Li-ion Battery Thermal Runaway De-orbiting

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Solution Overview

Problem

Small satellites lack independent de-orbit capabilities, leading to prolonged orbital lifetimes and increased risk of space debris due to passive de-orbiting through atmospheric drag, and there is a risk of battery explosions generating additional debris.

Innovation Solution

Utilizing Li-ion batteries by inducing a thermal runaway to release stored electrochemical energy as thrust, directing the hot gases through a nozzle for de-orbiting, which also passivates the batteries and reduces debris risk.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Loss of time

If small satellites rely on passive atmospheric drag for de-orbiting, then no additional propulsion mass is required, but the de-orbiting time extends to decades and creates space debris

Engineering Contradiction:

Improvede-orbiting timeVSAvoidpropulsion system complexity

Core Design Contradiction:

Loss of timeVSDevice complexity

Solution Approach 1:

The Li-ion battery serves dual functions: providing electrical power during satellite operation and generating thrust for de-orbiting at end-of-life. By utilizing the battery's stored chemical energy and venting hot gases through a nozzle, the same component becomes a propulsion device, eliminating the need for separate propulsion systems while dramatically reducing de-orbiting time from decades to days or hours

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The patent converts the potentially harmful thermal runaway event, which would normally be a safety risk causing battery explosion and debris, into a beneficial thrust generation mechanism. By intentionally triggering controlled thermal runaway and directing the resulting hot gas expansion through a nozzle, the harmful energy release becomes a useful propulsive force for rapid de-orbiting

Inventive Principle:

Principle #22Blessing in disguise (Convert harm into benefit)

2Loss of time

If small satellites carry dedicated propulsion systems for active de-orbiting, then de-orbiting time is reduced to days or hours, but satellite mass and complexity increase

Engineering Contradiction:

Improvede-orbiting timeVSAvoidsatellite mass

Core Design Contradiction:

Loss of timeVSWeight of moving object

Solution Approach 1:

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The patent merges the electrical power system and propulsion system into a single integrated Li-ion battery unit. The battery's chemical energy storage and gas venting mechanisms are combined with a simple nozzle structure to create a unified de-orbiting system, eliminating the need for separate fuel tanks, engines, and control systems that would add significant mass

Inventive Principle:

Principle #5Merging (Combining)

3Productivity

If Li-ion batteries are triggered into thermal runaway for thrust generation, then de-orbiting capability is achieved, but battery safety risks increase

Engineering Contradiction:

Improvede-orbiting capabilityVSAvoidbattery safety

Core Design Contradiction:

ProductivityVSReliability

Solution Approach 1:

The satellite performs collision avoidance maneuvers during its operational lifetime by utilizing controlled thermal runaway of the Li-ion battery to generate thrust. This preliminary use of the battery's thermal energy for active maneuvering prevents future collision risks, and the battery is subsequently passivated at end-of-life, eliminating the safety risk of uncontrolled thermal runaway later

Inventive Principle:

Principle #10Preliminary action

Solution Approach 2:

The satellite actively uses the battery's thermal runaway capability for collision avoidance maneuvers before de-orbiting, thereby preventing potential collisions that would create debris. This preliminary anti-action neutralizes the future safety risk by utilizing the battery's energy before passivation, transforming a potential hazard into a protective measure

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 method enables faster de-orbiting of small satellites, reduces orbital lifetime, and eliminates the risk of battery explosions, effectively managing space debris and collision avoidance.

Implementation Method 1

triggering a thermal runaway of each of the one or more Li-ion batteries. The thermal runaway causes the one or more Li-ion batteries to release stored electrochemical energy

Methodology Applied

Scientific EffectThermal runaway: Exothermic Reaction

Implementation Method 2

one or more heaters surrounding each of the one or more Li-ion batteries configured to send each of the one or more Li-ion batteries into a thermal runaway

Methodology Applied

Scientific EffectConductive heating: Conduction (thermal)

Implementation Method 3

releasing, by a vent for each of the one or more Li-ion batteries, hot gasses into a thruster or expansion chamber for de-orbiting of the space vehicle

Methodology Applied

Scientific EffectPressure gradient flow: Pressure Gradient

Data Source

PatentUS11713140B2Lithium ion battery de-orbiter

Publication Date: 2023.08.01 AEROSPACE CORP

AI summary

A de-orbiting system for a space vehicle may include one or more lithium ion (Li-ion) batteries configured to release hot gases to be used for thrusting during de-orbiting of the apparatus. The system may also include one or more heaters surrounding each of the one or more Li-ion batteries, which are configured to send each of the one or more Li-ion batteries into a thermal runaway. The thermal runaway causes the one or more Li-ion batteries to release stored electrochemical energy within each of the one or more Li-ion batteries.