Aerothermal Testing for Project Orion Crew Exploration Vehicle

Berry, Scott A.; Horvath, Thomas J.; Lillard, Randolph P.; Kirk, Benjamin S.; Fischer-Cassady, Amy

doi:10.2514/6.2009-3842

Cited by 19 publications

(10 citation statements)

References 45 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…LENS has been used for supporting space activities such as the development of the Orion vehicle through studies related to roughness and ablation effects, turbulent heating and radiation [95,96]. The capabilities of LENS-XX for radiation investigation at superorbital velocity for Earth entry has been demonstrated [97] as highlighted in Fig.…”

Section: Cubrc Lens Facilitymentioning

confidence: 98%

“…Here also, the main objective was to investigate CN radiation emission, however normalized population of carbon, atomic hydrogen, nitrogen (N 2 ), N 2 þ , CH, and C 2 are also available. Most of the experimental data measured for air in the USA and covering the VUV range have been obtained in the EAST facility for supporting the Orion project [95] involving a Lunar return. As a consequence several campaigns [185,186] were conducted for measuring VUV emission for an entry velocity of 10 km/s.…”

mentioning

confidence: 99%

See 1 more Smart Citation

Survey of high-enthalpy shock facilities in the perspective of radiation and chemical kinetics investigations

Reynier¹

2016

Progress in Aerospace Sciences

View full text Add to dashboard Cite

Section: Cubrc Lens Facilitymentioning

confidence: 98%

mentioning

confidence: 99%

Survey of high-enthalpy shock facilities in the perspective of radiation and chemical kinetics investigations

Reynier¹

2016

Progress in Aerospace Sciences

View full text Add to dashboard Cite

“…Although not discussed herein, the CEV TPS design must also account for ablation effects, including shape change, flowfield radiation-ablation coupling, and ablated surface roughness heating augmentation. An overview of the CEV design and development program is given in [6] and a summary of all CEV aerothermodynamic testing to date is presented in [7].…”

Section: B Crew Exploration Vehiclementioning

confidence: 99%

Blunt-Body Entry Vehicle Aerotherodynamics: Transition and Turbulent Heating

Hollis

2012

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

Recent, current, and planned NASA missions that employ blunt-body entry vehicles pose aerothermodyamic problems that challenge state-of-the-art experimental and computational methods. The issues of boundary-layer transition and turbulent heating on the heat shield have become important in the designs of both the Mars Science Laboratory and Crew Exploration Vehicle. While considerable experience in these general areas exists, that experience is mainly derived from simple geometries; e.g., sharp-cones and flat-plates, or from lifting bodies such as the Space Shuttle Orbiter. For blunt-body vehicles, application of existing data, correlations, and comparisons is questionable because an all, or mostly, subsonic flowfield is produced behind the bow shock, as compared with the supersonic (or even hypersonic) flow of other configurations. Because of the need for design and validation data for projects such as Mars Science Laboratory and Crew Exploration Vehicle, many new experimental studies have been conducted in the last decade to obtain detailed boundary-layer transition and turbulent heating data on this class of vehicle. In this paper, details of several of the test programs are reviewed. The laminar and turbulent data from these various test are shown to correlate in terms of edge-based Stanton and Reynolds number functions. Correlations are developed from the data for transition onset and turbulent heating augmentation as functions of momentum thickness Reynolds number. These correlations can be employed as engineering-level design and analysis tools.adiabatic wall enthalpy H 0 = total freestream enthalpy H w = wall static enthalpy H 300 K = wall static enthalpy at 300 K M 1 = freestream Mach number M e = boundary-layer edge Mach number P 1 = freestream pressure Pr = Prandtl number _ q w = heat transfer rate R N = hemispherical nose radius Re 1 = freestream unit Reynolds number 1 U 1 = 1 Re e = boundary-layer edge unit Reynolds number e U e = e Re = boundary-layer momentum thickness Reynolds number e U e = e St = Stanton number based on freestream conditions _ q w = 1 U 1 H 0 H w St e = Stanton number based on boundary-layer edge conditions _ q w = e U e H aw H w T 1 = freestream temperature U 1 = freestream velocity U e = boundary-layer edge velocity x=R = normalized distance along model centerline for Mars Science Laboratory local coordinate system z=R = normalized distance along model centerline for Crew Exploration Vehicle local coordinate system = angle of attack L = factor in laminar heating correlation 1 1 = e e 1=2 e = 1 1=4 T = factor in turbulent heating correlation 1 1 = e e 1=3 e = 1 1=4 = boundary-layer momentum thickness 1 = freestream viscosity e = boundary-layer edge viscosity = turbulent heating augmentation factor St measured =St predicted;laminar I. BackgroundT HIS work deals with the correlation of blunt-body boundarylayer transition and turbulent heating data obtained from recent NASA entry vehicle development programs. Blunt-body configurations are the most common geometries employed for ent...

show abstract

“…Various regolith formation and manufacturing methods will be investigated and traded-off against each other. Regolith heat-shield coupons will be tested in an arc jet facility at ARC to model the high heat and molecular impact stresses [11 ][12] [13] [ 15] [16].…”

Section: Feasibilitymentioning

confidence: 99%

Regolith-Derived Heat Shield for Planetary Body Entry and Descent System with In Situ Fabrication

Hogue

Mueller²,

Sibille

et al. 2012

Earth and Space 2012

View full text Add to dashboard Cite

In this paper we will discuss a new mass-efficient and innovative way of protecting high-mass spacecraft during planetary Entry, Descent & Landing (EDL). Heat shields fabricated in situ can provide a thermal-protection system (TPS) for spacecraft that routinely enter a planetary atmosphere. By fabricating the heat shield with space resources from regolith materials available on moons and asteroids, it is possible to avoid launching the heat-shield mass from Earth. Three regolith processing and manufacturing methods will be discussed: 1) oxygen & metal extraction ISRU processes produce glassy melts enriched in alumina and titania, processed to obtain variable density, high melting point and heat-resistance; 2) compression and sintering of the regolith yield low density materials; 3) in-situ derived high-temperature polymers are created to bind regolith particles together, with a lower energy budget.Artists' concept of a regolith derived re-entry heat shield. ABSTRACTIn this paper we will discuss a new mass-efficient and innovative way of protecting high-mass spacecraft during planetary Entry, Descent & Landing (EDL). Heat shields fabricated in situ can provide a thermal-protection system (TPS) for spacecraft that routinely enter a planetary atmosphere. By fabricating the heat shield with space resources from regolith materials available on moons and asteroids, it is possible to avoid launching the heat-shield mass from Earth. Three regolith processing and manufacturing methods will be discussed: 1) oxygen & metal extraction ISRU processes produce glassy melts enriched in alumina and titania, processed to obtain variable density, high melting point and heat-resistance; 2) compression and sintering of the regolith yield low density materials; 3) in-situ derived high-temperature polymers created to bind regolith particles together, with a lower energy budget.

show abstract

Aerothermal Testing for Project Orion Crew Exploration Vehicle

Cited by 19 publications

References 45 publications

Survey of high-enthalpy shock facilities in the perspective of radiation and chemical kinetics investigations

Survey of high-enthalpy shock facilities in the perspective of radiation and chemical kinetics investigations

Blunt-Body Entry Vehicle Aerotherodynamics: Transition and Turbulent Heating

Regolith-Derived Heat Shield for Planetary Body Entry and Descent System with In Situ Fabrication

Contact Info

Product

Resources

About