Download the datasheet for more information
The SUA is an electro-hydraulic system controlling the connected interface in response to
electrical commands received from its Electronic Control Unit.
The SUA design is based on a configuration consisting of hydraulic and electrical system without
redundancy design philosophy.
The SUA proposed basically consists of three main items integrated as a single LRU system:
– Power Module (PM) to provide the required loads by an unbalanced Hydraulic Actuator.
The PM will be also equipped with a LVDT providing positional feedback and monitoring to the
aircraft system. A further provision consists in a locking device that, when required or in case of
failure, holds the piston in pre-determined positions.
– Control Module (CM) to provide electrical selection by dedicated solenoid selector valves and
servo valve to operate hydraulically the PM in a closed loop position control through a dedicated
Electrical Control Unit.
The CM is flange mounted on the PM by means of screws fitted in dedicated bosses.
The PM hydraulic ports (i.e. extension and retraction) are directly rooted to the CM manifold by
connecting hydraulic joints.
– Electronic Control Unit (ECU) that receives the external command (position target) and manage
the system actuation. It also implement monitoring functionalities in order to detect system health
status and system failures.