Thermal Tomography for Propellant Distribution Control

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Conventional methods for propellant gauging in spacecraft, such as dead reckoning and thermal propellant gauging techniques, fail to provide accurate propellant level measurements throughout the on-orbit lifetime, often resulting in inaccuracies of ±10% or more, which can impact mission duration and efficiency.

Innovation Solution

A system utilizing thermal tomography elements with temperature-control elements and sensors around the propellant tank to detect and redistribute propellant by heating or cooling, allowing for precise determination and management of propellant distribution, including the use of tomography data analysis to achieve desired distribution patterns.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Measurement precision

If conventional dead reckoning or thermal propellant gauging techniques are used, then the system is simple to operate, but propellant level measurement accuracy deteriorates to ±10% or more

Engineering Contradiction:

Improvepropellant level measurement accuracyVSAvoidgauging system complexity

Core Design Contradiction:

Measurement precisionVSDevice complexity

Solution Approach 1:

The patent replaces conventional mechanical or simple thermal gauging methods with thermal tomography technology. Multiple temperature sensors arranged in arrays around the propellant tank create detailed thermal maps, allowing precise 3D reconstruction of propellant distribution and level measurement with accuracy significantly better than ±10%, transforming a simple measurement task into a sophisticated thermal imaging system.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The patent introduces thermal fields as an intermediary between the propellant and measurement system. By heating or cooling specific regions of the propellant tank and measuring the resulting thermal responses with multiple sensors, the system indirectly maps propellant distribution and level, using thermal energy as a mediator to achieve high-precision measurement.

Inventive Principle:

Principle #24Intermediary (Mediator)

2Measurement precision

If thermal tomography elements with temperature-control elements are used to redistribute propellant, then propellant distribution precision is improved, but energy consumption increases

Engineering Contradiction:

Improvepropellant distribution precisionVSAvoidenergy consumption for propellant redistribution

Core Design Contradiction:

Measurement precisionVSUse of energy by moving object

Solution Approach 1:

The patent applies local quality by using multiple independent temperature-control elements positioned at specific locations around the propellant tank. Each element can be independently controlled to heat or cool local regions, enabling precise redistribution of propellant to desired locations with minimal overall energy consumption, rather than heating or cooling the entire tank uniformly.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The patent changes thermal parameters (temperature distribution) in specific regions of the propellant tank to control propellant movement. By locally adjusting temperature parameters rather than changing global conditions, the system achieves precise propellant redistribution while minimizing energy consumption, exploiting the sensitivity of propellant flow to local thermal gradients.

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

This approach provides accurate propellant level measurements and enables extended mission duration by ensuring precise propellant distribution, enhancing propellant recovery and reducing uncertainties in propellant availability, thereby optimizing spacecraft operations.

Implementation Method 1

controlling the plurality of temperature-control elements to redistribute the propellant inside the propellant tank body by heating and/or cooling the propellant

Methodology Applied

Scientific EffectHeating: Heating

Implementation Method 2

controlling the plurality of temperature-control elements to redistribute the propellant inside the propellant tank body by heating and/or cooling the propellant

Methodology Applied

Scientific EffectCooling: Cooling

Implementation Method 3

a plurality of thermal tomography elements, including a plurality of temperature-control elements and a plurality of temperature sensors, disposed around the body for detecting the distribution of the propellant inside the body

Methodology Applied

Scientific EffectTemperature detection: Thermography

Data Source

PatentUS10189584B2Controlling a propellant distribution in a spacecraft propellant tank

Publication Date: 2019.01.29 AIRBUS DEFENCE AND SPACE LTD

AI summary

A system for controlling a distribution of propellant in a propellant tank assembly for a spacecraft comprises a body for containing the propellant, a plurality of thermal tomography elements, including a plurality of temperature-control elements and a plurality of temperature sensors, disposed around the body for detecting the distribution of the propellant inside the body; and a tomography element control module arranged to control the plurality of temperature-control elements to redistribute the propellant inside the propellant tank body by heating and/or cooling the propellant. In an embodiment, the propellant tank body includes a propellant management device inside the body and the tomography elements are disposed in proximity to the propellant management device. Tomography data can be obtained from the plurality of tomography elements, and a distribution of propellant within the propellant tank body can be determined based on the obtained tomography data.