Mars 1969B

The device was one of the two identical first multi-ton AMS in the USSR and the world. The device had a starting weight of 4850 kg, the fuel tank of the probe had a spherical shape with an internal partition, so that it consisted of two separate compartments. Two solar panels with a total area of ​​7 square meters were installed on both sides of the device. The parabolic antenna had a diameter of 2.8 m, mounted in the upper part of the probe, together with three airtight compartments, the first for electronics, the second for radio communications and navigation systems, and the third for cameras, batteries and telemetry devices. Also, two cone-shaped antennas and a set of sensors were installed on the outer side of the spacecraft. ^[3]

The main engine was installed at the bottom of the probe and used TNA to run on nitrogen tetroxide and asymmetric dimethylhydrazine ( UDMH ), which were the basis of the fuel. Eight engines with their own fuel tanks and 9 pressurized tanks that control the supply of helium for (2 engines), control over the trajectory (2), for control (4). The stabilization of the flight with a three-dimensional orientation was achieved due to: 2 Solar sensors, 2 Earth sensors, 2 Mars sensors, a star sensor, gyroscopes, and small engines that use compressed gaseous nitrogen, which is stored in 10 airtight tanks. A power of 12 amperes was generated by the solar batteries of the device, and then energy was accumulated in nickel-cadmium batteries with a capacity of 110 amperes * hour. ^[3]

Communication was carried out through two transmitters of the centimeter range (6 GHz), transmitting data at a speed of 6000 bits / s; two transmitters and three receivers of decimeter range (790-940 MHz), consuming 100 watts of electricity and transmitting data at a speed of 128 bit / s on 500 telemetry channels. A high magnification parabolic antenna was used as a transmitter when approaching Mars, as well as a low gain antenna conical semi-directional antenna. Thermal control was achieved through passive screen-vacuum insulation using a system of sealed compartments consisting of ventilation and an air circulation unit that pass through radiators and are exposed to sunlight and shade. ^[3]

The scientific equipment of the apparatus consisted mainly of three television cameras designed to take pictures of the surface of Mars. The camera had 3 color filters with two lenses: a 50 mm lens with a resolution of 1,500 x 1,500 km and a 350 mm lens with a resolution of 100 x 100 km. Image size was 1024 x 1024 pixels with a maximum resolution of 200 to 500 meters. The camera system consisted of a recording unit, a processing unit, and a unit for preparing an image for transmission. The camera can store 160 images. The apparatus had a radiometer, a water vapor detector, an ultraviolet and infrared spectrometer, a radiation tracking detector, a gamma spectrometer, a hydrogen / helium mass spectrometer, a solar plasma spectrometer, and a low-energy ion spectrometer. ^[3]

Launching a spacecraft into Earth orbit with a Proton-K launch vehicle and Block-D upper stage.

Bringing to the trajectory of flight to Mars. Reclosing the upper stage after one orbit in Earth orbit. Dosgon spacecraft built-in engine.

Two maneuvers of trajectory correction during 6 months of flight to Mars.

The launch of the AMS into the orbit of the artificial satellite of Mars 34000 X 1700 km with an inclination of 40 degrees and a period of revolution of 24 hours. Photographing and other studies from this orbit. Orbit correction to reduce periapsis to 500-700 km. Conducting research and photography from this orbit for three months. ^[3]

“Mars 1969B” was launched on April 2, 1969 at 10:33:00 UTC from the Baikonur Cosmodrome 81/23, the Proton-K booster rocket and Upper Stage D ^{[4] [5]} . The launch of the device failed. Immediately after 0.02 seconds after the start, one of eight - the 11D43 rocket - exploded ^[6] . The INITIALLY control system tried to compensate for the thrust of the lost rocket, the thrust was performed by 5 engines for up to 25 seconds, gaining a height of about 1 km, due to the lack of thrust the rocket began to tip over into a horizontal position. All 6 engines were turned off, under this influence, the rocket exploded at 41 seconds after launch and fell about 3 km ^[1] from the launch pad. ^[2]

The AMS flight program “Mars 1969B” was not completed.

• Mars 1969A is the third-generation Soviet automatic interplanetary station from the M-69 series, designed to study Mars from the orbit of an artificial satellite.