A Flagship-class Uranus Orbiter and Probe mission concept using aerocapture

Girija, Athul Pradeepkumar

doi:10.1016/j.actaastro.2022.10.005

Cited by 12 publications

(4 citation statements)

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“…( 2020 ) estimated that carrying a 30-kg probe and 4 kg of mounting hardware through the Uranus orbit insertion maneuver with a of 1680 m s −1 would consume 43 kg of additional propellant. The concern of additional propellant for orbit insertion prior to secondary probe release could be largely eliminated if the mission uses aerocapture for orbit insertion (Girija 2023 ), although a higher fidelity assessment is needed to understand the impacts of aerocapture on mission design, spacecraft design, and concept of operations.…”

Section: Opportunities and Challenges For Secondary Probesmentioning

confidence: 99%

Multiple Probe Measurements at Uranus Motivated by Spatial Variability

Wong,

Rowe-Gurney,

Markham

et al. 2024

Space Sci Rev

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A major motivation for multiple atmospheric probe measurements at Uranus is the understanding of dynamic processes that create and maintain spatial variation in thermal structure, composition, and horizontal winds. But origin questions—regarding the planet’s formation and evolution, and conditions in the protoplanetary disk—are also major science drivers for multiprobe exploration. Spatial variation in thermal structure reveals how the atmosphere transports heat from the interior, and measuring compositional variability in the atmosphere is key to ultimately gaining an understanding of the bulk abundances of several heavy elements. We review the current knowledge of spatial variability in Uranus’ atmosphere, and we outline how multiple probe exploration would advance our understanding of this variability. The other giant planets are discussed, both to connect multiprobe exploration of those atmospheres to open questions at Uranus, and to demonstrate how multiprobe exploration of Uranus itself is motivated by lessons learned about the spatial variation at Jupiter, Saturn, and Neptune. We outline the measurements of highest value from miniature secondary probes (which would complement more detailed investigation by a larger flagship probe), and present the path toward overcoming current challenges and uncertainties in areas including mission design, cost, trajectory, instrument maturity, power, and timeline.

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Section: Opportunities and Challenges For Secondary Probesmentioning

confidence: 99%

Multiple Probe Measurements at Uranus Motivated by Spatial Variability

Wong,

Rowe-Gurney,

Markham

et al. 2024

Space Sci Rev

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“…However, the demonstration of aerocapture at Mars or Venus will enhance its readiness for outer planet missions where its performance benefit is significantly greater [20,21]. Even though aerocapture is not currently considered for the Uranus Orbiter and Probe which is the top priority for the Flagship mission of the next decade [22,23], studies have shown aerocapture offers significant mission design advantages [24]. Aerocapture has also been shown to provide signficant benefits for a New Frontiers class Titan orbiter [25,26], and a Neptune Flagship mission [27,28].…”

Section: Applications For Future Missionsmentioning

confidence: 99%

“…For programmatic reasons, baseline Uranus mission architectures do not consider aerocapture [25,26]. However, aerocapture can offer significant mission design benefits for Uranus missions [27,28,29]. Figure 8 (bottom) shows the conditions for aerocapture at Uranus using an MSL-derived lift modulation vehicle (L/D = 0.24) entering at 29 km/s.…”

Section: Uranusmentioning

confidence: 99%

“…Due to risk considerations such as lack of confidence in the atmosphere models (potentially more perceived risk compared to actual risk), current baseline Uranus mission architectures have not used aerocapture [29,30]. However, aerocapture has been shown to offer significant benefits for future Uranus missions [31,32]. Two design reference missions are considered here.…”

Section: Uranusmentioning

confidence: 99%

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Small Low-Cost Orbiters for Planetary Science using Photon and Aerocapture

Pradeepkumar Girija

2023

Preprint

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With advancements in low-cost launchers and small interplanetary spacecraft, NASA has recognized the potential of small missions to perform focused planetary science investigations at Mars and Venus. The EscaPADE, part of the NASA SIMPLEx program will deliver two small spacecraft to elliptical orbits around Mars using the Photon spacecraft. Orbit insertion, particularly to low-circular orbits requires significant propellant, taking up a substantial fraction of the Photon wet mass and present a significant challenge for small missions. The large ΔV requirements for low-circular orbit make it difficult to insert small satellites into these orbits even with the highly capable Photon, as the total ΔV for Earth escape and orbit insertion exceeds its capability. Drag modulation aerocapture offers a promising alternative, using the atmospheric drag to obtain the large ΔV.The study shows how the Photon when combined with drag modulation aerocapture can deliver small orbiters to low-circular orbits, enabling a wide range of small orbiter missions. Aerocapture eliminates the need for Photon to provide 2 to 3.5 km/s of ΔV for orbit insertion, which translate into mass and cost savings, and can enable frequent low-cost small orbiters and small satellite constellations at Mars and Venus in the near future.

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