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| Raketoplan Raketoplan designs. From left to right: Low L/D re-entry vehicle (LK-1 circumlunar spacecraft as flown); High L/D re-entry vehicle with containerised winged lander inside jettisoned aerodynamic shell; High L/D re-entry vehicle, advanced (provisional, based on LKS design that followed). 19,804 bytes. 626 x 281 pixels. |
Chelomei began preparatory theoretical work on manned spacecraft in the late 1950's. This analysis was a necessary prologue to later development. Various solutions for recovery of the spacecraft were considered: fixed wings, automatically deployable wings, and lifting body shapes. The best technical solution was completely original and received a patent. This design would re-enter the atmosphere in a heat shield container, which would be jettisoned after the spacecraft had passed through the period of maximum heating. Swing wings would then be deployed, and the spacecraft would glide to a horizontal runway landing. The heat shield itself was shaped like an asymmetric cone. This shape could provide lift during re-entry and manoeuvre with the assistance of rudder petals at the base of the cone. This approach reduced aerodynamic resistance during re-entry and reduced the hot structure of the Raketoplan by ejecting the heat shield after re-entry.
Decree 715-296 of 23 June 1960 �On the Production of Various Launch Vehicles, Satellites, Spacecraft for the Military Space Forces in 1960-1967� authorised Chelomei�s OKB-52 design bureau to prepare a draft project for a manned Raketoplan spacecraft for orbital manoeuvring flight and recovery at conventional airfields. At that time total mass was to be 10 to 12 tonnes, total gliding range during re-entry 2,500 to 3,000 km. An unpiloted version was to be designed in 1960 to 1961, followed by a piloted version in 1963 to 1965. Completion of the final draft project was planned for 1965. Actual hardware development and flight trials would only take place in the second half of the 1960's.
Sub-scale prototypes of the satellite interceptor operational version were to be tested in 1962 to 1964. The full-scale lifting manned spacecraft would conduct interception, inspection, and destruction of US satellites up to 290 km altitude. It would have a two man crew, a 24 hour mission duration, and was equipped with large aft drag brakes. Preliminary designs of a similar nature had been completed under the VKA project at the Myasishchev and Tsybin design bureaux, which were closed and their staff absorbed by Chelomei in October 1960.
During development of the draft project progressively more complex models of the design were flown. First to be tested was the sub-scale MP-1, with a mass of 1750 kg. This had the oblique conical heat shield, with an arrangement of 'tail feathers' on the stern that looked like a deployable umbrella. Tests of this model would verify the predicted aerodynamic characteristics of the design, test the heat shield material, and measure the minimal temperatures and vibrations experienced in actual flight. The MP-1 was boosted by an R-5 rocket to an altitude of 405 km in late 1961. It re-entered the atmosphere 1760 km from the Kaputsin Yar launch site at a velocity of 3800 m/s. The test flight produced valuable material on aerodynamic and heating characteristics.
The second flight test was of the more sophisticated M-12 sub-scale unpiloted version took place on 21 March 1963. This had a mass of 1700 kg, and the fixed 'umbrella' tail fathers were replaced by movable rudders to test manoeuvrability of the design at hypersonic speeds. This test provided additional actual data of the aerodynamic characteristics which were necessary to complete the draft project.
By the time of the 1963 draft project for the intended launch vehicle, the Proton UR-500, Chelomei had expanded the Raketoplan concept to cover a broad spectrum of modular spacecraft, destined to solve defence, scientific investigation, and national economic tasks. These all were to be called Raketoplans - piloted spacecraft for solving military tasks in space. For example, orbital Raketoplans were intended to fulfil intelligence, satellite inspection, and destruction tasks. For these purposes the Raketoplan was to be equipped with an orbital manoeuvring engine, targeting systems, rendezvous systems, and space-to-space weapons. Later Raketoplans would be used for scientific tasks, including flight to the moon and return to earth, and economic exploitation of near-earth space. Due to their high lift to drag ratios, Raketoplans could, after completing their tasks in space, make a guided descent into the earth�s atmosphere with a landing on Soviet territory.
 | Kosmoplan profile - Kosmoplan landing profile Credit: © Mark Wade. 36,301 bytes. 617 x 420 pixels. |
In 1964 Chelomei had submitted to the VVS the advanced project for a single-place Raketoplan, which would be launched into low earth orbit using a Korolev Soyuz launch vehicle or (preferably) the Chelomei UR-500. This final design came in two versions. The unpiloted R-1 would fly first, and would be used to check out and test all systems in orbit. These included wringing out the orientation and stabilisation system, the engines, proving the reliability of the systems, measuring the arrangement of the jettisonable section and the dynamic characteristics of the whole vehicle, and test of the heat shield and its aerodynamic parameters.
The piloted R-2 would be used to solve problems of the capabilities of pilot-cosmonauts to control the spacecraft both in orbit and aerodynamic flight; to test communications systems; and to conduct reconnaissance and inspection functions in space. Both the R-1 and R-2 would have a mass of 6300 kg in a 160 km x 290 km orbit, a flight duration of 24 hours, and use lift on re-entry to keep forces under 3.5 to 4.0 G's.
In October 1964 Khrushchev was ousted from power and the new leadership, under Brezhnev, was adverse to all that Khrushchev had supported- including Chelomei. An expert commission under M V Keldysh examined Chelomei�s projects and recommended that the Raketoplan project be cancelled (although work on one variant of the ballistic design, the LK-1manned lunar flyby program, continued).
The Mikoyan MiG design bureau was assigned the responsibility for further development of Soviet manned spaceplanes. The materials prepared by Chelomei for the Raketoplan were handed over to OKB MiG, as well as many of the engineers that had worked on the project. Lozino-Lozinskiy was named head of the new unit at MiG, which would design the Spiral lifting body by the end of the 1960's. Chelomei would be excluded from further work on the topic for ten years, until he proposed his LKS spaceplane as an alternative to the Buran space shuttle.
Craft.Crew Size: 1. Total Length: 10.0 m. Maximum Diameter: 4.0 m. Total Mass: 6,300 kg.
Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On the Development of Research on Cosmic Space-future of Soviet space program (piloted. interplanetary, spaceplane)' was issued.
Decree 715-295 'On approval of preliminary work on the Raketoplan, UR-200 ICBM, and IS anti-satellite system' was issued.
Central Committee of the Communist Party and Council of Soviet Ministers Decree 1057-434 'On transfer of OKB-23 as Branch No. I of OKB-52 and on course of work on IS anti-satellite system' was issued. Chelomei acquired the OKB-23 of Vladimir Mikhailovich Myasishchev, (which had formerly designed heavy bombers), as well as the M K Khrunichev heavy aviation factory. Both of these organisations had a very high level of technical and manufacturing expertise, and assisted Chelomei in quickly moving ahead on his new space projects.
Immediately after cancellation of similar projects at Myasishchev and Tsybin bureaus, Chelomei's new bureau is assigned to build equivalent of US Dynasoar / Saint II. Winged manned spacecraft for interception, inspection, and destruction of US satellites up to 290 km altitude. Two man crew, 24 hour mission duration, large aft drag brakes.
Soviet Decree 'On the Revision of Plans for Space Objects for Accomplishing Goals of Defence Designations--heavy boosters, course of work on Elektron, and suspension of work of work on the Kosmoplan and Raketoplan with continuation of new Raketoplan work' was issued. The decree set the end of 1965 as the date for the first launch of the N1. It also authorised Chelomei to stop work on Kosmoplan interplanetary probes and instead concentrate on a specific Raketoplan design - the LK-1 manned lunar flyby spacecraft.
First flight of Raketoplan Chelomei, launched at 16:40 Moscow Time. The reentry vehicle is destroyed during reentry. Maximum Altitude - 400 km. Maximum Speed - 14,400 kph. Distance of free flight - 1900 km.
Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On termination of work on the Kosmoplan and Raketoplan at OKB-52 and approval for the LK-1' was issued.
Ministry of Defence Decree 'On military space programs for 1964-69, including the R spaceplane' was issued. The decree was issued by Defence Ministry Marshal Rodiono Yakovlevich Malinovksiy. Included in this plan were new versions of the automatic Zenit, More-1 (US series) spacecraft, the Spiral spaceplane, the Soyuz-R manned combat spacecraft, and others. Chelomei's Raketoplan spaceplane was cancelled.
Decree 'On end of work on the Raketoplan at OKB-52' was issued. This action was in accordance with the Five Year Military Space Plan approved on 18 June 1964.