Contents

Buran (spacecraft)

Buran

Буран
BuranonAn-225 at the 1989 Paris Air Show
Type	Buran-class orbiter
Construction number	1.01
Country	Soviet Union
Named after	Russian for "Snowstorm"[1] or "Blizzard"
Status	Destroyed 12 May 2002; 22 years ago (2002-05-12)[2]
First flight	15 November 1988; 35 years ago (1988-11-15)[1]
No. of missions	1[1]
Crew members	0[1]
No. of orbits	2[1]

Buran (Russian: Буран, IPA: [bʊˈran], meaning "Snowstorm" or "Blizzard"; GRAU index serial number: 11F35 1K, construction number: 1.01) was the first spaceplane to be produced as part of the Soviet/Russian Buran program. Buran completed one uncrewed spaceflight in 1988, and was destroyed in 2002 due to the collapse of its storage hangar.^[3] The Buran-class orbiters used the expendable Energia rocket, a class of super heavy-lift launch vehicle. Besides describing the first operational Soviet/Russian shuttle orbiter, "Buran" was also the designation for the entire Soviet/Russian spaceplane project and its flight articles, which were known as "Buran-class orbiters".

Construction[edit]

The construction of the Buran spacecraft began in 1980, and by 1984 the first full-scale orbiter was rolled out. Over 1000 companies all over the Soviet Union were involved in construction and development. The Buran spacecraft was made to be launched on the Soviet Union's super-heavy lift vehicle, Energia. The Buran program ended in 1993.^[4]

Technical description[edit]

The Buran orbiter is built around the airframe, which is its main structural component, since all other components are attached to it. The components necessary for flight make up about 20% of the weight of the orbiter, while another 11% of weight is added by payload systems and removable parts. The wings of the Buran orbiter contain elevators whose position can be changed from +35° to −20°.^[7]

Exterior[edit]

Buran orbiters have their exterior covered in 38,600 heat shielding tiles designed to withstand 100 reentries,^[8][9] which themselves were very similar to the ones on the US Space Shuttle.^[10] However, the carbon-carbon Buran heat tiles have an antioxidant molybdenum disilicide coating. The black coating in the carbon-carbon heat tiles helps dissipate heat, and, similarly to the heat tiles used in the Space Shuttle, Buran heat tiles are glued to the orbiter, and the bottom of the heat tiles are left uncoated to equalize the pressure in the tile with that of its surroundings, preventing additional mechanical loads. The gaps between tiles are deliberate to allow for thermal expansion. The gaps were filled with quartz fiber, rope, alkaline elements, inserts and brush seals, and the carbon-carbon heat tiles were also waterproofed.^[8][11]

The Buran and Space Shuttle orbiters are exposed to similar temperatures, and both have similar levels of insulation. Buran has a different carbon-carbon heat tile layout in its underside, in which all gaps between heat tiles are parallel or perpendicular to the direction of airflow through the orbiter's underside, reducing heat in between heat tiles and in the boundary layer between the heat tiles and surrounding air, while helping maintain a laminar airflow around the orbiter.^[9][8]

Crew module[edit]

The crew module is an all-metal, welded, pressurised compartment housing the crew's workplaces, control and life support systems. It has three decks. The flight deck, known as the Command Compartment (KO), is the workspace for the crew and serves to accommodate the commander, pilot, engineer and mission specialist's seats, as well as the RMS operator's workplace. The middeck or Habitation Compartment (BO), serves as the living and sleeping quarters for the crew. It contains lockers, a galley, sleeping bags and a toilet in addition to three instrument bays with radio equipment and thermal control systems. Up to six crew members could be seated in the middeck during launch and reentry. The lower deck, known as the Aggregate Compartment (AO) houses the life support system, the power supply systems and parts of the thermal control system.^[12] The cockpit is similar in layout to that of the space shuttle, with three cathode-ray tube displays.^[13]

Docking system[edit]

The docking module (Стыковочный Модуль) is mounted into the forward part of the payload bay. It is a spherical compartment with a diameter of 2.67 m (8.8 ft), with a cylindrical tunnel leading to the androgynous peripheral docking unit (APAS-89). Unlike the U.S. Space Shuttle, the docking compartment for Buran features an extendable tunnel to increase clearance between orbiter and station. Another hatch, facing into the payload bay, was to support extravehicular activity from the orbiter.^[14]

Remote manipulator[edit]

The Onboard Manipulator System (Система Бортовых Манипуляторов), similar to the Space Shuttle's RMS, was developed at the Central Research and Development Institute for Robotics and Technical Cybernetics to support operations with payload. It could be operated both in manual and automatic modes. Buran-class orbiter could carry, depending on the mission, one or two manipulator arms.^[14][15][16]

Laboratory modules[edit]

To expand Buran's capabilities, pressurised modules similar to ESA's Spacelab were designed based on the 37K design. These modules had to be both compartments to conduct experiments and logistics volume, could be mounted either in the payload bay and connected to the crew cabin via tunnel or be temporarily docked to Mir's Kristall radial docking port. On Buran's maiden flight, the Accessory Unit (Блок Дополнительных Приборов) 37KB No.37070 was installed into the orbiter's payload bay. It carried recording equipment and accumulators providing power to onboard systems as the regular fuel cells based power system were not ready at the time. The second unit, 37KB No.37071 was built in 1987. It was planned to build a third unit, 37KB No.37072, but this never happened because of programme cancellation.^[17]

Propulsion[edit]

Orbital maneuvering is provided by the Joint Propulsion System (Объединенная Двигательная Установка).^[18]

Automatic landing system[edit]

The automatic landing system is capable of performing a fully automatic descent, approach and landing from any point located in the "admissible starting conditions area" at 100 kilometres (62 mi) altitude, controlling the orbiter's flight during the descent. Covering 8,000 kilometres (4,300 nmi) during the approach and eventually slowing down from 28,000 kilometres per hour (15,000 kn) to zero.^[19]

The first Buran flight was notable for the automatic landing system electing to perform an unlikely (estimated 3% probability) manoeuvre at the 20 kilometres (66,000 ft) key point, which was needed to extend the glide distance and bleed excessive energy. The standard approach was from the south and consisted of two left turns onto the final approach course. Instead, it performed additional turns in both directions and overflew the field to its northern side, before making a right turn back onto the final course. The landing system elected to perform the manoeuvre as the orbiter's energy didn't decrease enough due to strong-gusty winds in the area, measured at 15 metres per second (29 kn) and gusting up to 20 metres per second (39 kn) at ground level.^[20]

Specifications[edit]

The dry mass of Buran-class orbiters is quoted as 62 tonnes, with a maximum payload of 30 tonnes, for a maximum launch mass of 105 tonnes.^[21]

Mass breakdown^[3]

• Total mass of structure and landing systems: 42,000 kg (93,000 lb)
• Mass of functional systems and propulsion: 33,000 kg (73,000 lb)
• Maximum payload: 30,000 kg (66,000 lb)
• Maximum liftoff weight: 105,000 kg (231,000 lb)

Dimensions^[3][4]

• Length: 36.37 m (119.3 ft)
• Wingspan: 23.92 m (78.5 ft)
• Height on gear: 16.35 m (53.6 ft)
• Payload bay length: 18.55 m (60.9 ft)
• Payload bay diameter: 4.65 m (15.3 ft)
• Wing chine sweep: 78 degrees
• Wing sweep: 45 degrees

Propulsion^[4]

• Total orbital manoeuvring engine thrust: 17,600 kgf (173,000 N; 39,000 lbf)
• Orbital manoeuvring engine specific impulse: 362 seconds (3.55 km/s)
• Total manoeuvring impulse: unknown
• Total RCS thrust: 14,866 kgf (145,790 N; 32,770 lbf)
• Average RCS specific impulse: 275–295 seconds (2.70–2.89 km/s)
• Normal maximum propellant load: 14,500 kg (32,000 lb)

Unlike the US Space Shuttle, which was propelled by a combination of solid boosters and the orbiter's own liquid-propellant engines fuelled from a large tank, the Soviet/Russian Energia launch system used thrust from each booster's RD-170 liquid oxygen/kerosene engine (each with four nozzles), developed by Valentin Glushko, and another four RD-0120 liquid oxygen/liquid hydrogen engines attached to the central block.^[22]

Operational history[edit]

Orbital flight[edit]

The only orbital launch of a Buran-class orbiter, 1K1 (1К1: first orbiter, first flight^[23]) occurred at 03:00:02 UTC on 15 November 1988 from Baikonur Cosmodrome launch pad 110/37.^[3][24] Buran was lifted into space, on an uncrewed mission, by the specially designed Energia rocket. The automated launch sequence performed as specified, and the Energia rocket lifted the vehicle into a temporary orbit before the orbiter separated as programmed. After boosting itself to a higher orbit and completing two orbits around the Earth, the ODU (Russian: Объединенная Двигательная Установка, romanized: Ob"yedinennaya Dvigatel'naya Ustanovka, lit. 'Combined Propulsion System') engines fired automatically to begin the descent into the atmosphere, return to the launch site, and horizontal landing on a runway.^[25]

After making an automated approach to Site 251,^[3] Buran touched down under its own control at 06:24:42 UTC and came to a stop at 06:25:24,^[26] 206 minutes after launch.^[27] Under a crosswind of 61.2 kilometres per hour (38.0 mph), Buran landed 3 metres (9.8 ft) laterally and 10 metres (33 ft) longitudinally from the target mark.^[27][28] It was the first spaceplane to perform an uncrewed flight, including landing in fully automatic mode.^[29] It was later found that Buran had lost eight of its 38,000 thermal tiles over the course of its flight.^[28]

Projected flights[edit]

In 1989, it was projected that Buran would have an uncrewed second flight by 1993, with a duration of 15–20 days.^[23] However, the dissolution of the Soviet Union led to funding drying up and the Buran programme was officially cancelled in 1993.^[30]

See also[edit]

• List of Buran missions
• OK-GLI – Buran Analog BST-02 test vehicle
• Buran shuttle 1.02 Ptichka
• Buran shuttle 2.01
• Buran shuttle 2.02
• Buran shuttle 2.03

• MAKS (spacecraft) – Soviet air-launched spaceplane concept
• Mikoyan-Gurevich MiG-105 – Soviet spaceplane test program
• Space Shuttle program – American spaceplane program
• Tupolev OOS – Soviet air-launched spaceplane concept

References[edit]

Further reading[edit]

• Hendrickx, Bart; Vis, Bert (2007). Energiya-Buran: The Soviet Space Shuttle. Springer-Praxis. p. 526. Bibcode:2007ebss.book.....H. ISBN 978-0-387-69848-9.
• Elser, Heinz; Elser-Haft, Margrit; Lukashevich, Vladim (2008). History and Transportation of the Russian Space Shuttle OK-GLI to the Technik Museum Speyer. Technik Museum Speyer. ISBN 978-3-9809437-7-2.

External links[edit]

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