Mavr

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Mavr

Part of TMK

Mavr Mars Spacecraft
A model of the Mars flyby spacecraft 'Mavr' at the Tsniimash museum. Mavr was a revision of the TMK in the mid-1960's to incorporate a flyby of Venus on the return leg of the voyage. This would reduce propulsion requirements and total time for the primary Mars flyby mission.
Credit: © Mark Wade

Russian manned Mars flyby. Study 1963. A variation of the TMK-1 scenario by Maksimov's unit would still use a single N1 launch. However a flyby of Venus would be undertaken on the return voyage from Mars.

Status: Study 1963. Gross mass: 75,000 kg (165,000 lb). Specific impulse: 350 s. Height: 25.00 m (82.00 ft). Span: 12.00 m (39.00 ft).

This would reduce both flight time and the earth-return velocity. The project was given the code name "Mavr" ('Moor' or MArs - VeneRa).

Crew Size: 3.

Family: Mars Expeditions, Mars flyby. Country: Russia. Launch Vehicles: Mars tactical rocket, N1, N1 1969. Propellants: Lox/Kerosene. Agency: Korolev bureau.

Photo Gallery

Mavr Spacecraft
MAVR Mars-Venus flyby spacecraft. The original TMK was similar.
Credit: © Mark Wade

1970 October 20 - . LV Family: N1.

Lox/LH2 upper stages for the N1 necessary to achieve program - . Related Persons: Mishin, Chelomei, . Spacecraft: , MKBS, MAVR, Almaz, Salyut, LK, L3M.
Mishin reviews the work and configurations of the Lox/LH2 (S and Sr) upper stages for the N1 necessary to achieve various programs. Mishin reviews the work and configurations of the Lox/LH2 (S and Sr) upper stages for the N1 necessary to achieve various programs (Mishin Diaries 2-293). Here was see evidence for several previously hinted-at but poorly-documented projects: the Lunar Orbital Station (N1+Almaz), the MAVR manned Mars-Venus-Flyby Spacecraft: AM Isaev - about speeding work on the engine 11D56. AM Lyulka - about speeding work on the engine 11D57.
1. S, Sr - LOS (lunar orbital station?) SNTV satellite for direct TV broadcasting, MAVT (MAVR?), DOS-II (later Mir).
2. S + Sr - L3M, Mavr, MKBS
3. S + S + Sp - L3M, MKBS, Mavr and others.
4. NII - DOS (20t - indecipherable) - this apparently refers to later plans to dump Chelomei's Proton vehicle and go back to the original plan to use the NII (consisting of the second and third stages of the N1) for this earth orbit payload class.
5. N1S => 110 t (the low earth payload for this version of the improved N1). (Mishin Diaries 2-293).

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