CubeSat De-Orbiting Heat Shield Assembly for Compact Re-Entry

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Solution Overview

Problem

Existing CubeSat technologies lack effective and reliable systems for de-orbiting and thermal protection, particularly during the re-entry phase, which are cost-effective and compact, given the economic and engineering constraints of CubeSats.

Innovation Solution

A de-orbiting and thermal protection assembly comprising a fixing frame with hinges and arms supporting a heat shield, equipped with a spherical spring pin for precise positioning and reversible fixing, ensuring both thermal protection and accelerated de-orbiting without increasing the CubeSat's size or cost.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If a de-orbiting device and heat shield are provided on CubeSats, then thermal protection and de-orbiting capability are improved, but cost and size increase significantly

Engineering Contradiction:

Improvethermal protection and de-orbiting capabilityVSAvoidcost and size

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The patent combines the de-orbiting device and heat shield into a single integrated assembly that serves both functions simultaneously. The fixing frame structure provides both the de-orbiting surface area and the heat shield mounting, eliminating the need for separate systems and reducing overall complexity and cost.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The assembly is designed to perform multiple functions: it provides de-orbiting capability through atmospheric drag, thermal protection during re-entry, and structural mounting for the CubeSat. This multi-functional design reduces the number of separate components needed.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Reliability

If deployable sails are used for de-orbiting, then de-orbiting capability is improved, but device complexity and size increase

Engineering Contradiction:

Improvede-orbiting capabilityVSAvoidstructural complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The de-orbiting assembly is divided into modular components including the fixing frame, arms, and heat shield that can be independently manufactured and assembled. This segmentation simplifies the overall structure while maintaining de-orbiting effectiveness.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Instead of using complex deployable sails that extend outward, the invention uses a compact fixed frame structure that provides de-orbiting surface area in a minimized configuration, inverting the traditional approach of using large deployable surfaces.

Inventive Principle:

Principle #13The other way round (Inversion)

3Temperature

If a heat shield is added to protect against aerodynamic heating, then thermal protection is improved, but size and cost increase

Engineering Contradiction:

Improvethermal protectionVSAvoidsize and cost

Core Design Contradiction:

TemperatureVSDevice complexity

Solution Approach 1:

The heat shield is integrated with the de-orbiting frame structure, where the same components that provide de-orbiting surface area also serve as the mounting structure for thermal protection. This eliminates redundant structural elements.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The heat shield is implemented as a thin protective layer that provides thermal protection without adding significant mass or volume, allowing effective thermal shielding while maintaining the compact CubeSat form factor.

Inventive Principle:

Principle #30Flexible shells and thin films

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

The assembly provides reliable thermal protection and rapid de-orbiting, reducing de-orbiting time from five years to one year and ensuring compliance with safety standards, while maintaining the economic and compact nature of CubeSats.

Implementation Method 1

during the re-entry phase the vehicles lose their kinetic energy, converting it into heat by means of friction with the atmospheric gases surrounding the vehicle itself

Methodology Applied

Scientific EffectAerodynamic heating: Aerodynamic Heating

Implementation Method 2

converting it into heat by means of friction with the atmospheric gases surrounding the vehicle itself

Methodology Applied

Scientific EffectFriction: Friction

Data Source

PatentEP4667366A1De-orbiting and thermal protection assembly to be applied to cubesats

Publication Date: 2025.12.24 SPACE FACTORY SRL

Figure 1
Figure 2~4

AI summary

A de-orbiting and thermal protection assembly (1) to be applied to CubeSats comprising a fixing frame (2), suitable for being reversibly fixed to an external perimeter of a load-bearing structure (7) of a relative CubeSat (8), and a plurality of arms (3) fixed to the fixing frame (2) by means of a plurality of respective hinges (4) and suitable for supporting a heat shield. The assembly comprises a position indicator (10) fixed to the CubeSat (8) and suitable for cooperating with a contrast portion (11) of the fixing frame (2) and reversible fixing means (10, 11) for fixing the fixing frame (2) to the CubeSat (8).