CN109582033A - A kind of civil aircraft fax flight control computer control model conversion method - Google Patents
A kind of civil aircraft fax flight control computer control model conversion method Download PDFInfo
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- CN109582033A CN109582033A CN201811440119.5A CN201811440119A CN109582033A CN 109582033 A CN109582033 A CN 109582033A CN 201811440119 A CN201811440119 A CN 201811440119A CN 109582033 A CN109582033 A CN 109582033A
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- atmosphere data
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- 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
Abstract
The present invention relates to a kind of control model conversion methods of civil aircraft fax flight control computer；System is initialized first, FCC fully enters system degradation mode first；The mode conversion of FCC is divided into 5 channels to control, corresponding 5 main control surfaces are respectively: left and right elevator, left and right aileron and rudder；Later according to the availability deciding of atmosphere data as a result, the switching condition in conjunction with each channel individually carries out pattern switching to each channel.When system breaks down, the distributed AC servo system mode for realizing system degrades, and it is too fast to avoid system performance degradation；Current civil aircraft fly-by-wire flight control system is efficiently solved due to redundance actuator allocation, caused power dispute problem is likely to be out of synchronization during mode conversion；The crosslinking communication between actuator control electronics is avoided, significantly reduces design complexities, while reducing development cost.
Description
Technical field
The present invention relates to a kind of control model conversion methods of civil aircraft fax flight control computer.
Background technique
In order to which the configuration states according to flight control system realize different control performances, civil aircraft fly-by-wire flight control system is general
There are three types of control models for tool: normal mode, degraded mode and Direct Model.
Wherein, flight-control computer (Flight control computer, FCC) has normal control mode and drop
Grade two kinds of control models of control model: when FCC receives effective air data sensor signal, FCC is in normal control
Mode, execution is restrained according to the optimal performance normal control of atmosphere data and flap configuration adjusting parameter, exports normal mode
Control law instruction；When FCC is not received by effective air data sensor signal, FCC is in fallback control mode, executes
Be the output degradation scheme control rule instruction according to the degradation control law of wing flap configuration adjusting parameter.
Actuator control electronics (Auctuator Control Electronics, ACE) receive FCC output it is normal (or
Degrade) scheme control rule instruction, drive ram moved.When that can receive effective FCC instruction, ACE driving is made
Dynamic device realizes normal (or degradation) scheme control rule instruction；When that can not receive effective FCC instruction, ACE will execute basis
The Direct Model control law of wing flap configuration tune ginseng resolves, and drive ram realizes the instruction of Direct Model control law.
In addition, in order to meet the security requirement of civil aircraft flight control system, the main operation face of civil aircraft flight control system (include: it is left,
Right elevator, left and right aileron and rudder) generally by two (or three) actuator co- controllings, each equal work of actuator
Make in master-master (or main-main-main) mode.
Summary of the invention
The purpose of the present invention: proposing a kind of civil aircraft fax flight control computer control model conversion method, realizes two kinds of controls
The switching of mode, and ensure that two (or three) actuator of same control surface work in identical operating mode.
Technical solution of the present invention:
A kind of civil aircraft fax flight control computer control model conversion method: it comprises the steps of；
The first step, system initialization, FCC fully enter system degradation mode first；
Second step judges the validity of atmosphere data according to atmosphere data monitored results, if being efficiently entering in next step, if
It is invalid then Atmosphere System is waited to power on；
Third step, FCC enter system normal mode；
The mode conversion of FCC is divided into 5 channels to control, corresponding 5 main control surfaces are respectively: left and right lifting
Rudder, left and right aileron and rudder；
1) FCC left elevator channel control model is converted,
When meeting for the following conditions any one, FCC left elevator channel control model is converted to degradation from normal mode
Mode:
A) atmosphere data monitoring display atmosphere data is invalid；
B) the ACE operating mode for controlling left inside elevator actuator is Direct Model；
C) the ACE operating mode for controlling left outside elevator actuator is Direct Model；
2) FCC right elevator control model is converted,
When meeting for the following conditions any one, FCC right elevator channel control model is converted to degradation from normal mode
Mode:
A) atmosphere data monitoring display atmosphere data is invalid；
B) the ACE operating mode of elevator actuator is Direct Model in the control right side；
C) the ACE operating mode of the right outer elevator actuator of control is Direct Model；
3) FCC port aileron channel control model is converted,
When meeting for the following conditions any one, FCC port aileron channel control model is converted to degradation mould from normal mode
Formula:
A) atmosphere data monitoring display atmosphere data is invalid；
B) the ACE operating mode for controlling left inside aileron actuator is Direct Model；
C) the ACE operating mode for controlling left outside aileron actuator is Direct Model；
4) FCC starboard aileron channel control model is converted,
When meeting for the following conditions any one, FCC starboard aileron channel control model is converted to degradation mould from normal mode
Formula:
A) atmosphere data monitoring display atmosphere data is invalid；
B) the ACE operating mode of aileron actuator is Direct Model in the control right side；
C) the ACE operating mode for controlling right external aileron actuator is Direct Model；
5) FCC rudder channel control model is converted,
When meeting for the following conditions any one, FCC rudder channel control model is converted to degradation mould from normal mode
Formula:
A) atmosphere data monitoring display atmosphere data is invalid；
B) the ACE operating mode for controlling upper rudder actuator is Direct Model；
C) the ACE operating mode of rudder actuator is Direct Model in control；
D) the ACE operating mode for controlling lower rudder actuator is Direct Model.
Further, when FCC control model changes, control instruction jump occurs in order to prevent, needs to carry out just
The desalt processing of the instruction of norm formula control law and the instruction of degraded mode control law, desalination algorithm are linear desalination.When FCC controls mould
After formula changes, fading function carries out initialization immediately and carries out desalt processing, desalination rule to signal are as follows:
Y (t)=[y (0)-u (t)] × f (t)+u (t),
Wherein: y (t) --- the output valve of-desalination apparatus；
Y (0) --- when-connection desalination apparatus, the control law instruction value for the upper bat that desalination apparatus is retained；
U (t) ----in fade time, the input value of desalination apparatus；
F (t) ----fading function, form are shown below, and t0 is fade time in formula.
Further, the determination method of atmosphere data validity described in second step is as follows:
The mean value for determining atmosphere data signal value first, calculates the absolute difference of each group atmosphere data signal value and mean value
Value judges whether each absolute value differences are more than threshold value and lasting preset time, if there are two wherein or more than two more than door
Limit value and lasting preset time, then it is assumed that atmosphere data is invalid；Otherwise it is assumed that atmosphere data is effective.
Advantageous effects of the invention:
The invention proposes a kind of civil aircraft fax flight control computer control model conversion methods, can be realized flight control computer
The conversion of two kinds of control models of normal mode and degraded mode, has the advantage that
(1) mode conversion and control is carried out according to control surface subchannel, when system breaks down, realizes the distribution of system
Formula control model degrades, and it is too fast to avoid system performance degradation；
(2) current civil aircraft fly-by-wire flight control system is efficiently solved due to redundance actuator allocation, in mode conversion
The dispute problem of power caused by being likely to be out of synchronization in the process；
(3) the crosslinking communication between actuator control electronics is avoided, design complexities is significantly reduced, reduces simultaneously
Development cost.
Detailed description of the invention
Fig. 1 is left elevator channel control model transition diagram,
Fig. 2 is right elevator channel control model transition diagram,
Fig. 3 is port aileron channel control model transition diagram,
Fig. 4 is starboard aileron channel control model transition diagram,
Fig. 5 is rudder channel control model transition diagram.
Specific embodiment
A kind of civil aircraft fax flight control computer control model conversion method: the specific implementation steps are as follows；
The first step, system initialization, FCC fully enter system degradation mode first；
Second step judges the validity of atmosphere data according to atmosphere data monitored results, if being efficiently entering in next step, if
It is invalid then Atmosphere System is waited to power on；
Third step, FCC enter system normal mode；
The mode conversion of FCC is divided into 5 channels to control, corresponding 5 main control surfaces are respectively: left and right lifting
Rudder, left and right aileron and rudder；
1) FCC left elevator channel control model is converted,
When meeting for the following conditions any one, FCC left elevator channel control model is converted to degradation from normal mode
Mode:
D) atmosphere data monitoring display atmosphere data is invalid；
E) the ACE operating mode for controlling left inside elevator actuator is Direct Model；
F) the ACE operating mode for controlling left outside elevator actuator is Direct Model；
2) FCC right elevator control model is converted,
When meeting for the following conditions any one, FCC right elevator channel control model is converted to degradation from normal mode
Mode:
D) atmosphere data monitoring display atmosphere data is invalid；
E) the ACE operating mode of elevator actuator is Direct Model in the control right side；
F) the ACE operating mode of the right outer elevator actuator of control is Direct Model；
3) FCC port aileron channel control model is converted,
When meeting for the following conditions any one, FCC port aileron channel control model is converted to degradation mould from normal mode
Formula:
D) atmosphere data monitoring display atmosphere data is invalid；
E) the ACE operating mode for controlling left inside aileron actuator is Direct Model；
F) the ACE operating mode for controlling left outside aileron actuator is Direct Model；
4) FCC starboard aileron channel control model is converted,
When meeting for the following conditions any one, FCC starboard aileron channel control model is converted to degradation mould from normal mode
Formula:
D) atmosphere data monitoring display atmosphere data is invalid；
E) the ACE operating mode of aileron actuator is Direct Model in the control right side；
F) the ACE operating mode for controlling right external aileron actuator is Direct Model；
5) FCC rudder channel control model is converted,
When meeting for the following conditions any one, FCC rudder channel control model is converted to degradation mould from normal mode
Formula:
E) atmosphere data monitoring display atmosphere data is invalid；
F) the ACE operating mode for controlling upper rudder actuator is Direct Model；
G) the ACE operating mode of rudder actuator is Direct Model in control；
The ACE operating mode for controlling lower rudder actuator is Direct Model.
On atmosphere data Effective judgement, by taking triplex redundance atmosphere data type as an example, atmosphere data validity monitoring side
Method is as follows:
The first step determines atmosphere data signal 1 (ADS1), atmosphere data signal 2 (ADS2), atmosphere data signal 3
(ADS3) mean value (ADS_M)；
Second step calculates the absolute difference Δ 1 of ADS1 and ADS_M；Calculate the absolute difference Δ 2 of ADS2 and ADS_M；It calculates
The absolute difference Δ 3 of ADS3 and ADS_M；
Third step judges whether Δ 1, Δ 2, Δ 3 are more than threshold value and lasting preset time, if having in Δ 1, Δ 2, Δ 3
Two or more are more than threshold value and lasting preset time, then it is assumed that atmosphere data is invalid；Otherwise it is assumed that atmosphere data has
Effect.
Claims (3)
1. a kind of civil aircraft fax flight control computer control model conversion method: it is characterized by: comprising the steps of；
The first step, system initialization, FCC fully enter system degradation mode first；
Second step judges the validity of atmosphere data according to atmosphere data monitored results, if being efficiently entering in next step, if in vain
Then Atmosphere System is waited to power on；
Third step, FCC enter system normal mode；
The mode conversion of FCC is divided into 5 channels to control, corresponding 5 main control surfaces are respectively: left and right elevator, left,
Starboard aileron and rudder；
1) FCC left elevator channel control model is converted,
When meeting for the following conditions any one, FCC left elevator channel control model is converted to degraded mode from normal mode:
A) atmosphere data monitoring display atmosphere data is invalid；
B) the ACE operating mode for controlling left inside elevator actuator is Direct Model；
C) the ACE operating mode for controlling left outside elevator actuator is Direct Model；
2) FCC right elevator control model is converted,
When meeting for the following conditions any one, FCC right elevator channel control model is converted to degraded mode from normal mode:
A) atmosphere data monitoring display atmosphere data is invalid；
B) the ACE operating mode of elevator actuator is Direct Model in the control right side；
C) the ACE operating mode of the right outer elevator actuator of control is Direct Model；
3) FCC port aileron channel control model is converted,
When meeting for the following conditions any one, FCC port aileron channel control model is converted to degraded mode from normal mode:
A) atmosphere data monitoring display atmosphere data is invalid；
B) the ACE operating mode for controlling left inside aileron actuator is Direct Model；
C) the ACE operating mode for controlling left outside aileron actuator is Direct Model；
4) FCC starboard aileron channel control model is converted,
When meeting for the following conditions any one, FCC starboard aileron channel control model is converted to degraded mode from normal mode:
A) atmosphere data monitoring display atmosphere data is invalid；
B) the ACE operating mode of aileron actuator is Direct Model in the control right side；
C) the ACE operating mode for controlling right external aileron actuator is Direct Model；
5) FCC rudder channel control model is converted,
When meeting for the following conditions any one, FCC rudder channel control model is converted to degraded mode from normal mode:
A) atmosphere data monitoring display atmosphere data is invalid；
B) the ACE operating mode for controlling upper rudder actuator is Direct Model；
C) the ACE operating mode of rudder actuator is Direct Model in control；
D) the ACE operating mode for controlling lower rudder actuator is Direct Model.
2. a kind of civil aircraft fax flight control computer control model conversion method according to claim 1, it is characterised in that: when
After FCC control model changes, fading function carries out initialization immediately and carries out desalt processing, desalination rule to signal are as follows:
Y (t)=[y (0)-u (t)] × f (t)+u (t),
Wherein: y (t) --- the output valve of-desalination apparatus；
Y (0) --- when-connection desalination apparatus, the control law instruction value for the upper bat that desalination apparatus is retained；
U (t) ----in fade time, the input value of desalination apparatus；
F (t) ----fading function, form are shown below, and t0 is fade time in formula.
3. a kind of civil aircraft fax flight control computer control model conversion method according to claim 1, it is characterised in that: the
The determination method of atmosphere data validity described in two steps is: first determining the mean value of each group atmosphere data signal value, calculates each group
The absolute value differences of atmosphere data signal value and mean value, when judging whether each absolute value differences are more than threshold value and persistently preset
Between, if there are two wherein or more than two more than threshold value and lasting preset time, then it is assumed that atmosphere data is invalid；Otherwise, recognize
It is effective for atmosphere data.
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|---|---|---|---|
| CN201811440119.5A CN109582033B (en) | 2018-11-28 | 2018-11-28 | Control mode conversion method for civil aviation telex flight control computer |
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|---|---|---|---|
| CN201811440119.5A CN109582033B (en) | 2018-11-28 | 2018-11-28 | Control mode conversion method for civil aviation telex flight control computer |
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| CN109582033B CN109582033B (en) | 2022-02-08 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023035497A1 (en) * | 2021-09-07 | 2023-03-16 | 中国商用飞机有限责任公司 | Fly-by-wire flight backup control system and method |
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Cited By (1)
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| WO2023035497A1 (en) * | 2021-09-07 | 2023-03-16 | 中国商用飞机有限责任公司 | Fly-by-wire flight backup control system and method |
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| CN109582033B (en) | 2022-02-08 |
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