Rotating Mass Attitude Control for Spacecraft

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Solution Overview

Problem

Current attitude control systems for satellites and spacecraft, particularly in low or zero gravity environments, face challenges such as mass constraints, inefficiency, and potential damage from thruster residue, which limit agile and precise attitude adjustments.

Innovation Solution

A rotating mass attitude control system utilizing multiple circular or disk-shaped masses equally spaced around a circumference, powered by electric motors, which spin to generate counter-rotational forces for agile attitude control without chemical fuels, allowing for precise and efficient orientation adjustments.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If thrusters are used for attitude control, then attitude adjustments can be made, but mass and cost increase and thruster residue may cause damage

Engineering Contradiction:

Improveattitude control reliabilityVSAvoidsystem mass

Core Design Contradiction:

ReliabilityVSWeight of moving object

Solution Approach 1:

The patent replaces the chemical propulsion system (thrusters) with an electromagnetic system (magnetic torquers) for attitude control. Magnetic torquers generate control torques through interaction with the Earth's magnetic field, eliminating the need for propellant and reducing system mass while avoiding thruster residue contamination.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The patent introduces the Earth's magnetic field as an intermediary medium to achieve attitude control. Instead of directly expelling mass through thrusters, the system uses magnetic torquers to interact with the ambient magnetic field, converting electromagnetic energy into mechanical torque for attitude adjustments without consuming propellant.

Inventive Principle:

Principle #24Intermediary (Mediator)

2Stability of the object's composition

If reaction wheels are used for three-axis stabilization, then steady spacecraft orientation is achieved, but mass increases and momentum desaturation maneuvers are required

Engineering Contradiction:

Improvespacecraft orientation stabilityVSAvoidsystem mass

Core Design Contradiction:

Stability of the object's compositionVSWeight of moving object

Solution Approach 1:

The patent replaces mechanical reaction wheels with an electromagnetic control system using magnetic torquers. This substitution eliminates the need for heavy rotating masses while achieving three-axis stabilization through direct electromagnetic torque application, reducing system mass and eliminating momentum accumulation issues.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The patent changes the control mechanism from mechanical momentum exchange to electromagnetic torque generation. By varying the current through the magnetic torquers, the system can dynamically adjust the generated torque to maintain precise orientation without the mass and complexity of reaction wheels.

Inventive Principle:

Principle #35Parameter changes

3Productivity

If spin stabilization is used, then continuous sweeping motion is provided for instruments, but de-spin mechanisms are required for targeted observations

Engineering Contradiction:

Improveinstrument scanning capabilityVSAvoidde-spin system complexity

Core Design Contradiction:

ProductivityVSDevice complexity

Solution Approach 1:

The patent employs a dynamic control system using magnetic torquers that can rapidly adjust the spacecraft's rotation state. The system can transition between spinning and stationary modes on demand, providing instrument scanning when needed while enabling precise targeting when required, all controlled by variable electromagnetic torque without mechanical de-spin mechanisms.

Inventive Principle:

Principle #15Dynamics

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 solution reduces the mass and cost of attitude control systems, enables precise and agile attitude adjustments, and avoids potential damage from thruster residue, enhancing the operational life and efficiency of satellites and spacecraft.

Implementation Method 1

Methodology Applied

Scientific EffectElectromagnetic motor drive: Electromagnetic Induction

Implementation Method 2

Spin stabilization is accomplished by setting the spacecraft spinning, using the gyroscopic action of the rotating spacecraft mass as the stabilizing mechanism

Methodology Applied

Scientific EffectGyroscopic action: Gyroscope

Implementation Method 3

They provide a means to trade angular momentum back and forth between spacecraft and wheels

Methodology Applied

Scientific EffectAngular momentum conservation: Angular Momentum Conservation

Data Source

PatentUS11174046B2System and method for rotating mass attitude control

Publication Date: 2021.11.16 SINCLAIR LARRY D

AI summary

The disclosure relates to a method and apparatus of rotating mass attitude control. The method and apparatus entails rotating a mass to generate thrust. Varying the speed and direction of rotation provides some control of the magnitude and direction of the thrust generated. The method and apparatus of the invention pertinent to an attitude control system for spacecrafts or astromotive vehicles under conditions of zero to low gravity and atmosphere.