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Daniel Guggenheim School of Aerospace Engineering

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Author: Werner, Michael S. × End date: 2017 × Start date: 2017 × Item Type: Publication × search.filters.applied.f.isOrgUnitOfPublicationTitle: Space Systems Design Laboratory (SSDL) ×

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Development of an Earth SmallSat Flight Test to Demonstrate Viability of Mars Aerocapture

2017-05-01 , Werner, Michael S.

A smallsat mission concept is developed to demonstrate the feasibility of an aerocapture system at Earth. The proposed mission utilizes aerocapture to transfer from a GTO rideshare trajectory to a LEO. Single-event drag modulation is used as a simple means of achieving the control required during the maneuver. Low- and high-fidelity guidance algorithm choices are considered. Numeric trajectory simulations and Monte Carlo uncertainty analyses are performed to show the robustness of the system to day-of-flight environments and uncertainties. Similar investigations are performed at Mars to show the relevance of the proposed mission concept to potential future applications. The spacecraft design consists of a 24.9 kg vehicle with an attached rigid drag skirt, and features commercially-available hardware to enable flight system construction at a university scale. Results indicate that the proposed design is capable of targeting the desired final orbit, surviving the aerothermodynamic and deceleration environments produced during aerocapture, and downlinking relevant data following the maneuver

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Characterization of Guidance Algorithm Performance for Drag Modulation-Based Aerocapture

2017-02 , Werner, Michael S. , Braun, Robert D.

Discrete-event drag modulation systems are an attractive option for flight control during aerocapture. These systems require precise timing of the drag modulation events to ensure accurate final orbit delivery. Two different guidance schemes for discrete-event drag-modulated aerocapture are evaluated: a heuristic deceleration profile curve-fit method and a higher-fidelity numeric predictor-corrector algorithm. The accuracy and computational performance of these algorithms is examined in a series of Monte-Carlo simulations of aerocapture missions at Earth, Mars, and Titan. Results indicate that while the deceleration curve-fit method requires minimal amounts of computation time, additional modifications must be made to ensure its robustness to day-of-flight uncertainties. At both low and medium guidance rates, the numeric predictor-corrector algorithm is able to effectively guide drag modulation events in the face of uncertainty.

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Development of an Earth Smallsat Flight Test to Demonstrate Viability of Mars Aerocapture

2017-01 , Werner, Michael S. , Woollard, Bryce A. , Tadanki, Anirudh , Pujari, S. R. , Braun, Robert D. , Lock, Robert E. , Nelessen, Adam P. , Woolley, Ryan C.

A smallsat mission concept is developed to demonstrate the feasibility of an aerocapture system at Earth. The proposed mission utilizes aerocapture to transfer from a GTO rideshare trajectory to a LEO. Single-event drag modulation is used as a simple means of achieving the control required during the maneuver. Numeric trajectory simulations and Monte Carlo uncertainty analyses are performed to show the robustness of the system to day-of-flight environments and uncertainties. Similar investigations are performed at Mars to show the relevance of the proposed mission concept to potential future applications. The spacecraft design consists of a 24.9 kg vehicle with an attached rigid drag skirt, and features commercially-available hardware to enable flight system construction at a university scale. Results indicate that the proposed design is capable of targeting the desired final orbit, surviving the aerothermodynamic and deceleration environments produced during aerocapture, and downlinking relevant data following the maneuver.

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