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Beta 2: a near term, fully reusable, horizontal takeoff and landing two-stage-to-orbit launch vehicle concept
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Burkardt, Leo A. |
| Copyright Year | 1992 |
| Description | A recent study has confirmed the feasibility of a near term, fully reusable, horizontal takeoff and landing two-stage-to-orbit (TSTO) launch vehicle concept. The vehicle stages at Mach 6.5. The first stage is powered by a turboramjet propulsion system with the turbojets being fueled by JP and the ramjet by LH2. The second stage is powered by a space shuttle main engine (SSME) rocket engine. For about the same gross weight as growth versions of the 747, the vehicle can place 10,000 lbm. in low polar orbit or 16,000 lbm. to Space Station Freedom. |
| File Size | 189958 |
| Page Count | 10 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19920012293 |
| Archival Resource Key | ark:/13960/t0cv9dv9r |
| Language | English |
| Publisher Date | 1992-01-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Turboramjet Engines Hypersonic Speed Launch Vehicles Space Shuttle Main Engine Flight Paths Rocket Engines Polar Orbits Space Station Freedom Multistage Rocket Vehicles Propulsion System Configurations Trajectory Optimization Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
