2002-042A
USERS, the Unmanned Space Experiment Free Flyer (mujin uchu jikken shisutemu,
\uni{ 無人宇宙実験システム }{ }
) was a recoverable microgravity satellite. The Japanese name's literal translation is Uninhabited Space Experiment System.MITI (Min of International Trade and Industry) Unmanned Space Experiment Recovery System, launch by H-2A 2001. 926 kg REM reentry vehicle plus SEM service module. Total mass 1700 kg (800 kg SEM). SM will remain in orbit for long term expts. Nissan RV 1.4m dia 2.5m long including retro . Solar arrays 15.5m span. SM by Mitsubishi Electric. Managed by Inst. for Unmanned Space Experiment Free Flyers, Tokyo. Control from USEF OCC (USOC) via Tsukuba. Recovery zone near Ogasawara Is. 6 mo after launch at about 151.5E 22.5N. Deorbit control from Malindi, 160-180 m/s at -20 deg. I calculate a -71 x 483 km reentry orbit and a probable propellant mass of 54 kg.
16-m fairing. The USERS/REM Reentry Module has the Reentry Vehicle (REV) 1.48d 1.32l, a rounded cone and the Propulsion Module (PM). The PM is a truncated cone 0.5l 1.4dia. The RBM (solid retro boost motor) is 0.4d 0.7l. The SEM is a box + 2 panels 1.6 x 1.5 x 1.2m, span was 15.5m. H-2A with 4 SSB and 2 SRB-A, and 4/4D-LC fairing.
The SEM mission was ended in Jan 2005 and the spacecraft orbit lowered for rapid decay. The SEM was kept alive to maintain attitude, increasing drag.
| USERS | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2002 Sep 10 | 0820 | Launch by H2A 2024 | |
| T+1:10 SSB 1-2 on | |||
| T+1:46 SRB-A sep | |||
| T+1:47 SSB 3-4 sep | |||
| T+2:24 SSB 1-2 sep | |||
| T+4:10 upper fairing sep | |||
| 0826 | T+6:28 MECO | ||
| 0826 | T+6:36 Stage 1 sep | ||
| 0826 | T+6:42 SES-1 | ||
| 0832 | T+12:58 SECO-1 | ||
| 0833 | T+13:48 USERS sep | ||
| 0836 | T+16:18 Lower fairing sep | ||
| 0846 | T+26:17 SES-2 | ||
| 0848 | T+28:42 SECO-2 | ||
| 0849 | T+29:18 DRTS sep | ||
| 2002 Sep 10 | 93.54 439 x 455 x 30.4 | ||
| 2002 Sep 16 | 93.48 437 x 451 x 30.4 | ||
| Orbit raise | |||
| 2002 Sep 17 | 94.85 503 x 518 x 30.4 | ||
| 2002 Nov 20 | 94.70 498 x 510 x 30.4 | ||
| 2003 Jan 2 | 94.62 493 x 505 x 30.4 | ||
| 2003 Mar 9 | 94.51 488 x 501 x 30.4 | ||
| 2003 Apr 3 | 94.47 487 x 498 x 30.4 | ||
| 2003 Apr 4 | Orbit raise | ||
| 2003 Apr 5 | 94.73 500 x 510 x 30.4 | ||
| 2003 Apr 6 | 94.73 500 x 511 x 30.4 | ||
| 2003 May 3 | 94.71 499 x 511 x 30.4 | ||
| 2003 May 19 | 94.17 473 x 483 x 30.4 | ||
| 2003 May 29 | 94.18 473 x 485 x 30.4 | ||
| 2003 May 29 | 1906 | SM separation | |
| 2045 | RBM burn - 42?E 12?N | ||
| 2110 | 120 km PM sep from REM (134E 28N?) | ||
| 2123 | Splash 22 40 18N 150 42 25E | ||
| 2134 | Observed in water | ||
| 2003 May 29 | 94.24 474 x 489 x 30.4 | ||
| 2003 Jun 3 | 95.36 529 x 542 x 30.4 | ||
| 2003 Jun 5 | 96.20 570 x 583 x 30.4 | ||
| 2005 Jan 31 | End of SEM operations | ||
| 2005 Feb 2 | Test burn, 53 kg left | 96.00 562 x 571 x 30.41 | |
| 2005 Feb 4 | Descent burns | 510 x 560 x 30.4 | |
| 2005 Feb 12 | Descent burns | 465 x 510 x 30.4 | |
| 2005 Feb 21 | Depletion burn | ||
| 2005 Feb 25 | End of SEM mission | ||
| 2005 Feb 28 | 93.78 455 x 462 x 30.41 | ||
| 2007 Jun 15 | 0915 | Reentry over 41.6W 1.2N | |
Payload:
- RV
- SGHF Superconducting materials processing experiment in REM; Processing furnaces, 3
- READ Reentry Environment Advanced Diagnostics (in REM)
- PM Solid retro propulsion module
- SEM hydrazine AOCS
- OBCA Onboard computer, Automotive electronics technology
- AIRU Advanced inertial reference unit
- DFSG Dual Freq Space GPS
- AS3 Advanced Star Sensor System
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