In addition to the development of the flight control laws, we offer the design of safety-critical flight control systems. This primarily covers the software development process, which complies with:
The guidelines for the development of civil aircraft and systems (SAE ARP4754A),
Software considerations in airborne systems and equipment (RTCA DO-178C), and
Model-based development and verification supplement to RTCA DO-178C and DO-278 (RTCA DO-331).
We address the whole development cycle for safety-critical software to be used in embedded systems, which are certifiable according to current EASA regulations (including RTCA DO-178C). In addition to the actual flight control laws and the model-based software development, we also provide all documents required for certification. Among others, these comprise:
Plan of Software Aspects of Certification,
Software Development Plan,
Software Verification Plan,
Software Configuration Management Plan, and
Software Quality Assurance Plan.
The verification consists of highly accurate non-linear flight simulations. They are used for flight
control law design, as well as for Software-in-the-Loop (SiL) and Hardware-in-the-Loop (HiL)
testing. In case of small-unmanned aircraft, we are using our in-house hardware for implementation of the flight control system software and as interface for sensors and actuators. For optionally piloted aircraft, we use third-party hardware.
The applied process chain ensures traceability between source code and object code up to Design Assurance Level A.
Our solutions address the Key Risk Areas identified by EASA, in particular, reducing the risks of:
A. Aircraft Upset,
B. System Failure, and
C. Third-Party Conflict.
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