Phobos program

Not to be confused with Fobos-Grunt.
Phobos 2

Illustration of the Phobos spacecraft
Operator IKI
Mission type Orbiter
Launch date July 12, 1988
Launch vehicle Proton-K rocket
Satellite of Mars
Orbital insertion date January 29, 1989
COSPAR ID 1988-059A
Homepage Phobos Mission
Mass 2600 kg (6220 kg with orbital insertion hardware attached)

The Phobos (Russian: Фобос, Fobos, Greek: Φόβος) program was an unmanned space mission consisting of two probes launched by the Soviet Union to study Mars and its moons Phobos and Deimos. Phobos 1 was launched on July 7, 1988, and Phobos 2 on July 12, 1988, each aboard a Proton-K rocket.

Phobos 1 suffered a terminal failure en route to Mars. Phobos 2 attained Mars orbit, but contact was lost before the final phase, prior to deployment of a planned Phobos lander. Phobos 1 and 2 were of a new spacecraft design, succeeding the type used in the Venera planetary missions of 1975–1985, last used during the Vega 1 and Vega 2 missions to comet Halley. They each had a mass of 2600 kg (6220 kg with orbital insertion hardware attached).

The program featured co-operation from 14 other nations, including Sweden, Switzerland, Austria, France, West Germany, and the United States (which contributed the use of its Deep Space Network for tracking the twin spacecraft).

Objectives

The objectives of the Phobos missions were to:

Spacecraft design

The main section of the spacecraft consisted of a pressurized toroidal electronics section, surrounding a modular cylindrical experiment section. Below these were mounted four spherical tanks (the Fregat stage) containing hydrazine for attitude control and, after the main propulsion module was to be jettisoned, orbit adjustment. A total of 28 thrusters (twenty-four 50 N thrusters and four 10 N thrusters) were mounted on the spherical tanks, with additional thrusters mounted on the spacecraft body and solar panels. Attitude was maintained through the use of a three-axis control system, with pointing maintained with Sun and star sensors.

Phobos 1

Phobos 1 operated nominally until an expected communications session on September 2, 1988 failed to occur. The failure of controllers to regain contact with the spacecraft was traced to an error in the software uploaded on August 29/August 30, which had deactivated the attitude thrusters. By losing its lock on the Sun, the spacecraft could no longer properly orient its solar arrays, thus depleting its batteries.

Software instructions to turn off the probe's attitude control, normally a fatal operation, were part of a routine used when testing the spacecraft on the ground. Normally this routine would be removed before launch. However, the software was coded in PROMs, and so removing the test code would have required removing and replacing the entire computer. Because of time pressure from the impending launch, engineers decided to leave the command sequence in, though it should never be used. However, a single-character error in constructing an upload sequence resulted in the command executing, with subsequent loss of the spacecraft.[1]

Phobos 2

Sample image taken by the Phobos 2 probe. Enhanced image released by the IKI. Taken 430 km away with a resolution of 80/420 m.

Phobos 2 operated nominally throughout its cruise and Mars orbital insertion phases on January 29, 1989, gathering data on the Sun, interplanetary medium, Mars, and Phobos. Phobos 2 investigated Mars surface and atmosphere and returned 37 images of Phobos[1] with a resolution of up to 40 meters.

Shortly before the final phase of the mission, during which the spacecraft was to approach within 50 m of Phobos' surface and release two landers, one a mobile "hopper", the other a stationary platform, contact with Phobos 2 was lost. The mission ended when the spacecraft signal failed to be successfully reacquired on March 27, 1989. The cause of the failure was determined to be a malfunction of the on-board computer.[1]

The Phobos design was used again for the long delayed Mars 96 mission which ended in failure when the launch vehicle's fourth stage misfired.

Systems and sensors

Phobos probes carried several instruments: solar x-ray and ultraviolet telescopes, a neutron spectrometer and the Grunt radar experiment designed to study the surface relief of Phobos. The lander had an x-ray/alpha spectrometer to provide information on the chemical element composition of the surface of Phobos, a seismometer to determine the internal structure of Phobos, and the "Razrez" penetrator with temperature sensors and an accelerometer for testing the physical and mechanical properties of the surface.

The Phobos 2 infrared spectrometer (ISM) obtained 45000 spectra in the near infrared (from 0.75 to 3.2 µm) in the equatorial areas of Mars, with a spatial resolution ranging from 7 to 25 km, and 400 spectra of Phobos at 700 m resolution. These observations made it possible to retrieve the first mineralogical maps of the planet and its satellite, and to study the atmosphere of Mars. ISM was developed at IAS and DESPA (Paris Observatory) with support from CNES.

List of instruments:

See also

References

  1. ↑ 1.0 1.1 1.2 Risks digest summary of the malfunctions, from SCIENCE magazine, Vol 245, 8 September 1989

External links