Hypercone Inflatable Supersonic Decelerator

Brown, Glen; Epp, Chirold; Graves, Claude; Lingard, Steve; Darley, Matthew G.; Jordan, Kenneth G.

doi:10.2514/6.2003-2167

Cited by 18 publications

(7 citation statements)

References 2 publications

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“…SAPE has many capabilities, but for the purposes of this study it is used to quickly produce a Master Equipment List (MEL) and mass estimate for the vehicles aerocapture HIAD, separation system, and EDL HIAD. SAPE contains a number of mass models for HIAD systems including flexible Thermal Protection System (TPS) [6], inflatable structure [7][8], inflation system [9], and rigid nose [10]. These were created by interviewing HIAD subject matter experts and using their previous works.…”

Section: Methods: Sape Sape-c and Associated Toolsmentioning

confidence: 99%

A Cost Modeling Approach for Entry Systems Analysis of Human Mars Missions

Friz

Samareh

Hosder

2018

2018 AIAA SPACE and Astronautics Forum and Exposition

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Cost is one of the biggest obstacles to sending humans to Mars. However, spacecraft costs are typically not estimated until after the preliminary vehicle and mission concepts have been designed. By automating the cost estimation process, the effect of any change in vehicle or mission design on the mission cost can be determined more efficiently. This paper describes an extension to the tool Systems Analysis for Planetary Entry, Descent, and Landing which integrates the cost modeling software System Estimation and Evaluation of Resources-Hardware with a number of systems analysis tools. This new method is used to analyze several tradespaces of an entry vehicle for human Mars missions utilizing a Hypersonic Inflatable Aerodynamic Decelerator and provide preliminary results. Key findings include quantifying how ballistic coefficient, main engine specific impulse, and thrust to weight ratio affect the cost of the vehicle and how the payload per lander and number of landers affects the cost of a campaign to Mars.

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Section: Methods: Sape Sape-c and Associated Toolsmentioning

confidence: 99%

A Cost Modeling Approach for Entry Systems Analysis of Human Mars Missions

Friz

Samareh

Hosder

2018

2018 AIAA SPACE and Astronautics Forum and Exposition

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“…The tension cone SIAD requires an onboard inflation system. This device comes in various configurations, including a high-pressure vessel gas system or a chemical reaction gas system [22,25]. The isotensoid IADs use an alternative inflation process.…”

Section: Decelerator Configurationsmentioning

confidence: 99%

Investigation of Drag-Modulated Supersonic Inflatable Aerodynamic Decelerators for Sounding Rocket Payloads

Miller

Steinfeldt

Braun

2015

Journal of Spacecraft and Rockets

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The goal of this investigation is to understand the sizing and performance of supersonic inflatable aerodynamic decelerators for Earth-based sounding rocket applications. The recovery system under examination is composed of a supersonic inflatable aerodynamic decelerator and a guided parafoil system to achieve sub-100 m miss distances. Three supersonic inflatable aerodynamic decelerator configurations (tension cone, attached isotensoid, and trailing isotensoid) are examined using the metrics of decelerator mass, aerodynamic performance, and vehicle integration. In terms of aerodynamic performance, the tension cone is the preferred choice for the sizes investigated. The attached isotensoid was shown to be the most mass efficient decelerator, whereas the trailing isotensoid was found to be the more ideal decelerator for vehicle integration. A three-degree-of-freedom trajectory simulation is used in conjunction with Monte Carlo uncertainty analysis to assess the landed accuracy capability of the proposed architectures. In 95% of the cases examined, the drag-modulated inflatable aerodynamic decelerator provides arrivals within the 10 km parafoil capability region, meeting the sub-100 m landed recovery goals. In 76% of the cases examined, the dragmodulated inflatable aerodynamic decelerator arrives within 5 km of this target zone. Nomenclaturenumber m = mass, kg q = dynamic pressure, N∕m 2 S = area, m 2 s = downrange, m T = reference temperature, K t = time, s u = eastward wind velocity, m∕s V = velocity, m∕s v = northward wind velocity, m∕s β = ballistic coefficient equal to m∕C D A, kg∕m 2 δDR = change in downrange, km λ = launch elevation angle, deg Subscripts D = drag deploy = deployment est = estimate f = areal max = maximum min = minimum para = parafoil ref = reference target = target

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“…This device can be a pressure vessel with inert gas stored at high pressures or a system which expels gas as a by-product of a chemical reaction. 43 -Pre-inflation gas system is a gas generation system need to expose the ram-air inlets to the free stream. This is usually a small vial of methyl alcohol.…”

Section: Vehicle Integrationmentioning

confidence: 99%

Supersonic Inflatable Aerodynamic Decelerators for use on Sounding Rocket Payloads

Miller

Steinfeldt

Braun

2014

AIAA Atmospheric Flight Mechanics Conference

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This paper presents an assessment of a supersonic inflatable aerodynamic decelerator for use on a sounding rocket payload bus structure for a high-altitude sample return mission. Three decelerator configurations, the tension cone, attached isotensoid, and the trailing isotensoid, were examined on the metrics of decelerator mass, aerodynamic performance, and vehicle integration. The attached isotensoid configuration is shown to be the least mass solution. Aerodynamic analysis shows that a drag performance degradation of up to 40% for the attached decelerators results when the attachment point is recessed from the forebody of the bus structure. Vehicle integration mechanisms are identified and examined for each decelerator configuration. Using multiattribute decision making techniques, the trailing isotensoid is identified to be the most advantageous decelerator option for use in this application.

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Hypercone Inflatable Supersonic Decelerator

Cited by 18 publications

References 2 publications

A Cost Modeling Approach for Entry Systems Analysis of Human Mars Missions

A Cost Modeling Approach for Entry Systems Analysis of Human Mars Missions

Investigation of Drag-Modulated Supersonic Inflatable Aerodynamic Decelerators for Sounding Rocket Payloads

Supersonic Inflatable Aerodynamic Decelerators for use on Sounding Rocket Payloads

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