UAV Engine Speed Control via Direct Fueling

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Solution Overview

Problem

Current UAV flight control systems rely on throttle position-based strategies, which provide coarse and indirect control over altitude, introducing inaccuracies due to variations in engine type and performance, limiting fine control and complexity in compensating for these differences.

Innovation Solution

Implementing a method where an engine speed target is set by the flight controller and communicated to the engine control unit, allowing direct control over engine speed through parameters like target altitude and air speed, using closed-loop control to adjust fuelling rate, timing, and ignition timing, independent of throttle position.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of operation

If throttle position based flight control strategy is used, then the flight controller can control engine operation, but the control over altitude becomes coarse and indirect, introducing inaccuracies

Engineering Contradiction:

Improveengine control capabilityVSAvoidaltitude control precision

Core Design Contradiction:

Ease of operationVSMeasurement precision

Solution Approach 1:

The patent changes the control parameter from throttle position to engine speed. The flight controller directly controls engine speed by adjusting fuel injection timing and amount, bypassing the throttle servo mechanism. This parameter change enables fine control over engine operation and direct control over altitude, eliminating the coarse and indirect nature of throttle position based control.

Inventive Principle:

Principle #35Parameter changes

Solution Approach 2:

The patent extracts the flight controller's direct control authority over engine speed from the throttle servo mechanism. By communicating engine speed targets directly to the engine control unit, the flight controller removes the intermediate throttle position step, achieving direct engine speed control and eliminating the inaccuracies introduced by throttle based indirect control.

Inventive Principle:

Principle #2Taking out (Extraction)

2Adaptability or versatility

If throttle position based flight control strategy is used, then the flight controller can adjust engine operation, but it requires accounting for engine type and performance differences, introducing inaccuracies and complexity

Engineering Contradiction:

Improveengine type compatibilityVSAvoidcontrol accuracy

Core Design Contradiction:

Adaptability or versatilityVSMeasurement precision

Solution Approach 1:

The patent changes the control parameter to engine speed, which is directly measurable and controllable by the engine control unit regardless of engine type. This eliminates the need for the flight controller to account for differences in engine type and performance characteristics, as the direct engine speed control parameter is universally applicable across different engine configurations.

Inventive Principle:

Principle #35Parameter changes

Solution Approach 2:

The patent implements a feedback mechanism where the flight controller receives actual engine speed information from the engine control unit and compares it with the target engine speed. This closed-loop feedback enables accurate control adaptation to different engine types without requiring complex pre-programmed compensation for engine variations.

Inventive Principle:

Principle #23Feedback

3Ease of operation

If throttle position based flight control strategy is used, then the flight controller can control engine speed, but the control methodology becomes more complex to compensate for inaccuracies

Engineering Contradiction:

Improveengine speed control capabilityVSAvoidcontrol methodology complexity

Core Design Contradiction:

Ease of operationVSDevice complexity

Solution Approach 1:

The patent extracts the direct engine speed control function from the complex throttle position based control system. By enabling the flight controller to communicate engine speed targets directly to the engine control unit, it removes the need for complex compensation algorithms required to correct inaccuracies in throttle position based control, significantly simplifying the control methodology.

Inventive Principle:

Principle #2Taking out (Extraction)

Solution Approach 2:

The engine control unit serves as an intermediary that receives engine speed targets from the flight controller and automatically manages the complex fuel injection and ignition timing adjustments. This intermediary approach simplifies the flight controller's role while achieving precise engine speed control without complex flight controller algorithms.

Inventive Principle:

Principle #24Intermediary (Mediator)

Data Source

PatentUS9187182B2Method of controlling operation of an unmanned aerial vehicle

Publication Date: 2015.11.17 ORBITAL ENGINE COMPANY (AUSTRALIA) PTY LIMITED

AI summary

This disclosure describes a method of controlling operation of an unmanned aerial vehicle (UAV) having a flight control system comprising: a flight controller for implementing a flight control strategy; and an engine control unit interfaced with the flight controller for controlling engine operation. An engine speed target is set for the flight control system in response to one or more signals communicated by the flight controller to the engine control unit which controls engine operation to achieve the engine speed target by closed loop control over fueling without requiring throttle position control.