Systems and methods for temperature control

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Solution Overview

Problem

Current spacecraft temperature control systems are inefficient during launch and reentry phases due to inaccessible radiators and high power consumption, and offer limited fine-tuning capabilities for crew cabin temperature.

Innovation Solution

A temperature control system incorporating a sublimator as an active heat sink, outer mold line radiators, and a ground-based heat exchanger to cool the crew cabin, with radiator bypass valves and leakage prevention valves to manage coolant flow and maintain cabin temperature during various flight phases.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If radiators are used to cool the crew cabin, then cooling efficiency is improved, but the system becomes inaccessible during launch and reentry phases

Engineering Contradiction:

Improvecrew cabin temperature controlVSAvoidradiator accessibility

Core Design Contradiction:

TemperatureVSEase of operation

Solution Approach 1:

The patent employs a sublimator that utilizes phase change of water (from liquid to gas) to provide cooling during launch and reentry phases when radiators are inaccessible. This parameter change from passive radiator-based cooling to active sublimation-based cooling enables temperature control across all flight phases.

Inventive Principle:

Principle #35Parameter changes

Solution Approach 2:

The system dynamically switches between different cooling methods based on flight phase: using radiators during orbital phases and sublimator during launch/reentry phases. This dynamic adaptation ensures continuous cooling capability throughout the mission.

Inventive Principle:

Principle #15Dynamics

2Temperature

If traditional coolant circulation systems are used, then temperature control is achieved, but power consumption increases

Engineering Contradiction:

Improvecrew cabin temperature controlVSAvoidpower consumption

Core Design Contradiction:

TemperatureVSUse of energy by moving object

Solution Approach 1:

The sublimator system uses the phase change of water from liquid to gas, which absorbs heat automatically without requiring external power input for active cooling. This self-service mechanism reduces power consumption compared to traditional electrically-driven coolant circulation systems.

Inventive Principle:

Principle #25Self-service

Solution Approach 2:

The patent utilizes the phase transition of water (sublimation from solid/liquid to gas) as the primary cooling mechanism during critical flight phases. This phase change process provides passive cooling that does not require additional power input, thereby reducing overall system power consumption.

Inventive Principle:

Principle #36Phase transitions

3Temperature

If radiators are installed on the spacecraft, then cooling capability is improved, but the system requires protection during ascent

Engineering Contradiction:

Improvecooling capabilityVSAvoidradiator protection requirements

Core Design Contradiction:

TemperatureVSDevice complexity

Solution Approach 1:

The patent extracts the vulnerability of radiators during ascent by using a different cooling mechanism (sublimator) that is inherently protected or can be positioned to withstand launch loads. This eliminates the need for complex protection systems for radiators during the ascent phase.

Inventive Principle:

Principle #2Taking out (Extraction)

4Temperature

If more coolant is carried onboard, then cooling effectiveness is improved, but spacecraft weight increases

Engineering Contradiction:

Improvecooling effectivenessVSAvoidspacecraft weight

Core Design Contradiction:

TemperatureVSWeight of moving object

Solution Approach 1:

The sublimator system uses water stored in a frozen or liquid state that sublimates to provide cooling. This phase change mechanism allows the system to carry less coolant mass while maintaining cooling effectiveness, as the phase transition provides additional cooling capacity without proportional weight increase.

Inventive Principle:

Principle #36Phase transitions

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 system ensures crew comfort by efficiently managing temperature fluctuations during all flight phases, reduces resource consumption, and minimizes the need for bulky cooling systems, while also reducing spacecraft weight and energy usage.

Implementation Method 1

a sublimator configured to cool the coolant

Methodology Applied

Scientific EffectSublimation: Sublimation

Implementation Method 2

a heat exchanger configured to cool air within a pressurized enclosed crew cabin when the air is circulated across the heat exchanger and coolant is circulated through the heat exchanger

Methodology Applied

Scientific EffectHeat exchange: Heat Exchanger

Implementation Method 3

at least one radiator configured to cool the coolant, where the sublimator is configured to cool the coolant during a first stage of flight, and where the at least one radiator is configured to cool the coolant during a second stage of flight

Methodology Applied

Scientific EffectThermal radiation: Thermal Radiation

Data Source

PatentUS10967992B2Systems and methods for temperature control

Publication Date: 2021.04.06 THE BOEING CO

AI summary

A temperature control system may include a heat exchanger configured to cool air within a pressurized enclosed crew cabin when the air is circulated across the heat exchanger and coolant is circulated through the heat exchanger. The system may further include a sublimator configured to cool the coolant. The system may also include a primary coolant line configured to transport the coolant from the sublimator through the heat exchanger.