Modeling a Hydraulically Powered Flight Control Actuation System
Abstract
:Featured Application
Abstract
1. Introduction
- The development of a model to provide sufficient data on hydraulically powered flight control actuation systems using an SOS approach targeting the subsystems, not just the components involved. Past attempts at HPFCAS fault findings were based on specific components, like a pump, bearing, and seal of an actuator. Hence, only the data and diagnostics of a specific component out of the many components are analyzed.
- Although other forms of models for diagnostics have been in the past, they do not consider the effects of the propagated or cascaded faults in a system. They are only good for isolated faults.
- The proposed development of the HPFCAS shows that a complex system can be broken down into subsystem models to obtain the rich data required for fault analysis due to the non-availability of the required data. This helps to analyze faults under different conditions of operation, where symptom vectors of different faults are grouped according to how they affect the subsystems.
2. Literature Review
3. Simulation Model for a Hydraulic Powered FCAS
- i.
- A proposed system block diagram depicting the subsystems.
- ii.
- An experimental block schematic showing how the various components were connected in the IVHM Laboratory.
- iii.
- The identified fault modes, causes, and effects.
- iv.
- The formation of the functional model elements and fault injection schematic.
- v.
- Simulations
3.1. Methodology and System Model Blocks
3.2. FCAS Experimental Process Block Schematic
3.2.1. Identification of Fault Modes, Causes, and Effects
3.2.2. Experiment and Component Connections
3.2.3. Operating Procedure of the Preliminary Experiment
- Before the rig was operated, the operator ensured the following:
- The power supplies were switched on.
- The main tanks were filled to the required quantity of fluid by visually inspecting the tanks for their integrity and that the tanks were intact.
- Two converters, CDAQ-9172 devices, were switched on.
- The button for the motor drives situated below the emergency button was switched on.
- The PC was switched on and LabVIEW launched (this allows the Modified Fuel Rig System file in the Fuel Rig system project folder to be created):
- Experiments were run and stopped at intervals of 10s each.
- Readings were taken and saved for healthy cases.
- Then faults were injected for unhealthy scenarios, and the procedures were repeated.
4. Derivation of Boundary Conditions for Steady-State Simulation Model Parameters
Developing Subsystem Models for Fault Injection
5. HPFCAS Model Development and Simulations
5.1. Simulations at Steady State
5.2. Procedures for Actuator Integration with the Model
5.3. Simulations of Model in a Transient State
6. Results and Discussions
6.1. Healthy Cases
6.2. Unhealthy Cases
7. Conclusions
- In the hydraulic system, any single system or component failure, e.g., an actuator, valve, or leakage, is a principal failure mode and can trigger multiple faults.
- Any combination of failures (e.g., dual electrical and hydraulic system failures or any single failure in combination with any probable hydraulic or electrical failure) are principal faults.
- Common-mode failures/single failures (e.g., leakage) are principal failure modes that can affect multiple systems.
- In the absence of the required data, the development of suitable models for the HPFCAS for the different performance conditions generated sufficient data that were used to carry out the analysis.
- The data generated were classified and are to be used to train algorithms for diagnostics. It is proposed that this model approach can be completed appropriately for all systems.
8. Future Work and Challenges
Author Contributions
Funding
Institutional Review Board Statement
Informed Consent Statement
Data Availability Statement
Acknowledgments
Conflicts of Interest
Nomenclature
AP | Autopilot |
AC | Alternating Current |
CBM | Condition Based Maintenance |
CND | Can Not Display |
DPV | Directional Proportional Valve |
DC | Direct Current |
ECs | Electrical Components |
FC | Flight Controls |
FCAS | Flight Control Actuation System |
FCS | Flight Control System |
FDI | fault Detection and Isolation |
FF | Fault Found |
FMECA | Failure Modes Effects and Criticality Analysis |
FTA | Fault Tree Analysis |
HCs | Hydraulic Components |
HPFCAS | Hydraulically Powered Flight Control Actuator System |
IVHM | Integrated Vehicle Health Monitoring |
KF | Kalman Filter |
MCs | Mechanical Components |
MFCAS | Mechanical Flight Control Actuation System |
NFF | No Fault Found |
PFCAS | Primary Flight Control Actuation System |
PHM | Prognostics Health Monitoring |
SOS | System of systems |
RPM | Revolution Per Minute |
RUF | Remaining Useful Life |
VAC | Volt Alternating Current |
VDC | Volt Direct Current |
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Failure Modes | Causes of Faults | Effects | Failure Types |
---|---|---|---|
HPFCAS1 | Filter Clogging | Decrease in pressure | Mechanical, Hydraulic |
HPFCAS2 | Pipe Leaking | Decrease in pressure | Mechanical, Hydraulic |
HPFCAS3 | Motor (demagnetization) loss of output to the pump | Decrease in rpm | Mechanical, Electrical |
HPFCAS4 | Low power to the electric pump | Decrease in rpm or no pressure | Electrical |
HPFCAS5 | Clogged nozzle/malfunction (flow control valve NRV) | Decrease or no pressure, damage to the flow line | Mechanical, Hydraulic |
HPFCAS6 | Low power to the flow control valve (Solenoid valve) | No pressure, damage to the flow lines | Electrical, Hydraulic |
HPFCAS7 | Temperature rise (windings, heat) | More power required, pressure decrease | Thermal, Mechanical, Electrical |
HPFCAS8 | Vibrations (electrical connections, position sensor measurements) | Actuator components, electrical cables, | Electrical, sensors |
Inputs | Initial Boundary Conditions | Descriptions |
i (Pressure values) | P1 and P4 | both atmospheric |
ii (Rpm settings) | 400 | RPM of pump |
iii (DPV opening) | 100% | RPM of pump |
Iv (Pressure values) | P2 and P3 | Unknowns |
Process | ||
i (Flow rate values) | 0.5 L/min | Guess mass flow |
ii (Pressure values) | P3 | Obtained from DPV curve |
iii (Pressure ratio values) | P3/P2 | Obtained from pump curve |
iv (Flow rate values) | Flow | Obtained from Bernoulli using stations 1 and 2 |
v (Flow rate values) | Mass flow | Adjust the flow rate and repeat the process. |
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Iyaghigba, S.D.; Petrunin, I.; Avdelidis, N.P. Modeling a Hydraulically Powered Flight Control Actuation System. Appl. Sci. 2024, 14, 1206. https://doi.org/10.3390/app14031206
Iyaghigba SD, Petrunin I, Avdelidis NP. Modeling a Hydraulically Powered Flight Control Actuation System. Applied Sciences. 2024; 14(3):1206. https://doi.org/10.3390/app14031206
Chicago/Turabian StyleIyaghigba, Samuel David, Ivan Petrunin, and Nicolas P. Avdelidis. 2024. "Modeling a Hydraulically Powered Flight Control Actuation System" Applied Sciences 14, no. 3: 1206. https://doi.org/10.3390/app14031206
APA StyleIyaghigba, S. D., Petrunin, I., & Avdelidis, N. P. (2024). Modeling a Hydraulically Powered Flight Control Actuation System. Applied Sciences, 14(3), 1206. https://doi.org/10.3390/app14031206