The Small Mars System

Fantino, Elena; Grassi, Michele; Pasolini, Pietro; Causa, Flavia; Molfese, C.; Aurigemma, Renato; Cimminiello, N.; Torre, Dominique; Dell'Aversana, P.; Esposito, F.; Gramiccia, L.; Paudice, F.; Punzo, F.; Roma, Ilaria; Savino, Raffaele; Zuppardi, Gennaro

doi:10.1016/j.actaastro.2017.04.024

Cited by 5 publications

(3 citation statements)

References 18 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The foldable mechanisms utilise umbrella-like designs where a skirt made of flexible thermal protection materials is bounded onto rigid deployable ribs. Revolute or translational joints allow the ribs to fold and unfold, thereby deploy the skirt and potentially perform flight manoeuvres by manipulating the skirt's shape [24,25,26,27,28,29,30,31].…”

Section: Introductionmentioning

confidence: 99%

Deployable self-regulating centrifugally-stiffened decelerator (DESCENT): Design scalability and low altitude drop test

Roberts

et al. 2021

Aerospace Science and Technology

View full text Add to dashboard Cite

Section: Introductionmentioning

confidence: 99%

Deployable self-regulating centrifugally-stiffened decelerator (DESCENT): Design scalability and low altitude drop test

Roberts

et al. 2021

Aerospace Science and Technology

View full text Add to dashboard Cite

“…Examples can be found in the use of miniaturized COTS solid-state sensors [ 3 , 4 , 5 ], or MEMS-NEMS, [ 6 ], or even micro-propulsion systems [ 7 , 8 , 9 ]. Besides the obvious cost reduction, payload miniaturization allows the use of smaller spacecraft, such as penetrators [ 10 , 11 ], or the possibility of placing the sensors in small rovers [ 12 ], and landers [ 13 , 14 ]. It may also enable the use of the sensors in aerial platforms [ 15 , 16 , 17 , 18 ], or increase the science output in opportunistic missions.…”

Section: Introductionmentioning

confidence: 99%

Analyzing the Performance of a Miniature 3D Wind Sensor for Mars

Domínguez-Pumar

Kowalski

Jiménez

et al. 2020

Sensors

View full text Add to dashboard Cite

This paper analyzes the behavior of a miniature 3D wind sensor designed for Mars atmosphere. The sensor is a spherical structure of 10 mm diameter divided in four sectors. By setting all the sectors to constant temperature, above that of the air, the 3D wind velocity vector can be measured. Two sets of experiments have been performed. First, an experimental campaign made under typical Mars conditions at the Aarhus Wind Tunnel Simulator is presented. The results demonstrate that both wind speed and angle can be efficiently measured, using a simple inverse algorithm. The effect of sudden wind changes is also analyzed and fast response times in the range of 0.7 s are obtained. The second set of experiments is focused on analyzing the performance of the sensor under extreme Martian wind conditions, reaching and going beyond the Dust Devil scale. To this purpose, both high-fidelity numerical simulations of fluid dynamics and heat transfer and experiments with the sensor have been performed. The results of the experiments, made for winds in the Reynolds number 1000–2000 range, which represent 65–130 m/s of wind speed under typical Mars conditions, further confirm the simulation predictions and show that it will be possible to successfully measure wind speed and direction even under these extreme regimes.

show abstract

“…Deployable aerodynamic decelerators for atmospheric entry have been attracting increasing attention due to the demand for a next generation Mars entry system for heavy payloads, as well as a small recoverable orbital scientific platform, such as a CubeSat that can de-orbit and recover the payload using a re-entry vehicle [1,2,3,4,5,6,7,8,9]. The advantages of deployable heat shields over conventional rigid ones mainly come from two aspects [4, 10]:…”

Section: Introductionmentioning

confidence: 99%