NASA Logo, National Aeronautics and Space Administration
NASA Space Science Data Coordinated Archive Header

Mars 96 Penetrator



The Mars 96 spacecraft was launched into Earth orbit, but failed to achieve insertion into Mars cruise trajectory and re-entered the Earth's atmosphere at about 00:45 to 01:30 UT on 17 November 1996 and crashed within a presumed 320 km by 80 km area which includes parts of the Pacific Ocean, Chile, and Bolivia. The cause of the crash is not known.

The Russian Mars 96 mission was designed to send an orbiter, two small autonomous stations, and two surface penetrators to Mars to investigate the evolution and contemporary physics of the planet by studying the physical and chemical processes which took place in the past and which currently take place. Mars 96 was scheduled to arrive at Mars on 12 September 1997, about 10 months after launch, on a direct trajectory.

The two Mars 96 Penetrators were mounted on the bottom of the orbiter near the propulsion system. The penetrators were long thin cylinders, pointed at the bottom, or forebody, and with a widened, funnel-shaped top. Instruments were contained inside throughout the length of the cylinder. The scientific objectives of the penetrator experiments were to obtain images of the surface, study martian meteorology, examine the physical, chemical, magnetic, and mechanical properties of the martian regolith, including its water content, collect data on the magnetic field, and record seismic activity.

After orbit insertion, adjustment to 300 km periapsis, and 7 to 28 days of orbital maneuvers, the orbiter would be properly oriented and the first penetrator would be spun about its long axis and released. When the penetrator had moved away from the orbiter, its solid rocket motor was to ignite and put it into an atmospheric entry trajectory. Entry would occur 21 to 22 hours later. The penetrator was to enter the atmosphere at about 4.9 km/sec at an angle 10-14 degrees. The probe would first be slowed aerodynamically, followed by inflation of a braking device. The penetrator was to strike the surface at approximately 80 m/s. The forebody would separate on impact and can penetrate 5 to 6 meters into the ground, attached by wires to the aftbody, the top of the aftbody remaining above the surface. The plan called for the first penetrator to land near the site of one of the surface stations, and the second to land at least 90 degrees away. Both penetrators could have been released on the same orbit.

The penetrator was equipped with instruments in both the forebody and aftbody. The forebody held a seismometer, accelerometer, thermoprobe, neutron detector, and an alpha-proton-X-ray spectrometer. The aftbody contained a gamma-ray spectrometer and thermoprobe within the part of the cylinder underground, and meteorology sensors, a magnetometer, a television camera, and transmitter exposed at the top. The experiments were to begin after landing. Data was to be transmitted to the orbiter and then relayed to Earth. The penetrators have an expected lifetime of 1 year.

Alternate Names

  • Mars96Penetrator2

Facts in Brief

Launch Date: 1996-11-16
Launch Vehicle: Proton
Launch Site: Tyuratam (Baikonur Cosmodrome), Kazakhstan
Mass: 45 kg

Funding Agency

  • Russian Space Agency (Russia)


  • Planetary Science

Additional Information

Questions and comments about this spacecraft can be directed to: Dr. David R. Williams



NameRoleOriginal AffiliationE-mail
Dr. Alexander V. ZakharovProject ScientistRussian Academy of
Dr. Albert A. GaleevProgram ScientistRussian Academy of

Other Mars 96 Information from NSSDCA

Mars 96 Failure - Timeline from launch to re-entry
Mars 96 Orbiter
Mars 96 Surface Station

Other Sources of Mars 96 Information

Mars 96 Project (IKI)

Information about Mars

Mars Page

[] NASA Logo -