1964-U02
The Project FIRE High Velocity Reentry Package studied a blunt body reentry at 11.3 km/s and 15 degree angle. Total launch mass was 2000 kg including the velocity package shell and control system, 1400 kg without but including the Antares IIA5 with 1179 kg of propellant. Fairing is a modified DAC Nimbus fairing. Velocity package contractor was LTV. Reentry package was Republic Aviation Corp. Planned apogee was 837 km.
FIRE 1 reached 11.5736 km/s (or 11.52 km/s, TN-D-2996) at 16.6W 7.8S, 122 km on descent from 840 km, at an angle of -14.608 deg and azimuth 122.5 deg. Range was 8370 km. Possible initial trajectory -2900 x 840 x 30.0. Post burn trajectory -219 x Inf x 32 deg.
| FIRE 1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1964 Apr 14 | 2142:25 | Launch by Atlas 263D | CKAFS LC12 |
| 2144:38 | T+2:13 BECO, 24.4 deg ascent | ||
| 2144:39? | Booster sep | ||
| 2147:13 | T+4:48 SECO | ||
| 2147:20 | VP fairing jettison | ||
| 2147:31 | T+5:09 VECO, 8.0 deg ascent | ||
| 2147:25 | 6.28km/s rel, 15.0 deg 299 km | -2920 x 840 x 31.1 | |
| 2147:36 | Spacecraft sep from Atlas | ||
| 2147:45 | Fire 1 orientation | ||
| 2149:26 | Coast phase | ||
| 2158:05 | Apogee 840 km | ||
| 2208:39 | Spinup | ||
| 2208:42 | Velocity package shell sep | ||
| 299.43 km -15.32 deg 6.3395 km/s rel | -2820 x 841 x 30.8? | ||
| 2208:45 | Antares burn dV = 5.2km/s | ||
| 2209:17 | Antares burnout | ||
| 2209:43 | Simulation fidiucial time 149.5 km -15 deg 11.55 km/s | ||
| 2209:45 | Reentry package sep | -219 x -51626 x 32.1 | |
| 2209:52 | Reentry 122 km 11.5736 km/s -14.608 deg 16.7W 7.8S | ||
| 2209:57 | Yaw disturbance; Antares bow shock hits Fire | ||
| 2210:14 | Heat shield 1 sep | ||
| 2210:21 | Heat shield 2 sep | ||
| 2210:31 | End of blackout | ||
| 2215:10 | Impact 10.227S 12.643W | ||
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