MAKS mockup - side - MAKS mockup - side view Credit: Dr.Vadim P.Lukashevich. 17,290 bytes. 339 x 195 pixels.

The MAKS spaceplane was the ultimate development of the OK-M studies NPO Molniya conducted with NPO Energia. The draft project for MAKS was completed in 1988 and consisted of 220 volumes, generated by NPO Molniya and 70 sub-contractors and government institutes. Development of MAKS was authorised but cancelled after Perestroika. At the time of the cancellation, mock-ups of both the MAKS orbiter and the external tank had been finished. A 9,000 kgf experimental engine with 19 injectors was tested. There were 50 test burns proving the separate modes and a smooth switch between them. Since it was expected that MAKS could reduce the cost of transport to earth orbit by a factor of ten, it was hoped in the 1990’s that development funding could be found. However this has not happened to date. MAKS was to have flown by 1998.

The MAKS air-launched manned space system weighed 620 tonnes on takeoff and consisted of three elements:

• An-225 Mriya carrier aircraft, the largest in the world, originally developed to transport the Buran orbiter. The Mriya would take the 275 tonne MAKS piggy-back to an altitude of 8,000 to 9,500 m and then release it at a speed of 900 kph.

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  MAKS mockup - aft - MAKS mockup - aft view of RD-701 engines Credit: Dr.Vadim P.Lukashevich. 19,249 bytes. 281 x 200 pixels.

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• External tank. This carried liquid oxygen, kerosene, and liquid hydrogen propellants. It was 6.38 m in diameter and 32.1 m long, with a total mass of 248,000 kg and an empty mass of 11,000 kg.

• MAKS Orbiter. This spaceplane, designed for 100 reuses, was derived from the OK-M1 designed for NPO Energia. On-board systems were based on those already developed for Energia and Buran. The orbiter had an empty mass of 18,400 kg, with a wingspan of 12.5 m and a length of 19.3 m. An unmanned version could deliver 9.5 tonnes to a 200 km, 51 degree orbit in a payload bay 3.0 m diameter x 8.7 m long. The manned version took two crew and a payload of 8.3 tonnes in a bay 2.6 m diameter x 6.8 m long to the same orbit. At MAKS’ tail were two RD-701 tripropellant engines. These were designed for 15 re-uses and used dense kerosene and liquid oxygen for initial operations, then switched modes to a reduced thrust and higher specific impulse using low density liquid hydrogen and liquid oxygen. This reduced the size of the huge hydrogen tank otherwise required. The RD-701 engine assembly in the MAKS had a total mass of 3990 kg and delivered a total thrust of 400,000 kgf at separation from the An-225.

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MAKS propellant tank - MAKS propellant tank mockup Credit: Dr.Vadim P.Lukashevich. 19,027 bytes. 310 x 200 pixels.

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Craft.Crew Size: 2. Design Life: 100 flights. Total Length: 19.3 m. Total Mass: 27,000 kg. Total Payload: 8,300 kg.

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MAKS side view - MAKS side view drawing Credit: Dr.Vadim P.Lukashevich. 42,391 bytes. 721 x 371 pixels.

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MAKS top view - MAKS top view drawing Credit: Dr.Vadim P.Lukashevich. 49,732 bytes. 724 x 393 pixels.

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MAKS draft project is completed.

• 302 - Buran Home Page, . HTML when accessed: http://www.buran.ru/homepage.htm

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MAKS launch - MAKS launches from back of An-225 Credit: Dr.Vadim P.Lukashevich. 9,910 bytes. 220 x 234 pixels.

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MAKS mission profile Credit: Dr.Vadim P.Lukashevich. 17,033 bytes. 302 x 264 pixels.

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MAKS cutaway drawing Credit: Dr.Vadim P.Lukashevich. 18,056 bytes. 361 x 301 pixels.

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