Sealed Solid Rocket Motor for Debris-Free Spacecraft Deorbiting

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Solution Overview

Problem

Existing methods for deorbiting spacecraft, such as those using solid-propellant propulsion systems, face challenges in ensuring safe, reliable, and debris-free operation under space conditions for extended periods, particularly due to the risks of outgassing, mechanical failure, and the generation of large particles or fragments.

Innovation Solution

A solid-fuel rocket motor designed with a sealed interior filled with inert gas, tight connections, and shielding elements to maintain operational integrity and prevent the release of particles larger than 1 mm, while being resistant to space radiation and micrometeorites, ensuring reliable operation for years or decades.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of operation

If a solid-propellant rocket motor is used for deorbiting, then handling safety and environmental friendliness are improved, but the risk of outgassing and mechanical failure under space conditions worsens

Engineering Contradiction:

Improvehandling safetyVSAvoidoperational reliability under space conditions

Core Design Contradiction:

Ease of operationVSReliability

Solution Approach 1:

The patent applies preliminary action by pre-filling the sealed interior of the solid-propellant rocket motor with inert gas (such as nitrogen or helium) before launch. This inert gas atmosphere is maintained throughout the space mission to prevent outgassing of the solid propellant and to protect against mechanical failure. The inert gas filling is performed during manufacturing, and the seal is designed to maintain this atmosphere for the entire mission duration, including the deorbiting phase.

Inventive Principle:

Principle #10Preliminary action

Solution Approach 2:

The patent implements an inert atmosphere by sealing the motor interior and filling it with inert gas (nitrogen or helium). This creates a protective environment that prevents the solid propellant from outgassing under vacuum conditions and protects internal components from degradation. The inert atmosphere is maintained throughout the space mission by the seal, ensuring reliability during deorbiting operations.

Inventive Principle:

Principle #39Inert atmosphere (Inert environment)

2Reliability

If the motor is sealed and filled with inert gas, then operational reliability is improved, but device complexity increases

Engineering Contradiction:

Improveoperational reliabilityVSAvoidsealing and gas filling system

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The patent merges the sealing function and inert gas containment into the motor's existing structural components. The seal is integrated into the motor housing design, and the inert gas filling is performed during manufacturing as part of the assembly process. This integration avoids adding separate, complex sealing systems or gas management mechanisms, thereby limiting the increase in device complexity while maintaining high operational reliability.

Inventive Principle:

Principle #5Merging (Combining)

3Reliability

If shielding elements are added to protect against radiation and micrometeorites, then reliability is improved, but manufacturing complexity increases

Engineering Contradiction:

Improveresistance to space radiation and micrometeoritesVSAvoidmanufacturing simplicity

Core Design Contradiction:

ReliabilityVSEase of manufacture

Solution Approach 1:

The patent employs thin-film shielding elements that can be applied to the motor exterior during manufacturing. These thin films provide protection against space radiation and micrometeorite impacts without requiring thick, heavy shielding structures. The thin-film approach simplifies the manufacturing process compared to traditional bulk shielding materials, as the films can be deposited or attached to the motor housing in a straightforward manner while providing the necessary protective function.

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 motor achieves safe, debris-free deorbiting by maintaining thrust capability and preventing the release of large particles, while withstanding space conditions for extended periods, thus minimizing the risk of space debris creation.

Implementation Method 1

the engine is designed as a solid-propellant rocket motor

Methodology Applied

Scientific EffectCombustion: Combustion

Implementation Method 2

a gas filling introduced into an interior of the engine containing the solid propellant before the start of the mission is substantially maintained during the operational period

Methodology Applied

Scientific EffectPressure gradient: Pressure Gradient

Data Source

PatentEP4692532A1Motor for applying a speed change to a missile in space, and missile

Publication Date: 2026.02.11 BAYERN CHEM GES FUR FLUGCHEM ANTRIEBE MBH

Figure 1~2
Figure 3(a)~4

AI summary

The present invention relates to an engine (2) for applying a change in velocity, in magnitude and/or direction, to a spacecraft (1), in particular for deorbiting the spacecraft, wherein the engine is designed as a solid-propellant rocket engine with a solid propellant (24) and the engine is designed and configured such that the engine remains operational under space conditions predefined for the mission of the spacecraft at least until the end of a predefined operational period (100) of the spacecraft or at least during a predefined, substantial part (204) of a mission duration (200) of the spacecraft. The invention further relates to a spacecraft comprising such an engine.