Autonomy Computer Fail-Safe Flight Control Without Redundant FCCs

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Solution Overview

Problem

Traditional redundant flight control systems for autonomous vehicles, particularly in smaller systems like drones, incur significant weight, cost, and power consumption due to the need for multiple sets of hardware, which is prohibitive and increases sustainment costs.

Innovation Solution

A flight control system that utilizes a second computer, typically an autonomy computer, to provide non-primary flight control functions as a backup, monitoring the primary flight control computer for failures and taking over critical flight functions in a fail-safe mode, thereby reducing the need for redundant hardware.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If traditional redundant flight control systems are implemented, then system reliability is improved, but weight, cost, and power consumption increase significantly

Engineering Contradiction:

Improvesystem reliabilityVSAvoidsystem weight

Core Design Contradiction:

ReliabilityVSWeight of moving object

Solution Approach 1:

The autonomy computer is designed to perform dual functions: it serves as the primary autonomy computer for high-level control tasks during normal operation, and simultaneously acts as a backup flight control computer that can take over critical flight functions when the primary FCC fails. This multi-functionality eliminates the need for dedicated redundant hardware while maintaining reliability.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Reliability

If traditional redundant flight control systems are implemented, then system reliability is improved, but cost increases significantly

Engineering Contradiction:

Improvesystem reliabilityVSAvoidmanufacturing cost

Core Design Contradiction:

ReliabilityVSEase of manufacture

Solution Approach 1:

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Reliability

If traditional redundant flight control systems are implemented, then system reliability is improved, but power consumption increases

Engineering Contradiction:

Improvesystem reliabilityVSAvoidpower consumption

Core Design Contradiction:

ReliabilityVSUse of energy by moving object

Solution Approach 1:

Inventive Principle:

Principle #6Universality (Multi-functionality)

4Reliability

If a second FCC is used as standby, then system reliability is improved, but weight and cost double

Engineering Contradiction:

Improvesystem reliabilityVSAvoidFCC system weight

Core Design Contradiction:

ReliabilityVSWeight of moving object

Solution Approach 1:

Inventive Principle:

Principle #6Universality (Multi-functionality)

Data Source

PatentUS12422866B2Fault tolerant flight control architecture

Publication Date: 2025.09.23 TEXTRON INNOVATIONS INC

AI summary

A flight control system, including a flight control computer (FCC) configured for providing a first and second flight function, and sending, to effectors of an aircraft, first command signals based on the first and second flight functions, and a second computer configured for providing one or more autonomy functions associated with operation of the aircraft, and that are different from the first and second flight functions, monitoring operation of the FCC, determining whether the FCC has failed, and providing a fail-safe mode for at least the first flight function in response to determining that the FCC has failed. Providing the fail-safe mode includes providing one or more critical flight functions that includes the first flight function, and sending, to the effectors, second command signals that replace a first command signal associated with the first flight function and that are based on the critical flight functions.