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<p>This study presents a novel asteroid deflection strategy that integrates an intelligent Fuzzy Logic Decision-Making (FLDM) controller to autonomously manage the on/off operation of thrusters on a tractor spacecraft attached to the Didymos asteroid. The controller evaluates real-time orbital parameters, namely orbital phase, distance ratio, and velocity ratio to apply heuristic, context-aware thrust commands aimed at optimizing propellant use and trajectory control. An analysis initialized at perihelion demonstrates the method’s effectiveness: a total deflection of 49.124 (m) and a ΔV of 0.038 <InlineEquation ID="IEq1"> <EquationSource Format="TEX">\(\:\left(\frac{mm}{s}\right)\)</EquationSource> </InlineEquation> were achieved with 860.14 (kg) of propellant consumption. The FLDM system maintained stable deflection accumulation, evidenced by a low deflection-rate variance of 1.22<InlineEquation ID="IEq2"> <EquationSource Format="TEX">\(\:{10}^{-10}\)</EquationSource> </InlineEquation> (<InlineEquation ID="IEq3"> <EquationSource Format="TEX">\(\:\frac{m}{s}\)</EquationSource> </InlineEquation>)², and effectively managed thruster activity, with duty cycles of 20.1% and 77.5% for the primary and fine-adjustment thrusters, respectively. The results confirm that fuzzy logic control can mitigate unstable oscillatory behavior, enabling a feasible, fuel-efficient, and stable deflection strategy for planetary defense applications.</p>

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Intelligent Thruster Policy for Asteroid Deflection Regarding: A Fuzzy Logic Control Approach Applied to Didymos

  • 期刊论文

  • 发表日期：

    2026年7月30日

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  • Iman Shafieenejad

摘要

This study presents a novel asteroid deflection strategy that integrates an intelligent Fuzzy Logic Decision-Making (FLDM) controller to autonomously manage the on/off operation of thrusters on a tractor spacecraft attached to the Didymos asteroid. The controller evaluates real-time orbital parameters, namely orbital phase, distance ratio, and velocity ratio to apply heuristic, context-aware thrust commands aimed at optimizing propellant use and trajectory control. An analysis initialized at perihelion demonstrates the method’s effectiveness: a total deflection of 49.124 (m) and a ΔV of 0.038 \(\:\left(\frac{mm}{s}\right)\) were achieved with 860.14 (kg) of propellant consumption. The FLDM system maintained stable deflection accumulation, evidenced by a low deflection-rate variance of 1.22 \(\:{10}^{-10}\) ( \(\:\frac{m}{s}\) )², and effectively managed thruster activity, with duty cycles of 20.1% and 77.5% for the primary and fine-adjustment thrusters, respectively. The results confirm that fuzzy logic control can mitigate unstable oscillatory behavior, enabling a feasible, fuel-efficient, and stable deflection strategy for planetary defense applications.