Modular Space Platform Layout for Attitude and Thermal Control

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Solution Overview

Problem

Existing orbital structures face limitations in controllability, mass optimization, and thermal dissipation due to their centralized and functional architectures, particularly when dimensions exceed several hundred meters, leading to attitude control difficulties and significant flexions.

Innovation Solution

A space module designed with identical flat elements, including solar panels, radiators, and payloads, arranged in specific planes to form a space platform with homogeneous mass distribution, utilizing a robot for deployment and attitude control, and passive control by Earth's gravity gradient.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If the dimensions of the space platform are increased to provide additional functions, then the platform's capability is improved, but attitude control becomes more difficult due to significant flexions from large dimensions exposed to solar flux

Engineering Contradiction:

Improveplatform capabilityVSAvoidattitude control

Core Design Contradiction:

Adaptability or versatilityVSReliability

Solution Approach 1:

The space platform is divided into multiple identical modular units, each with its own payload and solar panels. These modules are distributed along the platform structure, allowing the platform to be scaled by adding modules while maintaining manageable control segments throughout the structure.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Each modular unit has localized functions (payload, solar panels, attitude control) distributed throughout the platform rather than centralized. This local distribution of functions reduces the moment arms and flexion effects on the overall platform attitude while maintaining full platform capability.

Inventive Principle:

Principle #3Local quality

2Ease of manufacture

If a centralized architecture like ISS is used, then subsystem assembly is simplified, but mass optimization is reduced and thermal dissipation losses increase due to distance between different functions

Engineering Contradiction:

Improvesubsystem assemblyVSAvoidthermal dissipation loss

Core Design Contradiction:

Ease of manufactureVSLoss of energy

Solution Approach 1:

The platform uses identical modular units distributed along its length, each containing complete functional sets (payload, solar panels, support structure). This segmentation allows standardized manufacturing while reducing thermal loss distances by placing solar panels locally adjacent to each module's payload.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Each modular unit is designed as a universal, self-contained element that can be replicated indefinitely. The identical modules perform the same functions locally, eliminating the need for long thermal and power transmission paths while maintaining assembly simplicity through standardization.

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Reliability

If actuators such as CMG or reaction wheels are used to control platform attitude, then attitude control is achieved, but the mass of the platform increases significantly

Engineering Contradiction:

Improveattitude controlVSAvoidplatform mass

Core Design Contradiction:

ReliabilityVSWeight of moving object

Solution Approach 1:

The attitude control function is segmented and distributed to individual modular units rather than using large centralized actuators. Each module has its own small actuators that control local orientation, collectively providing platform-wide attitude control with minimal mass.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The patent replaces heavy mechanical attitude control systems (CMG, reaction wheels) with a distributed system using small actuators on modular units combined with passive control methods, significantly reducing the mass required for attitude control while maintaining effectiveness.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

4Reliability

If thrusters are used for attitude control, then attitude adjustment is possible, but propellant consumption increases

Engineering Contradiction:

Improveattitude controlVSAvoidpropellant consumption

Core Design Contradiction:

ReliabilityVSLoss of substance

Solution Approach 1:

Attitude control is distributed across multiple modular units with local actuators, allowing precise small adjustments that require minimal propellant compared to using large thrusters for the entire platform. The segmented control enables localized corrections without moving the entire platform mass.

Inventive Principle:

Principle #1Segmentation

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 easy expansion of space platforms while ensuring attitude controllability, optimizing mass and thermal management, minimizing structural bending, and reducing the need for propellant-consuming actuators.

Implementation Method 1

passive control by Earth's gravity gradient

Methodology Applied

Scientific EffectGravity gradient: Gravitation

Data Source

PatentUS20250382071A1Space module designed to be deployed in space to form a space platform and associated space platform

Publication Date: 2025.12.18 THALES SA

AI summary

A space module designed to be deployed in space to form a space platform, the space module being formed of a predetermined number of elements all having the same flat shape in an extension plane of the corresponding element, each element being of a predetermined type, with at least one element forming a payload.