Electric Aircraft Temperature Control Without Engine Bleed Air

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Solution Overview

Problem

Existing aircraft temperature control systems rely on engine bleed air, which is not available in electric and hybrid aircraft, necessitating the development of electrically powered systems that can efficiently provide heating and cooling without engine bleed air.

Innovation Solution

An electric temperature control system comprising a vapor cycle cooling system and an electric heater, controlled by a controller that adjusts operations based on user inputs and sensor feedback to achieve desired temperatures, using PTC heaters and variable displacement compressors to optimize power usage.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If engine bleed air is used for temperature control, then heating and cooling functions are provided, but the system cannot be used in electric and hybrid aircraft without engines

Engineering Contradiction:

Improveapplicability to electric and hybrid aircraftVSAvoidtemperature control functionality

Core Design Contradiction:

Adaptability or versatilityVSReliability

Solution Approach 1:

The patent replaces the mechanical engine bleed air system with an electrically-powered vapor cycle cooling system. The vapor cycle system uses an electric compressor, condenser, expansion device, and evaporator to provide cooling without requiring engine operation, enabling temperature control in electric and hybrid aircraft.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The temperature control system is designed to provide both heating and cooling functions through a unified electrically-powered platform. The system can switch between electric heater for heating and vapor cycle cooling system for cooling, making it universally applicable to different aircraft types including electric, hybrid, and conventional aircraft.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Adaptability or versatility

If electrically-powered cooling system is implemented, then engine bleed air dependency is eliminated, but power consumption increases

Engineering Contradiction:

Improveindependence from engine bleed airVSAvoidelectrical power consumption

Core Design Contradiction:

Adaptability or versatilityVSUse of energy by moving object

Solution Approach 1:

The vapor cycle cooling system incorporates a variable displacement compressor that can adjust its operation based on cooling demand and available electrical power. The system dynamically modulates compressor displacement and refrigerant flow to optimize the balance between cooling performance and power consumption, allowing efficient operation across varying flight conditions.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The system changes operational parameters including refrigerant charge, compressor speed, and condenser air flow to optimize performance. By adjusting these parameters based on ambient conditions and power availability, the system achieves efficient cooling with minimized electrical power consumption.

Inventive Principle:

Principle #35Parameter changes

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

Enables efficient temperature control in unpressurized aircraft by minimizing power consumption and eliminating the need for engine bleed air, ensuring comfortable environments for passengers and cargo.

Implementation Method 1

a vapor cycle cooling system for cooling air

Methodology Applied

Scientific EffectVapor cycle: Phase Change

Implementation Method 2

a vapor cycle cooling system including a compressor, a condenser heat exchanger, a condenser blower, and an evaporator heat exchanger

Methodology Applied

Scientific EffectHeat exchange: Heat Exchanger

Implementation Method 3

an electric heater for heating air

Methodology Applied

Scientific EffectJoule heating: Joule Heating

Data Source

PatentUS12515805B2Electric temperature control system for unpressurized aircraft

Publication Date: 2026.01.06 TEXTRON INNOVATIONS INC

AI summary

An electric temperature control system for unpressurized aircraft and methods for operating are disclosed. The electric temperature control system may be electrically powered and used on all-electric aircraft or hybrid aircraft. The electric temperature control system may comprise a vapor cycle cooling system for cooling air and an electric heater for heating air. The electric heater may be a PTC electric heater with individually-controllable heating elements. Various input devices may be disposed in the aircraft allowing an operator to set a compartment temperature, an air source, and a fan speed. A controller controls operations of the electric temperature control system based on feedback received from a plurality of feedback devices and the operator inputs.