Beyond Earth: A Chronicle of Deep Space Exploration, 1958–2016 by Asif A. Siddiqi

Author:Asif A. Siddiqi [Siddiqi, Asif A.]
Language: eng
Format: epub
Published: 2018-09-07T17:31:17+00:00

184

Mars 8 / Mars 96

Nation: Russia (106)

Objective(s): Mars orbit and landing

Spacecraft: M1 (no. 520)

Spacecraft Mass: 6,795 kg

Mission Design and Management: NPO imeni Lavochkina

Launch Vehicle: Proton-K + Blok D-2 (8K82K no. 392-02 + 11S824F no. 3L)

Launch Date and Time: 16 November 1996 / 20:48:53 UT

Launch Site: GIK-5 / Site 200/39

Scientific Instruments:

Orbiter:

1. Argus imaging complex

– TV camera (HRSC)

– spectroscopic camera (WAOSS)

– Omega infrared and optical spectrometer

2. infrared Fourier spectrometer (PFS)

3. Termoskan mapping radiometer

4. Svet mapping spectrometer

5. Spikam multi-channel spectrometer

6. ultraviolet spectrophotometer (UFS-M)

7. long-wave radar (RLK)

8. Foton gamma-ray spectrometer

9. Neytron-S neutron spectrometer

10. mass spectrometer (MAK)

11. Aspera-S ion and particles power and mass analyzer

12. Fonema omni non-scanning energy-mass ion analyzer

13. Dimio omni ionosphere energy mass spectrometer

14. Mari-prob ionospheric plasma spectrometers

15. Maremf electron analyzer/magnetometer

16. Elisma wave complex experiment

17. Sled-2 low energy charged particle spectrometer

18. precision gamma-ray spectrometer (PGS)

19. Lilas-2 cosmic and solar gamma-burst spectrometer

20. Evris stellar oscilllation photometer

21. solar oscillation spectrometer (SOYa)

22. Radius-M dosimeter

23. tissue-equivalent dosimeter (TERS)

Small Autonomous Stations (MAS):

1. meteorology complex (MIS)

2. meteorology complex (DPI)

3. alpha-particle proton and x-ray spectrometer

4. Optimizm seismometer/magnetometer/inclinometer

5. panoramic camera (PanCam)

6. descent phase camera (DesCam)

7. soil oxidization capacity instrument (MOx)

Penetrators:

1. PTV-1 camera

2. Mekom meteorological unit

3. Pegas gamma-ray spectrometer

4. Angstrem x-ray spectrometer

5. Alfa alpha/proton spectrometer

6. Neytron-P neutron spectrometer

7. Grunt accelerometers

8. Termozond temperature probes

9. Kamerton seismometer

10. IMAP-7 magnetometer

Results: Mars 8, the only Soviet/Russian lunar or planetary probe in the 1990s, was an ambitious mission to investigate the evolution of the Martian atmosphere, its surface, and its interior. Originally planned as two spacecraft, Mars 94 and Mars 96, the missions were delayed and became Mars 96 and Mars 98. Subsequently Mars 98 was cancelled leaving Mars 96 as the first Russian deep space mission beyond Earth orbit since the collapse of the Soviet Union. The entire spacecraft comprised an orbiter, two small autonomous stations, and two independent penetrators. The three-axis stabilized orbiter carried two platforms for pointing several optical instruments for studying the Martian surface and atmosphere. After an initial period in low orbit lasting three to four weeks acting as a relay to the landers, the orbiter was designed to spend approximately two Earth years in a 250 × 18,000-kilometer orbit at 101° inclination mapping Mars. The orbiter would have released the two 88-kilogram small autonomous stations (Malaya avtonomnaya stantsiya, MAS), four to five days before entering orbit. The small stations would have landed on the Martian surface, cushioned by an inflatable shell that was to split open after landing. The stations were to have transmitted data daily (initially) and then every three days for about 20 minutes each session. The stations would have also studied soil characteristics and taken photos on the surface. The two 123-kilogram penetrators, each 2.1 meters long, would have impacted the Martian surface at a velocity of 76 meters/second to reach about 6 to 8 meters in depth. The plan was for the orbiter to release them between 7 and 28 days after entering orbit. During their one-year lifetimes, the penetrators would have served as nodes of a seismic network. In the event, the Proton-K rocket successfully delivered the payload to Earth orbit (after the first firing of the Blok D-2 upper stage). Initial orbit parameters were 150.8 × 165.7 kilometers at 51.53° inclination. At that point, the Blok D-2 was to fire once again to place Mars 8 into an elliptical orbit, after which the Fregat propulsion module (with its S5.

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