OREX
| Mission type | Technology |
|---|---|
| Operator | NASDA |
| COSPAR ID | 1994-007A |
| SATCAT no. | 22978 |
| Website | www |
| Mission duration | 2 hours |
| Spacecraft properties | |
| Manufacturer | NASDA |
| Launch mass | 865 kilograms (1,907 lb) |
| Landing mass | 761 kilograms (1,678 lb) |
| Start of mission | |
| Launch date | 3 February 1994, 22:20 UTC |
| Rocket | H-II |
| Launch site | Tanegashima Yoshinobu 1 |
| End of mission | |
| Landing date | 4 February 1994, 00:30 UTC |
| Landing site | Pacific Ocean |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Low Earth |
| Perigee | 448 kilometres (278 mi) |
| Apogee | 458 kilometres (285 mi) |
| Inclination | 30.5 degrees |
| Period | 93.64 minutes |
| Epoch | 3 February 1994 |
OREX (Orbital Re-entry Experiment) was a NASDA re-entry demonstrator prototype which was launched in 1994 on the H-II launcher; the satellite was renamed Ryūsei (りゅうせい Shooting star?). It was a precursor for the Japanese space Shuttle Hope.
OREX tested various communications systems, heating profiles and heat shielding components for Hope.
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