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Framework for the Multi-Objective Design Optimization of Aerocapture Missions

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Publicado no:Aerospace vol. 12, no. 5 (2025), p. 387
Autor principal: Urraza Atue Segundo
Outros Autores: Bruce, Paul
Publicado em:
MDPI AG
Assuntos:
Fuels
Design optimization
Atmospheric flight
Trajectory optimization
Success
Orbital maneuvers
Cost function
Decision making
Computational efficiency
Missions
Computing costs
Algorithms
Multiple objective analysis
Spacecraft
Airframes
Aerocapture
Trajectory planning
Uncertainty
Acesso em linha:Citation/Abstract
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Resumo:Developing spacecraft for efficient aerocapture missions demands managing extreme aerothermal environments, precise controls, and atmospheric uncertainties. Successful designs must integrate vehicle airframe considerations with trajectory planning, adhering to launcher dimension constraints and ensuring robustness against atmospheric and insertion uncertainties. To advance robust multi-objective optimization in this field, a new framework is presented, designed to rapidly analyze and optimize non-thrusting, fixed angle-of-attack aerocapture-capable spacecraft and their trajectories. The framework employs a three-degree-of-freedom atmospheric flight dynamics model incorporating planet-specific characteristics. Aerothermal effects are approximated using established Sutton–Graves, Tauber–Sutton, and Stefan–Boltzmann relations. The framework computes the resulting post-atmospheric pass orbit using an orbital element determination algorithm to estimate fuel requirements for orbital corrective maneuvers. A novel algorithm that consolidates multiple objective functions into a unified cost function is presented and demonstrated to achieve superior optima with computational efficiency compared to traditional multi-objective optimization approaches. Numerical examples demonstrate the methodology’s effectiveness and computational cost at optimizing terrestrial and Martian aerocapture maneuvers for minimum fuel, heat loads, peak heat transfers, and an overall optimal trajectory, including volumetric considerations.
ISSN:2226-4310
DOI:10.3390/aerospace12050387
Fonte:Advanced Technologies & Aerospace Database