Distributed Aircraft Control Using Supplemental Attitude Switching

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Solution Overview

Problem

Aircraft are prone to drift due to wind or sensor noise, making them difficult to control, and modern fly-by-wire systems are vulnerable to single-point failures, necessitating a robust and failure-resistant control system.

Innovation Solution

A distributed control system with supplemental attitude adjustment, where aircraft components receive commands from sensors and generate response commands based on engagement data, combining aircraft attitude with supplemental attitudes to counteract drift, using either position or velocity-based adjustments depending on the engagement state.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If a traditional fly-by-wire system is used to control the aircraft, then the control response is direct and simple, but the system is vulnerable to single-point failures and cannot compensate for drift effectively

Engineering Contradiction:

Improvesystem failure resistanceVSAvoidcontrol system structure

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The control system is divided into multiple independent aircraft components (first aircraft component, second aircraft component, etc.), each capable of receiving commands and generating response commands independently. This segmentation eliminates single-point failures as each component can operate autonomously if others fail.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The system dynamically changes control parameters by selecting different supplemental attitude types (position-based or velocity-based) depending on the engagement state of the aircraft control. When the control is engaged, velocity supplemental attitude is used; when disengaged, position supplemental attitude is used, optimizing both reliability and responsiveness.

Inventive Principle:

Principle #35Parameter changes

2Measurement precision

If no supplemental attitude adjustment is applied, then the control system is simple, but the aircraft drifts due to wind or sensor noise making it difficult to control

Engineering Contradiction:

Improvecontrol precisionVSAvoidcontrol system structure

Core Design Contradiction:

Measurement precisionVSDevice complexity

Solution Approach 1:

The system continuously monitors the engagement state of the aircraft control and the drift conditions, then generates appropriate supplemental attitude commands to counteract drift. The feedback loop adjusts the aggregate attitude by combining aircraft attitude with supplemental attitude based on real-time conditions.

Inventive Principle:

Principle #23Feedback

Solution Approach 2:

The supplemental attitude acts as an intermediary between the pilot's control inputs and the actual aircraft response. It provides an additional layer of control that counteracts drift without interfering with the pilot's direct commands, improving precision without adding complex mechanical structures.

Inventive Principle:

Principle #24Intermediary (Mediator)

3Stability of the object's composition

If position supplemental attitude is used when control is disengaged, then the aircraft can maintain stable position, but the response to pilot input may be delayed

Engineering Contradiction:

Improveaircraft position stabilityVSAvoidcontrol response speed

Core Design Contradiction:

Stability of the object's compositionVSSpeed

Solution Approach 1:

The system dynamically switches between position supplemental attitude and velocity supplemental attitude based on the engagement state. When the control is disengaged, position supplemental attitude maintains stability; when engaged, velocity supplemental attitude provides faster response, creating a dynamic adaptation to operational conditions.

Inventive Principle:

Principle #15Dynamics

4Speed

If velocity supplemental attitude is used when control is engaged, then the aircraft responds quickly to pilot input, but position stability may be reduced during disengaged states

Engineering Contradiction:

Improvecontrol response speedVSAvoidaircraft position stability

Core Design Contradiction:

SpeedVSStability of the object's composition

Solution Approach 1:

The system adapts its control mode dynamically based on engagement state. Velocity supplemental attitude provides rapid response when the pilot is actively controlling, while position supplemental attitude maintains stability when the control is disengaged, optimizing both speed and stability across different operational phases.

Inventive Principle:

Principle #15Dynamics

Data Source

PatentUS11467606B1Methods and systems for a distributed control system with supplemental attitude adjustment

Publication Date: 2022.10.11 BETA AIR LLC

AI summary

A distributed control system with supplemental attitude adjustment including an aircraft control having an engaged state and a disengaged state. The system also including a plurality of flight components and a plurality of aircraft components communicatively connected to the plurality of flight components, wherein each aircraft component is configured to receive an aircraft command and generate a response command directing the flight components as a function of supplemental attitude. The supplemental attitude based at least in part on the engagement datum and generating a supplemental attitude includes choosing a position supplemental attitude if the aircraft control is disengaged and choosing a velocity supplemental attitude if the aircraft control is engaged. In generating the response command, the aircraft attitude is combined with the supplemental attitude to obtain an aggregate attitude, and the aircraft component is configured to generate the response command based on the aggregate attitude.