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Electric Actuator Control Units
about project
The client, a manufacturer of actuators for aircraft, required a comprehensive safety assessment, the development of plans and standards, requirements engineering, and software verification for control units that manage various aircraft systems. These systems included the wing devices control system, the electric flap control system, the aircraft spoiler electric drive, and the electric drive of an aircraft engine reverse device.
Our role did not involve source code development; instead, we focused on all other aspects, such as safety assessment according to ARP4761, and the development of system requirements in compliance with ARP4754A.
The testing process was particularly complex due to the need to simulate a wide range of analog signals from sensors and motors, as well as to measure PWM parameters accurately. Without a real motor available, we had to simulate responses from analog sensors and measure the outputs and inputs from the control units. The majority of the testing was conducted on a bench, with a small portion involving a real motor.
tasks
Safety Assessment:
Conduct a thorough safety assessment according to ARP4761, ensuring all control units meet the necessary safety standards.
Development of Plans and Standards:
Develop detailed plans and standards in accordance with ARP4754A, ensuring alignment with industry requirements and client expectations.
Requirements Engineering:
Develop system requirements, including high-level and low-level software requirements, ensuring they meet the technical specifications and address the specific challenges of each control unit.
Software Verification:
Verify the client's software to ensure it meets all specified requirements and complies with DO-178C standards for safety-critical software.
Results
Comprehensive Implementation:
Over 3.5 months, we successfully executed the safety assessment, requirements engineering, and software verification processes. These were conducted for each control unit, including the wing devices control system, electric flap control system, aircraft spoiler electric drive, and electric drive of an aircraft engine reverse device.
Successful Transition:
The client successfully transitioned to a new electronic components base and a new product line of motors, with all processes completed to the highest safety standards.
High-Quality Deliverables:
All deliverables, including safety assessments, plans, standards, and verification reports, were completed to ensure compliance with ARP4761, ARP4754A, DO-178C, and DO-254.
process
Project Implementation
Requirement Definition
Initially, the project lacked detailed processes, so we collaborated with the client to define system requirements, high-level, and low-level requirements.
Safety Assessment
We conducted a safety assessment according to ARP4761, identifying potential hazards and ensuring all systems were compliant with safety standards.
Parallel Code Refinement
While we developed and refined the requirements, the client simultaneously updated their code to meet the newly defined specifications.
Software Verification
We performed several iterations of software verification, ensuring the software met DO-178C standards, with the software achieving DAL A certification.
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