presentación de powerpointamc 25.415 ground gust conditions cs 25.675 control systems, stops cs...
TRANSCRIPT
CESA – Compañía Española de Sistemas Aeronáuticos
Background
RESEARCH Introduction
System Requirements & Trade-off of Architectures
Elevator Flight Control System
Safety
HUMS – Health and Usage Monitoring
Reliability & Safety Enhanced
Electrical Actuation System
Architectures
1
2
3
4
5
6
2
7
CESA
Founded more than 25 years ago, CESA has
extensive experience in developing, producing
and providing support for mechanical fluid
equipment and systems.
1
CESA Shareholders
3 Turnover by Product Line
• Compañía Española de Sistemas Aeronáuticos
C295 Accumulator
EFA Foreplane Actuator
A380 Reservoir
A330 tail boom HOIST and ERAS
A400M Cargo door actuator
E-ELT Support System and
Position Actuator
FT4B Actuator
Background
• CESA participation in European Projects
2
Modular Electro Mechanical Actuators for
ACARE 2020 aircraft and helicopters
RESEARCH
Design, development and manufacturing
of an electro-mechanical actuator and
test rig for AiRcrafts Main LandIng Gear
acTuation systems
Advanced Flight Control System –
Design Development and Manufacturing
of an Electro Mechanical Actuator with
associated Electronic Control Unit and
Dedicated test Bench
REliability and Safety Enhanced electrical Actuation System ARCHitectures.
FLIGHT EMA
(e-RUDDER)
ARMLIGHT
Others: GreenAir, SuperSkySense, Fastwing, IND-Dampers, Titalum, Newtiral,
POA, LAMA, ELGAR, NIPSE…
CESA E-Rudder EMA
CESA Armlight EMA
4
RESEARCH Introduction
• RESEARCH Consortium
3
5
Coordinator:
University of Moscow
TSagi
RESEARCH Introduction
• RESEARCH
Objective Development of electrical
architectures for Flight Control
Systems capable of controlling flight
control surface on an A/C with the
help of electrically operated
actuators, thus replacing the
hydraulic actuators commonly used
in current A/C designs
6
Example of Typical Hydraulic A/C System
Full Electric Flight Control System
Flight Controls
3
RESEARCH Introduction
• RESEARCH Workpackage structure
3
7
System Requirements
• Definition of System Requirements • CS-25
4
CS 25.393
Loads parallel to hinge line
CS 25.395
Control system
CS 25.397
Control system loads
AMC 25.415
Ground Gust Conditions
CS 25.675
Control Systems, Stops
CS 25.679
Control system gust locks
CS 25.683
Operation tests
CS 25.685
Control system details
CS 25.1309
Equipment, systems and
installations
(…)
• The probabilty of Jamming of at least one Aileron out of neutral shall be less than 1.0E-07 per Flight Hour
Safety
• The mínimum rudder deflection rate shall be 40 degree per second
Speed
• The stall hinge moment for the elevator Surface shall be 4 KNm Force
Examples of System level requirements for Regional Aircraft
Certification specification
requirements for Large Aircrafts 8
Trade-off of Architectures
• Architecture selection
4
Selection of Architecture
Performance
Safety Weight
Preliminary Fault Tree Analysis Full
Electric Elevator Flight Control Example
Trade-off architecture main factors
Preliminary Weight estimation example
for Rudder Configurations
Preliminary Force vs Speed assessment for
Aileron configurations
9
Elevator Flight Control System
• Final Selection: Elevator Architecture
Both type of actuators can be chosen. From a safety point of view, the implementation of an
anti-jamming device in the EMA makes it a perfect candidate to be selected for its
installation is primary flight control surface as the rudder or elevator while EHA provides the
required damping mode just as the traditional Hydraulic Servoactuator with the proven
safety rating
5
Elevator Control Architecture selected for the RESEARCH project
10
Safety
• System Safety Assessment Process
(SAE-ARP-4761)
6
FHA PSSA SSA
Main Safety Challenge of Electric Elevator
Jamming
REQ. Jamming of at least one Elevator surface out of neutral (CAT)
System Safety Assessment Process
11
• Safety features: EMA with anti-jamming
CESA has developed a proprietary anti-
jamming system to avoid catastrophic failure
in EMAs for primary flight controls (and
Landing gear actuation) system. The solution
is a locking device that keep anti-jamming
system locked until a failure or a degraded
performance is detected internally by CBIT
function; afterwards, the auxiliary anti-
jamming system acts extending the actuator
freely
Jamming!!!
Control Loop: Emergency Mode
Electronic Controller (ECU) receives EMA status and send it to
System Controller (SECU)
SECU shares information with the crosschecked SECU
Crosschecked SECU activates
Antijamming system of the EMA failed
12
Safety 6
EMA Main parts
HUMS
• Benefits of HUMS
7
Identification of faults prior CAT failure
Efficient Proactive
Maintenance On-Condition
Enhanced Safety &
Maintainability
Safety Benefits Maintainability Benefits
13
CESA Electromechanical Actuator
prototype with antijamming system for
RESEARCH
HUMS
• Health Usage Monitoring strategy for EMA
7
Measurement of Efficiency
• Development and endurance test data recorded to get an “Ideal Efficiency” curve implemented in Control System
• Simulation of degradations: loss of grease, overload in bearings, dust in ballscrew
• Frequency spectrum
Life estimation
• Comparison of health monitoring with “Ideal Curve”
Health Monitoring from Sensors
• Load, current, temperature, etc.
Cycle counter with variables record
• Histogram of performance recorded in each operation
14
• HUMS implementation in SECU
Health Monitoring
• Load
• Motor Current
• Temperature
• Vibration
• Position
Test correlations / mathematical algorithms
Prognosis Remaining Useful Life Prediction
15
HUMS 7
www.cesa.aero
Thanks for your attention!
16