Apollo-Derived Terminal Control for Bank-Modulated Mars Entries with Altitude Maximization

Garcia-Llama, Eduardo

doi:10.2514/6.2008-6819

Cited by 12 publications

(5 citation statements)

References 4 publications

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“…11 However, as shown by Garcia-Llama and others, optimal trajectories are often not robust to day-of-flight uncertainties in vehicle, environmental, and state parameters. 12 This study seeks to use optimal trajectory results to inform flight strategies, rather than dictate them, to achieve robust flight performance for high ballistic coefficient vehicles.…”

Section: Maximum Altitude At Terminal Descent Initiationmentioning

confidence: 99%

“…Initial Velocity, km/s 6 8 Initial (10), (11), and (12) where u and v are the horizontal and vertical components of velocity, g is the gravitational acceleration, T is the total thrust, µ is the constant thrust angle (defined as zero facing forwards along the horizon), m 0 is the starting vehicle mass, g 0 is the gravitational acceleration on Earth, and I sp is the propulsion system specific impulse.…”

Section: Altitude Difference Kmmentioning

confidence: 99%

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Strategies for Landing Large Ballistic Coefficient Vehicles on Mars

Anderson

Putnam

Braun

2016

AIAA Atmospheric Flight Mechanics Conference

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Large ballistic coefficient entry, descent, and landing vehicles are likely required to achieve more ambitious exploration goals at Mars. This paper investigates strategies for safe landing on Mars for vehicles with large ballistic coefficients, with a focus on maintaining sufficient altitude for terminal descent. Specifically, requirements and guidance strategies for the use of aerodynamic lift in the hypersonic regime are assessed over a range of ballistic coefficients. Results indicate that, for moderately high ballistic coefficients, judicious use of lift may allow safe landing. These strategies may be applicable to future large-scale robotic or human entry, descent, and landing architectures.

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Section: Maximum Altitude At Terminal Descent Initiationmentioning

confidence: 99%

Section: Altitude Difference Kmmentioning

confidence: 99%

Strategies for Landing Large Ballistic Coefficient Vehicles on Mars

Anderson

Putnam

Braun

2016

AIAA Atmospheric Flight Mechanics Conference

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“…It is hoped that this work will continue in the future and include consideration of guidance performance; one positive result for bank-only modulation is reported by Ref. 10.…”

Section: Study Limitations and Considerations For Future Workmentioning

confidence: 99%

Angle of Attack Modulation for Mars Entry Terminal State Optimization

Lafleur

Cerimele

2009

AIAA Atmospheric Flight Mechanics Conference

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From the perspective of atmospheric entry, descent, and landing (EDL), one of the most foreboding destinations in the solar system is Mars due in part to its exceedingly thin atmosphere. To benchmark best possible scenarios for evaluation of potential Mars EDL system designs, a study is conducted to optimize the entry-to-terminal-state portion of EDL for a variety of entry velocities and vehicle masses, focusing on the identification of potential benefits of enabling angle of attack modulation. The terminal state is envisioned as one appropriate for the initiation of terminal descent via parachute or other means. A particle swarm optimizer varies entry flight path angle, ten bank profile points, and ten angle of attack profile points to find maximum

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“…Entry, descent, and landing (EDL) phases pose difficult challenges to Mars missions. For an MSL-type mission, the maximum final altitude is desired because it is typically a concern and a limitation to the use of parachutes or other aerodynamicallydriven deceleration mechanisms [2]- [4]. For a preliminary design phase of a Mars mission, and before the selection of the landing site, the entry trajectory is often optimized and designed to achieve the highest parachute deployment altitude [3]- [5].…”

Section: Introductionmentioning

confidence: 99%

Entry Trajectory Optimization for Mars Science Laboratory Class Missions Using Indirect Unified Trigonometrization Method

Mall¹,

Taheri²

2019

Preprint

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Application of traditional indirect optimization methods to optimal control problems (OCPs) with control and state path constraints is not a straightforward task. However, recent advances in regularization techniques and numerical continuation methods have enabled application of indirect methods to very complex OCPs. This study demonstrates the utility and application of an advanced indirect method, the Unified Trigonometrization Method (UTM), to a Mars Science Laboratory type entry problem. The objective is to maximize the parachute deployment altitude for a free-time, fixed-finalvelocity entry trajectory. For entry vehicles, in addition to the bank angle that is characterized by bang-bang control profiles, there are typically three state path constraints that have to be considered, namely, the dynamic pressure, heat rate and g-load. This study shows that the UTM enables simultaneous regularization of the bang-bang control and satisfaction of the state path constraints. Two scenarios with and without state path constraints are considered. The results obtained using the UTM for both of these cases are found to be in excellent agreement with a direct optimization method. Furthermore, an interesting feature emerges in the optimal control profile of the UTM during the initial high-altitude part of the resulting optimal trajectory for the scenario with state path constraints, which has an appealing practical implication.

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Apollo-Derived Terminal Control for Bank-Modulated Mars Entries with Altitude Maximization

Cited by 12 publications

References 4 publications

Strategies for Landing Large Ballistic Coefficient Vehicles on Mars

Strategies for Landing Large Ballistic Coefficient Vehicles on Mars

Angle of Attack Modulation for Mars Entry Terminal State Optimization

Entry Trajectory Optimization for Mars Science Laboratory Class Missions Using Indirect Unified Trigonometrization Method

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