Satellite Wheel Cluster Formation Control via Orbital Parameter Adjustment

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Solution Overview

Problem

Current deployment and control algorithms for satellite formations in wheel cluster configurations require frequent station-keeping burns to maintain formation against perturbing forces, leading to high propellant usage.

Innovation Solution

A deployment algorithm and control algorithm that determine and minimize deviations in satellite orbits by adjusting eccentricity and argument of perigee, using onboard propulsion and navigation systems to maintain a wheel-shaped formation with satellites on closely separated orbits in the same plane, reducing differential perturbing forces.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If multiple station-keeping burns are performed per orbit to maintain cluster formation against J2 effects and perturbing forces, then formation stability is improved, but propellant usage increases

Engineering Contradiction:

Improveformation stabilityVSAvoidpropellant usage

Core Design Contradiction:

ReliabilityVSLoss of substance

Solution Approach 1:

The patent changes the orbital parameters (eccentricity and argument of perigee) of the sub-satellites to create a wheel cluster formation. By carefully selecting these parameters, the formation can maintain its configuration against J2 effects without requiring frequent station-keeping burns, thus reducing propellant usage while maintaining formation stability.

Inventive Principle:

Principle #35Parameter changes

Solution Approach 2:

The patent performs preliminary deployment of sub-satellites into specific orbital configurations with predetermined eccentricities and arguments of perigee. This preliminary arrangement allows the formation to be self-sustaining for extended periods, reducing the need for subsequent station-keeping maneuvers and propellant consumption.

Inventive Principle:

Principle #10Preliminary action

2Stability of the object's composition

If constant range restriction is imposed on sub-satellites, then geometrical configuration stability is improved, but station-keeping requirements increase

Engineering Contradiction:

Improvegeometrical configuration stabilityVSAvoidstation-keeping efficiency

Core Design Contradiction:

Stability of the object's compositionVSProductivity

Solution Approach 1:

The patent utilizes changes in orbital parameters (eccentricity and argument of perigee) to achieve both constant range and reduced station-keeping requirements. The wheel cluster formation geometry, combined with these parameter variations, allows the sub-satellites to maintain stable geometrical configuration while experiencing reduced differential perturbing forces.

Inventive Principle:

Principle #35Parameter changes

3Speed

If sub-satellites have different eccentricities and orbit inclinations, then constant range is achieved, but differential perturbing forces increase

Engineering Contradiction:

Improverange consistencyVSAvoiddifferential perturbing forces

Core Design Contradiction:

SpeedVSObject-affected harmful factors

Solution Approach 1:

The patent carefully selects and varies eccentricity and argument of perigee parameters to achieve the desired range consistency while minimizing differential perturbing forces. The wheel cluster formation geometry, combined with these parameter variations, allows the sub-satellites to maintain stable geometrical configuration while experiencing reduced differential perturbing forces.

Inventive Principle:

Principle #35Parameter changes

Data Source

PatentUS20190300206A9Deployment and control algorithms for wheel cluster formations of satellites

Publication Date: 2019.10.03 AEROSPACE CORP

AI summary

A control algorithm that determines one or more deviations in an orbit of a companion satellite, and control the companion satellite to minimize effects of perturbing forces.