Supersonic Inflatable Aerodynamic Decelerators For Use on Future Robotic Missions to Mars

Clark, Ian G.; Hutchings, Allison; Tanner, Christopher; Braun, Robert D.

doi:10.1109/aero.2008.4526289

Cited by 30 publications

(31 citation statements)

References 9 publications

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“…Note, the IAD model considered here is similar to, but not identical to, the IAD model in previous works. 1,7,8,19 For example, inflation tubes are not considered in the model presented here. Nevertheless, the IAD model presented here is sufficiently close to the physical IAD model to evaluate our analytical methods.…”

Section: A the Grc Swt Iad Modelmentioning

confidence: 99%

“…This system is near the limits of current parachute technology and future missions with larger landed mass may find it necessary to resort to a different decelerator technology. 1,2 One alternative is the inflatable aerodynamic decelerator (IAD). The main advantage of IADs over parachutes is that they do not have the inflation instabilities that parachutes suffer at higher Mach numbers (M >∼ 1.5).…”

Section: Introductionmentioning

confidence: 99%

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Estimating the Collapse Pressure of an Inflatable Aerodynamic Decelerator

Baginski

Brakke

Cruz

2013

AIAA Aerodynamic Decelerator Systems (ADS) Conference

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Section: A the Grc Swt Iad Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Estimating the Collapse Pressure of an Inflatable Aerodynamic Decelerator

Baginski

Brakke

Cruz

2013

AIAA Aerodynamic Decelerator Systems (ADS) Conference

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“…A "tension cone" refers to a type of inflatable decelerator shaped so as to contain tensile stresses; e.g. see Clark et al (2009) Harri et al, 1999, andLinkin et al, 1998) for entry, descent and landing. Heavier semi-hard landers, e.g.…”

Section: Brief Overview Of Mars Lander Technologiesmentioning

confidence: 99%

The MetNet vehicle: a lander to deploy environmental stations for local and global investigations of Mars

Harri

Pichkadze

Zeleny³

et al. 2017

Geosci. Instrum. Method. Data Syst.

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Abstract. Investigations of global and related local phenomena on Mars such as atmospheric circulation patterns, boundary layer phenomena, water, dust and climatological cycles and investigations of the planetary interior would benefit from simultaneous, distributed in situ measurements. Practically, such an observation network would require low-mass landers, with a high packing density, so a large number of landers could be delivered to Mars with the minimum number of launchers.The Mars Network Lander (MetNet Lander; MNL), a small semi-hard lander/penetrator design with a payload mass fraction of approximately 17 %, has been developed, tested and prototyped. The MNL features an innovative Entry, Descent and Landing System (EDLS) that is based on inflatable structures. The EDLS is capable of decelerating the lander from interplanetary transfer trajectories down to a surface impact speed of 50-70 m s −1 with a deceleration of < 500 g for < 20 ms. The total mass of the prototype design is ≈ 24 kg, with ≈ 4 kg of mass available for the payload.The EDLS is designed to orient the penetrator for a vertical impact. As the payload bay will be embedded in the surface materials, the bay's temperature excursions will be much less than if it were fully exposed on the Martian surface, allowing a reduction in the amount of thermal insulation and savings on mass.The MNL is well suited for delivering meteorological and atmospheric instruments to the Martian surface. The payload concept also enables the use of other environmental instruments. The small size and low mass of a MNL makes it ideally suited for piggy-backing on larger spacecraft. MNLs are designed primarily for use as surface networks but could also be used as pathfinders for high-value landed missions.

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“…On the membrane aeroshell, a simple equation that considers the heat balance between the convective aerodynamic heating and radiative cooling was adopted as expressed in equation (3). The heat convection in the thickness direction was ignored on the aeroshell because the membrane aeroshell was very thin.…”

Section: Surface Heat Flux Q Intmentioning

confidence: 99%

“…Recently, NASA's Program to Advance Inflatable Decelerators for Atmospheric Entry (PAIDAE) started a program aimed at developing and implementing Inflatable Aerodynamic Decelerators (IAD) for both human and robotic use. To date, material development, mission and system design, wind-tunnel testing, and flight tests of deployable aerodynamic decelerators have been actively researched in this program 3,4) . On the other hand, since 2000, our group has researched and developed a flexible aeroshell for atmospheric entry capsules [5][6][7] , focusing on a flare-type aeroshell composed of a conical membrane and a ring-shaped outer frame attached to a blunt rigid capsule.…”

Section: Introductionmentioning

confidence: 99%

Hypersonic Wind Tunnel Test of a Flare-type Membrane Aeroshell for Atmospheric Entry Capsules

Yamada

Koyama

Kimura

et al. 2010

AEROSPACE TECHNOLOGY JAPAN

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A flexible aeroshell for atmospheric entry vehicles has attracted attention as an innovative space transportation system. In this study, hypersonic wind tunnel tests were carried out to investigate the behavior, aerodynamic characteristics and aerodynamic heating environment in hypersonic flow for a previously developed capsule-type vehicle with a flare-type membrane aeroshell made of ZYLON textile sustained by a rigid torus frame. Two different models with different flare angles (45º and 60º) were tested to experimentally clarify the effect of flare angle. Results indicate that flare angle of aeroshell has significant and complicate effect on flow field and aerodynamic heating in hypersonic flow at Mach 9.45 and the flare angle is very important parameter for vehicle design with the flare-type membrane aeroshell.

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Supersonic Inflatable Aerodynamic Decelerators For Use on Future Robotic Missions to Mars

Cited by 30 publications

References 9 publications

Estimating the Collapse Pressure of an Inflatable Aerodynamic Decelerator

Estimating the Collapse Pressure of an Inflatable Aerodynamic Decelerator

The MetNet vehicle: a lander to deploy environmental stations for local and global investigations of Mars

Hypersonic Wind Tunnel Test of a Flare-type Membrane Aeroshell for Atmospheric Entry Capsules

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