Development of LOX/LH2 tank system for H-I launch vehicle
Abstract
Design features of the second stage of the prospective Japanese H-1 launch vehicle are described. The stage will use an LO2/LH2 fueled engine. The fuels will be contained in a 2219 Al alloy tank insulated with sprayed polyurethane foam. The total stage length will be 5.5 m, the volume 6.8 m, pressure 3.2 kg/sq cm (LOX) and 2.5 kg/sq cm (LH2). The diameter is 2.5 m and total fuel mass is 8.7 tons. Design verification tests, consisting of burning tests and thermal evaluation, are scheduled for the near future.
- Publication:
-
13th Symposium on Space Technology and Science
- Pub Date:
- 1982
- Bibcode:
- 1982spte.symp..425N
- Keywords:
-
- Cryogenic Fluid Storage;
- Fuel Tanks;
- Hydrogen Oxygen Engines;
- Japanese Spacecraft;
- Launch Vehicles;
- Aluminum Alloys;
- Helium;
- Honeycomb Cores;
- Multilayer Insulation;
- Polyurethane Foam;
- Propulsion System Configurations;
- Tensile Strength;
- Titanium Alloys;
- Launch Vehicles and Space Vehicles