Tag: in-situ resource utilization

  • The Planetary Defense Asteroid Interception and Resource Utilization Problem

    From first principles, design a fully autonomous, scalable, and economically self-sustaining system for planetary defense against near-earth objects (NEOs) between 50 and 500 meters in diameter.

    Constraints and Requirements:

    1. Detection & Tracking: Your system cannot rely solely on Earth-based observatories. It must include a space-based detection and tracking component (e.g., a constellation of satellites in various orbits) capable of identifying and calculating the trajectory of threatening NEOs with at least 5 years of lead time for a 150-meter object.
    2. Interception: You must design a primary interception vehicle/method. Kinetic impactors are an option, but you must solve for the terminal guidance problem to ensure precise impact. Also, design a secondary or follow-up method (e.g., a “gravity tractor” or laser ablation system) to make fine adjustments to the post-impact trajectory or to handle fractured objects. The system must be deployable from a standby orbit to an intercept trajectory within 30 days.
    3. Economic Self-Sustenance (The Core Challenge): The system cannot be a pure cost center funded by governments. Design a mechanism for it to generate revenue. This must involve in-situ resource utilization (ISRU). Your interceptor vehicles, after a kinetic impact mission, must have a secondary function. For example, a “shepherd” drone that follows the main impactor could be designed to autonomously rendezvous with the now-neutralized (or other non-threatening) asteroid, mine it for valuable materials (e.g., water ice, platinum-group metals), and process them in-space.
    4. Propulsion & Logistics: The entire system must rely on propellant that can be, at least in part, sourced and refined in space (e.g., from water ice on asteroids or the Moon) to enable rapid and repeated deployment without costly Earth launches for every mission. You need to architect the logistics of how you would refuel your interceptor fleet in orbit.
    5. Scalability: The architecture must be scalable. How does your system go from handling one potential impact threat every decade to handling multiple threats per year as detection capabilities improve? Your economic model must scale with your operational tempo. What is the business case for building the 100th interceptor/miner versus the first?

    Solve for the optimal design of the detection constellation, the interceptor/miner vehicle, the in-space refining process, and the overall business model that makes planetary defense profitable, and therefore, robust and enduring.

  • The Problem: Planetary Atmospheric Retention for Mars

    Mars loses its atmosphere to space at a rate of approximately 1-2 kg/s, primarily due to scavenging by the solar wind, as it lacks a global magnetic field. Your task is to design a system, from first principles, to solve this problem and enable the long-term terraforming goal of creating a denser, breathable atmosphere.

    Constraints & Specifications:

    1. Mechanism: You must design an artificial magnetosphere for Mars. The system cannot be a single, massive ground-based dipole. It must be a distributed or orbital system.
    2. Power: The entire system must be self-sufficiently powered using only resources available on Mars or in situ (e.g., solar, geothermal, limited fission from mined uranium). You must calculate the total power budget required to generate a magnetic field strong enough to deflect the majority of high-energy solar wind particles before they reach the upper atmosphere (ionosphere).
    3. Deployment & Maintenance: Your design must include a plausible, multi-stage strategy for deployment using vehicles like SpaceX’s Starship. Critically, it must be designed for near-zero human maintenance, relying on robotic servicing and having a designed operational lifespan of at least 500 years.
    4. Physics: From first principles, calculate the required magnetic moment (M) for your system to create a magnetopause standoff distance of at least two Mars radii (RM​) from the planet’s center. The formula for the magnetopause standoff distance (Rmp​) is approximately Rmp​=(8π2ρV2μ0​M2​)1/6, where μ0​ is the permeability of free space, ρ is the solar wind density, and V is the solar wind velocity at Mars’ orbit.
    5. Systemic Risk: Analyze the second and third-order failure modes. What happens if a critical node in your distributed system fails? How do you prevent catastrophic, cascading failure? What are the potential negative impacts of your artificial magnetosphere on future communication systems or human biology on the surface?

    Your final proposal should not be a vague concept but a detailed engineering and physics plan, including material selection, orbital mechanics for deployment, power generation architecture, and a risk mitigation strategy.