Articulable Thruster Support Module Thermal Management

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Existing spacecraft propulsion systems are limited by thermal constraints, allowing only one electric thruster to be fired at a time due to heat management issues, restricting simultaneous operation of multiple thrusters.

Innovation Solution

A propulsion system with an articulable thruster support module that includes a thermal/structural mounting arrangement, electrical interface assembly, and pneumatic interface assembly, configured to safely dissipate waste heat from multiple high-power electric thrusters, allowing simultaneous operation without exceeding temperature limits.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Productivity

If multiple electric thrusters are operated simultaneously, then propulsion capability and orbit transfer efficiency are improved, but thermal constraints are exceeded causing overheating of critical components

Engineering Contradiction:

Improvepropulsion capabilityVSAvoidthermal constraints

Core Design Contradiction:

ProductivityVSTemperature

Solution Approach 1:

The mounting arrangement is divided into a distal portion (with high thermal load from thrusters) and a proximal portion (with temperature-sensitive components), connected by a thermal barrier that segments the thermal pathways to prevent heat propagation

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

A thermal barrier is introduced as an intermediary element between the distal and proximal portions of the mounting arrangement, acting as a mediator that blocks heat transfer while maintaining structural connectivity

Inventive Principle:

Principle #24Intermediary (Mediator)

2Temperature

If only one thruster is fired at a time, then thermal constraints are maintained, but orbit transfer time and productivity increase

Engineering Contradiction:

Improvethermal constraintsVSAvoidorbit transfer time

Core Design Contradiction:

TemperatureVSLoss of time

Solution Approach 1:

The mounting arrangement is segmented into thermally isolated zones, allowing multiple thrusters to operate simultaneously in the distal portion without transferring heat to the proximal portion, thereby reducing orbit transfer time while maintaining thermal constraints

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Multiple thrusters can fire continuously and simultaneously without thermal interruption, enabling continuous high-productivity propulsion operations rather than sequential single-thruster firing

Inventive Principle:

Principle #20Continuity of useful action

3Power

If high-power electric thrusters are used, then propulsion efficiency is improved, but heat generation increases causing thermal management issues

Engineering Contradiction:

Improvepropulsion efficiencyVSAvoidwaste heat

Core Design Contradiction:

PowerVSLoss of energy

Solution Approach 1:

The thermal barrier converts the harmful waste heat from high-power thrusters into a manageable thermal load by directing it away from sensitive components, allowing the system to benefit from high-power propulsion while neutralizing the harmful thermal effects

Inventive Principle:

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

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 simultaneous operation of two or more high-power electric thrusters for extended periods at high duty cycles, effectively managing heat transfer to prevent overheating of critical components, thereby enhancing propulsion capabilities.

Implementation Method 1

the mounting arrangement is configured to conduct a first portion of waste heat from a mounting plate of each thruster to a surface of the mounting arrangement

Methodology Applied

Scientific EffectHeat conduction: Conduction (thermal)

Implementation Method 2

such that the first portion of the waste heat is radiated to space in a direction approximately transverse to the thrust vector

Methodology Applied

Scientific EffectThermal radiation: Thermal Radiation

Data Source

PatentUS11155368B1Multiple thruster firing on a single articulable module

Publication Date: 2021.10.26 LANTERIS SPACE LLC

AI summary

A spacecraft includes a propulsion subsystem including at least two electric thrusters, an electrical interface assembly that couples electrical conductors from the thrusters to a spacecraft harness, a pneumatic interface assembly that controls flow rate of propellant to the thrusters and a thruster support module (TSM) including a pointing arrangement and a mounting arrangement. A proximal portion of the mounting arrangement is coupled with a distal portion of the pointing arrangement; the at least two electric thrusters are disposed on a distal portion of the mounting arrangement; the electrical interface assembly and the pneumatic interface assembly are disposed on the proximal portion of the mounting arrangement. The mounting arrangement is configured to limit heat transfer between the thrusters and (b) one or more of the proximal portion of the mounting arrangement, the electrical interface assembly and the pneumatic interface assembly.