Abstract
In this paper a Two-Stage-To-Orbit, aeroplane-like, space launcher called 'Phantom' is presented. This launcher is intended to serve as a reference baseline for the AEOLUS project.
The take-off mass of the total vehicle is about 352 ton. The total mass of the first stage is 251 ton
and of the second stage 101 ton. Fuel/propellant mass is 125 ton for the first stage and 75 ton for
the second stage. The first stage has a range capability of about 2100 km, allowing the vehicle to be launched in Europe, whereas still reaching 28.5° latitude. Second stage separation occurs at hypersonic flight conditions. Payload mass into circular orbit (120 km altitude) is 7 ton.
The take-off mass of the total vehicle is about 352 ton. The total mass of the first stage is 251 ton
and of the second stage 101 ton. Fuel/propellant mass is 125 ton for the first stage and 75 ton for
the second stage. The first stage has a range capability of about 2100 km, allowing the vehicle to be launched in Europe, whereas still reaching 28.5° latitude. Second stage separation occurs at hypersonic flight conditions. Payload mass into circular orbit (120 km altitude) is 7 ton.
| Original language | English |
|---|---|
| Publisher | Delft University of Technology |
| Number of pages | 73 |
| Volume | AE-DUT-TN-9502(1) |
| Publication status | Published - 1995 |
Publication series
| Name | AEOLUS |
|---|---|
| No. | AE-DUT-TN-9502(1) |
Keywords
- Two-stage-to-orbit
- Space launcher
- Space launch vehicle
- Winged space launcher
- Horizontal-take-of launch vehicle