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The numerical predictor-corrector guidance method with a linear bank angle parameterization has been widely applied to various atmospheric entry guidance problems. However, it has been found that the linear bank angle approach has limitations in satisfying the final state requirement of a specific type of atmospheric entry mission. In response, this paper proposes a novel bank angle parameterization based on a logistic function, which improves the energy preservation capability and increases the potential final altitude at the end of the entry phase. The paper also suggests a guideline to determine a guidance law activation point for better entry performance. Numerical simulations demonstrate that the proposed guidance scheme outperforms the linear bank profile approach and is suitable for future human Mars landing missions.
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This content will become publicly available on January 23, 2026
Hypersonic Entry Guidance via Numerical Predictor-Corrector Guidance
Entry guidance has played a vital role in planetary landing missions from the Apollo era to now. Modern techniques that directly utilize highly nonlinear entry dynamics, unlike the Apollo reentry guidance, are gaining attention. This study demonstrates that numerical predictor-corrector guidance can generate a trajectory that closely resembles the historic Apollo final reentry path. Secondly, it compares a conventional bank reversal algorithm with a prediction-based lateral guidance algorithm. Finally, the study proposes a predictive no-fly zone avoidance guidance algorithm that can effectively address geographic constraints for hypersonic gliding vehicles.
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- Award ID(s):
- 2327379
- PAR ID:
- 10567705
- Publisher / Repository:
- AIAA/AAS
- Date Published:
- Subject(s) / Keyword(s):
- Reentry Guidance Predictive control
- Format(s):
- Medium: X
- Location:
- Kaua'i, Hawaii
- Sponsoring Org:
- National Science Foundation
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