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TKS VA
Part of TKS

TKS VA Test

TKS VA Test
Configuration of the 82LB72 LVI dual-VA capsule test configuration. Externally the test configuration was identical with an all-up TKS ferry. The second VA, housed within the fairing, had no launch escape system and could not be rescued in the case of a launch vehicle failure.

Russian manned spacecraft module. The VA reentry capsule was similar in configuration to the American Apollo, but 30% smaller. Reusable re-entry capsule.

AKA: 11F74;Vozvrashchaemiy apparat. Status: Operational 1976. First Launch: 1976-12-15. Last Launch: 1979-05-22. Number: 8 . Payload: 1,880 kg (4,140 lb). Gross mass: 3,800 kg (8,300 lb). Height: 3.64 m (11.94 ft). Diameter: 2.79 m (9.15 ft).

It was derived from earlier capsule designs for the Chelomei ballistic Raketoplan and LK-1 manned circumlunar spacecraft of the 1960's. Although extensively flight tested, it never flew with a crew aboard.

The TKS VA BSO test configuration of the TKS VA was used to prove the recovery systems. Two TKS capsules were orbited in a single launch. The upper spacecraft consisted of the TKS SA capsule, the TKS BSO module on its nose for orbital maneuvering and retrofire, and the SAS launch escape tower. The lower spacecraft consisted of only the TKS and BSO and was lost in the event of a launch vehicle failure.

The VA was capable of 31 hours of autonomous flight after separation from the FGB. The crew of three were provided with seats with customized form-fitting liners facing a control panel similar to that used in Soyuz T. Access to the FGB on the pad was through a square hatch in the side of the capsule. This could also be used to conduct EVA's in orbit, with the VA acting as an air lock for the FGB. Access to the FGB was via a hatch in the heat shield below the middle seat.

With the crew, 50 kg of payload could be returned. Without the crew 500 kg of payload could be returned. Total internal volume was 8.37 m3. Retrofire was initiated by the BSO block on the nose of the VA. The VA capsule had a hypersonic lift to drag ratio of 0.25. This allowed the BSU-V manned capsule guidance system to maneuver the spacecraft to its landing point using the optimum path for minimal heating and G-forces.

The reusable heat shield material developed for the VA was far superior to that used on the Soyuz capsule and was used as well on Chelomei's K-1 and LKS manned spacecraft designs. Once the capsule was subsonic a drogue parachute deployed for seven seconds, followed by the main chute with 1770 square meters of area. The capsule made a soft landing using a retrorocket in the parachute lines. This was triggered by the Probki radioactive sensor system within the Kaktus gamma ray altimeter, which set off the DU braking unit for a soft landing of the capsule.

Crew Size: 3. Habitable Volume: 4.56 m3. Crew: 255 kg (562 lb). Miscellaneous Contingency: 50 kg (110 lb).


More at: TKS VA.

Family: Manned spacecraft module. Country: Russia. Spacecraft: TKS. Launch Vehicles: Proton, Proton-K. Launch Sites: Baikonur, Baikonur LC81/24. Bibliography: 2, 274, 279, 439, 6, 67, 13283.
Photo Gallery

TKS VA capsuleTKS VA capsule
The landing capsule of the three crew military TKS transport/resupply spacecraft for the Almaz space station. Called ‘our Apollo’ by cosmonaut Leonov. After separation of the capsule from the Almaz the retrorocket assembly at top deorbited the capsule. TKS capsules (VA is the Russian acronym) flew 13 times between 1976 and 1983, ten times in capsule tests, three times as part of complete TKS spacecraft which docked with Salyut space stations. They were never flown manned.
Credit: © Mark Wade


TKS capsule hatchTKS capsule hatch
The crew of the TKS went from the descent capsule to the main spacecraft cabin through this hatch in the heat shield of the capsule. The central crew couch folded up to give access to the hatch. A similar arrangement was to be used in Gemini B for the USAF MOL (Manned Orbiting Laboratory).
Credit: © Mark Wade


TKS capsule interiorTKS capsule interior
Left control panel of the descent capsule of the TKS spacecraft. The TKS crew instruments were assembled from the same building blocks as those used in the Soyuz series of spacecraft. The standard clock, used since Vostok, is in the top middle of the panel. The large central panel was used to call up sequences of automated spacecraft procedures.
Credit: © Mark Wade


TKS capsule interiorTKS capsule interior
At the junction of the left and right instrument panels of the TKS was a Vzor optical device, as used in Vostok and Soyuz. The Vzor allowed the crew to line up the spacecraft for retrofire and return to earth even if all other spacecraft systems failed.
Credit: © Mark Wade


TKS capsuleTKS capsule
TKS capsule at Khrunichev factory.
Credit: Khrunichev



1976 December 15 - . 01:30 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/24. LV Family: Proton. Launch Vehicle: Proton-K.
1977 August 4 - . 22:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/24. LV Family: Proton. Launch Vehicle: Proton-K. FAILURE: First stage engine steering unit failure at T+40.1 seconds. Failed Stage: 1.
1978 March 30 - . 00:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/24. Launch Pad: LC81/24?. LV Family: Proton. Launch Vehicle: Proton-K.
1979 April 20 - .
1979 April 20 - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/24.
1979 April 20 - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/24. LV Family: Proton. Launch Vehicle: Proton-K. FAILURE: Engines ignited but immediately shut down on launch pad. Booster could be reused with new payload.. Failed Stage: 1.
1979 May 22 - . 23:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/24. LV Family: Proton. Launch Vehicle: Proton-K.

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