eVTOL Flight Control Reversion Using Analog Backup Signals
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Solution Overview
Problem
Vertical take-off and landing (VTOL) aircraft lack the capability for flight control reversion, which is essential for ensuring pilot control in case of digital data communication malfunctions between pilot controls and flight controllers, posing a significant safety risk.
Innovation Solution
A system and method for reversionary flight control in eVTOL aircraft, featuring redundant flight controllers and sensors that convert analog control data from pilot interactions into digital signals, allowing for primary and reversionary command data transmission to actuators, ensuring continuous control even if digital data communication fails.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Extent of automation
If fly-by-wire flight control systems are used in eVTOL aircraft, then automation and control precision are improved, but the ability to revert to manual control in case of malfunction is lost
Solution Approach 1:
The patent implements preliminary action by maintaining a standby analog flight control system that is pre-configured and ready to take over immediately upon detection of digital system failure. The analog system includes pre-positioned control linkages and pre-calibrated actuators that can assume control without requiring complex reconfiguration during emergency conditions.
Solution Approach 2:
The patent employs an intermediary mechanism in the form of a control system that can operate in two modes: normal digital fly-by-wire operation and reversionary analog operation. This intermediary control architecture includes switching mechanisms and dual-path signal processing that allows seamless transition between automated and manual control modes, mediating between the conflicting requirements of automation and reversion capability.
2Measurement precision
If digital control signals are used for flight control, then control precision and data processing capability are improved, but vulnerability to communication malfunctions increases
Solution Approach 1:
The patent applies beforehand cushioning by implementing a redundant analog control pathway that serves as a protective buffer against digital communication failures. This cushioning mechanism ensures that if digital signals are disrupted by electromagnetic interference, software errors, or communication bus failures, the aircraft maintains control capability through the analog system, preventing complete loss of control.
Solution Approach 2:
The patent utilizes parameter changes by transitioning the control signal type from digital to analog upon detection of communication malfunctions. This parameter change involves converting control commands from discrete digital values to continuous analog voltages, fundamentally altering the signal characteristics to bypass digital communication vulnerabilities while maintaining control authority.
3Reliability
If redundant flight controllers are implemented, then system reliability is improved, but device complexity increases
Solution Approach 1:
The patent applies segmentation by dividing the flight control system into distinct functional segments: a primary digital flight control computer for normal operation and a secondary analog flight control system for reversionary operation. This segmentation allows each subsystem to be independently designed, tested, and maintained with optimized complexity appropriate to its function, reducing overall system complexity while maintaining reliability.
Data Source
AI summary
Aspects relate to methods and systems for reversionary flight control for an electrical vertical take-off and landing (eVTOL) aircraft. An exemplary system includes a pilot control, a sensor configured to sense and transmit analog control data associated with a pilot interaction with the pilot control, a pilot interface module configured to receive the analog control data, convert the analog control data to digital control data, and transmit digital control, an actuator, and a flight controller. The flight controller may be configured to receive the digital control data, determine a primary command datum as a function of the digital control data, transmit the primary command datum to the actuator, determine that the digital control signal is non-functional, receive the analog control data, determine a reversionary command datum as a function of the analog control data, and transmit the reversionary command datum to the actuator.