Air Platforms Electrical Power SystemsAERIAL

With its more than 35-year experience in the field of hardware design,  mechanical design, Printed Circuit Board (PCB) design, Environmental Conditions and EMI/EMC tests and production of the Power Distribution and Control Units (PDCU), Control Panels, Interface Units and Display Panels, Savronik has produced about 3000 units of the approximately 90 configurations compliant with MİL-STD-810G, MIL-STD-461F, RTCA/DO-160G and EN61000-4-2 level -3 standards to be integrated onto land, marine and air platforms.

As a part of its capability for the on-board aircraft, unmanned aerial vehicle and helicopter electrical power systems, in accordance with the Military Standards, Savronik designs, tests and produce different systems for different requirements providing, distributing and controlling  electrical power all over the  air vehicle.

The PDCU provides and controls electricity all over the aircraft/helicopter platforms.

The DC PDCU controls the electrical power output according to the exterior data and, through the electromechanic switching components (relays and contactors), distributes the electrical power need to the units connected to it in a protective and controlled way.

The AC PDCU, with FPGA, monitors and controls the electrical power to be used by the air vehicle equipment and distributes the power of 15 VAC-28 VDC in a controlled way through the electromechanic switching components (relays and contactors) and Savronik-designed Solid State Power Controller (SSPC). Critical aircraft hardware is designed in accordance with the Design assurance Level a (DAL_A). The units have the infrastructure compliant with MIL-SDT 1553 and ARINC-429.

The on-board aircraft power systems have the proven and platform-specific designed product lines, both in the field of Primary Power Distribution Unit (PPDU) and Secondary Power Distribution Unit (SPDU).

Power System designs are created in accordance with RTCA/DO-254, Design Assurance Guidance for Airborne Electronic Hardware and MIL-SDT-704, Aircraft Electric Power Characteristics and they are compliant with the qualification requirements of MIL-SDT-810, MIL-SDT-461 and RTCA/DO-160.