Aircraft Engineering
Design and control of a Converted Three to Two Redundant Hydraulic System Military Aircraft. Use cranfield (NLM) citation style from mendeley.
Below short description available, samples are attached to be used for outlines etc. Emphasize on custom drawings, schematics and safety assessment sections will be appreciated.
The aim of this project is to design a converted three to two redundant hydraulic system of a military aircraft. The Hydraulic Power Generation and
Power Distribution System provides a 3000 psi hydraulic supply to power the aircraft’s Flight Controls, Landing Gear and Bomb Bay Doors’ actuation
systems. The System provides data for the flight deck displays and the necessary functions to control, monitor and maintain the system:
The Hydraulic System comprises three main segregated systems coded Blue, Green and Yellow, and an Emergency Sub-System located in the Blue
System. Hydraulic power is supplied from four Engine Driven Pumps (EDP’s), three AC electric motor Pumps and one DC electric motor Pump and one
PTU. Normally, two EDP’s are controlled by the USMS, but all four EDP’s can be selected OFF from the Control Panel. The Blue AC Pumps are
controlled by the USMS when the switch is selected to the AUTO position, the YLW AC pump is controlled by the USMS when selected to STBY, but
both can also be switched manually to ON and OFF. The DC pump is controlled manually by its selector switch only. The PTU is normally controlled by
the USMS when its switch is selected to AUTO, but can also be manually switched ON or OFF.
Removal of Yellow system and allocate its functions to the Blue and Green system is the aim of this project which causes weight and cost advantage.
The work includes:
– Study of conventional hydraulic system
– Design of Two redundant system
– Advantages and challenges of new system: safety, cost, complexity, weight