|Mission type||Mars Orbiter|
|Mission duration||Failed to orbit|
|Launch mass||6,180 kg (13,620 lb)|
|Dry mass||3,159 kg (6,964 lb)|
|Start of mission|
|Launch date||16 November 1996, 20:48:53 UTC|
|Rocket||Proton-K / D-2|
|Launch site||Baikonur Cosmodrome,|
|Contractor||Khrunichev State Research and Production Space Center|
|Entered service||Failed to orbit|
|End of mission|
|Decay date||17 November 1996|
|Reference system||Geocentric orbit|
|Regime||Low Earth orbit|
Mars 96 (sometimes called Mars-8) was a failed Mars mission launched in 1996 to investigate Mars by the Russian Space Forces and not directly related to the Soviet Mars probe program of the same name. After failure of the second fourth-stage burn, the probe assembly re-entered the Earth's atmosphere, breaking up over a 320 km (200 mi) long portion of the Pacific Ocean, Chile, and Bolivia. The Mars 96 spacecraft was based on the Phobos probes launched to Mars in 1988. They were of a new design at the time and both ultimately failed. For the Mars 96 mission the designers believed they had corrected the flaws of the Phobos probes, but the value of their improvements was never demonstrated due to the destruction of the probe during the launch phase.
Mars 96, 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.
It was, however, a very ambitious mission and the heaviest interplanetary probe launched up to that time. The mission included a large complement of instruments provided by France, Germany, other European countries and the United States. Similar instruments have since been flown on Mars Express, launched in 2003. Its project scientist was Alexander Zakharov.
Mars 96 was intended to solve several problems concerning our understanding of Mars. The scientific goal of the mission was to analyze the planet's evolutionary history of its surface, atmosphere, and inner structure. Other studies during cruise, such as astrophysical studies were to be made. They can be broken down into several categories.
Studies of the martian surface were to include a global topographical survey, mineralogical mapping, soil composition, and studies of the cryolithozone and its deep structure.
Studies of the atmosphere were to include studies of the climate, abundance of certain elements, ions, and chemicals such as water, carbon dioxide, ozone, and others, general global monitoring, pressure variations over time, and characterization of aerosols.
Studies of planet structure were to find the thickness of the crust, study the martian magnetic field, study of thermal flux, search for the possibility of active volcanoes, and study seismic activity.
Plasma studies were to study the strength and orientation of the magnetic field, study of ions and energy composition of plasma during interplanetary cruise and near Mars, and the study of the magnetosphere and its boundaries.
Astrophysical studies were to take place during interplanetary cruise. They included studies of cosmic gamma-bursts and the study of oscillations of the Sun and other stars.
The Mars 96 orbiter was a 3-axis Sun/star stabilized spacecraft which was based on the design of the Phobos orbiters. It had a deployable high and medium gain antennae. Two large solar panels were attached to either side of the spacecraft. It also had a jettisonable propulsion unit to be separated sometime after Mars orbit insertion. Two Surface Stations were attached on top of the spacecraft. Two Penetrators were attached to the propulsion unit. It also had a MORION system which was the central interface, microprocessor, and memory system. The orbiter had a total mass, with fuel, of 6180 kg. It had a dry mass of 3159 kg.
Each Surface Station was contained in an aeroshell about 1 meter high and about 1 meter in diameter. Each station had a Station Data Processing Unit (SDPI) for controlling station operations, telecommunications unit with a transmitter and a receiver for data transfer, and a power supply consisting of two radio-isotope thermoelectric generators (RTGs), a battery, and electronics for controlling battery charge. Each Surface Station also carried a compact disc which contained science fiction stories, sound, and art that have inspired Mars exploration. It was intended as a gift for future human explorers. The expected lifetime of each Surface Station was one year.
Each penetrator consisted of two major structures: the forebody and the afterbody. When the penetrator struck the surface the forebody was designed to separate and delve 5 to 6 meters into the surface while the afterbody remained on the surface connected to the forebody by wires. The forebody contained the housekeeping equipment and part of the analysing package while the afterbody contained the rest of the analysing package and the radio equipment. Each penetrator was powered by a Radioisotope thermoelectric generator (RTG) and a battery. The expected lifetime of each penetrator was one year.
Two surface stations, each having:
Two penetrators, each having:
The launch was to take place on 16 November 1996 on a Proton 8K82K/11S824F launch vehicle. This is a four-stage rocket in a configuration which had flown only twice before, both times to launch Phobos spacecraft towards Mars in 1988. The first three stages were to burn to fuel depletion. The fourth stage, called the Blok D-2, would then ignite to place it and the spacecraft into a parking orbit around the Earth. Later it was to re-ignite to begin the trans-Mars injection maneuver. After the fourth stage shut-down, the spacecraft was to separate, deploy its antennae, and use its propulsion unit to complete the burn. After this was complete, the spacecraft was to deploy its solar panels and the PAIS science platform.
The cruise was to take about 10 months. Two course corrections were planned on the way. Astrophysical studies were also to take place during interplanetary cruise. Mars arrival was scheduled to take place on 12 September 1997.
Four to five (preferably five) days before arrival, the spacecraft was to release both Surface Stations to land at two separate sites in the northern hemisphere. After release, the spacecraft would perform a deflection maneuver to change the orbiter's trajectory to a fly-by path in preparation for orbit insertion. At the appropriate moment, with the main engine of the propulsion unit facing the direction of flight, the spacecraft would make a burn to slow down and enter Mars orbit. Initial Mars orbit would have a periapsis of 500 km, an apoapsis of about 52,000 km, with an orbital period of 43.09 hours.
While the orbiter performed the orbit insertion burn, both Surface Stations were to make a soft landing on Mars. Both landing sequences were identical. They began with the craft being slowed down by aerodynamic pressure. At an altitude of 19.1 km, a parachute would deploy, followed by heat shield separation at 18.3 km, and inflation of the airbags at 17.9 km. When the lander, cushioned by the airbags, hit the ground, the parachute would separate. The airbag would eventually roll to a stop. After which both airbags would separate revealing the lander. The four petals would open and the lander would signal the orbiter when it passed over the landing site.
The first task the orbiter would perform after achieving Mars orbit was to receive a signal from both Surface Stations to confirm landing. The window to land the Penetrators would be seven to twenty-eight days after Mars orbit insertion. The primary science phase of the orbiter could not begin until after both Penetrators were released and the propulsion unit was jettisoned.
The landing of each penetrator would be identical. It began with the spinning up of the penetrator for stability followed by separation from the orbiter. The penetrator would fire a solid rocket motor which would begin to drop it from orbit. After 20–22 hours, the penetrator would encounter the martian atmosphere. It then deploys a braking device. When it impacts, the forebody separates and goes in deeper than the main body. It then performs a communications session with the orbiter to confirm landing.
About a month after orbit insertion, after the penetrators have been released, the orbiter would jettison its propulsion unit. The propulsion unit would get in the way of the deployment of the LWR instrument and ARGUS platform and has to be jettisoned before the primary science phase can begin. The nominal mission of the orbiter would have lasted one Earth year. After the propulsion unit was jettisoned, the orbiter had a low power thrust system for orbit maintenance. During the nominal phase a fly-by of Deimos was possible, but a fly-by of Phobos was not possible until after the nominal mission. If an extended mission were approved, aerobraking over a period of two to three months would have reduced the orbital period to around nine hours.
The launch vehicle lifted off on 16 November 1996 at 20:48:53 UTC. The launch vehicle performed properly up to parking orbit. The planned second burn of the Blok D-2 fourth stage failed to take place. The spacecraft separated and then performed its engine burn automatically. Unfortunately, without the fourth stage burn, the spacecraft lowered its perigee back into the Earth's atmosphere causing reentry. The fourth stage re-entered on a later orbit. There is disagreement between American and Russian sources on the timeline.
A review board could not determine whether the Mars 96 crash was due to failure of the Proton-K launch vehicle Blok D-2 upper stage or a malfunction of the Mars 96 spacecraft itself. The failure investigation board concluded that lack of telemetry data during critical parts of the mission prevented identification of the cause of the failure. The failure occurred at the second ignition of the Proton Blok D-2 upper stage, while the spacecraft was out of range of Russian ground stations. The Mars 96 spacecraft carried 200 grams of plutonium-238 in the form of small pellets. They were designed to withstand heat and impact and are thought to have survived re-entry. The Block D-2 stage carried no plutonium. The spacecraft is believed to have crashed somewhere in a 320 km long by 80 km wide oval running southwest to northeast and centered 32 km east of Iquique, Chile. No parts of the spacecraft or upper stage have been recovered.
It was originally believed that the Mars 96 assembly burnt up in the atmosphere and the debris fell into the Pacific Ocean. However, in March 1997, the United States Space Command admitted that it had miscalculated the satellite's path of re-entry. "We were aware of a number of eyewitness accounts of the re-entry event via the media several weeks after the re-entry occurred", wrote Major Stephen Boylan, Chief of the Media Division at the United States Space Command in Colorado Springs, Colorado. "Upon further analysis, we believe it is reasonable that the impact was in fact on land". Mars 96 carried four assemblies designed to enter the martian atmosphere, two surface penetrators and two surface stations. These would almost certainly have survived entry into Earth's atmosphere. The two surface penetrators were designed to survive an impact with the ground. Despite this and the fact that the four assemblies carried a combined total of 200 grams of plutonium-238 for fuel, the Russians have not mounted any recovery effort to date.
A number of later missions, both planned and successful, are based on the technology of Mars 96, for example ESA's Mars Express (launched in 2003), NetLander (cancelled) and its successor MetNet (proposed for launches in 2016–2019), cancelled. Some of the equipment designs from Mars 96 were used for MARS-500 experiments.