Aerocapture Trajectory Design in Uncertain Entry Environments

Heidrich, Casey R.; Braun, Robert D.

doi:10.2514/6.2020-1741

Cited by 7 publications

(2 citation statements)

References 36 publications

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“…Concept studies have shown that using aerocapture in place of an all-propulsive system can increase the delivered mass to a science orbit around Neptune by 1.4 times [12,26,27], can decrease the required launch mass for a Mars robotic mission by 3-4 times [28], and can decrease the required mass for a Titan robotic mission by between 40 and 80% [29,30]. While recent works have studied open-loop aerocapture with parametric uncertainty [31] and with density uncertainty modeled as a GRF [1,32]…”

Section: B Aerocapturementioning

confidence: 99%

Chance-Constrained Covariance Steering in a Gaussian Random Field via Successive Convex Programming

Ridderhof¹,

Tsiotras²

2021

Preprint

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The problem of optimizing affine feedback laws that explicitly steer the mean and covariance of an uncertain system state in the presence of a Gaussian random field is considered. Spatiallydependent disturbances are successively approximated with respect to a nominal trajectory by a sequence of jointly Gaussian random vectors. Sequential updates to the nominal control inputs are computed via convex optimization that includes the effect of affine state feedback, the perturbing effects of spatial disturbances, and chance constraints on the closed-loop state and control. The developed method is applied to solve for an affine feedback law to minimize the 99 th percentile of Δ𝑣 required to complete an aerocapture mission around a planet with a randomly disturbed atmosphere.

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Section: B Aerocapturementioning

confidence: 99%

Chance-Constrained Covariance Steering in a Gaussian Random Field via Successive Convex Programming

Ridderhof¹,

Tsiotras²

2021

Preprint

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“…This technique has been studied for decades, but not implemented in flight. In recent years, significant work has contributed to the development of aerocapture and related technologies, including development of advanced thermal protection systems [8], robust flight-control methods and guidance algorithms [9][10][11], uncertainty quantification [12][13][14][15], deployable decelerator technology [6,16,17], and broad aerocapture technology studies [18][19][20] to list a few. A 2016 study at the NASA Jet Propulsion Laboratory concluded that, while aerocapture technology readiness is destination dependent, no prior flight demonstration would be needed to implement aerocapture on Titan, Mars, and possibly Venus [18].…”

Section: Introductionmentioning

confidence: 99%

Flight Mechanics Feasibility Assessment for Co-Delivery of Direct-Entry Probe and Aerocapture Orbiter

Albert

Schaub

Braun

2022

Journal of Spacecraft and Rockets

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The co-delivery of a direct-entry probe and an aerocapture orbiter from a single atmospheric entry state is a novel way to include ride-along probes or orbiters on interplanetary missions. This is made possible through combining two technologies: low-cost small satellites and aerocapture. This study investigates the feasibility of this co-delivery method from a flight-mechanics perspective. The availability of direct-entry and aerocapture trajectories from a single entry flight-path angle is assessed for a large range of feasible ballistic coefficients at Earth, Mars, Venus, Titan, and Neptune. Apoapsis altitude, peak heat flux, total heat load, and peak g-load are also quantified across this trade space. A representative scenario implementing closed-loop guidance is presented for a proof of concept, and the trajectory dispersions due to relevant uncertainties are quantified in a Monte Carlo analysis. Passive ballistic impactor or penetrator probes as a secondary mission with a primary lift-modulated aerocapture orbiter is identified as the most promising configuration.

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