Fly-by-wire Control Law Adaptation via Delta Actuator Command
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Solution Overview
Problem
Conventional Fly-by-wire (FBW) systems require extensive time and effort to modify qualified control law architectures after FAA verification and certification, and subsequent changes to aircraft structure affecting flight performance necessitate lengthy recertification processes.
Innovation Solution
A portable unqualified computer interfaces with the FBW system to make real-time adjustments to control laws within preapproved FAA limits, allowing fine-tuning without violating DO-178B Level A requirements by creating a Delta Actuator Command that modifies the control laws within a predetermined percentage of the control demand range.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional FBW control law architecture is modified after FAA verification and certification, then flight performance can be optimized, but extensive time and effort is required for recertification
Solution Approach 1:
The patent segments the control law architecture into a certified base layer and a modifiable adaptive layer. The adaptive control law module can be modified and tuned without affecting the certified core architecture, allowing performance optimization while maintaining certification compliance. This segmentation enables independent modification of non-critical components.
Solution Approach 2:
The patent introduces an intermediary adaptive control law module that sits between the certified control architecture and the flight control actuators. This intermediary layer can be adjusted for performance optimization while the underlying certified architecture remains unchanged, avoiding the need for full recertification.
2Adaptability or versatility
If control laws are adjusted after aircraft structure changes, then optimal flight performance is achieved, but lengthy recertification process is required
Solution Approach 1:
The patent implements a dynamic adaptive control law module that can be reconfigured in response to aircraft structure changes. This dynamic module allows real-time or near-real-time adaptation to structural modifications without requiring static recertification processes, enabling the control system to evolve with the aircraft configuration.
Solution Approach 2:
The patent utilizes parameter changes within pre-approved ranges to adapt control laws after structural modifications. By adjusting control parameters within certified boundaries rather than changing the core control architecture, the system achieves adaptability while maintaining certification compliance without lengthy recertification.
3Productivity
If qualified control law architecture is changed, then flight performance improves, but FAA approval process becomes more complex
Solution Approach 1:
The patent performs preliminary certification of the base control law architecture with built-in adaptability features. By pre-certifying the adaptive module's ability to operate within specific parameter ranges and architectural boundaries, subsequent performance optimizations fall within pre-approved frameworks, reducing certification complexity for future modifications.
Data Source
AI summary
A system and method to modify a qualified actuator command with an unqualified actuator command modifier. The method includes creating a modified actuator command as the difference between the qualified actuator command and the unqualified actuator command and thereafter limiting the modified actuator command with an authority limiter. The system includes a qualified computer having an unqualified control law interfaced with an unqualified computer having a qualified control law.