represent electric remaining A and an electric remaining B in two remaining sensors respectively, 2C represents the control channel CON of first controller 2, and 2M represents the monitor channel MON of first controller 2, and 3C represents the control channel CON of second controller 3,3M represents the monitor channel MON of second controller 3
Fig. 3 reaches the high lift control system wing flap control fundamental diagram of asynchronous technique synchronously for a kind of combination of the utility model.
The specific embodiment
Below in conjunction with accompanying drawing the specific embodiment of the present utility model is described further.
Participate in Fig. 1, a kind of combination reaches the high lift control system of asynchronous technique synchronously, comprise the bar handle 1 with electric 4 remainings, first controller 2, second controller 3, the first slat motor 4, the second slat motor 5, slat compensating gear 6, slat mechanical drive linear system 7, leading edge slat 8, left side slat position transduser 9, right slat position transduser 10, the first wing flap motor 11, the second wing flap motor 12, wing flap compensating gear 13, wing flap mechanical drive linear system 14, trailing edge flap 15, port flap position transduser 16 and right flap position transducer 17, A wherein, B represents electric remaining A and an electric remaining B in two remaining sensors respectively, 2C represents the control channel CON of first controller 2,2M represents the monitor channel MON of first controller 2,3C represents the control channel CON of second controller 3,3M represents the monitor channel MON of second controller 3, sees for details shown in Figure 1.The bar handle 1 every electric remaining that wherein has electric 4 remainings connects the control channel CON of first controller 2 respectively, the monitor channel MON of first controller 2, the monitor channel MON of the control channel CON of second controller 3 and second controller 3, the first slat motor 4 connects the control channel CON of first controller 2, the second slat motor 5 connects the control channel of second controller 3, the first slat motor 4, the output shaft of the second slat motor 5 connects slat compensating gear 6, the output shaft of slat compensating gear 6 connects slat mechanical drive linear system 7, slat transmission linear system 7 connects leading edge slat 8, left side slat position transduser 9 is installed on slat mechanical drive linear system 7 left distal end, the A channel of left side slat position transduser 9 is connected to the control channel CON of first controller 2, the B passage of left side slat position transduser 9 is connected to the monitor channel MON of second controller 3, right slat position transduser 10 is installed on slat mechanical drive linear system 7 right end, the A channel of right slat position transduser 10 is connected to the control channel CON of second controller 3, the B passage of right slat position transduser 10 is connected to the monitor channel MON of first controller 2, the first wing flap motor 11 connects the control channel CON of first controller 2, the second wing flap motor 12 connects the control channel of second controller 3, the first wing flap motor 11, the output shaft of slat motor 12 connects wing flap compensating gear 13, the output shaft of wing flap compensating gear 13 connects wing flap mechanical drive linear system 14, wing flap transmission linear system connects 14 trailing edge flaps 15, port flap position transduser 16 is installed on wing flap mechanical drive linear system 15 left distal end, the A channel of port flap position transduser 16 is connected to the control channel CON of first controller 2, the B passage of port flap position transduser 16 is connected to the monitor channel MON of second controller 3, right flap position transducer 17 is installed on wing flap mechanical drive linear system 15 right end, the A channel of right flap position transducer 17 is connected to the control channel CON of second controller 3, and the B passage of right flap position transducer 17 is connected to the monitor channel MON of first controller 2.
The slat control principle is seen shown in Figure 2, first controller, 2 control channel CON and monitor channel MON receive respectively from two remainings in the electric instruction of 4 remainings in the bar handle 1 with electric 4 remainings and instruct, namely instruct 1 and the instruction 2, and earlier it is finished on-line monitoring ILM, in first controller, 2 control channel CON, instruction 1 after the selection or instruct 2 with carry out synchronized sampling from the A channel information of left slat position transduser 9, the A channel information of left side slat position transduser 9 is called slat position 1, in first controller, 2 monitor channel MON, instruction 1 after the selection or instruct 2 with carry out synchronized sampling from the B channel information of right slat position transduser 10, the B channel information of right slat position transduser 10 is called slat position 2, slat position 1 after the sampling and slat position 2 respectively in the control channel CON of first controller 2 and monitor channel MON comprehensive back as rudder face feedback and the command signal of selecting calculating rudder face position command in first controller, 2 control channel CON and monitor channel MON respectively, the comprehensive back control first slat motor 4 is carried out in instruction after the calculating in first controller, 2 control channels, the control principle of second controller 3 is identical with first controller 2, the instruction output control second slat motor 5 after it resolves, thus the output of the first slat motor 4 and the second slat motor 5 drives the slat motion by slat compensating gear 6 comprehensive rear drive slat mechanical drive linear systems 7.
The wing flap control principle is seen shown in Figure 3, first controller, 2 control channel CON and monitor channel MON receive respectively from two remainings in the electric instruction of 4 remainings in the bar handle 1 with electric 4 remainings and instruct, namely instruct 1 and the instruction 2, and earlier it is finished on-line monitoring ILM, in first controller, 2 control channel CON, instruction 1 after the selection or instruct 2 with carry out synchronized sampling from the A channel information of port flap position transduser 16, the A channel information of port flap position transduser 16 is called flap configuration 1, in first controller, 2 monitor channel MON, instruction 1 after the selection or instruct 2 with carry out synchronized sampling from the B channel information of right flap position transducer 17, the B channel information of right flap position transducer 17 is called flap configuration 2, flap configuration 1 after the sampling and flap configuration 2 respectively in the control channel CON of first controller 2 and monitor channel MON comprehensive back as rudder face feedback and the command signal of selecting calculating rudder face position command in first controller, 2 control channel CON and monitor channel MON respectively, the comprehensive back control first wing flap motor 11 is carried out in instruction after the calculating in first controller, 2 control channels, the control principle of second controller 3 is identical with first controller 2, the instruction output control second wing flap motor 12 after it resolves, thus the output of the first wing flap motor 11 and the second wing flap motor 12 drives the wing flap motion by wing flap compensating gear 13 comprehensive rear drive wing flap mechanical drive linear systems 14.
Claims (1)
1. a combination reaches the high lift control system of asynchronous technique synchronously, it is characterized in that, native system comprises the bar handle (1) with electric 4 remainings, first controller (2), second controller (3), the first slat motor (4), the second slat motor (5), slat compensating gear (6), slat mechanical drive linear system (7), leading edge slat (8), left side slat position transduser (9), right slat position transduser (10), the first wing flap motor (11), the second wing flap motor (12), wing flap compensating gear (13), wing flap mechanical drive linear system (14), trailing edge flap (15), port flap position transduser (16) and right flap position transducer (17), wherein, described four sensors all are two remaining sensors that electric remaining A and electric remaining B form, each electric remaining of bar handle (1) connects the control channel CON of first controller (2) respectively, the monitor channel MON of first controller (2), the monitor channel MON of the control channel CON of second controller (3) and second controller (3), the first slat motor (4) connects the control channel CON of first controller (2), the second slat motor (5) connects the control channel of second controller (3), the first slat motor (4), the output shaft of the second slat motor (5) connects slat compensating gear (6), the output shaft of slat compensating gear (6) connects slat mechanical drive linear system (7), slat transmission linear system (7) connects leading edge slat (8), left side slat position transduser (9) is installed on slat mechanical drive linear system (7) left distal end, the A channel of left side slat position transduser (9) is connected to the control channel CON of first controller (2), the B passage of left side slat position transduser (9) is connected to the monitor channel MON of second controller (3), right slat position transduser (10) is installed on slat mechanical drive linear system (7) right end, the A channel of right slat position transduser (10) is connected to the control channel CON of second controller (3), the B passage of right slat position transduser (10) is connected to the monitor channel MON of first controller (2), the first wing flap motor (11) connects the control channel CON of first controller (2), the second wing flap motor (12) connects the control channel of second controller (3), the first wing flap motor (11), the output shaft of slat motor (12) connects wing flap compensating gear (13), the output shaft of wing flap compensating gear (13) connects wing flap mechanical drive linear system (14), wing flap transmission linear system connects (14) trailing edge flap (15), port flap position transduser (16) is installed on wing flap mechanical drive linear system (15) left distal end, the A channel of port flap position transduser (16) is connected to the control channel CON of first controller (2), the B passage of port flap position transduser (16) is connected to the monitor channel MON of second controller (3), right flap position transducer (17) is installed on wing flap mechanical drive linear system (15) right end, the A channel of right flap position transducer (17) is connected to the control channel CON of second controller (3), and the B passage of right flap position transducer (17) is connected to the monitor channel MON of first controller (2).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320049625 CN203111496U (en) | 2013-01-29 | 2013-01-29 | High lifting force control system combining synchronous technology and asynchronous technology |
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| Application Number | Priority Date | Filing Date | Title |
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| CN 201320049625 CN203111496U (en) | 2013-01-29 | 2013-01-29 | High lifting force control system combining synchronous technology and asynchronous technology |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107719639A (en) * | 2017-09-12 | 2018-02-23 | 陕西飞机工业（集团）有限公司 | A kind of double remaining wing flap automatic control systems |
| CN111026088A (en) * | 2019-12-24 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | Simulation-based detection method for uncommanded motion protection function of slat controller |
| CN111143987A (en) * | 2019-12-24 | 2020-05-12 | 中国航空工业集团公司西安飞机设计研究所 | Dynamics modeling method for aircraft high-lift system |
| CN111319757A (en) * | 2020-03-20 | 2020-06-23 | 中国商用飞机有限责任公司 | High lift system for aircraft |
| CN111439370A (en) * | 2020-04-21 | 2020-07-24 | 中国商用飞机有限责任公司 | High lift system and flap control method |
| CN111532418A (en) * | 2020-05-20 | 2020-08-14 | 中国商用飞机有限责任公司 | Aircraft high lift system |
-
2013
- 2013-01-29 CN CN 201320049625 patent/CN203111496U/en not_active Expired - Lifetime
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107719639A (en) * | 2017-09-12 | 2018-02-23 | 陕西飞机工业（集团）有限公司 | A kind of double remaining wing flap automatic control systems |
| CN111026088A (en) * | 2019-12-24 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | Simulation-based detection method for uncommanded motion protection function of slat controller |
| CN111143987A (en) * | 2019-12-24 | 2020-05-12 | 中国航空工业集团公司西安飞机设计研究所 | Dynamics modeling method for aircraft high-lift system |
| CN111143987B (en) * | 2019-12-24 | 2023-08-04 | 中国航空工业集团公司西安飞机设计研究所 | Dynamics modeling method for high-lift system of airplane |
| CN111319757A (en) * | 2020-03-20 | 2020-06-23 | 中国商用飞机有限责任公司 | High lift system for aircraft |
| CN111319757B (en) * | 2020-03-20 | 2021-05-11 | 中国商用飞机有限责任公司 | High lift system for aircraft |
| CN111439370A (en) * | 2020-04-21 | 2020-07-24 | 中国商用飞机有限责任公司 | High lift system and flap control method |
| CN111439370B (en) * | 2020-04-21 | 2021-06-15 | 中国商用飞机有限责任公司 | High lift system and flap control method |
| CN111532418A (en) * | 2020-05-20 | 2020-08-14 | 中国商用飞机有限责任公司 | Aircraft high lift system |
| CN111532418B (en) * | 2020-05-20 | 2021-09-24 | 中国商用飞机有限责任公司 | Aircraft high lift system |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130807 |
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| CX01 | Expiry of patent term |