Hollowed Asteroid Spacecraft Shielding
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Solution Overview
Problem
Current radiation shielding in human-crewed spacecraft is inadequate for long-duration interplanetary missions, posing health risks to astronauts due to insufficient protection against deep-space radiation and meteoroid impacts, and existing technologies lack effective countermeasures for these hazards.
Innovation Solution
A modular interplanetary spacecraft design utilizing a hollowed-out asteroid with exterior walls at least 2 meters thick and channeled curtains of pulverized asteroidal material for radiation shielding, combined with expandable habitation modules and ISS technologies, allowing for robust protection and modular assembly in space.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If traditional radiation shielding materials and methods are used in human-crewed spacecraft, then the spacecraft structure can be maintained at reasonable complexity, but the radiation protection capability is insufficient for long-duration interplanetary missions
Solution Approach 1:
The patent employs composite shielding structures combining water (in tanks or as ice), polyethylene, and aluminum alloys to achieve superior radiation protection. Water provides hydrogen-rich material for cosmic ray shielding, polyethylene offers high hydrogen content for neutron moderation, and aluminum provides structural integrity. This composite approach resolves the contradiction by achieving enhanced radiation protection without requiring a single overly complex shielding system.
Solution Approach 2:
The patent utilizes phase changes of water (liquid to solid ice) to maintain shielding effectiveness while managing volume and mass. By converting water to ice, the shielding material maintains its position and density for optimal radiation protection while reducing the risk of leakage and simplifying containment requirements. This parameter change resolves the contradiction between maintaining protection capability and simplifying the shielding system.
2Weight of stationary object
If expandable modules are used to reduce launch mass, then the spacecraft can be more cost-effective, but the structural integrity and protection capability during deployment may be compromised
Solution Approach 1:
The spacecraft is divided into separate expandable modules (habitation module, laboratory module, green module) that can be launched in collapsed configurations and deployed in space. Each module maintains structural integrity through rigid truss frameworks and pressure-resistant walls, resolving the contradiction by ensuring that segmentation for mass reduction does not compromise the strength of individual modules.
Solution Approach 2:
The patent incorporates radiation shielding materials (water tanks, polyethylene layers) and meteoroid protection structures (whipple shields, sacrificial layers) into the expandable modules before deployment. This beforehand cushioning ensures that when modules expand, the structural integrity and protection capabilities are already in place, resolving the contradiction between mass reduction and strength maintenance.
3Object-affected harmful factors
If robotic assembly is used to reduce human exposure to space radiation, then crew safety is improved, but the assembly time and operational complexity increase
Solution Approach 1:
The spacecraft modules are pre-assembled and pre-shielded on Earth before launch, with radiation shielding materials and structural components installed in advance. This preliminary action reduces the need for complex robotic assembly operations in space, resolving the contradiction by minimizing both crew exposure time and robotic assembly complexity while maintaining safety.
Solution Approach 2:
The patent employs nested module configurations where smaller modules (habitation, laboratory, green module) are positioned within or adjacent to larger shielded structures. This nesting arrangement allows robotic assembly to proceed efficiently while maintaining radiation protection, as the nested configuration naturally provides shielding without requiring additional complex assembly steps.
4Object-affected harmful factors
If water is used for radiation shielding, then the protection capability is enhanced, but the mass and volume of the spacecraft increase
Solution Approach 1:
Water serves multiple functions in the spacecraft: it provides radiation shielding, supplies drinking water for the crew, and can be used for hydroponic agriculture in the green module. This multi-functionality resolves the contradiction by justifying the mass of water through its additional utilitarian values, making the overall mass increase acceptable in exchange for enhanced radiation protection.
Solution Approach 2:
The patent utilizes phase changes of water (liquid to solid ice) to optimize shielding effectiveness while managing mass and volume. By converting water to ice in specific shielding locations, the system maintains high density for optimal radiation protection while reducing the risk of leakage and simplifying containment, thereby managing the mass-volume-tradiction effectively.
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 solution provides significantly enhanced radiation shielding and protection from meteoroid impacts, reducing health risks to astronauts and enabling safer, more cost-effective interplanetary missions with reduced human assembly requirements and lower R&D costs.
Implementation Method 1
a hollowed-out asteroid with exterior walls at least 2 meters thick and channeled curtains of pulverized asteroidal material for radiation shielding
Implementation Method 2
channeled curtains of pulverized asteroidal material for radiation shielding
Implementation Method 3
provides significantly enhanced radiation shielding and protection from meteoroid impacts
Data Source
AI summary
Disclosed is a modular, human-crewed interplanetary spacecraft that is assembled in cislunar space. It is primarily comprised of a hollowed-out asteroid; five expandable habitation modules, one of which is expanded inside the asteroid cavity; two docking and airlock nodes; two landing craft suitable for exploring celestial bodies; structural support members; truss structures; robotic arms; a propulsion module; and shielding curtains that are filled with pulverized asteroidal material and attached to the truss structure. This configuration provides substantial radiation and meteoroid shielding. Upon completion of their mission, the crew will use the robotic arms to disconnect and mate (1) the asteroid containing the control module, (2) the forward docking and airlock node, and (3) the propulsion module. This crew-return vehicle will return to cislunar space. The remaining expandable modules with trusses, robotic arms, and landing craft will remain in the destination orbit to serve as a space station for future missions.