The Skeldar UCS takes this division even further by having a system design that guarantees the integrity of the information and commands sent to and from the UCS.
A Flight Safety Critical (FSC) Computer containing the VSM, implemented to Design Assurance Level DO-178B, DAL C (or higher if specified), controls all flight-critical information and controls which information and commands are sent to and from the UCS.
To ensure flight safety of the UAS, the Flight Safety Critical Computer is redundant. The CUCS software is installed onto a Mission Computer, connected to the FSC Computer, and is responsible for handling the mission and payload control, i.e. all non-flight-critical information and controls.
Due to the separated design of flight-critical and non-flight-critical information and control, the CUCS only requires Design Assurance Level DO-178B, DAL D. The Mission Computer could be a stand-alone computer or part of an existing computer network, e.g. a C4I-system.
Given this relationship between the FSC and Mission Computer, the system design is not only compliant with the NATO STANAG 4586, it also ensures the integrity of the information and commands, while being adaptable to different configurations (installations), types of air vehicle and payloads.