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10,4
6,4
STL 945.7136/97
Performance comparison : major results and conclusions
5.19
All measurements of smoothness and stability
favoured the sidestick by a large margin :
- for roll and pitch angles and rates, standard
deviations and rate through zero were reduced
by 20% or more when flying with the sidestick,
- accelerations in all three axes showed a large
reduction in standard deviation and rate
through zero when flying with the sidestick
STL 945.7136/97
Performance comparison of sidestick/FWB and conventional controls
5.20
N1 engine No.1
Standard deviation
N1 engine No.1
Reversal rate
Pitch trim + elevator
+ aileron reversals
vs
Any sidestick reversal
STL 945.7136/97
Performance comparison : major results and conclusions
5.21
All parameters related to fuel burn showed
significantly better values with sidestick :
- the sidestick/EFCS combination should
improve fuel economy through unnecessary
control surface movements and increased rear
C.G. limits.
Pilot control inputs were reduced by 50% or more
and the system still achieved much better overall
performance :
- lower pilot workload should allow more time for
dealing with emergencies and managing flight
efficiency.
STL 945.7136/97
A319/A320/A321 EFCS architecture
5.22
G Y Y G G Y Y G
G
B B
B G B
G Y
B G Y B
ELAC 2 SEC 1 2 3
2 Elevator/Aileron Computers (ELAC)
Ground spoiler
LAF*
Roll
Speed brake
LH Aileron
ELAC 1 2
SEC 2 1 1 3 3
Normal control
Normal
control
THS actuator**
Hydraulic
B – Blue system
G – Green system
Y – Yellow system
* LAF = Load Alleviation Function (A320 only)
**THS = Trimmable Horizontal Stabilizer
LH Elevator LH Elevator
ELAC 1 2 2 1 2 1 ELAC
SEC 1 2 1 2 2 1 SEC
Mechanical
3 Spoiler/Elevator Computers (SEC)
Ground spoiler
LAF*
Roll
Speed brake
RH Aileron
3 3 1 1 2 SEC
STL 945.7136/97
A319/A320/A321 EFCS redundancy aspects
5.23
Use of dissimilar redundancy
Two types of computer - two ELACs to achieve aileron
control and normal pitch
control
- three SECs to achieve spoiler
control and standby pitch
control
No single type of μ P : ELAC - Motorola 68000
SEC - INTEL 80186
Each ELAC and SEC is divided into two units :
- one Control Unit (COM)
- one Monitoring unit (MON)
Four different softwares : ELAC COM + MON
SEC COM + MON.
Physical separation of hardware for COM and MON units.
In addition, mechanical back-up (through rudder and
stabilizer control) will ensure adequate control in case of
temporary loss of all electrical power sources including
batteries.
STL 945.7136/97
A319/A320/A321 EFCS electronic protections
5.24
Self tests
Each computer is able to detect its own failures :
- processor test (check sum, watchdog…)
- electrical supply monitoring
- input and output test
- wrap around of output to input.
-
Inputs are monitored :
- by comparison of signals of the same type but
sent by different sources
- by checking the signal coherence.
Other protections
Specific routes are dedicated to :
control signals
monitoring signals
Signals are linked :
ELAC 1 and SEC 1 computers on one side
ELAC 2, SEC 2 and SEC 3 computers on the other
side.
ELAC and SEC computers are qualified in
convenience with DO 160 for electrical susceptibility
test, the most severe category (Z) being applied.
- Wires are installed in metal shields in the exposed
areas.
- For each signal, wires are twisted.
- No signal grounding in the exposed areas.
- Computer inputs and outputs connected to
exposed wires are protected against the most
severe spikes.
This protection, combined with the precautions taken
in the software, ensure good protection against
lightning strikes and electromagnetic disturbances.
STL 945.7136/97
A319/A320/A321 EFCS flight envelope protection
5.25
Overspeed protection
Positive load factor demand automatically applied
when Vmo + 6kt ot Mmo + 0.01 is reached,
-
Speed limited to Vmo + 16kt and Mmo + 0.04 when
full nose-down stick is maintained,
Vmo/Mmo warning :
- continuous repetitive chime
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A319/A320/A321飞行员驾驶舱和系统简介(8)
