Simulation Research in Fault Diagnosis of Environmental Control System for Fighter Aircraft

2009 ◽  
Author(s):  
Shi-Quan Lin ◽  
Jing-Quan Zhao
Keyword(s):  
Control System ◽  
Fault Diagnosis ◽  
Environmental Control ◽  
Fighter Aircraft ◽  
Simulation Research

Health Assessment and Fault Diagnosis for the Heat Exchanger of the Aircraft Environmental Control System Based on STF-LR

2015 ◽  
Vol 764-765 ◽  
pp. 294-299
Author(s):  
Jian Ma ◽  
Chen Lu ◽  
Hong Mei Liu
Keyword(s):  
Control System ◽  
Heat Exchanger ◽  
Fault Diagnosis ◽  
Environmental Control ◽  
Fault Simulation ◽  
Health Assessment ◽  
Estimation Methods ◽  
Root Cause ◽  
Degradation Data ◽  
Parameter Estimation Methods

The aircraft environmental control system (ECS) is a critical aircraft system that provides the appropriate environmental conditions to ensure the safe transport of air passengers and equipment. The functionality and reliability of ECS have elicited an increasing amount of attention in recent years. The heat exchanger is a particularly significant component of ECS because its failure reduces the system’s efficiency and can lead to catastrophic consequences. Health assessment and fault diagnosis for the heat exchanger are necessary to perform maintenance and prevent risks in a timely manner. This paper presents fault-related parameter estimation methods based on strong tracking filter (STF) and logistic regression (LR) algorithm for heat exchanger health assessment and root cause classification, respectively. Heat exchanger fault simulation is conducted to generate performance degradation data, through which the proposed methods are validated. Results demonstrate that the proposed methods are capable of providing stable, effective, and accurate heat exchanger health assessment and root cause classification.

System-Level Fault Diagnosis with Application to the Environmental Control System of an Aircraft

2015 ◽  
Author(s):  
James Hare ◽  
Shalabh Gupta ◽  
Nayeff Najjar ◽  
Paul D'Orlando ◽  
Rhonda Walthall
Keyword(s):  
Control System ◽  
Fault Diagnosis ◽  
Environmental Control ◽  
System Level

Computational Analysis and Characterization of Cockpit Environmental Control System of a Fighter Aircraft in Humid Environment

2014 ◽  
Vol 629 ◽  
pp. 263-269 ◽  
Author(s):  
Muhammad Ayaz ◽  
J. Masud
Keyword(s):  
Control System ◽  
Computational Analysis ◽  
Environmental Control ◽  
Great Flexibility ◽  
Fighter Aircraft ◽  
Efficient Operation ◽  
Analysis Techniques ◽  
Humid Environment ◽  
Computational Fluid Dynamics Cfd

he Environmental Control System (ECS) is an important part of any fighter aircraft and has far reaching repercussions in terms of its capability to operate as an effective weapon system under adverse weatherconditions. The aircrew and majority of electronics depend on ECS to keep temperature, pressure and humidity levels within acceptable limits for efficient operation. These limits are explicitly defined in relevant MIL standards MIL-E-18927E(AS)[1]. In order to thoroughly analyze the ECS of under study aircraft[2, 3], Computational Fluid Dynamics (CFD) analysis techniques have been used. CFD techniques offer great flexibility since various conditions can be simulated and analyzed results can be used for required improvements in the system.

Bayesian network method for fault diagnosis of civil aircraft environment control system

2019 ◽  
Vol 234 (5) ◽  
pp. 662-674
Author(s):  
Cui Liu ◽  
Jianzhong Sun ◽  
Fangyuan Wang ◽  
Shungang Ning ◽  
Guofan Xu
Keyword(s):  
Control System ◽  
Fault Diagnosis ◽  
Bayesian Network ◽  
Environmental Control ◽  
Fault Isolation ◽  
Commercial Aircraft ◽  
Extraction Technology ◽  
Data Set ◽  
Network Method ◽  
Environment Control

This paper addresses the issues of fault diagnosis of the environmental control system of a certain commercial aircraft model of which the environmental control system has a high failure rate in field and causes many unplanned maintenance events. Because of the complexity and reciprocal compensation mechanism of the environmental control system, it is difficult to carry out fault isolation timely once the failure occurred during aircraft turnaround time, which thus may cause flight delay or even cancelation. The original contribution of this work is to propose a Bayesian network–based fault diagnosis method for commercial aircraft environmental control system where a multi-information fusion mechanism is used to incorporate the system first principle, expert experience and condition monitoring data. It incorporates extraction technology of sensor feature parameters and the structural learning of Bayesian network to realize the effective diagnosis of multiple faults. A case study is conducted based on a data set from a commercial aircraft fleet. The results show that the fault isolation ratio of this method is greater than 89%. The proposed Bayesian fault diagnosis network method can be used as a troubleshooting tool for airline maintenance technicians in fault isolation of environmental control system, reducing the time spent on-line troubleshooting and aircraft downtime.

Knowledge Graph Construction for Fault Diagnosis of Aircraft Environmental Control System

2021 ◽  
Author(s):  
Shutong Zhang ◽  
Yini Zhang ◽  
Yongsheng Yang ◽  
Wei Cheng ◽  
Honghua Zhao ◽  
...  
Keyword(s):  
Control System ◽  
Fault Diagnosis ◽  
Environmental Control ◽  
Knowledge Graph

Environmental Control of an Electronic System Integrated Into a Fighter Aircraft Pod

2004 ◽  
Author(s):  
Michel Engelhardt
Keyword(s):  
Control System ◽  
Environmental Control ◽  
Cooling System ◽  
Thermal Analyses ◽  
Thermal Control ◽  
Electronic System ◽  
Analytical Models ◽  
Fighter Aircraft ◽  
Performance Predictions ◽  
Main Components

An Environmental Control System (ECS) concept is developed to control the temperature of an Electronic System (ES) and to cool the airborne system Electronic Units (EUs). These units are integrated into a Pod that is attached to the centerline station of a fighter aircraft. The objective of this paper is to describe the thermal control system concept used to control the ES bay air temperature, humidity, and pressure; and the cooling system used to cool the EUs. Another objective of this paper is to provide a summary of the thermal-fluid analytical models and the ECS performance predictions. The main components of the ECS are based on vapor cycle cooling. The EUs that support system management and recording are air-cooled. Ground operations are accomplished through the autonomous ECS thermal control of the ES and fan cooling of the EUs. Thermal analyses at aircraft operational altitudes and speeds predict that the ES temperature is controlled within ±5°C of its temperature at take-off by the ECS. ES bay temperatures are held between preset lower and upper bound ES temperatures during the required MIL-STD-210A tropical day without condensation of moisture in the ES bay. In addition, thermal analyses indicate that the EUs are cooled throughout ground and airborne operation to ensure that electronic components are below their manufacturers’ rated temperature requirements.

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