CN106483977A - A kind of redundance flight control system and control method - Google Patents
A kind of redundance flight control system and control method Download PDFInfo
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- CN106483977A CN106483977A CN201611087503.2A CN201611087503A CN106483977A CN 106483977 A CN106483977 A CN 106483977A CN 201611087503 A CN201611087503 A CN 201611087503A CN 106483977 A CN106483977 A CN 106483977A
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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 title claims abstract description 23
- 238000000034 method Methods 0.000 title claims abstract description 13
- 230000005611 electricity Effects 0.000 claims description 6
- 238000012544 monitoring process Methods 0.000 claims description 6
- 230000002159 abnormal effect Effects 0.000 description 2
- 241000941123 Euhybus triplex Species 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
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- Automation & Control Theory (AREA)
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Abstract
The present invention relates to aircraft flight control system technical field, more particularly to a kind of redundance flight control system and control method.Redundance flight control system includes：The first computer side by side, second computer and the 3rd computer；Left angle of attack sensor, which includes first angle of attack arranged side by side electrically and second angle of attack is electric, and wherein, first angle of attack is electrically connected with first computer, and second angle of attack is electrically connected with the second computer；Right angle of attack sensor, which includes the 3rd angle of attack arranged side by side electrically and the 4th angle of attack is electric, wherein, the 3rd angle of attack is electrically connected with the 3rd computer, and the 4th angle of attack is electrically connected with first computer, the second computer and the 3rd computer respectively.Redundance flight control system of the present invention and control method, being prevented from any one electric fault causes angle of attack sensor to fail, it is ensured that the availability of angle of attack sensor.
Description
Technical field
The present invention relates to aircraft flight control system technical field, more particularly to a kind of redundance flight control system and control
Method processed.
Background technology
Angle of attack signal is the signal of interest in flight control system, is crucial feedback signal in flight control system, uses
In the stability for increasing aircraft.At present, in order to ensure the correctness of signal, the angle of attack signal for gathering multiple remainings is generally required,
And which is put to the vote, choose correct value and be input into as system；While being monitored to redundance signal, fault-signal is entered
Row isolation.
But, how to be met using the double remainings of machinery (configuring two electric remainings in each mechanical remaining) on some unmanned planes
Angle weathercock sensor, and computer is then many using triplex redundance structure, both remainings are mismatched, if redundancy architecture is arranged not
Good, the degradation speed of system can be accelerated, affect aircraft safety.
Content of the invention
It is an object of the invention to provide a kind of redundance flight control system and control method, at least to solve existing machine
The double remaining angle of attack weathercock sensors of tool and the unmatched problem of triplex redundance computer configuation remaining.
The technical scheme is that：
A kind of redundance flight control system, including：
The first computer side by side, second computer and the 3rd computer；
Left angle of attack sensor, which includes first angle of attack arranged side by side electrically and second angle of attack is electric, wherein, first angle of attack
Electrically it is connected with first computer, second angle of attack is electrically connected with the second computer；
Right angle of attack sensor, which includes the 3rd angle of attack arranged side by side electrically and the 4th angle of attack is electric, wherein, the 3rd angle of attack
Electrically be connected with the 3rd computer, the 4th angle of attack electrically respectively with first computer, the second computer
And the 3rd computer connection.
Present invention also offers a kind of control method of redundance flight control system, comprises the steps：
Step one, first computer, second computer and the 3rd computer gather respectively first angle of attack electrically,
The electric angle of attack signal of electric and described 3rd angle of attack of second angle of attack；
Step 2, first computer, second computer and the 3rd computer are gathered respectively while gathering the described 4th
The electric angle of attack signal of the angle of attack；
Step 3, first computer, second computer and the 3rd computer electrically enter to the 4th angle of attack first
The monitoring voting of row triplex redundance, obtains the electric vote value of the 4th angle of attack；
Step 4, first computer, second computer and the 3rd computer angle of attack electric to first angle of attack
The electric angle of attack signal of the electric angle of attack signal of signal, second angle of attack, the 3rd angle of attack and the 4th angle of attack electricity
The vote value of gas carries out the monitoring voting of four remainings, so as to draw final angle of attack vote value.
Invention effect：
Redundance flight control system of the present invention and control method, being prevented from any one electric fault causes the angle of attack to pass
Sensor fails, it is ensured that the availability of angle of attack sensor.
Description of the drawings
Fig. 1 is the structural representation of existing redundance flight control system；
Fig. 2 is the structural representation of redundance flight control system of the present invention.
Specific embodiment
For making purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.Embodiment below with reference to Description of Drawings is exemplary, it is intended to use
In the explanation present invention, and it is not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment obtained under the premise of creative work is not made by member, belongs to the scope of protection of the invention.Under
Face combines accompanying drawing and embodiments of the invention is described in detail.
In describing the invention, it is to be understood that term " " center ", " longitudinal direction ", " horizontal ", "front", "rear",
The orientation of instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outward " or position relationship be based on accompanying drawing institute
The orientation for showing or position relationship, are for only for ease of the description present invention and simplify description, rather than the dress of instruction or hint indication
Put or element must be with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that protecting to the present invention
The restriction of scope.
1 to Fig. 2 is done further specifically to redundance flight control system of the present invention and control method below in conjunction with the accompanying drawings
Bright.
The method of attachment of existing redundance flight control system is as shown in figure 1, which deposits the problem being primarily present is：
One), when four remaining signals are effective：If the analog quantity acquisition circuit fault of 11 passage of the first computer, the
One angle of attack electric 21 and the 4th angle of attack electric 32 all gather abnormal (in most cases collection value be 0 near)；Now second
The angle of attack electric 22 and the 3rd angle of attack electric 31, electric with first angle of attack 21 and the 4th the angle of attack electric 32 occur 2：2 faults, four remainings
The angle of attack all fails, it is impossible to meets an electric fault normal work and requires.
Two), after second angle of attack electric 22 or any one failure of the 3rd angle of attack electric 31, it is electric that this sentences the 3rd angle of attack
As a example by 31 failures：If occurring the analog quantity acquisition circuit fault of 11 passage of the first computer again, first angle of attack electric 21 and
Four angles of attack electric 32 all gather abnormal (in most cases collection value be 0 near), now, first angle of attack electric 21 and the 4th
The angle of attack electric 32, electric with second angle of attack 22 is inconsistent, that is, occur 2：1 situation, redundancy management can be put electric for second angle of attack 22
For fault.System can now be caused using the angle of attack value of mistake, it is impossible to ensure flight safety.
For this purpose, the invention provides a kind of redundance flight control system, can include the first computer 11 arranged side by side, the
Two computers 12 and the 3rd computer 13 (i.e. triplex redundance computer)；Can also include that left angle of attack sensor 2 and the right angle of attack are sensed
Device 3.
Left angle of attack sensor 2 includes first angle of attack electric 21 arranged side by side and second angle of attack electric 22, wherein, first angle of attack electricity
Gas 21 is connected with the first computer 11, and second angle of attack electric 22 is connected with second computer 12.
Right angle of attack sensor 3 includes the 3rd angle of attack electric 31 arranged side by side and the 4th angle of attack electric 32, wherein, the 3rd angle of attack electricity
Gas 31 is connected with the 3rd computer 13, the 4th angle of attack electric 32 respectively with the first computer 11, second computer 12 and the 3rd
Computer 13 connects.
Further, present invention also offers a kind of control method of redundance flight control system, it is characterised in that include
Following steps：
Step one, the first computer 11, second computer 12 and the 3rd computer 13 gather first angle of attack electricity respectively
The angle of attack signal of gas 21, second angle of attack electric 22 and the 3rd angle of attack electric 31.
Step 2, first computer 11, second computer 12 and the 3rd computer 13 are gathered respectively while collection the
The angle of attack signal of four angles of attack electric 32.
Step 3, the first computer 11, second computer 12 and the 3rd computer 13 enter to the 4th angle of attack electric 32 first
The monitoring voting of row triplex redundance, obtains the vote value of the 4th angle of attack electric 32.
Step 4, the first computer 11, the angle of attack of 13 pairs of first angles of attack of second computer 12 and the 3rd computer electric 21
The table of signal, the angle of attack signal of second angle of attack electric 22, the angle of attack signal of the 3rd angle of attack electric 31 and the 4th angle of attack electric 32
Certainly value carries out the monitoring voting of four remainings, so as to draw final angle of attack vote value.
Advantages of the present invention is as follows：
One), when four remaining signals are effective：If the analog quantity acquisition circuit fault of 11 passage of the first computer, only shadow
Ring the output of first angle of attack electric 21, and the 4th angle of attack electric 32 1 remainings output (12 passage of second computer and the 3rd meter
13 channel acquisition of calculation machine is normal, does not interfere with electric 32 vote value of the 4th angle of attack), do not result in angle of attack failure.
Two), after second angle of attack electric 22 or any one failure of the 3rd angle of attack electric 31, equally electric with the 3rd angle of attack
As a example by 31 failures：If 11 channel acquisition fault of the first computer, the output of first angle of attack electric 21, and the 4th angle of attack is only affected
(12 passage of second computer and 13 channel acquisition of the 3rd computer normally, do not interfere with the 4th and meet for electric 32 1 remainings output
Electric 32 vote value in angle), the vote value electric with second angle of attack 22 of the 4th angle of attack electric 32 is worth consistent, both and first angle of attack electricity
Gas 21 is different, Systems Redundancy Management can correct first angle of attack of defective channel cut-out electric 21, correct signal will not be cut
Remove.
Redundance flight control system of the present invention and control method, being prevented from any one electric fault causes the angle of attack to pass
Sensor fails, it is ensured that the availability of angle of attack sensor.
The above, the only specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, and any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can readily occur in, all answer
It is included within the scope of the present invention.Therefore, protection scope of the present invention with the scope of the claims should be
Accurate.
Claims (2)
1. a kind of redundance flight control system, it is characterised in that include：
The first computer (11) side by side, second computer (12) and the 3rd computer (13)；
Left angle of attack sensor (2), which includes first angle of attack arranged side by side, and electrically (21) and second angle of attack are electrically (22), wherein, described
Electrically (21) be connecteds first angle of attack with the first computer (11), second angle of attack electric (22) and the second computer
(12) connect；
Right angle of attack sensor (3), which includes the 3rd angle of attack arranged side by side, and electrically (31) and the 4th angle of attack are electrically (32), wherein, described
Electrically (31) are connected 3rd angle of attack with the 3rd computer (13), and the 4th angle of attack electrically count with described first respectively by (32)
The connection of calculation machine (11), the second computer (12) and the 3rd computer (13).
2. the control method of a kind of redundance flight control system according to claim 1, it is characterised in that including as follows
Step：
Step one, first computer (11), second computer (12) and the 3rd computer (13) gather described first respectively
The angle of attack signal of the angle of attack electric (21), second angle of attack electric (22) and the 3rd angle of attack electric (31)；
Step 2, first computer (11), second computer (12) and the 3rd computer (13) are gathered respectively while collection
The angle of attack signal of the 4th angle of attack electric (32)；
Step 3, first computer (11), second computer (12) and the 3rd computer (13) are met to the described 4th first
Electrically (32) carry out triplex redundance monitoring voting at angle, obtain the vote value of the 4th angle of attack electric (32)；
Step 4, first computer (11), second computer (12) and the 3rd computer (13) are to first angle of attack electricity
The angle of attack signal of the angle of attack signal of gas (21), second angle of attack electric (22), the angle of attack letter of the 3rd angle of attack electric (31)
Number and the vote value of the 4th angle of attack electrically (32) carry out the monitoring voting of four remainings, so as to draw final angle of attack voting
Value.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201611087503.2A CN106483977A (en) | 2016-11-30 | 2016-11-30 | A kind of redundance flight control system and control method |
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| CN201611087503.2A CN106483977A (en) | 2016-11-30 | 2016-11-30 | A kind of redundance flight control system and control method |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108107910A (en) * | 2017-12-28 | 2018-06-01 | 中航联创科技有限公司 | A kind of system for flight control computer based on distributed redundance bus and winged prosecutor method |
| CN108415238A (en) * | 2018-02-02 | 2018-08-17 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of electricity trim monitoring switch method |
| CN110844119A (en) * | 2018-11-30 | 2020-02-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft attack angle voting method |
| CN112109907A (en) * | 2020-07-24 | 2020-12-22 | 中国南方航空股份有限公司 | Real-time monitoring method for aircraft angle of attack detector |
| CN112558461A (en) * | 2021-02-25 | 2021-03-26 | 四川腾盾科技有限公司 | Output signal voting method for redundancy unmanned aerial vehicle airplane management computer |
| CN112762816A (en) * | 2020-12-25 | 2021-05-07 | 兰州飞行控制有限责任公司 | Redundancy angular displacement sensor with self-isolation blocking fault and use method |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108107910A (en) * | 2017-12-28 | 2018-06-01 | 中航联创科技有限公司 | A kind of system for flight control computer based on distributed redundance bus and winged prosecutor method |
| CN108415238A (en) * | 2018-02-02 | 2018-08-17 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of electricity trim monitoring switch method |
| CN110844119A (en) * | 2018-11-30 | 2020-02-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft attack angle voting method |
| CN112109907A (en) * | 2020-07-24 | 2020-12-22 | 中国南方航空股份有限公司 | Real-time monitoring method for aircraft angle of attack detector |
| CN112109907B (en) * | 2020-07-24 | 2023-03-14 | 中国南方航空股份有限公司 | Real-time monitoring method for aircraft angle of attack detector |
| CN112762816A (en) * | 2020-12-25 | 2021-05-07 | 兰州飞行控制有限责任公司 | Redundancy angular displacement sensor with self-isolation blocking fault and use method |
| CN112558461A (en) * | 2021-02-25 | 2021-03-26 | 四川腾盾科技有限公司 | Output signal voting method for redundancy unmanned aerial vehicle airplane management computer |
| CN112558461B (en) * | 2021-02-25 | 2021-05-14 | 四川腾盾科技有限公司 | Output signal voting method for redundancy unmanned aerial vehicle airplane management computer |
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Application publication date: 20170308 |