Gyroscopic Stabilization via Turbo-Generator Pivot Mount

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Solution Overview

Problem

Hybrid electric VTOL aircraft face challenges in maintaining stability during thrust vector transitions and dynamic maneuvers due to misalignment of the thrust axis with the prime stability axis, leading to destabilizing yaw and roll moments, which can result in catastrophic events.

Innovation Solution

The implementation of a gyroscopic stabilization system using a turbo-generator with a gas turbine engine and electric generator, where the rotation axis and rotational speed can be decoupled from the thrust axis, allowing for adjustment via pivot mounts and rotational speed manipulation to align with the prime stability axis, thereby applying inertial forces to stabilize the aircraft.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Stability of the object's composition

If large control surfaces are used to maintain stability during dynamic maneuvers, then stability of the prime stability axis is improved, but drag on the aircraft increases significantly

Engineering Contradiction:

Improvestability of the prime stability axisVSAvoiddrag

Core Design Contradiction:

Stability of the object's compositionVSObject-affected harmful factors

Solution Approach 1:

The patent replaces traditional mechanical control surfaces (rudder, tail) with a gyroscopic stabilization system using a turbo-generator. The spinning mass of the turbo-generator creates gyroscopic effects that stabilize the prime stability axis during dynamic maneuvers, eliminating the need for large control surfaces and reducing drag significantly.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The patent changes the stabilization mechanism from aerodynamic forces (control surfaces) to rotational inertia forces (gyroscopic effect). By adjusting the rotational speed of the turbo-generator, the system can dynamically control the stabilization moment to maintain prime stability axis stability without increasing drag.

Inventive Principle:

Principle #35Parameter changes

2Adaptability or versatility

If the thrust axis is allowed to misalign with the prime stability axis during thrust vector transitions, then maneuverability is improved, but destabilizing yaw and roll moments occur

Engineering Contradiction:

Improvethrust vector transition capabilityVSAvoidaircraft stability

Core Design Contradiction:

Adaptability or versatilityVSStability of the object's composition

Solution Approach 1:

The patent introduces the turbo-generator as an intermediary stabilization system between the thrust vectoring system and the aircraft structure. During thrust vector transitions, the turbo-generator produces gyroscopic moments that counteract the destabilizing yaw and roll moments caused by thrust axis misalignment, allowing aggressive maneuvers while maintaining stability.

Inventive Principle:

Principle #24Intermediary (Mediator)

Solution Approach 2:

The system applies preliminary counteracting gyroscopic moments through the turbo-generator before destabilizing effects become severe. The control system monitors thrust vector position and preemptively adjusts turbo-generator rotation to generate stabilizing moments that prevent excessive yaw and roll oscillations during transitions.

Inventive Principle:

Principle #9Preliminary anti-action

Applied Scientific Principles

This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.

Function Achieved in This Case

This solution enhances aircraft stability during transitions and aggressive maneuvers, reduces the need for large control surfaces, and minimizes drag, thereby improving aerodynamics and safety.

Implementation Method 1

Hybrid electric aircraft with gyroscopic stabilization control

Methodology Applied

Scientific EffectGyroscopic effect: Gyroscope

Implementation Method 2

applying inertial forces to stabilize the aircraft

Methodology Applied

Scientific EffectInertial forces: Inertia

Data Source

PatentUS11945573B2Hybrid electric aircraft with gyroscopic stabilization control

Publication Date: 2024.04.02 GENERAL ELECTRIC CO

AI summary

A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.