Multilayer Insulation Reuse for Satellite Deorbiting Drag
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Solution Overview
Problem
Existing methods for deorbiting artificial satellites, such as active and passive devices, incur additional costs and weight, limiting their applicability to small satellites due to the need for additional components and forces.
Innovation Solution
The method involves partially detaching or splaying multilayer insulation (MLI) layers from the satellite to expose it to environmental influences, utilizing the MLI's material degradation to accelerate self-disintegration, and optionally using a heating element, spring elements, and bonding agents to facilitate detachment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If additional deorbiting devices are added to satellites, then deorbiting capability is improved, but satellite weight and complexity increase
Solution Approach 1:
The multilayer insulation itself serves as the deorbiting mechanism. By detaching or splaying the MLI layers, the satellite utilizes its own existing material to increase drag and facilitate deorbiting, eliminating the need for separate deorbiting devices and reducing overall system weight.
Solution Approach 2:
The multilayer insulation performs dual functions: thermal insulation during operational life and deorbiting mechanism at end of life. This multi-functionality eliminates the need for dedicated deorbiting hardware, reducing satellite weight and complexity.
2Reliability
If additional deorbiting devices are added to satellites, then deorbiting capability is improved, but device complexity increases
Solution Approach 1:
The satellite uses its own multilayer insulation structure to perform deorbiting functions. The MLI layers are manipulated through simple mechanisms (detachment or splaying) rather than requiring complex dedicated deorbiting systems, thereby reducing overall device complexity.
Solution Approach 2:
The deorbiting mechanism relies on changing the physical state or configuration of the MLI layers (from attached to detached, or from compact to splayed) rather than introducing complex mechanical systems. This parameter-based approach simplifies the overall device architecture.
3Productivity
If MLI layers are detached to accelerate deorbiting, then deorbiting speed is improved, but satellite protection from environmental influences is reduced
Solution Approach 1:
The MLI layers are detached or splayed at the predetermined end of the satellite's operational life when deorbiting is needed. During the operational phase, the MLI remains attached to provide thermal protection. This timing-based approach ensures protection during operation while enabling accelerated deorbiting when required.
Solution Approach 2:
The MLI configuration is made dynamic, transitioning from an attached state during operational life to a detached or splayed state at end of life. This dynamic reconfiguration allows the system to optimize both protection during operation and deorbiting speed when needed, resolving the contradiction between these two requirements.
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 approach reduces the need for additional components, effectively deorbiting satellites by accelerating material degradation without additional weight, aligning with ISO-24113 guidelines for safe space access.
Implementation Method 1
the heating element is configured to melt the bonding agent
Implementation Method 2
the heating element is configured to melt the bonding agent
Implementation Method 3
a spring element is integrated in the multilayer insulation and configured to separate the at least one layer from the satellite structure
Implementation Method 4
a greater braking effect through atmospheric residues in low Earth orbit is achieved by enlargement of the satellite surface
Implementation Method 5
The now unprotected satellite is disintegrated by oxygen radicals, ultraviolet radiation and strong temperature variations
Implementation Method 6
The now unprotected satellite is disintegrated by oxygen radicals, ultraviolet radiation and strong temperature variations
Implementation Method 7
The now unprotected satellite is disintegrated by oxygen radicals, ultraviolet radiation and strong temperature variations
Data Source
AI summary
A method and a device for deorbiting artificial satellites with multilayer insulation arranges a deorbiting device beneath it. The device includes a spring element, a bonding agent, and a heating element designed to melt the bonding agent, which at least partially detaches at least one layer of the multilayer insulation from the satellite when a signal is transmitted to the satellite by rolling up or splaying out in the manner of a flap, enlarging its cross-sectional area. The partial detachment exposes the underlying satellite structure to environmental influences. This exposure accelerates the self-disintegration of the artificial satellite, reduces the mass, and increases the ballistic coefficient throughout the deorbiting period. This area enlargement and mass reduction reduce energy, resulting in re-entry into Earth's atmosphere. A number of layers can be arranged so that, regardless of the satellite rotation, at least one surface is always directed against the aerodynamic flow.