Space Debris Interception Vehicle Elliptical Orbit Capture
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Solution Overview
Problem
Current methods for capturing and de-orbiting space debris are costly and complex, often requiring a host satellite and significant power and fuel consumption, with destructive techniques potentially worsening the debris problem by generating new smaller debris.
Innovation Solution
A dedicated launch system is used for a vehicle with a launching portion and an interception portion, which intercepts and engages with space debris using means like harpoons or airbags, transitioning to a lower elliptical orbit to ensure the debris burns up in the Earth's atmosphere, reducing propellant needs and avoiding new debris creation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a host satellite is used to host chaser or servicer components for capturing space debris, then the capture capability is improved, but the mission cost and system complexity increase significantly
Solution Approach 1:
The invention extracts the capture function from a host satellite platform and implements it as a standalone interception vehicle. The vehicle comprises a launching portion for orbital insertion and an interception portion with engagement means (harpoons, nets, or airbags) specifically designed for capturing space debris, eliminating the need for complex host satellite infrastructure while maintaining capture capability
Solution Approach 2:
The interception vehicle is segmented into distinct functional portions: a launching portion for driving the vehicle into orbit and an interception portion for engaging the target object. This segmentation allows each portion to be optimized independently, reducing overall system complexity while preserving the reliability of the capture function
2Reliability
If a host satellite is used for repeated docking or de-orbit manoeuvres, then the capture capability is improved, but the power and fuel consumption increase significantly
Solution Approach 1:
The vehicle is launched directly into an elliptical orbit with perigee at the target object's orbital altitude, pre-positioning the interception portion for optimal engagement. This preliminary orbital configuration eliminates the need for repeated docking manoeuvres and associated fuel consumption, while maintaining the ability to perform the de-orbit manoeuvre after capture
Solution Approach 2:
The interception vehicle is designed as a single-use disposable system that is launched, performs the interception and de-orbit manoeuvre, and then is discarded after completing its mission. This approach eliminates the need for expensive, fuel-intensive operations to maintain and reuse a host satellite, significantly reducing power and fuel consumption while maintaining capture capability
3Object-affected harmful factors
If chemical thrusters are used to provide braking force to reduce debris velocity, then the collision damage potential is reduced, but the target melting risk and mass efficiency worsen
Solution Approach 1:
The invention replaces the chemical thruster braking system with a mechanical interception and capture system. The vehicle uses engagement means (harpoons, nets, or airbags) to physically capture the target object and directly transfer momentum during the docking manoeuvre, eliminating the need for chemical propulsion and associated thermal hazards while still reducing the target's velocity potential
4Ease of operation
If ground-launched missiles are used to destroy space debris, then the operational simplicity is improved, but the debris problem worsens due to generation of smaller debris fragments
Solution Approach 1:
The invention converts the harmful effect of high-velocity impact from a destructive force into a beneficial capture mechanism. The engagement means are designed to withstand and utilize the relative velocity between the vehicle and target object, transforming the kinetic energy that would otherwise cause destruction into a controlled capture and de-orbit process that eliminates debris without generating fragments
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 significantly reduces costs and complexity by minimizing propellant use and preventing the generation of new debris, enabling efficient and non-destructive removal of space debris from orbit.
Implementation Method 1
the launching portion is arranged to drive the vehicle into a first elliptical orbit and the vehicle is arranged to adopt a second elliptical orbit on engagement with the target object
Implementation Method 2
the second elliptical orbit is such that the vehicle is arranged to move from the interception point towards the Earth's atmosphere when engaged with the target object
Data Source
AI summary
A vehicle for intercepting a target object orbiting in space is provided, comprising a launching portion for driving the vehicle into an orbit, and an interception portion for intercepting a target object when the vehicle is in orbit, wherein the interception portion comprises means for engaging with the target object and wherein the launching portion is arranged to drive the vehicle into a first elliptical orbit and the vehicle is arranged to adopt a second elliptical orbit when engaged with the target object in which the first elliptical orbit is arranged so as to intersect the orbit of the target object at an interception point, and the second elliptical orbit is such that the vehicle is arranged to move from the interception point towards the Earth's atmosphere when engaged with the target object. A method of controlling a vehicle for intercepting a target object orbiting in space is also provided, comprising controlling the vehicle to be driven into a first elliptical orbit to intersect the orbit of the target object at an interception point and controlling the vehicle to engage with the target object at the interception point and to adopt a second elliptical orbit when engaged with the target object in which the second elliptical orbit is such that the vehicle is arranged to move from the interception point towards the Earth's atmosphere when engaged with the target object.