SmallSat Aerocapture to Enable a New Paradigm of Planetary Missions

Austin, Alex; Nelessen, Adam; Strauss, B.; Ravich, Joshua; Jesick, Mark; Venkatapathy, Ethiraj; Beck, Robin A.; Wercinski, Paul; Aftosmis, Michael J.; Wilder, Michael C.; Allen, Gary; Braun, Robert D.; Werner, Michael S.; Roelke, Evan

doi:10.1109/aero.2019.8742220

Cited by 7 publications

(5 citation statements)

References 13 publications

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“…Four different orbits with varying apoapses were considered. These include an apoapsis altitude of 5-, 10-, 15-, and 20 ×10 3 km, where the spacecraft was placed into this orbit with the apoapsis accuracy found in Austin et al [30]. From this paper the spacecraft was placed into an orbit with an apoapsis error described in Table 4.5.…”

Section: Simulation Resultsmentioning

confidence: 83%

“…Step 3 is the focus of this study as the actual aerocapture maneuver was not modeled but rather it was assumed that the satellite could be placed into an elliptical orbit with the accuracies found in a previous study. Austin et al [30] looked at the feasibility of delivering a small satellite into an elliptical orbit around Venus through an aerocapture, and provided the theoretical accuracy of the maneuver. Even though this study looks at an elliptical orbit around Mars these accuracies were assumed applicable.…”

Section: Reference Missionmentioning

confidence: 99%

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Nonlinear Estimation for Autonomous Optical Navigation

Hallgrimson¹

2021

Preprint

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Many interplanetary mission concepts can benefit from autonomous orbit estimation, particularly during critical mission phases. Previous studies have examined the feasibility of optical navigation using nanosatellite class instruments. While promising, these techniques are not without drawbacks. Convergence of the navigation estimates are often sensitive to errors in initial state estimates. This thesis compares various methods to perform nonlinear estimation for autonomous optical navigation. These methods include an extended Kalman filter (EKF), an unscented Kalman filter (UKF), a particle filter (PF), a fixed-lag smoother (FLS), and moving horizon estimation (MHE). The EKF, UKF, and PF can be implemented in real time, while the FLS and MHE implement a delay into the estimation process. To compare the performance of each state estimator three initial reference scenarios around Mars were considered: a hyperbolic flyby, an elliptic orbit and a orbital maneuver using observations of Mars and its moons. Parameter estimation was also explored, where the mass of Mars was to be estimated as a reference parameter in both the hyperbolic and elliptical trajectories. One last reference scenario included a low Earth orbit (LEO) using observations of satellites in a geosynchronous equatorial orbit. In each case, the FLS and MHE showed similar or better performance over each state estimator but at the cost of an increased computation time with respect to the reference EKF. Similarly the UKF was able to provide improved results withe respect to the EKF. While, the PF provided poor estimates in the Mars trajectories but improvements were seen from the UKF and EKF in the LEO scenario.

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Section: Simulation Resultsmentioning

confidence: 83%

Section: Reference Missionmentioning

confidence: 99%

Nonlinear Estimation for Autonomous Optical Navigation

Hallgrimson¹

2021

Preprint

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“…Unlike the entry state, the numerical predictor guidance always uses the nominal values for β and L∕D, whereas the true state is propagated using the dispersed values for each trial, resulting in an imperfect predictor. The uniform 5% dispersion for these vehicle parameters represents modeling uncertainty associated with computational fluid dynamics analysis and ballistic range testing, and is based on values used in previous studies [55].…”

Section: Performance Under Uncertaintymentioning

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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“…Prior studies have highlighted the benefits that aerocapture technology can bring to large missions, and recent studies have focused on how the technology can enable small satellites to enter orbit [5]. Aerocapture is particularly well suited for SmallSat orbit insertion, due to the difficulty of designing and integrating a propulsion system to perform kilometers per second of delta-V on a small platform.…”

Section: Aerocapture Overviewmentioning

confidence: 99%

“…SmallSat aerocapture has been the focus of significant research and technology development in the last five years, focused on developing a simple and costeffective atmospheric control method that is implementable on a small spacecraft within the constraints of a SIMPLEx-class mission [13]. The simplest form of drag modulation aerocapture is the single-stage discreteevent architecture (Figure 3) [4].…”

Section: Aerocapture To Enable Planetary Small Satellite Science Missions (Simplex)mentioning

confidence: 99%