1994-004A
Formally known as the Deep Space Program Science Experiment (DSPSE), the Ballistic Missile Defense Organization's first space probe was known as Clementine. Lawrence Livermore National Lab (LLNL) provided sensors for this BMDO mission to expose advanced sensors to high radiation dosage; the probe was built by NRL and operated by NRL's Naval Center for Space Technology (NCST).
The probe had a dry mass of 183 kg, with 231 kg of propellant giving a mass of 414 kg after ISA separated. With the kick motor, the ISA and the launch adapter total launch mass was 1687 kg. Clementine was 1.1m in diameter and 1.8m high.
The initial attempt to fire the TTI (Transfer Trajectory Injection) burn on Feb 2 was unsuccessful due to a command error. Success came a day later, and the Star 37FM solid motor placed Clementine on the first leg of a stunted phasing loop trajectory. An engineering burn of the bipropellant engine was carried out to clear the fuel lines in preparation for a calibration burn, later cancelled because of delays in jettisoning the interstage just prior to first apogee. Two perigee burns of the engine were used to raise the apogee to lunar distance, and on Feb 19 the spacecraft executed the LOI-1 burn to enter lunar orbit. A second LOI burn to refine the orbit was aborted when telemetry incorrectly showed that the door protecting the delicate sensors was open; the LOI-2 burn was successfully carried out the following day and Clementine began its mapping of the Moon. A number of manuevers were made to ensure complete mapping coverage.
After its successful lunar mapping mission, Clementine departed lunar orbit on May 3. At perigee on May 7, a software failure caused all the attitude control propellant to be depleted. The original plan had called for Clementine to depart Earth orbit with a lunar flyby on May 27 and head off to fly past the minor planet (1620) Geographos on 1994 Aug 30, with a possible further flyby of (3221) Verenia on 1995 Oct 21. This plan was now impossible, and managers decided to try and keep Clementine in Earth orbit. The main propulsion fuel was unaffected by the failure, and it was realized that by using the sun sensor to tell the instant Clementine was pointing in the right direction as it spun on its axis once a second, and pulsing the engine at exactly those times, limited control of Clementine's orbit was possible. Two leading edge lunar swingbys could place Clementine in a 12000 x 240000 km orbit. On May 27 Clementine made its first lunar swingby, at a distance of 8900 km, and fell back toward perigee. The perigee burn on May 31 was only partially successful and a followup trim burn was also insufficient. Then, on June 4, the spacecraft started losing electrical power and its signal became too weak to track. On June 24 the probe passed by the Moon again (at a distance of around 10000-20000 km?) and finally on Jul 20 an 8200 km flyby sent the probe into heliocentric orbit. Contact was recovered briefly in May 1995.
|
| Clementine |
| |
|
| Date | Time | Event | Orbit |
|---|
|
| 1994 Jan 25 | 1634 | Launch by Titan 2G |
| 1994 Jan 25 | 1636 | Titan Stage 1 sep T+2:30 |
| | 1637? | Fairing sep |
| | 1639? | Titan stage 2 MECO |
| | 1639? | Titan stage 2 sep | 259 x 296 x 67 |
| 1994 Jan 26 | 0000 | | 251 x 287 x 66.96 |
| 1994 Jan 29 | 0000 | | 247 x 285 x 66.96 |
| 1994 Feb 3 | 0000 | | 244 x 285 x 66.96 |
| 1994 Feb 3 | 0610 | Spinup | 250 x 290 x 66.97 |
| 1994 Feb 3 | 0629 | TTI burn, Star 37, 2960 m/s | 51.2h 252 x 126728 x 66.42 |
| 1994 Feb 3 | 1859 | | 284 x 126962 x 66.48 |
| 1994 Feb 3 | 1900 | BPE engineering burn, 3.5 m/s | 284 x 126962 x 66.48 |
| 1994 Feb 4 | 0800?? | ISA separation near apogee | 292 x 126938 x 66.48 |
| 1994 Feb 4 |
| Apogee 1 | |
| 1994 Feb 5 | 1000 | Approach P1 | 289 x 126259 x 66.36 |
| 1994 Feb 5 | 1001 | P1 burn, 213 m/s | 413 x 364015 x 66.36 |
| 1994 Feb 6 | 0100 | Pass EL1:4 |
| 1994 Feb 6 | 0959 | Approach P1C | 437 x 367462 x 66.31 |
| 1994 Feb 6 | 1000 | P1C burn 31.9 m/s | 437 x 367464 x 66.31 |
| 1994 Feb 7 | | Titan stage 2 exploded |
| 1994 Feb 11 | s | Apogee 2 | 385673 km? |
| 1994 Feb 15 | 1252 | | 855 x 390389 x 63.04 |
| 1994 Feb 15 | 1253 | P2 burn, 7.4 m/s | 856 x 385388 x 63.04 |
| 1994 Feb 16 | 1259 | | 843 x 410558 x 63.25 |
| 1994 Feb 16 | 1300 | P2C burn 1.4 m/s | 860 x 409800 x 63.25 |
| 1994 Feb 17 | 0959 | | 793 x 410158 x 64.25 |
| 1994 Feb 18 | 2040? | Enter lunar sphere |
| 1994 Feb 19 | 1251 | LOI approach | 404 x Infinity x 89.5 |
| 1994 Feb 19 | 1251.32 | LOI-1 burn 460.3 m/s | |
| 1994 Feb 19 | 1257.42 | LOI-1 cutoff, lunar orbit | LO 401 x 5426 x 89.49 |
| 1994 Feb 20 | 1241 | LOI-2 burn 1.2 m/s | 402 x 5388 x 89.33 from 402 x 5425 x 89.33 |
| 1994 Feb 21 | 1216 | LOI-2 burn, 2nd attempt, 103.5 m/s | 397 x 2965 x 89.27 |
| 1994 Feb 22 | 1217 | LOI-2 trim, 5.3 m/s | 382 x 2971 x 89.32 |
| 1994 Mar 11 | 0600 | Pre LOM 1 | 445 x 2909 x 89.78 |
| 1994 Mar 11 | 0629 | LOM 1 burn, 19 m/s | 445 x 2909 x 89.78 |
| 1994 Mar 26 | 0221 | Apsidal Rot 1 burn, 106 m/s |
| | | Move periselene from 30S to 30N | 447 x 2904 x 89.78 |
| | 1241 | Apsidal Rot 2 burn, 106 m/s | 1008 x 3560 x 89.50 |
| 1994 Mar 27 | 1830 | Rotation trim, 3.8 m/s | 448 x 2905 x 90.06 |
| 1994 Apr 11 | 0629 | LOM 2 burn, 8.7 m/s | 428 x 2925 x 90.00 |
| 1994 May 3 | 1300 | | 369 x 2984 x 89.76 |
| 1994 May 4 | 0324:15 | LOD (Lunar Orbit Departure), 453.3 m/s | |
| 1994 May 4 | 0330 | | 24737 x Infinity x 107.9 |
| 1994 May 5 | 0055 | Depart lunar sphere
|
| 1994 May 7 | 1330 | | 68424 x 452909 x 21.36 |
| 1994 May 7 | 1345 | Attitude control failure | 68429 x 451989 x 21.34 |
| 1994 May 8 | 0556 | 2P1 Perigee 68408 |
| 1994 May 12 | 0154 | Pre Test mv 1 | 66832 x 453021 x 21.35 |
| 1994 May 12 | 0159 | Test mv 1 | 66963 x 453381 x 21.30 |
| 1994 May 13 | 0030 | Pre Test mv 2 | 66116 x 453547 x 21.30 |
| 1994 May 13 | 0034 | Test mv 2 | 66057 x 451669 x 21.21 |
| 1994 May 16 | 0530 | 2A1 Apogee 454929 km? |
| 1994 May 18 | 1300 | Pre 2A2 burn | 62600 x 451739 x 21.21 |
| 1994 May 20 | 1300 | Post 2A2 burn | 57261 x 444300 x 21.12 |
| 1994 May 24 | | 2A2 Apogee |
| 1994 May 27 | | Lunar flyby 8900 km |
| 1994 May 31 | 2057 | 2A3 burn, | 44768 x 388197 x 19.50 |
| 1994 May 31 | | Trim burn |
| 1994 Jun 5 | | Contact lost |
| 1994 Jun 24 | | Lunar flyby |
| 1994 Jul 20 | | Lunar flyby 8200 km |
| 1994 Jul 21 | | Solar orbit |
| 1995 Feb 20 | | DSN contact |
| 1995 Mar 1 | | Solar orbit | 1.02 x 1.06 AU x 0.07 |
| 1995 Apr 10 | | Commanded DSPSE |
| 1995 May 4 | | Fuel dump burn |
Payload:
- UV/Vis imager
- HiRes camera (connected to LIDAR)
- LWIR camera
- NIR camera
- Lidar for laser altimetry Nd YAG laser
