Overview of the NASA Entry, Descent and Landing Systems Analysis Stud

Zang, Thomas A.; Dwyer-Cianciolo, Alicia M.; Kinney, David J.; Howard, Austin; Chen, George T.; Ivanov, Mark C.; Sostaric, Ronald R.; Westhelle, Carlos H.

doi:10.2514/6.2010-8649

Cited by 32 publications

(21 citation statements)

References 10 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…2 Aerospace Engineer, Aerothermodynamics Branch, m/s 408a, AIAA Senior Member. 3 To date, only a handful of studies have been conducted to understand the fluid dynamic phenomena associated with SRP; most of those studies were performed decades ago, for example see Ref. 8.…”

Section: Introductionmentioning

confidence: 99%

Supersonic Retropropulsion Experimental Results from the NASA Ames 9- x 7-Foot Supersonic Wind Tunnel

Berry

Rhode

Edquist

2012

42nd AIAA Fluid Dynamics Conference and Exhibit

View full text Add to dashboard Cite

Section: Introductionmentioning

confidence: 99%

Supersonic Retropropulsion Experimental Results from the NASA Ames 9- x 7-Foot Supersonic Wind Tunnel

Berry

Rhode

Edquist

2012

42nd AIAA Fluid Dynamics Conference and Exhibit

View full text Add to dashboard Cite

“…The inflatable crew module will include more robust radiation protection. The standard BA-330 46 cm thick shell of materials including Kevlar, Nextel, and Nomex Fabric, will protect the crew [11] [15]. The inflatable module will also house a central core, which contains crew sleeping quarters, protected by additional shielding of 1 cm of aluminum and 6 cm of water.…”

Section: A Mars Transfer Vehiclementioning

confidence: 99%

“…These systems are currently in development and have a TRL of 4. Using this large shield, the spacecraft will be decelerated to subsonic speeds where a set of CH4/LOX retrorockets (explained later) will guide the vehicle as precisely as possible to its desired landing site [15].…”

Section: B Mars Cargo Vehiclementioning

confidence: 99%

NERIO-I: Nuclear Explorations for Realizing Interplanetary Objectives I

Leung

2014

SpaceOps 2014 Conference

View full text Add to dashboard Cite

Nuclear Explorations for Realizing Interplanetary Objectives I, or NERIO-I, is the stepping stone for Mars exploration, possible future Mars colonization, and ultimately other interplanetary voyages. The mission employs revolutionary advances in technology in order to send a crew of four to Mars for a thirty day surface stay. These revolutionary concepts include nuclear electric propulsion, improved radiation shielding and countermeasures, improved space medicine, and a biomass production unit. Six Block II Space Launch System launches send the crew and all necessary supplies to the surface of Mars. During their stay, the crew will collect geological specimens and set up devices for drilling and meteorological sensing. The mission begins in the year 2030 with three cargo launches.

show abstract

“…ecent system architecture studies for human and advanced robotic missions to Mars [1] have identified future deceleration technologies as a crucial element for entry, descent, and landing (EDL), given the inability of current parachute systems to deliver the large payloads required for these missions due to constraints on parachute size, materials, and performance. One of the technologies showing promise is supersonic retro-propulsion (SRP), or the use of propulsive thrust directed into the oncoming supersonic freestream flow to decelerate a vehicle during flight [2].…”

Section: Introductionmentioning

confidence: 99%

Estimation of Uncertainties for a Supersonic Retro-Propulsion Model Validation Experiment in a Wind Tunnel

Rhode

Oberkampf²

2012

42nd AIAA Fluid Dynamics Conference and Exhibit

View full text Add to dashboard Cite

A high-quality model validation experiment was performed in the NASA Langley Research Center Unitary Plan Wind Tunnel to assess the predictive accuracy of computational fluid dynamics (CFD) models for a blunt-body supersonic retro-propulsion configuration at Mach numbers from 2.4 to 4.6. Static and fluctuating surface pressure data were acquired on a 5-inch-diameter test article with a forebody composed of a sphericallyblunted, 70-degree half-angle cone and a cylindrical aft body.One non-powered configuration with a smooth outer mold line was tested as well as three different powered, forward-firing nozzle configurations: a centerline nozzle, three nozzles equally spaced around the forebody, and a combination with all four nozzles. A key objective of the experiment was the determination of experimental uncertainties from a range of sources such as random measurement error, flowfield non-uniformity, and model/instrumentation asymmetries. This paper discusses the design of the experiment towards capturing these uncertainties for the baseline non-powered configuration, the methodology utilized in quantifying the various sources of uncertainty, and examples of the uncertainties applied to non-powered and powered experimental results. The analysis showed that flowfield nonuniformity was the dominant contributor to the overall uncertainty -a finding in agreement with other experiments that have quantified various sources of uncertainty.

show abstract

Overview of the NASA Entry, Descent and Landing Systems Analysis Stud

Cited by 32 publications

References 10 publications

Supersonic Retropropulsion Experimental Results from the NASA Ames 9- x 7-Foot Supersonic Wind Tunnel

Supersonic Retropropulsion Experimental Results from the NASA Ames 9- x 7-Foot Supersonic Wind Tunnel

NERIO-I: Nuclear Explorations for Realizing Interplanetary Objectives I

Estimation of Uncertainties for a Supersonic Retro-Propulsion Model Validation Experiment in a Wind Tunnel

Contact Info

Product

Resources

About