Defense methods for distributed asteroid deflection by multiple spacecraft considering uncertainties

By employing a multi-spacecraft distributed deflection strategy and utilizing a genetic algorithm to optimize impact time and orientation angle, the problem of launch vehicle capacity limitations was solved, achieving effective defense against asteroids, reducing the risk of fragmentation and multiple debris scattering, and improving deflection performance.

CN117631680BActive Publication Date: 2026-06-30NORTHWESTERN POLYTECHNICAL UNIV
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
NORTHWESTERN POLYTECHNICAL UNIV
Filing Date
2023-11-03
Publication Date
2026-06-30

AI Technical Summary

Technical Problem

Existing kinetic impact methods are limited by the carrying capacity of launch vehicles, making it difficult to effectively defend against asteroids with large mass and volume. Furthermore, the energy released during the impact may exceed the asteroid's tolerance range, increasing the risk of fragmentation and multiple debris falling to Earth.

Method used

A distributed deflection strategy involving multiple spacecraft is adopted. The impact time and orientation angle are optimized through a genetic algorithm. Multiple spacecraft are used to impact the asteroid in a distributed manner to reasonably disperse the impact energy, reduce the risk of structural damage caused by single-point impact, and formulate a defense strategy that takes into account uncertainties.

Benefits of technology

It effectively overcomes the limitations of launch vehicle capacity, reduces the risk of asteroid fragmentation and multiple debris falling to Earth, improves asteroid defense capabilities, and achieves better deflection effects.

✦ Generated by Eureka AI based on patent content.

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Abstract

This application relates to the field of asteroid defense technology and discloses a multi-spacecraft distributed deflection defense method for asteroids that considers uncertainties. The method includes: selecting a target asteroid and determining the total number of spacecraft participating in the defense and their initial parameters; establishing a first functional relationship between the state information of each spacecraft upon arrival at the target asteroid and the time window, based on the orbital parameters of Earth, the target asteroid, and the initial parameters of the spacecraft; establishing a second functional relationship between the total deflection and the time window and orientation angle corresponding to each spacecraft, based on a deflection model considering impact uncertainties, the state information of each spacecraft upon arrival at the target asteroid, and the first functional relationships; and optimizing the second functional relationship using a genetic algorithm to determine the optimal time window and orientation angle corresponding to each spacecraft when the total deflection reaches its maximum value, thereby formulating a defense strategy for the target asteroid and providing better asteroid defense capabilities.
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