Orbital Debris Mitigation via In-Situ Fiber Interceptors
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Solution Overview
Problem
Orbital debris poses a significant threat to space assets due to the presence of non-functional satellites, rocket fragments, and collision debris, with current shielding and avoidance methods being inadequate and resource-intensive.
Innovation Solution
Deployment of fiber-based debris interceptors produced in space, which are made from materials like aluminum, glass, or polymer fibers, to intercept and de-orbit debris by altering its momentum, thereby reducing the threat of collisions with operational satellites.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If traditional shielding is used to protect satellites from debris, then some protection is provided, but the shielding is only effective for small impacts (1 cm) and cannot protect against larger debris
Solution Approach 1:
The debris interceptor is segmented into multiple fiber strands (e.g., 1000 strands) that work collectively to intercept debris. Each fiber strand contributes to the overall intercept capability, allowing the system to handle larger debris objects that would penetrate traditional monolithic shielding.
Solution Approach 2:
The invention transitions from two-dimensional planar shielding to a three-dimensional volumetric fiber network. The fiber bundle creates a distributed intercept volume that increases the probability of debris capture while maintaining low mass, effectively adding a spatial dimension to the protection mechanism.
2Difficulty of detecting and measuring
If ground tracking sites maintain data on debris objects, then tracking capability is provided, but tracking is only effective for objects down to about 10 cm in size
Solution Approach 1:
The fiber-based debris interceptor acts as an intermediary detection mechanism that complements ground-based tracking. While ground sites track objects down to 10 cm, the interceptor system provides a passive detection capability for smaller objects (down to 2 mm) by physically intercepting them, thereby extending the effective detection threshold.
3Object-affected harmful factors
If maneuvering is performed to avoid debris, then collision avoidance is attempted, but this consumes propellant and affects flight control operations
Solution Approach 1:
The debris interceptor system provides passive, autonomous protection that requires no active maneuvering or energy input from the satellite. The fiber bundle naturally intercepts debris through its spatial presence and drag-induced de-orbiting, eliminating the need for propellant-consuming avoidance maneuvers while maintaining continuous protection.
4Reliability
If a large number of fiber strands are used in the debris interceptor, then intercept capability is improved, but the mass of the interceptor increases
Solution Approach 1:
The debris interceptor uses thin fiber strands (diameter 1-100 micrometers) that have negligible individual mass but collectively provide extensive intercept surface area. The flexible fiber bundle can be deployed to large dimensions (e.g., 100 meters long) without significant mass penalty, achieving high intercept probability through surface area rather than mass.
Solution Approach 2:
The interceptor combines multiple fiber materials (e.g., Kevlar, Spectra, tungsten) with complementary properties to achieve high strength-to-mass ratios. This composite fiber construction maximizes intercept capability while minimizing mass, allowing thousands of strands to be used without proportionally increasing weight.
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 fiber-based debris interceptors effectively increase the chances of collision with debris over satellites, ensuring a 97% chance of intercepting debris rather than satellites, and their design minimizes the risk of posing a threat as broken fibers are fine enough not to cause significant damage, with the interceptors themselves de-orbiting due to drag, thus addressing the debris menace efficiently.
Implementation Method 1
intercept and de-orbit debris by altering its momentum
Implementation Method 2
the interceptors themselves de-orbiting due to drag
Data Source
AI summary
Fiber-based debris interceptors are used to intercept and/or contain space debris. The debris interceptors may be made up of fibers that are formed in space from a material supply on a space vehicle. The fibers for the debris interceptors may be formed by extrusion, with a heat source, such as a mirror to focus sunlight, used to heat the material of the material supply that is carried on the space vehicle. The debris interceptor may be separated from the space vehicle, and used to remove debris from an orbit, or otherwise prevent debris entering an orbit from damaging a satellite or other spacecraft that travels in that orbit. The debris interceptor may be deployed prior to later launch of a valuable spacecraft, in order to “cleanse” the intended orbit of debris. Debris objects may pass through the debris interceptor, but in so doing may lose energy so as to de-orbit.