Show simple item record

dc.contributor.authorSt. Germain, Brad Daviden_US
dc.contributor.authorOlds, John R.en_US
dc.date.accessioned2006-03-17T15:59:26Z
dc.date.available2006-03-17T15:59:26Z
dc.date.issued1999-06
dc.identifier.urihttp://hdl.handle.net/1853/8416
dc.description35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference Los Angeles, CA, June 20-24, 1999.en_US
dc.description.abstractThe Bantam-Argus reusable launch vehicle concept is a smaller version of the original Argus single-stage-to-orbit launch vehicle design. Like the original Argus, Bantam-Argus uses a Maglifter launch assist system to provide an initial horizontal launch velocity. Bantam-Argus is designed to deliver 300 lb. payloads to low earth orbit and, like the full sized Argus, the baseline Bantam-Argus concept utilizes two liquid oxygen/liquid hydrogen supercharged ejector ramjets as prime motive power. This paper presents the results of an investigation of two alternate propulsion systems for the Bantam-Argus launch vehicle. First, a thermally integrated combined- cycle system consisting of two deeply-cooled turbojets and two liquid rocket engines was evaluated. Second, a combination propulsion system utilizing two pulsed detonation rocket engines and two standalone ramjets was evaluated. The results show that both alternate propulsion systems have the potential to reduce both the dry weight and gross weight of the baseline Bantam-Argus concept (when resizing the vehicle while holding mission payload constant). The pulsed detonation rocket engine option is particularly attractive. However, these results must be treated with caution given the relative immaturity of the supporting propulsion data available for both alternatives. Trade studies on key performance parameters were performed to bound the potential gains to be expected from either alternative.
dc.format.extent238211 bytes
dc.format.mimetypeapplication/pdf
dc.language.isoen_US
dc.publisherGeorgia Institute of Technologyen_US
dc.relation.ispartofseriesSSDL ; AIAA 99-2354en_US
dc.subjectPropulsion systems
dc.subjectSpacecraft design
dc.titleAn Evaluation of Two Alternate Propulsion Concepts for Bantam-Argus: Deeply-Cooled Turbojet+Rocket and Pulsed Detonation Rocket+Ramjeten_US
dc.typePaper


Files in this item

Thumbnail

This item appears in the following Collection(s)

Show simple item record