Deformable Satellite Structural Element for Space Debris Capture
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Solution Overview
Problem
The increasing number of space debris in Low Earth Orbit poses a significant risk of collisions with operational satellites and meteoroids, leading to further orbital debris and potential catastrophic damage.
Innovation Solution
A satellite equipped with deformable structural elements that can capture space debris through collision, either by wrapping around larger objects or lodging smaller ones within its material layers, allowing for subsequent de-orbiting and incineration upon re-entry into Earth's atmosphere.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If a claw system is used to mechanically capture orbital debris, then small debris can be captured, but the system becomes complex and can only recover relatively small debris
Solution Approach 1:
The patent employs a flexible membrane structure that can deform during collision to wrap around captured debris. This membrane approach simplifies the capture mechanism compared to rigid claw systems while maintaining the ability to capture debris of various sizes through passive deformation rather than active mechanical gripping
Solution Approach 2:
The patent converts the harmful high-velocity collision impact into a beneficial capture mechanism. The kinetic energy of the debris is used to drive the membrane deformation and wrapping action, eliminating the need for complex active capture mechanisms while effectively capturing debris through the impact itself
2Quantity of substance
If a magnetic capture system is used, then orbital debris can be captured, but momentum transfer and tumbling debris remain problematic
Solution Approach 1:
The flexible membrane can adapt its shape during and after collision to accommodate tumbling debris, maintaining contact and capture effectiveness despite the debris's rotational motion. The membrane's flexibility allows it to conform to the debris surface regardless of orientation changes
Solution Approach 2:
The membrane structure transitions from a static configuration to a dynamic, deformable state during collision. This dynamic response allows the capture system to adapt to the high-velocity impact and subsequent tumbling motion of the debris, maintaining capture reliability without requiring active control mechanisms
3Quantity of substance
If a harpoon or net system is used with tether connection, then debris can be captured and dragged to atmosphere, but LIDAR or radar tracking is required adding complexity
Solution Approach 1:
The patent extracts the active tracking and control functions from the capture system, relying instead on passive collision dynamics. By eliminating the need for LIDAR/radar tracking and active tether management, the system reduces complexity while maintaining capture capability through direct impact and membrane wrapping
Solution Approach 2:
The capture system operates autonomously through passive collision dynamics. The membrane automatically deforms and wraps around debris upon impact without requiring external tracking or control inputs, making the system self-sufficient and eliminating complex tracking infrastructure
4Quantity of substance
If a laser system is used to ablate or deflect debris, then small debris (1 to 10 centimeter) can be slowed for atmospheric burn-up, but larger debris cannot be affected
Solution Approach 1:
The membrane capture system provides universal capability to capture debris across a wide range of sizes, from small particles to large objects. The passive collision and wrapping mechanism scales with debris size, allowing a single system design to handle diverse debris dimensions without requiring size-specific subsystems
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 satellite effectively captures and removes space debris from orbit, mitigating the risk of collisions and reducing the amount of orbital debris, while also being capable of de-orbiting and incinerating captured objects.
Implementation Method 1
at least one structural element that is deformable during a collision with one or more space object(s)... the structural element deforms (e.g., bends, folds, wraps, etc.) around at least part of the space object(s)
Implementation Method 2
a satellite is provided that includes at least one structural element that is deformable during a collision with one or more space object(s)
Implementation Method 3
capturing the space object(s). After capturing the space object(s), in some embodiments, the satellite may de-orbit along with the captured the space object(s). In some cases, the deorbiting satellite and the captured space object(s) may incinerate upon re-entry into Earth's atmosphere
Data Source
AI summary
A satellite includes a structural element that is deformable during a collision with space object(s). The structural element includes a first side, a second side spaced apart from the first side to define an interior portion between the first side and the second side. and at least one material disposed within the interior portion. The first side includes a first layer of material with payload element(s) disposed thereon, and the second side includes a second layer of material. The material disposed within the interior portion is designed to absorb energy over time during a collision process with each space object. The first layer, the second layer and/or the material disposed within the interior portion are configured to capture one or more space objects upon collision with the satellite.