The baseline Proton-K was a three-stage rocket. Thirty were launched in this configuration, with payloads including all of the Soviet Union's
Salyut space stations, all
Mir modules with the exception of the
Docking Module, which was launched on the United States
Space Shuttle, and the
Zarya and
Zvezda modules of the
International Space Station. It was intended to launch Chelomey's crewed
TKS spacecraft, and succeeded in launching four uncrewed tests flights prior to the program's cancellation. It was also intended for Chelomey's 20-ton
LKS spaceplane that was never realised. Like other members of the
Universal Rocket family, the Proton-K was fuelled by
unsymmetrical dimethylhydrazine and
nitrogen tetroxide. These
hypergolic propellants ignite on contact, avoiding the need for an ignition system, and can be stored at ambient temperatures. This avoids the need for low-temperature–tolerant components, and allowed the rocket to sit on the pad fully fuelled for long periods of time. In contrast,
cryogenic fuels would have required periodic topping-up of propellants as they boil off. The propellants used on the Proton, were, however,
corrosive and
toxic and required special handling. The Russian Government paid for the cleanup of residual propellant in spent stages that impact downrange. Proton components were built in factories near Moscow, then transported by rail to the final assembly point near the pad. The first stage of the Proton-K consisted of a central oxidiser tank, and six outrigger fuel tanks. This separated as one piece from the second stage, which was attached by means of a lattice structure interstage. The second stage ignited prior to first stage separation, and the top of the first stage was insulated to ensure that it retained its structural integrity until separation. The first stage used six RD-253 engines, designed by
Valentin Glushko. The RD-253 is a single-chamber engine and uses a
staged combustion cycle. The first-stage guidance system was open-loop, which required significant amounts of propellant to be held in reserve. The third stage was powered by an
RD-0210 engine and four
vernier nozzles, with common systems. The verniers provided steering, eliminating the need for
gimballing of the main engine. They also aided stage separation, and acted as
ullage motors. Ducts built into the structure channelled vernier exhaust before stage separation. The third stage guidance system was also used to control the first and second stages earlier in flight. Many launches used an upper stage to boost the payload into a higher orbit.
Blok D upper stages were used on forty flights, the majority of which were for the
Luna and
Zond programmes. Ten flights used the Blok D-1, mostly to launch spacecraft towards
Venus. Blok D-2 upper stages were used three times, with the
Fobos 1,
Fobos 2 and
Mars 96 spacecraft. The Blok DM upper stage was used on 66 launches. The most commonly used upper stage was the Blok DM-2, which was used on 109 flights, mostly with
GLONASS and
Raduga satellites. Fifteen launches used the modernised Block DM-2M stage, mostly carrying
Ekspress satellites, however other satellites, including
Eutelsat's
SESAT 1, also used this configuration. Two
Araks satellites were launched using Block DM-5 upper stages. The Block DM1, a commercial version of the DM-2, was used to launch
Inmarsat-3 F2. The Block DM2 upper stage was used to launch three groups of seven
Iridium satellites, including
Iridium 33. This configuration was also used to launch
INTEGRAL for the
European Space Agency. Block DM3 stages were used on twenty five launches, almost exclusively carrying commercial satellites.
Telstar 5 was launched with a Block DM4. The
Briz-M upper stage was used for four launches; three carrying payloads for the Russian Government, and one commercial launch with
GE-9 for
GE Americom. One launch was reported to have used a Block DM-3 upper stage, however this may have been a reporting error, and it is unclear whether this launch actually used a DM-3, DM3, or DM-2. ==List of launches==