2002-003B
The ISAS Demonstrator of Atmospheric Reentry System at Hypervelocity (DASH) is a secondary payload on H-IIA-F2. It will deorbit from GTO at high (hyperbolic) velocity. The mission is a test for MUSES-C. It was meant to reenter at 10.2 km/s between -18.5 and -16.5 at 200 km (corresponding to -423 x 34153 x 28.5 to -574 x 34305 x 28.5) and land in Africa (Mauritania? at about 8.5W 17.2N. in the Hodh el Gharbi region. In the event it failed to separate from VEP-3.
DASH consists of a hexagonal bus with a deorbit motor (DOM), and a blunt cone reentry capsule, and two DFM thrusters for orbit adjust at apogee. The size of DASH is 0.99m x 0.70m x 0.54m. including the comms antenna; bus size is 0.7 x 0.5m. Mass of the orbiter and DOM is 70 kg. The reentry capsule has a mass of 16 kg and is 0.40m dia, 0.20m high. A 3 kg adapter is mounted to the H-2A upper adapter.
In Japanese DASH is
\uni{ 高速再突入実験機}{ }
(Kosoku sai totsunyu jikken ki, High speed reentry experimental machine).| DASH (planned) | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2002 Jan 31 | Launch | ||
| T+0:10 SSB 1-2 on | |||
| T+1:10 SSB 1-2 sep | |||
| T+1:16 SSB 3-4 on | |||
| T+2:16 SSB 3-4 sep | |||
| SRB-A sep | |||
| Stage 1 sep | |||
| Stage 2 MES | |||
| Fairing sep | |||
| Stage 2 MECO-1 | |||
| Stage 2 MES-2 | |||
| Stage 2 MECO-2 | |||
| DASH/VEP-3 separates from Stage 2 | |||
| Stage 2 deploy MDS-1 | |||
| VEP-3 failed to deploy DASH | |||
| D+5:00 Sep ENA | |||
| D+5:56 SPM | |||
| D+37h DFM | |||
| D+43h DFM | |||
| 2002 Feb 4 | D+76h DOM burn | ||
| Yo-yo despin | |||
| Capsule separation | |||
| T+85h Reentry | |||
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