The Solar Thermal Propulsion Transfer Stage design for near-term science mission applications

McClanahan, James A.; Frye, Patrick

doi:10.2514/6.1994-2999

Cited by 5 publications

(2 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The scientifi c payload mass could be raised using solar thermal propulsion, although the size of the launcher and hence mission cost are considerably reduced [7,8]. The scientifi c payload mass could be raised using solar thermal propulsion, although the size of the launcher and hence mission cost are considerably reduced [7,8].…”

Section: B Interplanetary Spacecraftmentioning

confidence: 99%

Solar Thermal Propulsion for Upper Stages

2008

Advanced Propulsion Systems and Technologies, Today to 2020

View full text Add to dashboard Cite

Nomenclature D = drag, N g = gravitational acceleration, m/s 2 M = Machnumber m = mass, kg m = mass fl ow, kg/s n x = axial load factor n z = normal load factor P = total pressure, Pa Q = heat fl ux, W/m 2 T = thrust, N v = velocity, m/s W = weight, N α = angle of attack γ = fl ight-path angle ε = expansion ratio Π = pressure ratio P i /P i−1 ρ = density, kg/m 3 Acronyms AOA = angle of attack COTS = commercial off the shelf ESC-B = Etage Supérieur Cryotechnique (of Ariane 5) * Head DLR Space Launcher System Analysis Division SART. † FLPP Launch Systems Manager ESA.

show abstract

Section: B Interplanetary Spacecraftmentioning

confidence: 99%

Solar Thermal Propulsion for Upper Stages

2008

Advanced Propulsion Systems and Technologies, Today to 2020

View full text Add to dashboard Cite

show abstract

“…The validation of these issues with an integrated system can only be adequately performed by means of a space flight experiment. (13,14,15,16) …”

Section: Basics Of Solar Propulsionmentioning

confidence: 99%

Solar Orbit Transfer Vehicle Conceptual Design

CA¹

1999

View full text Add to dashboard Cite

Public reporting burden for this collection of information is estimated to average 1 hoi per response, including the time for reviewing instructions, searching exist ng data sources gamer ng and maMa ningthe data needed, and completing and reviewing this collection of informal™. S.lnd comments regarding this burden estimate or any other aspect of this collection ° '"^matio" MuaTnc suqqesfions for reducing this burden to Department of Defense, Washingtol HeadcLarters Services, Directorate for Information AbstractIn response to government and industry needs for greater space lift capability, greater space mobility, and more affordable spacecraft, the Air Force Research Lab has been researching advanced technologies that include solar thermal propulsion and solar thermionic based power systems. Efforts over the last ten years have focused on feasibility, design, and fabrication issues of the various components.Recent programs have progressed to the point of ground based demonstrations of major subsystems. Because solar thermal based concepts are designed to make use of the 0-g space environment, the validation of several key issues can only be accomplished with a space flight experiment. These issues include the long duration containment and acquisition of two-phase hydrogen, stability and dynamic control of large solar concentrators, exhaust plume impingement, and autonomous multi-impulse orbit raising.In an effort to validate these issues, a conceptual design of a space experiment has been created which includes basic layout and design drawings, performance predictions, and subsystem requirements. The design was produced using a design to cost approach. This paper gives a basic overview of the conceptual design as well as a description of the drivers and rational behind the design. The DTC method shows to be a valuable tool for defining low cost technology experiments although the results must be considered in the light of the driving factors.

show abstract