The Hypersonic Inflatable Aerodynamic Decelerator (HIAD) Mission Applications Study

Bose, David M.; Winski, Richard G.; Shidner, Jeremy D.; Zumwalt, Carlie H.; Johnston, Christopher O.; Komar, David R.; Cheatwood, F. McNeil; Hughes, Stephen J.

doi:10.2514/6.2013-1389

Cited by 17 publications

(9 citation statements)

References 14 publications

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“…HIADs use a flexible TPS for the inflated portion of the structure and can use various other forms of TPS for the rigid center structure. 7 An artistic rendering of the HIAD with potential payload placement is seen in Figure 1a.…”

Section: Vehicle Designsmentioning

confidence: 99%

Optimization of a Hot Structure Aeroshell and Nose Cap for Mars Atmospheric Entry

et al. 2016

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The National Aeronautics and Space Administration (NASA) is preparing to send humans beyond Low Earth Orbit and eventually to the surface of Mars. As part of the Evolvable Mars Campaign, different vehicle configurations are being designed and considered for delivering large payloads to the surface of Mars. Weight and packing volume are driving factors in the vehicle design, and the thermal protection system (TPS) for planetary entry is a technology area which can offer potential weight and volume savings. The feasibility and potential benefits of a ceramic matrix composite hot structure concept for different vehicle configurations are explored in this paper, including the nose cap for a Hypersonic Inflatable Aerodynamic Decelerator (HIAD) and an aeroshell for a mid liftto-drag (Mid L/D) concept. The TPS of a planetary entry vehicle is a critical component required to survive the severe aerodynamic heating environment during atmospheric entry. The current state-of-the-art is an ablative material to protect the vehicle from the heat load. The ablator is bonded to an underlying structure, which carries the mechanical loads associated with entry. The alternative hot structure design utilizes an advanced carbon-carbon material system on the outer surface of the vehicle, which is exposed to the severe heating and acts as a load carrying structure. The preliminary design using the hot structure concept and the ablative concept is determined for the spherical nose cap of the HIAD entry vehicle and the aeroshell of the Mid L/D entry vehicle. The results of the study indicate that the use of hot structures for both vehicle concepts leads to a feasible design with potential weight and volume savings benefits over current state-of-the-art TPS technology that could enable future missions.

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Section: Vehicle Designsmentioning

confidence: 99%

Optimization of a Hot Structure Aeroshell and Nose Cap for Mars Atmospheric Entry

et al. 2016

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“…Hypersonic Inflatable Aerodynamic Decelerator (HIAD) concepts are currently being developed at NASA. 4 Flexible insulative TPS presently developed for HIAD concepts is limited to a maximum entry heating rate of 75 W/ cm 2 to 100 W/ cm 2 , therefore requiring large decelerator diameters of 10 m to 15 m, thus limiting the application of this TPS to missions with low to medium entry velocities. Use of flexible ablative TPS for HIAD concepts could potentially withstand heating rates up to 200 W/cm 2 with corresponding shorter aerocapture/entry durations; and thus require a smaller decelerator diameter of 5 m. 5 Even though flexible ablative and insulative TPS HIAD concepts are very promising, they may not be able to cover the entire design space needed for various planetary entry systems.…”

Section: Introductionmentioning

confidence: 99%

A Multifunctional Hot Structure Heat Shield Concept for Planetary Entry

Walker¹,

Daryabeigi²,

Samareh³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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A multifunctional hot structure heatshield concept is being developed to provide technology enhancements with significant benefits compared to the current state-of-the-art heatshield technology. These benefits can potentially enable future planetary missions. The concept is unique in integrating the function of the thermal protection system with the primary load carrying structural component. An advanced carbon-carbon material system has been evaluated for the load carrying structure, which will be utilized on the outer surface of the heatshield, and thus will operate as a hot structure exposed to the severe aerodynamic heating associated with planetary entry. Flexible, highly efficient blanket insulation is sized for use underneath the hot structure to maintain required operational internal temperatures. The approach followed includes developing preliminary designs to demonstrate feasibility of the concept and benefits over a traditional, baseline design. Where prior work focused on a concept for an Earth entry vehicle, the current efforts presented here are focused on developing a generic heatshield model and performing a trade study for a Mars entry application. This trade study includes both structural and thermal evaluation. The results indicate that a hot structure concept is a feasible alternative to traditional heatshields and may offer advantages that can enable future entry missions.

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“…To increase the drag area and still meet launch vehicle constraints, a hypersonic inflatable aerodynamic decelerator (HIAD) and a supersonic inflatable aerodynamic decelerator (SIAD) are being investigated for future Mars missions [2][3][4][5][6]. One part of the low density supersonic decelerator (LDSD) system, the SIAD, had two test flights, one in 2014 and the other in 2015 [7][8][9].…”

Section: Introductionmentioning

confidence: 99%

Precision Guidance for Mars Entry with a Supersonic Inflatable Aerodynamic Decelerator

Liang

Mease

2019

Journal of Guidance, Control, and Dynamics

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The Hypersonic Inflatable Aerodynamic Decelerator (HIAD) Mission Applications Study

Cited by 17 publications

References 14 publications

Optimization of a Hot Structure Aeroshell and Nose Cap for Mars Atmospheric Entry

Optimization of a Hot Structure Aeroshell and Nose Cap for Mars Atmospheric Entry

A Multifunctional Hot Structure Heat Shield Concept for Planetary Entry

Precision Guidance for Mars Entry with a Supersonic Inflatable Aerodynamic Decelerator

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