Tumbling Space Object Capture Using Countermass Angular Momentum Matching

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Solution Overview

Problem

Existing methods for attenuating the angular velocity of tumbling space objects in orbit are inefficient and costly due to resource consumption, particularly fuel, and pose risks of collision and damage.

Innovation Solution

A method involving a spacecraft with deployable counter masses and a truss structure to offset the center of mass, matching the angular momentum of the object, and using thrusters and flywheels to generate torque for safe contact and zero relative motion.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If pneumatic impingement with gas plume is used to generate torque for detumbling, then angular velocity can be attenuated, but fuel consumption increases and collision risks arise

Engineering Contradiction:

Improvesafety of captureVSAvoidfuel consumption

Core Design Contradiction:

ReliabilityVSUse of energy by moving object

Solution Approach 1:

The patent employs countermasses positioned at specific locations relative to the spacecraft bus to generate gravitational torque that counteracts the tumbling motion. By strategically placing countermasses at distances and orientations that create appropriate gravitational forces, the system achieves detumbling without requiring fuel-consuming thrust mechanisms, thereby eliminating the trade-off between safety and fuel consumption.

Inventive Principle:

Principle #8Anti-weight (Counterweight)

Solution Approach 2:

The patent replaces active mechanical thrust systems (which consume fuel) with passive gravitational interaction systems. Instead of using engines to generate torque for detumbling, the invention uses the gravitational field interaction between the spacecraft and countermasses to naturally generate the required torque, substituting a non-consuming gravitational mechanism for a fuel-consuming mechanical one.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

2Adaptability or versatility

If countermasses are deployed away from the bus to offset center of mass, then angular momentum matching capability improves, but device complexity increases

Engineering Contradiction:

Improveangular momentum matching capabilityVSAvoidstructure complexity

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The patent divides the spacecraft system into distinct functional segments: the main bus containing propulsion and control systems, and separate countermasses that can be independently deployed. This segmentation allows the countermasses to be positioned optimally for angular momentum matching while keeping the main bus structure relatively simple and modular.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The patent utilizes spatial deployment of countermasses in three-dimensional space around the spacecraft bus to achieve center of mass offset. By positioning countermasses at different distances and orientations (utilizing spatial dimensions), the system achieves versatile angular momentum matching capability without requiring complex mechanical structures, as the deployment is accomplished through spatial arrangement rather than mechanical complexity.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

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 and safe capture of tumbling space objects by mechanically generating angular momentum without consuming resources, reducing collision risks and fuel costs.

Implementation Method 1

deploying one or more counter mass(es) away from a servicing spacecraft bus to offset the servicing spacecraft center of mass

Methodology Applied

Scientific EffectCenter of mass offset:

Implementation Method 2

imparting angular momentum to the servicing spacecraft to match the tumble rate of the object

Methodology Applied

Scientific EffectAngular momentum: Angular Momentum

Implementation Method 3

using thrusters and flywheels to generate torque for safe contact and zero relative motion

Methodology Applied

Scientific EffectFlywheel: Flywheel

Implementation Method 4

using thrusters and flywheels to generate torque for safe contact and zero relative motion

Methodology Applied

Scientific EffectThrust:

Implementation Method 5

contacting the object with one or more mechanical attachments to the servicing spacecraft

Methodology Applied

Scientific EffectMechanical contact: Mechanical Force

Data Source

PatentUS12479603B2Method and device for capture of tumbling space objects

Publication Date: 2025.11.25 ASTROSCALE HLDG INC

AI summary

According to an aspect of the present invention, there is provided a method comprising: propelling a servicing spacecraft to an object; deploying one or more counter mass(es) away from a servicing spacecraft bus to offset the center of mass of the servicing spacecraft into an empty volume; approaching the object, by the servicing spacecraft; positioning the center of mass of the servicing spacecraft in approximately the same location as the center of mass of the object; imparting angular momentum to the servicing spacecraft to match the tumble rate of the object; and contacting the object with one or more mechanical attachments to the servicing spacecraft.