1996-064
Originally Mars-94, the project was delayed to the 1996 window by the fall of the USSR. Launch in Nov 1996 was a failure, when the Blok-D-2 did not ignite for its second burn. The ADU fired to place Mars-96 in an elliptical orbit, from which it reentered at third perigee. Parts of the spacecraft were reportedly recovered in Bolivia at 20 44 50 S 67 44 20 W.
Mars-96 was Lavochkin probe M1 No. 520, based on the Fobos bus. It consisted of an orbiter, 2 penetrators and 2 meteo station landers.
Planned Mars orbit was 900 x 18200 km, 12h. Mass at Blok-D-2 separation is 6825 kg; at solar orbit insertion 5678 kg. Dry mass is 3001 kg station plus 573 kg ADU. The MAS landers are 85 kg and 90 kg and the penetrators were 124.5 and 126.5 kg [496].
Mass of GO (Fairing) was 1879 kg. Stage 3 at sep was 5362 kg.
Planned D-2 burn times were 97s, 529s, for 0.345 and 3.150 km/s. Actual times were 97s and ~0s, and the second burn was in the wrong direction of magnitude 20m/s. The Blok-D-2 had a dry mass of 1900 kg; at Mars-96 sep it had a mass of 14300 kg, and over the following hours the fuel was automatically vented.
The second burn had m2 = 6825 + 14300 = 21125 kg; for Ve= 3.46, m1 = 21247 so about 122 kg of prop used, about a 5 s burn. For the 97s burn about 2270 kg used, giving Blok D-2 initial mass of 16692 kg, reasonable given other sources' estimated mass of 16900 kg.
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| Mars-96 |
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| Date | Time | Event | Orbit |
|---|
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| 1996 Nov 16 | 2048:53 | Launch by Proton-K | KB LC200L |
| | 2050:51 | Stage 2 burn T+1:58 |
| | 2050:56 | RK-1 Stage 1 sep T+2:03, 42 km |
| | 2051:58 | GO Fairing sep T+3:05 |
| | 2054:20 | Stage 3 burn T+5:27 |
| | 2054:24 | RK-2 Stage 2 sep T+5:31, 120 km |
| | 2058:26 | PK |
| | 2058:36 | GK Stage 3 sep T+9:43 | 77.41 -881 x 157 x 51.61 |
| | 2059? | Eject MAS heat shields? |
| | 2059 | SOZ burn T+10:43 |
| | 2104:35 | Blok-D-2 burn T+15:42 | |
| | 2106:11 | Blok-D-2 shutdown T+17:18 | 159 x 160 x 51.61 |
| | 2114? | Stage 3 reentry |
| | 2051 | SOZ burn T+1:03:53 |
| | 2157:47 | Blok-D-2 burn 2 T+1:08:54 |
| | 2157:50? | SOZ separation | 155 x 206 km (expected) |
| | 2206:51? | Blok-D-2 sep | 139 x 155 x 51.5 |
| | 2208:00? | ADU burn |
| | 2210:54? | ADU burnout | |
| | | | 77 x 410 x 51? |
| | 2240? | Apogee 2 at 400+ km |
| | 2325 | Perigee 2 at 78 km over 58W? 30S |
| 1996 Nov 17 | 0010? | Apogee 3 at 400+ km |
| | 0053? | Perigee 3 at 78? km over 80W? 32S, S Pacific |
| | 0100? | Reentry over S Pacific |
| 0500 | (Blok-D-2) | 87.43 139 x 154 x 51.52 |
| | 1830 | (Blok-D-2) | 87.18 129 x 140 x 51.53 |
| 1996 Nov 18 | 0015 | (Blok-D-2) | 86.85 114 x 122 x 51.50 |
| 1996 Nov 18 | 0130 | Blok-D-2 reentry over S Pacific |
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| Scheduled flight prior to failure |
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| | 2206 | Blok-D-2 shutdown T+1:17:41 |
| | 2206 | Blok-D-2 sep T+1:17:57 | 11300.0 215 x 320670 x 51.79 |
| | 2208 | ADU burn T+1:19:07 | |
| | 2210 | ADU shutdown T+1:21:57 | |
| | 2211 | Solar orbit insertion | 0.793 x 1.498 x 2.11 (AU) |
| 1997 Sep | | MAS separation |
| | | MOI | 500 x 51800 x 106.4 |
| | | MOI-2 | 300 x 51800? x ? |
| | | ADU sep |
| 1997 Oct | | Penetrator release |
Payload:
- MAS (2) Maliya avtonomnaya stansiya, 50 kg each
- Penetrator (2), 65 kg each
- OA Orbital'niy apparat
- TSP platform with ARGUS instruments:
- HRSC stereo TV camera
- WAOSS Wide angle stereoscopic TV camera
- OMEGA visible and IR mapping spectrometer
- NC Navigation camera
- PAIS platform:
- SPIKA optical spectrometer
- EVRIS stellar photometer
- Foton Gamma spectrometer
- PFS Planetary IR fourier spectrmeter
- TERMOSCAN mapping radiometer
- SVET mapping high resolution spectrophotometer
- UVS-M ultraviolet spectrometer
- LWR Long wavelength radar?
- Neutron-S neutron spectrometer
- MAK quadrupole mass spectrometer
- ASPERA-S energy-mass ion spectrograph and neutral particle imager
- FONEMA Fast omnidirectional non scanning energy-mass ion analyser
- DYMIO Omnidirectional ionospheric energy-mass spectrometer
- MARIPROB ionospheric plasma spectrometer
- MAREMF electron analyser, magnetometer
- ELISMA electromagnetic waves
- SLED-2 Low energy charged particle spectrometer
- PGS Precision gamma spectrometer
- LILAS-2 Cosmic and solar gamma ray burst spectra
- RADIUS-M Radiation and dosimetry measurements
1996-064
The surface penetrators are 2.0m long and PN1 (520/4) had a mass of 124 kg. The forward and aft sections separate on impact, with the forward section reaching 1 to 6 m below the surface. One penetrator would have landed near the MAS stations and the other SW of Utopia Planitia. The penetrator carried 5 RHS radioactive Pu238 source, each with 15g of PuO2.
The tail section is 0.8m diameter with science instruments. The nose is 2.1m long and 0.15m in diameter. Sep from OA at 0.8m/s. Braking engine with thrust of 130 kgs. Then solid fuel descent engine.
Payload:
- Seismometer
- Temperature sensor
- Aft section camera
- APXS Alpha proton X-ray spectrometer
- APXS Alpha proton X-ray spectrometer
- REPS power source with 2 RHS capsules, 30g PuO2
- RHS capsules, 3, 45g PuO2
1996-064
The small station was one of two stations on Mars-96. The bus is 1m in diameter, with petals which unfold to 1.4m. The MAS carried a total of 4 RHS radiation heat source pellets, each with 15g of Pu-238 dioxide. Planned landing site for each of the MAS probes was west of Olympus Mons at 41.31N 153.77W and 32.48N 169.32W. MAS/520/1 was 85 kg.
Payload:
- REPS 1 power source with 1 RHS, 15 g PuO2
- REPS 2 power source with 1 RHS, 15 g PuO2
- RHS power sources, 2, 30g PuO2
- Pu-238 RTG (2)
- Camera (RKA)
- Magnetometer (CNES)
- Meteorological sensors (Finland)
- MOx Mars Oxidation Experiment (JPL)
- Relay radio system
