Development of a full scale experimental and simulation tool for environmental control system optimisation and fault detection

This paper documents the installation of a fast jet military aircraft Environmental Control System (ECS) ground test facility. The system used in this case is a bleed-air driven two-wheel bootstrap cycle with low pressure water extraction. The facility allows the ECS to be run at conditions similar to those in the aircraft during ground operation. Data from the rig is presented and used to validate a 1-D thermodynamic model. The relationships between aircraft altitude and speed against ECS Coefficient of Performance and system heat rejection are presented, seamlessly utilising both experimental and modelled data. Furthermore, a scenario depicting a ram air blockage in the secondary heat exchanger demonstrates the system’s ability to mask faults. The physical system is used for component-level analysis, whilst the model extends this to system-level. General attributes of the system operation are discussed.