A study of a near-term, low risk two-stage-to-orbit (TSTO) vehicle was undertaken. The goal of the study was to assess a fully reusable TSTO vehicle with horizontal takeoff and landing capability that could deliver 10,000 pounds to a 120 nm polar orbit. The configuration analysis was based on the Beta vehicle design. A cooperative study was performed to redesign and refine the Beta concept to meet the mission requirements. The vehicle resulting from this study was named Beta II. It has an all-airbreathing first stage and a staging Mach number of 6.5. The second stage is a conventional wing-body configuration with a single SSME
A study was conducted of a three-engined external hydrogen tank orbiter/heat sink booster utilizing ...
A definitive design/performance study was performed on a single-stage-to-orbit (SSTO) airbreathing p...
For a long time space engineers have been interested in the possibility of enabling single-stage-to-...
A study to improve the performance of the NASA two-stage-to-orbit vehicle was undertaken. The NASA c...
A NASA study of the propulsion systems for possible low-risk replacements for the Space Shuttle is p...
NASA LeRC is continuing to study propulsion concepts for a horizontal takeoff and landing, fully reu...
A conceptual design study of a two-stage-to-orbit vehicle is presented. Three configurations were in...
Two separate student design groups developed conceptual designs for a two-stage-to-orbit vehicle, wi...
An investigation into the feasibility of establishing a second generation space transportation syste...
The object of this design class was to design an earth-to orbit vehicle to replace the present NASA ...
NASA and the Air Force Research Laboratory are involved in a Joint System Study (JSS) on Two-Stage-t...
A two-stage-to-orbit (TSTO) spaceplane concept developed in 1993 is revisited, and new information i...
A preliminary, two-dimensional, mixed compression air induction system is designed for the Beta II T...
The concept to use twin turbo-powered boosters for acceleration to supersonic staging speed followed...
The goal of this conceptual design was to devise a reusable, commercially viable, single-stage-to-or...
A study was conducted of a three-engined external hydrogen tank orbiter/heat sink booster utilizing ...
A definitive design/performance study was performed on a single-stage-to-orbit (SSTO) airbreathing p...
For a long time space engineers have been interested in the possibility of enabling single-stage-to-...
A study to improve the performance of the NASA two-stage-to-orbit vehicle was undertaken. The NASA c...
A NASA study of the propulsion systems for possible low-risk replacements for the Space Shuttle is p...
NASA LeRC is continuing to study propulsion concepts for a horizontal takeoff and landing, fully reu...
A conceptual design study of a two-stage-to-orbit vehicle is presented. Three configurations were in...
Two separate student design groups developed conceptual designs for a two-stage-to-orbit vehicle, wi...
An investigation into the feasibility of establishing a second generation space transportation syste...
The object of this design class was to design an earth-to orbit vehicle to replace the present NASA ...
NASA and the Air Force Research Laboratory are involved in a Joint System Study (JSS) on Two-Stage-t...
A two-stage-to-orbit (TSTO) spaceplane concept developed in 1993 is revisited, and new information i...
A preliminary, two-dimensional, mixed compression air induction system is designed for the Beta II T...
The concept to use twin turbo-powered boosters for acceleration to supersonic staging speed followed...
The goal of this conceptual design was to devise a reusable, commercially viable, single-stage-to-or...
A study was conducted of a three-engined external hydrogen tank orbiter/heat sink booster utilizing ...
A definitive design/performance study was performed on a single-stage-to-orbit (SSTO) airbreathing p...
For a long time space engineers have been interested in the possibility of enabling single-stage-to-...
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