1966-099
The Gemini B test vehicle, the refurbished Gemini 2, was launched on the MOL test flight in 1966. The spacecraft had a tunnel and hatch through its heat shield for access to the MOL laboratory.
Gemini B consisted of the reentry module (REM) and the adapter module. The REM consisted of the cabin, the RCS section and the Rendezvous/Recovery (R&R) section as on the standard Gemini. A crewman simulator equipment pallet was installed in one of the ejection seats. Splashdown was near Ascension Island.
| OV4-3 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1966 Nov 3 | 1350:42 | Launch by Titan IIIC | CK LC40 |
| 1352:32 | Stage 1 burn 37.5 km Vi? 1.671 | ||
| 1352:44 | SRM sep 44.8 km Vrel 1.804 | ||
| 1355:00 | Stage 1 sep 120.5 km Vi? 4.230 km/s | ||
| 1358:21 | Stage 2 MECO 195.7 km 6.494 km/s | -2876 x 196 x 32.8 | |
| 1358:31 | Stage 2 sep | ||
| 1358:34 | Transtage burn 1 196 km? 6.492 km/s 21198 kg | ||
| Fuel burn rate 24.42 kg/s | |||
| Apogee 197 km | -2930? x 197 x 32.8 | ||
| Pitch down | |||
| 1403:42 | Transtage MECO-1 167.0 km 7.831 km/s | ||
| 1404:12 | Gemini B sep, 160 km Vi = 7.840 km/s 159.5 km -1.8035 deg | -1 x 427 | |
| 1404:15 | Transtage retro | ||
| 1404:37 | Pitch up | ||
| 1419:23 | Gemini B deploy chute | ||
| 1428:33 | Gemini B splash at 09 06S, 14 20W | ||
1966-099A
The Manned Orbiting Laboratory Canister, or MOL-HSQ Simulated Laboratory, was a mockup of the planned USAF Manned Orbiting Laboratory made from a Titan stage 1 oxidizer tank and a Gemini B adapter. The Gemini B spacecraft was launched on top of it, and it contained a set of ARSP research experiments which earned it the alternate name OV4-3. The vehicle was built by Martin.
Titan IIIC mission C-9 was designated MOL-HSQ (Manned Orbiting Laboratory - Heat Shield Qualification).
The Titan IIIC took off from Cape Kennedy on 1966 Nov 3. It reached apogee at 197 km and 6.46 km/s, then pitched down gaining speed to 7.82 km/s by 166 km, when the Gemini B spaceship separated and reentered at Ascension, testing the new heat shield. The Titan, with OV4-3, pitched up and entered a 300 km low Earth orbit. The Transtage remained attached to OV4-3.
| OV4-3 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1966 Nov 3 | 1350:42 | Launch by Titan IIIC | CK LC40 |
| 1352:32 | Stage 1 burn 37.5 km Vi? 1.671 | ||
| 1352:44 | SRM sep 44.8 km Vrel 1.804 | ||
| 1355:00 | Stage 1 sep 120.5 km Vi? 4.230 km/s | ||
| 1358:21 | Stage 2 MECO 195.7 km 6.494 km/s | -2876 x 196 x 32.8 | |
| 1358:31 | Stage 2 sep | ||
| 1358:34 | Transtage burn 1 196 km? 6.492 km/s 21198 kg | ||
| Fuel burn rate 24.42 kg/s | |||
| Apogee 197 km | -2930? x 197 x 32.8 | ||
| Pitch down | |||
| 1403:42 | Transtage MECO-1 167.0 km 7.831 km/s | ||
| 1404:12 | Gemini B sep, 160 km Vi = 7.840 km/s 159.5 km -1.8035 deg | -1 x 427 | |
| 1404:15 | Transtage retro | ||
| 1404:37 | Pitch up | ||
| 1404:47 | Transtage burn 2 at 151 km, 7.859 km/s 40s, 11550 kg at MES | ||
| 1405:29 | Transtage MECO-2 146.1 km 7.862 km/s | 88.96 142 x 311 x 32.88 | |
| 1419:23 | Gemini B deploy chute | ||
| 1428:33 | Gemini B splash at 09 06S, 14 20W | ||
| 1443:44 | Transtage burn 3 5s 7.687 km/s 10479 kg | ||
| 1443:50 | Transtage MECO-3 296.2 km 7.730 km/s 10329 kg? | ||
| 90.4 298 x 305 x 32.8 | |||
| 90.41 296 x 301 x 32.86 | |||
| 1446:11 | OV1-6 eject | ||
| 1447:54 | OV4-1T eject | ||
| 1448:14 | OV4-1R eject | ||
| 1959 | ACS fuel depleted | ||
| 2015 | ACS oxidizer depleted | ||
| 2050:43 | Transtage turned off (Pretoria pass) | ||
| 1966 Nov 6 | 90.59 300 x 306 x 32.8 | ||
| 1966 Dec 6 | OV4-3 end of operations | ||
| 1966 Dec 28 | 89.35 238 x 246 x 32.8 | ||
| 1967 Jan 7 | 88.28 187 x 191 x 32.8 | ||
| 1967 Jan 9 | Reentered | ||
