Hypersonic Vehicle Power Management Using Plasma Load Control

Solution Overview

Problem

State-of-the-art hypersonic platforms rely on batteries for in-flight power, which become mass and volume prohibitive as flight duration increases due to the increased demand of kW-hrs, necessitating onboard power generation solutions to support longer missions.

Innovation Solution

An onboard power generator in the form of a turbomachine, such as an expansion turbine, is coupled with a primary and auxiliary electrical system. The auxiliary system uses plasma devices to manage shaft speed and dissipate excess electrical power, including plasma actuators and sensors to govern electrical loads, enhancing electrical and aerodynamic performance.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Duration of action of moving object

If batteries are used for in-flight power, then the hypersonic platform can operate, but the mass and volume increase prohibitively as flight duration increases

Engineering Contradiction:

Improveflight durationVSAvoidbattery mass

Core Design Contradiction:

Duration of action of moving objectVSWeight of moving object

Solution Approach 1:

The power system is segmented into multiple components: a turbomachine for primary power generation, a generator for electrical conversion, and a battery system for energy storage and auxiliary power. This segmentation allows each component to be optimized independently, with the turbomachine providing sustained power without requiring proportionally increasing battery mass for longer durations.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The patent replaces the purely chemical energy storage system (batteries) with a mechanical power generation system (turbomachine coupled with generator). The turbomachine converts thermal or mechanical energy directly into electrical energy, eliminating the need for large mass batteries to sustain long-duration flight.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

2Duration of action of moving object

If batteries are used for in-flight power, then the hypersonic platform can operate, but the volume increases prohibitively as flight duration increases

Engineering Contradiction:

Improveflight durationVSAvoidbattery volume

Core Design Contradiction:

Duration of action of moving objectVSVolume of moving object

Solution Approach 1:

The power system is segmented into multiple components: a turbomachine for primary power generation, a generator for electrical conversion, and a battery system for energy storage and auxiliary power. This segmentation allows each component to be optimized independently, with the turbomachine providing sustained power without requiring proportionally increasing battery volume for longer durations.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The patent replaces the purely chemical energy storage system (batteries) with a mechanical power generation system (turbomachine coupled with generator). The turbomachine converts thermal or mechanical energy directly into electrical energy, eliminating the need for large volume batteries to sustain long-duration flight.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

3Productivity

If plasma devices are added to manage shaft speed and dissipate excess power, then electrical system performance is enhanced, but device complexity increases

Engineering Contradiction:

Improveelectrical system performanceVSAvoidsystem complexity

Core Design Contradiction:

ProductivityVSDevice complexity

Solution Approach 1:

The plasma devices serve multiple functions within the power management system: they act as variable electrical loads to control shaft speed, dissipate excess electrical energy, and potentially provide aerodynamic benefits. This multi-functionality justifies the added complexity by delivering multiple performance benefits from a single system integration.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The plasma devices automatically adjust their electrical load characteristics in response to system conditions, providing self-regulating shaft speed control and excess power dissipation without requiring complex external control systems. The plasma generation and termination responds naturally to electrical parameters, providing inherent stability.

Inventive Principle:

Principle #25Self-service

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

The system effectively manages turbomachine shaft speed and boosts electrical system and aerodynamic performance by utilizing plasma devices to stabilize power generation, reducing the mass and volume constraints of batteries.

Implementation Method 1

The auxiliary electrical system utilizes one or more plasma devices such as a plasma actuator or plasma sensor disposed at various locations of the hypersonic vehicle to dissipate excess electrical power generated by the onboard power generator

Methodology Applied

Scientific EffectPlasma: Plasma

Data Source

PatentUS20250250907A1Electrical power management system for a hypersonic vehicle

Publication Date: 2025.08.07 GENERAL ELECTRIC CO

AI summary

An electrical power management system includes a primary electrical system, an auxiliary electrical system including a plasma device, and a turbine generator. The primary electrical system is configured to exert a primary electrical load on the turbine generator, and the auxiliary electrical system is configured to exert a governing electrical load on the turbine generator via the plasma device.