Tu-2000 Credit - © Mark Wade

In reaction to US X-30 project, government decrees of 27 January and 19 July 1986 ordered development of a Soviet equivalent. The Ministry of Defense issued technical specifications on 1 September for an MVKS, a single-stage reusable aerospaceplane system. The MKVS was to provide effective and economic delivery to near-earth orbit; develop the technology for effective transatmospheric flight; provide super high-speed intercontinental transport, and fulfill military objectives in and from space.

It was known that the Tupolev, Yakovlev, and Energia design bureaus submitted designs.

Tupolev seems to have received the development go-ahead. The Tu-2000A was to be an experimental design to test the many advanced technologies required. It would have been 55 to 60 m long, have a 14 m wingspan, and a takeoff mass of 70 to 90 metric tons. It would have only been capable of Mach 6. Before work was stopped in 1992, some development work was completed: a wing torque box of nickel alloy had been built, as well as fuselage elements, cryogenic fuel tanks, and composite fuel lines. The Tu-2000A would have used a variable cycle turboramjet engine using methane or hydrogen fuel.

The Tu-2000A was to have been followed by two production designs, as Tupolev felt no single design could meet all of the military requirements. The Tu-2000B would have been a 10,000 km range bomber with a crew of two. 350 metric tons at takeoff, 200 metric tons empty, it would have been 100 m long, with a wing of 40.7 m span and 1250 square meters area. Six liquid hydrogen powered engines would take the bomber to Mach 6 cruise speed at 30,000 m altitude.

The Tu-2000 space launcher would have weighted 260 metric tons at lift-off and be capable of Mach 25 (orbital velocity). An 8 to 10 metric ton payload would have been delivered to a 200 km orbit. As with the X-30, airbreathing flight to orbit seemed questionable. The 8 turboramjets would have to be supplemented by a scramjet or a rocket engine in order to achieve orbit.

Typical orbit: 200 km, 51 degrees inclination. Length: 72.00 m (236.00 ft). Maximum Diameter: 13.00 m (42.00 ft). Span: 30.00 m (98.00 ft). Mass: 90,000 kg (198,000 lb). Main Engine Propellants: Air/LOX/LH2. Associated Launch Vehicle: Tu-2000.

• 1986 January 27 - Government decree orders design of a Soviet aerospaceplane - Launch Vehicle: Tu-2000, Yakovlev MVKS, VKS.

  In reaction to US X-30 project government decree ordered development of a Soviet equivalent.

• 1986 July 19 - Government decree orders development of a Soviet aerospaceplane - Launch Vehicle: Tu-2000, Yakovlev MVKS, VKS.

  The decree of 27 January 1986 was reaffirmed.

• 1986 September 1 - MVKS specification issued - Launch Vehicle: Tu-2000, Yakovlev MVKS, VKS.

  The Ministry of Defence issued technical specifications on 1 September for an MVKS, a single-stage reusable aerospaceplane system. The MKVS was to provide effective and economic delivery to near-earth orbit; develop the technology for effective transatmospheric flight; provide super high-speed intercontinental transport, and fulfil military objectives in and from space.

• Pesavento, Peter, Spaceflight, "Russian Space Shuttle Projects 1957-1994", 1995, Volume 37, page 226.

• Semenov, Yu. P., S P Korolev Space Corporation Energia, RKK Energia, 1994. ISBN: 1896522815. Dual English/Russian language picture book of the history of the Energia Corporation. Many unique photos and drawings of Korolev's rockets and spacecraft. Republished by Apogee books in 2000. More at amazon.com...

• Butowski, Piotr, Air Forces Monthly Special, X-Planes, "Black Reds", February 1998, p. 35.