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Russia: Soviet Manned Lunar Projects
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Soviet Lunar Landers

Soviet Lunar Landers
Landing stages for Soviet lunar expeditions. Top row, left to right: L3 original version; LK; LK-3; LK-700; two versions of the L3M; LEK for Energia-launched lunar landing. Bottom row, lunar base elements: Chelomei KLE; Chelomei Heavy Lunokhod; Barmin DLB base module; LZM, LZhM, Lunokhod, and LEK for Glushko LEK Vulkan-launched lunar base.
Credit: © Mark Wade

The failed Soviet lunar program, and the follow-on lunar base projects that came to nothing.

  • The First Lunar Projects - 1956 to 1959

  • The L1 - by R-7 around the Moon - 1959 to 1963

  • The L1, L2, L3, L4, L5 - by N1 to the Moon - 1960 to 1963

  • The Lunar Decision - 1964

  • The LK-1 - by UR-500K around the Moon - 1964 to 1965

  • The 7K-L1 - by UR-500K around the Moon - 1966 to 1970

  • The N1-L3 - by N1 to the Moon - 1964 to 1970

  • The Zvezda DLB - 1964 to 1974

  • The N1F-L3M - 1970 to 1974

  • The Vulkan LEK - 1974 to 1976

  • The Energia LEK - 1976 to 1978

The First Lunar Projects

The first official plan for future Soviet spaceflight was contained in a decree of 30 January 1956. This set forth the following objectives:

  • Orbiting of satellites of 1.8 to 2.5 metric tons mass by 1958
  • One week flight of a manned spacecraft by 1964
  • Unmanned reconnaissance satellite by 1970
  • Rocket capable of 12 metric ton escape velocity payload by 1970
  • Rocket with 100 metric ton low earth orbit payload, capable of placing 2 to 3 men on the moon (no date set)

The first approach to the rather vague last objective was to use nuclear power - a nuclear reactor heating ammonia propellant. Korolev's OKB-1 completed a draft project for three variants of rockets using such a propulsion system. The third variant designed was a 'Super Rocket' with a lift-off mass of 2,000 metric tons and a payload of 150 metric tons. This was a true antecedent of the later N1 moon rocket. The first and second stages were in the conical 'raketov' form later adopted for the N1. The first stage used a massive cluster of Kuznetsov NK-9 engines each with a thrust of 52 metric tons. The second stage used four nuclear engines with a total thrust of 850 metric tons. Operating at a temperature of 3500 degrees K a specific impulse of 550 seconds in vacuum using ammonia propellant was expected. A mixture of liquid hydrogen and methane was considered as a better-performance propellant at a later date. Although ideal for use in nuclear rockets, use of liquid hydrogen as a propellant was not considered technically possible in the short term.

Work on this form of nuclear propulsion was abandoned at the end of 1959 when it became apparent that conventional chemical propulsion could provide nearly equivalent performance with less development, safety, and environmental risk.

The L1 - by R-7 to the Moon - 1959 to 1963

Korolev had designed the Vostok manned spacecraft that gave Russia the lead in the space race in the first half of the 1960's. Studies for a follow-on to Vostok, with the objective of sending a manned capsule on a circumlunar flight, began in 1959 under Tikhonravov. At this point it was assumed that any such flight would be at an early date and require use of launch vehicles derived from Korolev's R-7 ICBM. Since planned derivatives of the R-7 could not put more than six metric tons into orbit, it was immediately obvious that a circumlunar spacecraft would have to be assembled in low earth orbit from several R-7 launches. Therefore it would be necessary to perfect techniques for rendezvous, docking, and refueling of rocket stages in orbit. By 1960 to 1961 the studies, now dubbed 'L1', were expanded to cover automatic rendezvous and docking of several stages, and use of manipulators to assemble the stages.

Meanwhile the configuration of the re-entry vehicle for a Vostok follow-on was being investigated by other sections of Korolev's bureau. Lead for work on the re-entry problem was Section 11. There was no shortage of ideas. In 1959 Chief Designer Tsybin of OKB-256 and Solovyev of OKB-1 Section 9 both offered designs for a winged manned spacecraft with a hypersonic lift-to-drag ratio of over 1.0. Prugnikov of Section 8 and Feoktistov of Section 9 proposed development of a ballistic capsule composed of variations of 'segmented spheres'.

Korolev requested TsAGI, the state's Central Aerodynamic-Hydrodynamic Institute, to investigate all possible configurations. In a letter from A I Makarevskiy to Korolev on 9 September 1959 TsAGI set out its study plan. Aerodynamic characteristics at various angles of attack for a wide range of winged, spherical, elliptical, sphere-with cones, and conical shapes were to be analyzed at velocities from Mach 0.3 to Mach 25. The ballistic vehicle was to have a basic diameter of 2.5 m, a total internal volume of 3 to 3.5 cubic meters, and a living volume of 2 to 3 cubic meters. Separately considered for all configurations were aerodynamics of ejection seats or capsules with a diameter of 0.9 cubic meters and a length of 1.85 meters. Most of the work was promised for completion by the end of 1959.

To exploit this database, Reshetin started a project group to conduct trade-off studies of the various configurations at the beginning of 1960. The government decree 715-296 of 23 June 1960 'On the Production of Various Launch Vehicles, Satellites, Spacecraft for the Military Space Forces in 1960-1967' included authorization for Korolev to develop draft projects on themes KS (heavy manned spacecraft, 2-3 crew, to demonstrate rendezvous, docking, and controlled flight, to be developed in 1961 to 1963) and KL (manned spacecraft for lunar flyby - to be developed in 1961 to 1964). The work was therefore upgraded to a project sector, under the leadership of Timchenko, in 1961.

The 1960 studies considered various configurations of ballistic capsule, 'Utka' winged schemes of conventional aircraft layout, and tail-less hybrid configurations. Each configuration had a complete theoretical study, from the standpoint of aerodynamics, trajectories, resulting spacecraft masses, thermal protection requirements, and so on. By the end of 1960 it was found that the winged designs were too heavy for launch by the R-7 and in any case presented difficult re-entry heating problems that were beyond the existing technology. Studies of re-entry trajectories from lunar distances showed that a modest lift-to-drag ratio of 0.2 would be sufficient to lower G forces and allow the capsule to fly 3,000 to 7,000 km from its re-entry point and land on the Soviet territory. When the existing guidance accuracies were taken into account, this was increased to 0.3 to allow sufficient maneuverability to ensure the capsule could land within 50 km of the aim point.

These studies were the most complex ever undertaken, and Korolev obtained assistance from the most brilliant Soviet aerodynamicists, notably Likhushin at NII-1, and those refugees from Chelomei's take-over of their bureaus, Myasishchev at TsAGI, and Tsybin at NII-88. In 1962 the classic Soyuz 'headlight' configuration was selected: a hemispherical forebody transition in a barely conical (7 degree) section to the section-of-a-sphere heat shield.

Section 11 had conceived of the modular scheme to reduce the mass of the re-entry vehicle in 1960. This was dubbed 'Soyuz'. Section 9's competing design, 'Sever' was two modules, like Apollo. Further iterative studies in 1961 to 1962 reached the conclusion that the Soyuz should consist of four sections. Use of this approach would result in a re-entry capsule 50% smaller than Sever. From fore to aft these modules were the living module; the landing module; the equipment-propulsion module; and an aft jettisonable module, that would contain the electronics for earth orbit rendezvous (this was to be jettisoned after the last docking was completed and before translunar injection. Until recently this compartment on the early Soyuz models was misidentified as a 'toroidal fuel tank' by Western space experts).

This configuration was selected only after considerable engineering angst. From the point of view of pulling the capsule away from the rocket in an emergency, positioning the capsule at the top of the spacecraft was ideal. But to use this layout with the living module concept, a hatch would have to be put through the heat shield to connect the two living areas. Korolev's engineers just could not accept the idea of violating the integrity of the shield (and would later get in bitter battles with other design bureaus when competing manned spacecraft - Kozlov's Soyuz VI and Chelomei's TKS - used such hatches).

The fundamental concept of the modular Soyuz design can be summarized as obtaining minimum overall vehicle mass for the mission by minimizing the mass of the re-entry vehicle. There were two major design elements to achieve this:

  • Put all systems and space not necessary for re-entry and recovery outside of the re-entry vehicle, into a separate jettisonable 'living module', joined to the re-entry vehicle by a hatch. Every gram saved in this way saved two or more grams in overall spacecraft mass - for it did not need to be protected by heat shields, supported by parachutes, or braked on landing. As a bonus the living module provided an airlock for exit into space and a mounting area for rendezvous electronics.
  • Use a re-entry vehicle of the highest possible volumetric efficiency (internal volume divided by hull area). Theoretically this would be a sphere. But re-entry from lunar distances required that the capsule be able to bank a little, to generate lift and 'fly' a bit. This was needed to reduce the G forces on the crew to tolerable levels. Such a maneuver is impossible with a spherical capsule. After considerable study, the optimum shape was found to be the Soyuz 'headlight'.

The end result of this design approach was remarkable. The Apollo capsule designed by NASA had a mass of 5,000 kg and provided the crew with six cubic meters of living space. A service module, providing propulsion, electricity, radio, and other equipment would add at least 1,800 kg to this mass for the circumlunar mission. The Soyuz spacecraft provided the same crew with nine cubic meters of living space, an airlock, and the equipment module for the mass of the Apollo capsule alone!

The modular concept was also inherently adaptable. By changing the fuel load in the equipment module, and the type of equipment in the living module, a wide variety of missions could be performed. The superiority of this approach is clear to see: the Soyuz remains in use 30 years later, while the Apollo was quickly abandoned.

Although only Korolev was authorized to do draft project work on lunar themes, the other Chief Designers pursued alternate approaches. Chelomei was Korolev's arch-rival, and had the advantage of having Nikita Khrushchev's son in his employ. He was said to have been ordered informally by Khrushchev on 13 May 1961 to begin development of a manned circumlunar spacecraft in response to the American Apollo program. This would be launched by his UR-500 rocket, already being designed as authorized in the same June 1960 decree that started work on Soyuz. The advantage of using the UR-500 was that a manned spacecraft could be launched around the moon in a single launch, as opposed to the complex earth-orbit assembly techniques being refined by Korolev. Funds for design work on the LK-1 were available from the Kosmoplan and Raketoplan projects. These were lifting-body unmanned and manned vehicles being designed by Chelomei for a range of military and planetary exploration missions as per the June 1960 decree.

The first 1961 draft of the Soyuz project (codes KS, KL, and Vostok-Zh of the 1960 decree) would exploit the modernized Vostok-Zh. Three rocket stages would be assembled in low earth orbit using a manned Vostok tug. They would then launch a Soyuz capsule on a lunar flyby and return to earth.

In the definitive December 1962 Soyuz draft project, the Vostok was gone and Soyuz A appeared as complete two-place spacecraft. The project included two other spacecraft - the Soyuz B 9K rocket acceleration block and Soyuz V 11K tanker. All of these would be launched into orbit by Soyuz 11A511 boosters. A circumlunar mission would begin with launch of the 9K tanker block. This would be followed by three or four 11K tankers, which would automatically rendezvous and dock with the 9K. They would transfer up to 22 metric tons of propellant. Finally the 7K spacecraft with the cosmonauts aboard would be launched, dock with the 9K, and be propelled on a lunar flyby trajectory.

Korolev understood very well that financing for a project of this scale would only be forthcoming from the Ministry of Defence. Therefore his draft project proposed two additional modifications of the 7K: the Soyuz-P space interceptor and the Soyuz-R command-reconnaissance spacecraft. The VVS and the rocket forces supported these improved variants of the Soyuz.

To Korolev's frustration, while Kozlov's OKB-1 Filial 3 in Samara received budget to develop the military Soyuz versions, his own circumlunar Soyuz-A was not included in the space program of the USSR. The 7K-9K-11K plan would have required five successful automatic dockings to succeed. This seemed impossible at the time. Chelomei's LK-1 single-manned spacecraft, to be placed on a translunar trajectory in a single launch of his UR-500K rocket, was still the preferred approach. But even Chelomei had no official authorization to undertake actual detailed design and development of the spacecraft or booster.

The L1, L2, L3, L4, L5 - by N1 to the Moon - 1960 to 1963

Even while attempting to obtain approval for his modest R-7-launched L1 circumlunar spacecraft, Korolev was attempting to sell more ambitious schemes using his N1 super-rocket. The space race with the Americans had heated up considerably since the promulgation of the casual program of 1956. In a letter to the Central Committee of the Communist Part in January 1960 Korolev proposed an aggressive program for Communist conquest of space. This would be accomplished by development of a new rocket of 1,000 to 2,000 metric tons gross lift-off mass with a 60 to 80 metric ton payload at the earliest possible date. Among the potential payloads for his rocket in the period 1963 to 1965 Korolev proposed a spacecraft with 2 to 3 men for flyby of the moon, entry into lunar orbit, and return to earth. Payload mass would be 10 to 12 metric tons in lunar orbit with 2 to 3 metric tons return payload. This lunar orbiter would be twice as large as the L1 'loop around the moon' spacecraft. Korolev pledged to place before the Central Committee in the third quarter of 1960 comprehensive plans for development of the new projects.

This letter was followed by a meeting with Khrushchev on the subject on 3 March 1960. Korolev believed it would be truly possible with backing from the very top to have a large rocket in the USSR in a very short span of time. Unfortunately at the meeting Korolev made a slip of the tongue he would always regret, admitting that his plan had not been agreed among all of the Chief Designers. This resulted in Khrushchev throwing the matter back for a consensus plan.

By 30 May 1960 Korolev was back with a plan that now included participation of his rivals, Chelomei and Yangel. But Korolev had managed to retain the lunar work. The consolidated plan included the following lunar elements relating to the program of lunar exploration:

  • N-I - (Korolev) - to be developed in 1960 - 1962. 40 to 50 metric tons payload to low earth orbit and 10 to 20 metric tons to Mars. Draft project to be completed by second quarter 1961.
  • N-II - (Korolev) - to be completed in 1963 - 1967. 60 to 80 metric ton payload to low earth orbit and 20 to 40 metric tons to Mars. Draft project to be completed in 1962.
  • KS - (Korolev) - Heavy manned spacecraft, 2-3 crew, to demonstrate rendezvous, docking, and controlled flight. To be developed in 1961 to 1963 (this would become Soyuz).
  • KL - (Korolev) - Manned spacecraft for lunar flyby. To be developed in 1961 to 1964 (this would become the L1).
  • Vostok recoverable spacecraft (Korolev) - Maneuverable rendezvous and docking version to be developed in 1961 to 1963 (this was the Vostok-Zh - never flown, replaced by Soyuz)
  • R-7 - Four-stage version of R-7- (Korolev) - 300 metric ton gross lift-off mass, available from 1960 for robotic lunar and interplanetary flights (this would be the Molniya booster)
  • R-7L - (Korolev) - Develop in 1960 to 1962 a 4 stage version of the R-7, utilizing R-9 technology, with a 300 metric ton gross lift-off mass and high specific impulse engines in the last stage. Payload 10 metric tons to low earth orbit and 3 metric tons to escape. Draft project to be completed in 1961 (this booster, later called the Molniya-L, was never developed).
  • E - (Korolev) - Launch to the moon (as per decree of 10 December 1959) E-1 lander probes in 1960 to 1961 and E-7 orbiters in 1961 (these lunar probes would eventually succeed many years behind schedule)

  • UR-500 - (Chelomei) - Develop a 600 metric ton gross lift-off mass rocket using new chemical propellants for sending spacecraft to nearby planets. Draft project to be completed in 1962. (This would become the UR-500 Proton booster - the later launch vehicle for the LK-1)
  • K - (Chelomei) - Development of unpiloted Kosmoplans for flight to Mars and Venus with return to earth and landing at conventional airfields. These would use new exotic chemical systems, low thrust nuclear engines (nuclear-plasma, ion, atomic hydrogen). Sub-variants with a total mass of 10 to 12 metric tons and 25 metric tons would be developed in 1965-1966. Draft project to be completed in 1962. (Chelomei would expand this Kosmoplan concept to include lunar probes as well).
  • R - (Chelomei) - Manned Raketoplan spacecraft for orbital maneuvering flight and recovery at conventional airfields. Total mass to be 10 to 12 metric tons, total gliding range during re-entry 2,500 to 3,000 km. Unpiloted version to be developed in 1960 to 1961, followed by piloted version in 1963 to 1965. Satellite interceptor operational version to be tested in 1962 to 1964 (Chelomei would later expand Raketoplan to a wide range of tasks, including manned lunar flyby and landing. The LK-1 manned circumlunar spacecraft would be designed under this heading).

Note that although completion of draft projects for the N1 and L1 were authorized, no work on a N1-launched lunar landing or lunar orbiter spacecraft was included. Therefore only N-I and L1 design work officially began as a result of the final government decree 715-296 of 23 June 1960 'On the Production of Various Launch Vehicles, Satellites, Spacecraft for the Military Space Forces in 1960-1967'.

By September 1960 Korolev's engineers had already settled on the N1 configuration they would defend formally in the review of the draft project nearly two years later: a monoblock 'carcass' scheme with a total lift-off mass of 2,000 metric tons and a payload of 70 to 75 metric tons.

Although only Korolev was authorized to do draft project work on lunar themes, the other Chief Designers pursued other approaches. Aside from Chelomei's LK-1 circumlunar spacecraft, the Yangel and Chelomei bureaus developed alternate booster designs (Yangel's was designated R-56 and Chelomei's was the UR-700). Both used clustered 4 m diameter rocket stages, equipped with a single large Glushko engine, using toxic storable propellants, with a thrust of 450 to 550 metric tons. Such stages could be built in factories in Moscow or Dnepropetrovsk and shipped on the existing Soviet rail system to Baikonur for final assembly.

The N-I draft project was completed on 16 May 1962. The design was defended before the other Chief Designers on 2 to 16 July 1962. Among the design objectives of the three stage N-I were:

  • Circumnavigation of the moon with a crew of two to three men; entry into lunar orbit of robotic and crewed modules for study of the lunar surface
  • Expeditions to the surface of the moon for the study of its soil, relief, inner structure, physical properties, and selection of a suitable site for a research base on the moon
  • Establishment of a lunar base and regular traffic between the earth and the moon;

After extensive study it was determined that the design objective of a single launch payload of 75 metric tons into a 300 km orbit best met the required payload masses for a variety of missions, among them a manned lunar orbiter and a manned lunar landing (if used with Lox-LH2 upper stages).

The expert commission supported the draft project. But the program was still without an authorized mission. At a meeting between Khrushchev and the Chief Designers at Pitsunda in August, Khrushchev ordered start of a project to put a 75 metric ton manned platform with nuclear weapons into low earth orbit. This was the initial payload; the official decree authorizing N-I production was issued on 24 September 1962 with first flight to occur in 1965. After two years of struggle, Korolev finally had his authorization to build a moon rocket - but not a spacecraft for it.

This did not stop Korolev from fleshing out the ambitious lunar plans set out in the draft project and trying again for approval. On 23 September 1963 Korolev submitted his plans for space projects in the period 1965 to 1975. He now saw a clear chance to again appeal to the leadership for a manned lunar landing program. He dusted off his rejected L-1 circumlunar project, and added four new spacecraft that would allow reconnaissance, followed by landing on the moon and extended exploration of its surface.

The first two projects, as before, would use R-7 based launch vehicles and extensive docking and refueling operations in low earth orbit. But elements of these would be used in the last three, which would map the moon from lunar orbit, land men on its surface, and explore it with a manned crawler.

L-1

This revision to the original L1 project of 1962 had the same objective of sending two men on a circumlunar flyby trajectory. But now the Soyuz had a reverse configuration of that used earlier. From fore to aft, the modules were: the Descent Capsule (SA), Living Module (BO); Equipment Module (AO); Propulsion Module (AO); Rendezvous electronics module (NO) and Docking Unit (SU). This configuration would be important in the later N1-based projects. As before, the system consisted of the 7K manned spacecraft, the 9K rocket spacecraft, and the 11K tanker. A total of six launches of the 11A511 Soyuz booster would be required. The 9K rocket stage would be put in orbit first. It would be followed by four 11K tankers which would top off the tanks of the rocket block. Then, when all was ready, the 7K manned craft would be put into orbit and dock with the 9K stage. The stage would fire and put the manned spacecraft on a translunar trajectory.

The 7K would be equipped with cinema cameras and scientific sensors to record the lunar surface during the flyby, which would be at from 1,000 to 20,000 km from the lunar surface. Total flight time was 7 to 8 days. The SA would separate from the 7K at 120 to 150 km altitude and re-enter the earth's atmosphere at 11 km-sec. After decelerating to subsonic speed, the SA's parachute would open at 10-18 km altitude. Total mass of the L1 in low earth orbit was 23,000 kg and the flyby mass of the Soyuz alone was 5,100 kg.

L-2

The L2 was a project to land a remote-controlled self-propelled rover on the surface of the moon. It would use the same rocket stage and tanker elements developed for the L1 manned circumlunar project. It can be seen to be the direct ancestor of the Ye-8 Lunokhod lunar rovers of the 1970's.

The objective of the L-2 would be to conduct scientific research on the lunar surface and to allow selection of a favorable landing point for later manned flights. A television system would send back panoramic television pictures. The rover would be nuclear-powered and equipped with a radio beacon for later manned expeditions to home on for precision landings. It would also investigate:

  • The relief of the lunar surface
  • The mechanical properties of the lunar soil
  • The microscopic structure of the surface
  • The magnetic fields of the moon
  • Cosmic ray flux
  • Solar insolation at the surface

The L-2 system consisted of:

  • The L-2 crawler. This had a maximum speed of 4 km-hour and a range of 2,500 km. The L-2 consisted of:

    • Motor compartment with equipment permitting speeds of up to 4 km-hour
    • Equipment compartment, with on-board radio, navigation, and control systems
    • Power generating system (evidently solar and-or radioisotope generators)

  • The 13K rocket system for midcourse corrections and lunar braking. This would brake the L-2 to a direct landing on the surface of the moon with no intermediate lunar orbit. It consisted:

    • Braking stage, for midcourse corrections and the main braking impulse for the landing on the surface. This would ignite at an altitude of 200-300 km above the surface.
    • The landing vehicle, with throttled engines, for the soft landing on the surface at a speed of only 2 to 4 m-s.
    • The guidance system
    • The maneuvering and guidance system for docking with the 9K in earth orbit, which was cast off before the translunar injection.

  • The 9K translunar injection stage for sending the L-2 towards the moon from the low earth assembly orbit. This was the Soyuz B rocket stage used on the L-1 project

Total mass of the L-2 + 13K + 9K complex at ignition of the 9K for translunar injection was 23,000 kg. Total mass of the L-2 and 13K in their translunar cruise configuration was 5,000 kg. As was the case for the L-1, six launches of the Soyuz 11A511 booster would be required to assemble the L-2 in a 225 km low earth assembly orbit.

L-3

Korolev's first version of the L-3 manned spacecraft was designed to make a direct lunar landing using the earth orbit rendezvous method. It was a 200 metric ton spacecraft requiring three N1 launches and a single Soyuz 11A5ll launch to assemble in low earth orbit. The first N1 launch would place the 75 metric ton partially-fuelled TLI stage and L3 spacecraft (except the L1 manned return craft) into low earth orbit. Two further N1 launches would orbit 75 metric ton tankers which would rendezvous and dock with the first payload and top off its propellant tanks. Then the Soyuz would be launched for an automated rear-end docking with the entire L3 stack. The L3 spacecraft thereby assembled consisted of:

  • Translunar injection stage, with a total mass of 138 metric tons
  • The lunar braking stage, which included a separate midcourse correction section cast off before the braking burn. Midcourse maneuvers would be made at 100,000 and 150,000 km from the earth to ensure a landing near the site pre-surveyed by the L-2 robotic lunar rover, which would be providing a homing signal for the L-3. The lunar braking stage had a total mass of just under 40 metric tons. The main braking burn would start 200 to 300 km above the surface.
  • The lunar soft landing-ascent stage, which had a total mass of 21 metric tons landed on the moon. The stage would use variable-thrust engines to make a soft landing at 2-4 m-s on the surface. The landing leg structure and soft landing engines would be left behind on the moon.
  • The ascent stage, which would separate from the landing legs and propel the manned capsule back toward the earth. This included the guidance system for the entire L-3 complex.
  • The Soyuz L1 manned spacecraft, which consisted of a 2.5 metric ton equipment module and 2.5 metric ton re-entry module. It could accommodate a crew of two to three.
The total L3 mission would take ten to seventeen days. 2.5 to 3.5 days would be spent on the translunar and transearth legs of the mission Five to ten days would be spent on the lunar surface.

The L3 was not authorized in this form and it would over two years before a very belated start was made to beat the Americans in the moon-landing race. The L3 reformulated for the crash program would require only a single uprated N1 launch and use the lunar-orbit-rendezvous method, with a single-man lander.

L-4

The L-4 Manned Lunar Orbiter Research Spacecraft would have taken two to three cosmonauts into lunar orbit for an extended survey and mapping mission. The L-4 complex, with a total mass of 75 metric tons, would be placed into orbit in a single N1 launch, and would consist of:

  • The trans-lunar injection stage, total mass 58 metric tons. If development of a fourth stage for the N1 was not authorized, this could be replaced by three sequentially-fired Soyuz B 9KM rocket blocks developed for the L-1 and L-2 projects.
  • The lunar orbit maneuvering stage, which would have a total mass of 11.5 metric tons. This would break the Soyuz manned spacecraft into lunar orbit and returned it on its transearth trajectory. Five metric tons of propellant would be used for lunar orbit insertion.
  • The L-4 spacecraft, which would be a modification of the 7K Soyuz. This would have a mass of 5.5 metric tons after being placed on a transearth trajectory with a descent capsule mass of 2.5 metric tons.

L-5

The L-5 Heavy Lunar Self-Propelled Craft would be used for extended manned reconnaissance of the lunar surface. With a maximum speed of 20 km-hour, it would provide living accommodation for three cosmonauts and 3,500 kg of provisions. The crews themselves would be landed on the moon using the L-3 complex.

  • Translunar injection stage, with a total mass of 64 metric tons
  • The lunar braking stage, which included a separate midcourse correction section cast off before the braking burn. The lunar braking stage had a total mass of just under 14 metric tons. The main braking burn would start 200 to 300 km above the surface.
  • The lunar soft landing-ascent stage, which had a mass of 1.3 metric tons landed on the moon. Presumably the stage would make a precision landing, homing on a beacon provided by an L-2 robot scout. The stage would use variable-thrust engines to make a soft landing at 2-4 m-s on the surface.
  • The L-5 rover, with a mass of 5.5 metric tons

The Lunar Decision - 1964

At the beginning of 1964, despite hard work in the previous year, it was apparent that there were still one to two years of development and construction to go and the target dates set in the decree would not be met.

On 24 March 1964 Korolev managed another meeting with Khrushchev, where he again advocated an aggressive plan of lunar and interplanetary exploration. He dusted off his old L3 lunar landing scheme. Two variants of the L3 would be developed: the basic version would use Lox and Kerosene in Rocket Blocks G and D, with N2O4-UDMH in Block E. A later version would use Lox-LH2 in all of these upper stages. This would add 4 metric tons to the lunar surface payload. Korolev promised to have an L3 draft proposal completed in 1964 and the spacecraft in service by 1966. Development of the Lox-LH2 engines would take place from 1964 to 1967. He even pressed development of the TMK - TMK-E interplanetary manned spacecraft, using the newest designs from his bureau with nuclear electric engines. Khrushchev expressed some interest now in the lunar landing scheme, in the face of the American's evident determination to press on with project Apollo.

Feeling he had Khrushchev's support, Korolev on 25 May 1964 drafted a letter to Brezhnev, then in charge of missile development. Korolev complained of the delays in the N-I due to lack of priority and financing. He

The N1-L3 - by N1 to the Moon - 1964 to 1970

Returning to 3 August 1964, Command number 655-268 issued by Central Committee of Communist Party gave Korolev the objective of putting one man on the moon and returning him safely to earth - ahead of the Americans (who had begun over three years earlier, in April 1961). To achieve this aim a large part of the industry had to be mobilized. It would require design of what was designated the L3 complex, with the combined launch vehicle/spacecraft termed the N1-L3. The L3 would utilize the same lunar orbit rendezvous method to achieve moon landing as was selected for the Apollo program. By upgrading the N1 from a 75 metric ton to a 95 metric ton payload capacity it was felt possible that a single N1 launch could accomplish the mission. The L3 complex itself, with a total mass of 95 metric tons, would consist of a fourth stage (Block G) for the N1 to take the L3 from low earth orbit to trans-lunar trajectory; a lunar orbiter with a Soyuz re-entry capsule for return to earth (LOK); a lunar lander (LK) for the landing of a single cosmonaut on the surface of the moon; and a deceleration stage (Block D) which would brake the L3 complex into low earth orbit and then take the LK lander to near zero velocity above the surface of the moon.

The N1-L3 complex was designed not just for a quick initial moon landing, but also for exploration of the moon and near-lunar space for both scientific and military purposes.

In what was only to be the first stage of a sustained campaign, single cosmonauts would land on the lunar surface. However this would be just part of a larger mission with the following objectives:

  • To measure the physical characteristics of near-lunar space and the lunar surface.

  • To place in orbit around the moon and on the surface high precision automatic and manually-operated scientific equipment.

  • To solve the navigation and biological problems associated with regular travel along the Earth-Moon trace;

  • To conduct detailed photo-reconnaissance of the lunar surface from lunar orbit.

  • To conduct research and determine the most effective means for exploiting the moon for military purposes.

The lunar expedition would utilize the lunar-orbit rendezvous method for reaching the surface. In this way the mission could be accomplished in just one launch of an improved N1. The lunar flight plan was as follows:

  • The L3 complex would be injected into a 220 km, 51.8 degree inclination parking orbit of the earth. Up to one day could be spent in earth orbit before trans-lunar injection.

  • The Block G stage burned to propellant depletion, putting the complex into translunar trajectory. The Block G then separated.

  • During a 3.5 day translunar coast the Block D stage would perform two mid-course corrections. It then would put the LOK/LK/Block D stack into an equatorial elliptical lunar orbit. The Block D would be restarted twice to adjust the orbit, first to a circular 110 km orbit, then to bring the pericynthion down to 14 km. The Block D could restarted for up to 4 days in lunar orbit.

  • The LK pilot-cosmonaut would spacewalk from the LOK to the LK and check out the lander and Block D systems.

  • The LK/Block D then separated from the LOK. As it approached the landing site, the Block D then began its main burn and braked the LK to 100 m/s at four kilometers above the lunar surface. The Block D then separated and crashed on the moon.

  • The LK ignited its engines and hovered to a precision piloted soft landing on the surface.

  • The LK cosmonaut would exit the LK to the lunar surface. From six to 24 hours would be spent on the lunar surface.

  • The LK Lunar Cabin and Block E ascent stage launched itself from the LK landing gear (LPU) into lunar orbit. It rendezvoused with the LOK and docked using the 'Kontakt' docking system. The LK cosmonaut spacewalked from the LK back to the LOK with the lunar samples. The LK was then cast off.

  • After up to one additional day in lunar orbit, the LOK's Block I engine would put the LOK into trans-earth trajectory. 3.5 days was to be spent on the coast back to earth with two midcourse corrections en route.

  • Before re-entry, the descent module separated from the LOK with the two cosmonauts aboard. It re-entered the earth's atmosphere over the South Pole at 11 km/sec, skipped back out to space after slowing down to 7.5 km/s, then soared 5,000 km before making final re-entry and landing on the territory of the USSR.
Total mission time was to be 11 to 12 days.

The work for the L3 project was split as follows:

  • OKB-1 (Korolev): General management, design of Blocks G and D, design of the engines for Block D, L, and LOK.
  • OKB-276 (N. D. Kuznetsov) - engines for Block G
  • OKB-586 (Yangel) - the LK lunar lander and the engines for the lander Block E rocket stage. The LK as designed had a mass of 5,560 kg, with the Block E stage weighing 2,950 kg. Takeoff mass of the LK was 3,800 kg.
  • OKB-2 (Isayev) - the complete propulsion system (tanks, controls, engines) for the LOK lunar orbiter Block I stage.
  • NII-94 (V. I. Kuznetsov) - guidance systems for the L3 (LOK/LK/Block D) lunar complex
  • NII-AP (Pilyugin) - guidance systems for the LOK
  • NII-885 (Ryazanskiy) - radio telemetry systems
  • GSKB Spetsmash (Barmin) - N1 launch complex and N1/L3 ground systems
  • Saturn Factory (Lyulka OKB) - 40 metric ton thrust engines for the Blocks G and V. They would also work with OKB-1 in design for the 8.5 metric ton thrust Block D engine, derived from the third stage engine developed for Korolev's GR-1/8K713 FOBS missile.

The original N1 with its payload of 75 metric tons to a 300 km, 65 degree inclination orbit would require two to three launches to assemble a lunar landing expedition in earth orbit. One result of the draft project was the decision to increase the N1 payload to 95 metric tons to allow the L3 to be launched toward the moon in one launch. The following measures would increase the N1 payload to 91.5 metric tons:

  • reduction of the altitude of the earth parking orbit from 300 km to 220 km
  • an increase of the propellant mass of the first stage by 25% (350 metric tons) by supercooling the propellants prior to loading in the launch vehicle (the kerosene to be at -15 to -20 degrees Centigrade, the liquid oxygen at -191 degrees Centigrade)
  • addition of six engines to the first stage
  • an increase in thrust of all the engines on the first, second, and third stages by 2%

Then the following measures would increase the payload to 95 metric tons:

  • Replace the steel helium pressurization tanks with plastic tanks
  • Reduce the parking orbit inclination from 65 degrees to 51.8 degrees
  • Reduce the telemetry equipment in operational vehicles

By September 1964 construction began of the first N1 launch pad (LC110R). On October 13, while Voskhod 1 was in orbit, Khrushchev was removed from power and Brezhnev's faction assumed control of Politburo. The advance design project for the N1-L3 was completed in collaboration with Kuznetsov's OKB-586 on 30 December 1964. The decree for production of 16 shipsets of spacecraft and boosters was issued on 26 January 1965. The N1-L3 was to manufactured to the following schedule: 4 in 1966; 6 in 1967; and 6 in 1968. The plan was for the first launch of the N1 to be in the first quarter of 1966, with the first lunar landings in 1967 to 1968, ahead of the American goal of 1969.

On January 14, 1966 Korolev died in Moscow during colon surgery. His successor, Mishin, did not have the forceful personality and political connections of the original Chief Designer. Korolev also had a legendary ability to motivate his staff and cajole co-operative design bureaus to prioritize work for OKB-1 that Mishin was never able to duplicate.

The project continued. In February 1966 construction started of the second N1 launch pad (LC 110L). By November the first N1 hardware arrived at Baikonur and construction of the 1M1 full-size mock-up of the launch vehicle began. On 16 November 1966 another Keldysh-headed expert commission considered the state of the program. With Korolev dead, once again Glushko, Chelomei, and Yangel advocated development of the UR-700 or R-56 in lieu of the N1. Chelomei, smarting from cancellation of his LK-1 project, offered an LK-700 direct flight manned lander in lieu of the L3. While it was agreed that engine development and studies of these alternate approaches could continue, the February 1967 government decree approved Mishin's draft plan for the first lunar landing.

This integrated L1/L3 project plan indicated a landing on the moon by the end of 1968 - still ahead of the Americans. The N1 test plan envisioned third quarter 1967 as the beginning of flight hardware construction. The first N1 launch was still set for March 1968. A moon landing would not come until the third quarter of 1969 at the earliest.

In February assembly of the first N1 began at the Progress plant in Samara. By the end of summer the first N1 launch pad (LC110R) was completed. Assembly of the first 1M1 mock-up was nearing completion at the MIK assembly building at Baikonur. In September 1967 the EU-28and EU-29 test models of the second and third stages began hot firing tests on their test stands at Samara. On 25 November 1967 the 1M1 mock-up was first erected on LC-110R.

A decree in November had recognized yet further slips in the schedule, with a first flight test of the vehicle not expected until the third quarter 1968. By March 1968 it was recognized that no Soviet manned lunar landing would take place until 1970. On May 7, 1968, N1 booster 4L was erected at launch complex 110R. Under its shroud was the 7K-L1S spacecraft. This modification of the 7K-L1 circumlunar Soyuz incorporated the Isayev forward propulsion module that would be used on the LOK and LK. A mass model representative of the LK lander was also included. A September 1968 flight test was planned. However the first stage oxidizer tank developed cracks during ground tests, and 4L was removed from the pad in June 1968. It had to be scrapped and improvements made to 3L, the next vehicle.

The first N1 countdown began in January with the roll-out of 3L to the pad. Finally, on February 21, 1969, N1 serial number 3L rose into the sky, thundering over the roofs of the assembly worker's apartments as they cheered it on. But immediately after launch a fire broke out in the tail compartment. The engine monitoring system detected the fire, but then gave an incorrect signal shutting down all engines at 68.7 seconds into the flight. The vehicle was destroyed by range safety 1.3 seconds later. The SAS escape tower worked as designed and the 7K-L1S capsule was recovered.

Against this failure, the Apollo program was achieving success after success in bimonthly missions. While beating the Americans to a moon landing was now clearly impossible, a dual unmanned mission was devised, which, if successful, would have stolen a little of the American's thunder. The plan was for the next N1 to launch an unmanned 7K-L1S spacecraft on a loop around the moon. It would take multi-spectral photographs of the lunar surface and far side. Meanwhile, a Proton rocket would launch an unmanned Ye-8 soil return spacecraft. This would soft land on the moon, deploy a core drill which would take a small sample of lunar regolith. Deposited in a small spherical re-entry capsule, this then would automatically be returned to earth.

N1 vehicle 5L was launched on July 3 1969, just two weeks before the Apollo 11 first moon landing. It was a catastrophe. 5L already began to fail at 0.25 second after lift-off when the oxidizer pump of engine number 8 ingested a slag fragment and exploded. A fire ensued as the vehicle climbed past the top of the tower. The KORD reacted and engines were shut down in pairs until the acceleration dropped below 1 G; then the vehicle began to fall back to the pad at a 45 degree angle. The escape tower fired at the top of the brief trajectory, taking the L1S descent module away from the pad. 5L exploded with the force of a small nuclear bomb, destroying launch complex 110R. To compound the failure, the Ye-8 robot made it to the moon but crashed onto the surface as the Apollo astronauts rested after the first moon walk.

With the moon race lost, the rationale for further development of the limited 7K-LOK and LK spacecraft for a dash to the moon disappeared. However project momentum resulted in several test flights of N1-L3 hardware. These were:

  • 1969-11-28 - Soyuz 7K-L1E s/n 1 - Attempted test flight of Block D upper stage in N1 lunar crasher configuration. Launch vehicle first stage failed. Mission flown successfully over a year later as Cosmos 382.

  • 1970-11-24 - Cosmos 379 - T2K s/n 1: LK moon lander test in earth orbit using T2K version (landing legs deleted, instrumentation added) launched by a Soyuz-L launch vehicle. In demonstration of lunar landing and ascent maneuvers, first went from 192 km x 233 km orbit to 196 km x 1206 km orbit, with a delta V of 263 m/s representing the hover and landing maneuver after separation from the Block D. It them simulated the ascent maneuver to lunar orbit, going from a 188 km X 1198 km orbit to a 177 km X 14,041 km orbit with a delta V of 1,518 m/s. No significant problems encountered.

  • 1970-12-02 - Cosmos 382 - Soyuz 7K-L1E s/n 2K - Test of Block D upper stage in its N1 lunar crasher configuration in earth orbit. The three maneuvers simulated the lunar orbit insertion burn; the lunar orbit circularization burn; and the descent burn to bring the LK lunar lander just over the surface. Payload was a modified Soyuz 7K-L1 circumlunar spacecraft, which provided guidance to the Block D and was equipped with television cameras that viewed the behavior of the Block D stage propellants under zero-G conditions. Maneuver Summary: 190 km x 300 km orbit to 303 km x 5038 km orbit, delta V 982 m/s; 318 km x 5040 km orbit to 1616 km x 5071 km orbit, delta V 285 m/s; 1616 km x 5071 km orbit to 2577 km x 5082 km orbit, delta V 1311 m/s.

  • 1971-02-26 - Cosmos 398 - T2K s/n 2 - Second LK moon lander test using T2K version. Maneuver Summary: 189 km x 252 km to 186 km x 1189 km orbit, delta V 251 m/s; 186 km x 1189 km orbit to 200 km x 10,905 km orbit, delta V 1320 m/s. No problems encountered.

  • 1971-06-26 - N-1 6L - Failure of N1 serial number 6L. This substantially improved vehicle began an axial rotation after lift-off. Due to gas dynamics interactions of the thirty engines with the air slipstream, the launch vehicle developed a roll beyond the capability of the control system to compensate. And began to break up. Control was lost at 50.2 seconds into the flight and it was destroyed by range safety a second later. No functional payload was carried.

  • 1971-08-12 - Cosmos 434 - T2K s/n 3 - Final LK moon lander test using T2K version. Maneuver Summary: 188 km x 267 km orbit to 190 km X 1261 km orbit, delta V 266 m/s; 188 km x 1262 km orbit to 180 km X 11,384 km orbit, delta V 1333 m/s. No problems and Yangel is said to have died soon thereafter content that he had done his part for the program.

  • 1972-11-23 - N-1 7L - Soyuz 7K-LOK / LK Mock-ups - Perhaps only flight test of 7K-LOK lunar orbiter. By this time it was just surplus hardware. N1 vehicle represented the later N1F configuration, except for the use of the original engines. The rocket's first engines ran 106.93 seconds, only seven seconds before completion of first stage burnout. Programmed shutdown of some engines to prevent overstressing of the structure led to propellant line hammering, rupture of propellant lines, and an explosion of engine number 4. The vehicle was destroyed by range safety.

By 1972 any thought of using the original N1-L3 hardware for a manned lunar mission had been abandoned. Instead it was planned to surpass the Americans after the Apollo flights were completed by establishing a lunar base.

The Zvezda DLB - 1964 to 1974

It may be recalled that the N1 draft project of 1962 spoke as well of 'establishment of a lunar base and regular traffic between the earth and the moon'. Korolev raised the matter informally at tea with Chief Designer of rocket complexes Vladimir Pavlovich Barmin, head of GSKB SpetsMash (State Union Design Bureau of Special Machine-Building). Barmin was interested in pursuing the subject, but how could such a base be placed on the moon. 'You just design the base', Korolev assured him, 'and I'll figure out how to get it there'. The project was known to SpetsMash as the 'Long-term Lunar Base' (DLB) and to OKB-1 as 'Zvezda'. Consideration was given to using the same elements in expeditions to other planets. Under the DLB studies SpetsMash defined purposes of the base, the principles of its construction, phases of its deployment and composition of its scientific and support equipment. The enthusiasts that worked on the project at Zvezda were naturally known as 'lunatics'.

Zvezda would have utilized unmanned spacecraft designed by the Lavochkin OKB to conduct initial reconnaissance of the prospective moon base site. These would use lunar soil core drills to obtain samples of the soil and return them to earth for analysis, and Lunokhod rovers to survey the site. If the site was found to be satisfactory, these craft had radio beacons which would guide follow-on elements of the base to precision landings.

Ambitious articulated mobile nuclear-powered Lunokhod laboratories would take the cosmonauts from the landing sites on long-duration traverses of the lunar surface. The Lunokhods were equipped with core samplers and manipulators so that the crew could conduct collection of surface samples from within the pressurized cab without the need to always exit the ship and conduct surface operations in space suits. One of the main objectives of the base would be the location and mining of Helium-3 for use in nuclear fusion reactors on earth. Rare on the earth, Helium-3 was abundant on the moon, having collected in the regolith from the solar wind.

Barmin's lunar base would be crewed by nine cosmonauts and consist of nine modules. These modules would have a length of 4.5 m during launch and transport on the moon. Once position in place on the surface of the moon and inflated with air, they would telescope out to 8.6 m length with a total floor area of 22.2 square meters. Power would be provided by nuclear reactors.

The nine modules would be pre-equipped in the factory for specialized functions: command module, laboratory/warehouse module, workshop module, midpoint module, medical/gymnasium module, galley module with dining room, and three living modules. A prototype of one of these modules was used in 1967 for a one-year closed-cycle living experiment at the IBMP (Institute for Bio-Medical Problems). Based on the results of this experiment it was planned that the units on the moon would have a false window, showing scenes of the Earth countryside that would change to correspond with the season back in Moscow. The exercise bicycle was equipped with a synchronized film projector, that allowed the cosmonaut to take a 'ride' out of Moscow with return. These psychological measures were felt important to maintain the crew's mental health.

In later versions, the manned elements apparently used the improved L3 complex (designed for the follow-on two man lunar landings) to ferry manned crews from earth orbit to lunar orbit and then from lunar orbit to the surface and back. The Block Sr LOX/LH2 stage would be used to insert the components of Zvezda into low lunar orbit.

By 1971 the lunar city project was practically complete and Chief Designer Barmin arranged a meeting with Secretary Ustinov, head of all military and space rocketry. He brought along two of this 'lunatics', Aleksandr Yegorov and Vladimir Yeliseyev. The project was defended in a marathon meeting - nine presentations over six hours. At the conclusion, Ustinov agreed that the project should go ahead - but he couldn't decide, at the pace of a walk or the speed of a freight train. In the event, the point was moot. The N1 never successfully flew, and the rocket, and its associated projects, were cancelled in May 1974. In any case, the Soviet economy very likely could never have sustained the cost of the project - 80 billion dollars in 1997 prices.

Unmanned elements of Zvezda designed by the Lavochkin bureau and using lunar core sampling drills designed by Barmin flew in 1969-1976 under the 'Luna' program. Although these flights were conducted in direct reconnaissance support of a manned lunar landing and lunar base, at the time it was declared that no Soviet manned lunar landing program existed, and that these unmanned flights represented a way to achieve the results of the American Apollo program without such expense and risk to life. After a number of launch vehicle failures this series of probes had some success. Luna 15 had crashed while attempting to land on the moon while the Apollo 11 astronauts were on the surface. But on September 20, 1970 Luna 16 safely soft landed on the moon and then returned lunar soil to Soviet territory. Lunokhod 1 travelled about a small portion of the Sea of Rains and returned photographs. Luna 19 mapped the gravity field of the moon in preparation of later manned flights. Luna 20 returned to earth more lunar soil, and Lunokhod 2 roved around an area representing the transition zone between the lunar maria and the highlands.

The N1M-L3M and N1F-L3M - 1970 to 1974

Concurrent with DLB studies, OKB-1 was already developing more powerful versions of the N1 to launch heavier payloads to the moon. The N1 growth study S. P. Korolev had signed shortly before his death had foreseen the wide use of oxygen-hydrogen propellants in modified versions of the N1 launch vehicle.

It will be recalled that the 1965 study foresaw development of a Block V-II Lox/LH2 replacement for the Block B second stage of the N1. At OKB-276 N. D. Kuznetsov led a project to develop a liquid oxygen/liquid hydrogen version of the NK-15V engine with a flight thrust of 200 metric tons for use in this modernized version of the second stage of the N1. However Kuznetsov was having enough difficulty in completing satisfactory development of the conventional version of this engine for use in the basic N1 and his 200 metric ton engine did not reach the hot firing test stage.

While these more ambitious plans would not be realized, the collectives OKB-2 (A. M. Isayev) and OKB-165 (A. M. Lyulka) were continuing studies and basic development that had begun in 1961. The first Russian use of hydrogen as a fuel was planned for rocket stages of relatively small size (with up to 50 metric tons of fuel). These stages, which were designated Block S and Block R, were to be introduced in place of N1 Blocks G and D as part of a modernized L3M lunar spacecraft complex. Use of oxygen-hydrogen propellants would permit expeditions to the moon of three crew, of which two would walk on the surface of the moon.

Isayev set about adapting the 11D56 engine, with a vacuum thrust of 7.5 metric tons, for the Block R. This engine had originally been designed in the early 1960's for use in the third stage of an uprated Molniya-L launch vehicle. The new Block R for the N1 was to have an empty mass of 4.3 metric tons, a maximum fuel load of 18.7 metric tons, and would have been 8.7 m long and 4.1 m in diameter.

Lyulka developed two variants of a 40 metric ton engine - the 11D54 (with fixed chamber) and 11D57 (with gimbaled chamber). These would be used for the new Block V-III third stage of the N1 (3 to 6 11D54) and in the Block S (one 11D57).

First hot firings of the 11D56 on the test stand began in June 1967. Both the 11D56 and 11D57 engines successfully completed their state development test series.

At the Tsniimash museum in Korolev a photograph is displayed of a dynamic test model of an N1 configuration that has been called N1M. This model shows an N1 first stage, with a Block V-III second stage, and Blocks S and R third and fourth stages. Calculations indicate that a two stage Block A / Block V-III N1 would have a low earth orbit payload comparable to that of the basic N1 (around 95 metric tons). Evidently this configuration was considered as an alternative to a conventional three stage N1 for launching the L3M complex into low earth orbit.

The original draft project for the new N1M-L3M lunar landing complex anticipated use of a two-launch profile. On the first launch a Block R RTB braking stage would be put on a translunar trajectory. The RTB would place itself in lunar orbit. Next, the manned L3M lunar lander would be launched. This new spacecraft was much larger than the LK, with a mass of 21 metric tons landed on the lunar surface. The L3M would dock, tail-first, with the RTB stage in lunar orbit. The RTB would act as a lunar crasher stage. The L3M would separate from the RTB just over the lunar surface, then hover to a soft landing. The crew would spend up 16 days on the surface. Following completion of their work, the landing legs would be left behind, and the L3M would launch itself on a trans-earth trajectory. Just before arrival at earth, the crew would enter their Soyuz capsule, separate from the L3M, and make a lifting re-entry into the earth's atmosphere. It was felt that within the existing funding allocation of the original N1-L3 program, enough N1's would be available to support a series of landings in 1978-1980.

At least two drawings of varying designs for the L3M have emerged to date. In one, the Soyuz return capsule is perched atop the landing stage. A small toroidal crew compartment provides accommodation for space-suited cosmonauts to land the vehicle on the moon. Evidently the crew, which would have been limited to two cosmonauts, would be required to space walk from the Soyuz capsule to the toroidal chamber prior to the landing attempt. A return spacewalk would have to be made after ascent from the surface. This L3M had a landed mass of 21 metric tons on the surface, an ascent mass of 18 metric tons, a trans-earth injection spacecraft mass of 5 metric tons, and sufficient supplies for 14 to 16 days of operations on the surface. This probably represents the original N1M-L3M variant.

In July 1970 Kuznetsov was given authorization to design substantially improved versions of the N1 rocket engines. The N1 that would utilize these engines was designated the N1F and would have a payload to a 225 km orbit of 105,000 kg.

Full go-ahead to develop a liquid hydrogen/liquid oxygen high energy upper stage for the N1F finally came in June 1970. The decision was made to develop a multi-engine Block Sr with a propellant mass of 66.4 metric tons. This single stage would be used in place of the previously-planned Blocks S and R to insert spacecraft of what was now termed the Lunar Expeditionary Complex (LEK) into low lunar orbit. It was also to be used to insert heavy spacecraft into geosynchronous orbit and on interplanetary trajectories.

The revised L3M for use with the Block Sr completed design in 1972. In this version the Soyuz capsule is completely enclosed in a pressurized ‘hangar' (the OB, cocooned habitation block) which provides the crew with accommodation space. In this variant the crew could simply step out of the capsule into the hangar area without having to don space suits and conduct an EVA. This L3M would have had a mass of about 23 metric tons landed on the surface and have allowed stays of up to 90 days by a crew of three. The two-launch scenario would still be followed, with a single Block Sr from each N1 launch taking over duties of both the Blocks S and R in the previous plan. The DU engine block would perform the same ascent stage duties as the Block E of the original LK.

With the cancellation of the N1 in 1974, work on the upper stages and spacecraft for lunar expeditions did not end. The designs were simply modified for use on the replacement launch vehicle, the Vulkan.

The Vulkan LEK - 1974 to 1976

Although the N1, L3, and Zvezda projects were cancelled, Glushko still considered the establishment of a moon base to be a primary goal for his country. While the Americans had achieved the first moon landing, it was known that all moon flights after Apollo 17 had been cancelled. There existed an opportunity, through establishment of a permanent moon base, to steal the lead in the space race once again. Furthermore, analysis of the results of the previous unmanned and manned indicated that the moon was suited for a variety of 'special investigations', and that a permanent lunar expeditionary complex (LEK) would be required to accomplish this.

To launch the elements of the LEK, Glushko designed a new launch vehicle, the Vulkan. The Vulkan would use the LOX/LH2 engine technology developed for the US Space Shuttle in the core stage. This would be surrounded by six strap-on boosters, using LOX/Kerosene engines, to be developed by NPO Yuzhnoye in the Ukraine. This use of cryogenic propellants represented a complete turnaround for Glushko, who had advocated use of storable but toxic rocket propellants in a bitter fight with Korolev and Mishin for fifteen years.

The Vulkan was designed to deliver 230 metric tons into a 200 km low earth orbit; 60 metric tons to lunar orbit; and 22 metric tons to the lunar surface.

The LEK consisted of expeditionary and transport lunar spacecraft (Chief Designer K D Bushchev) and equipment for the permanent base station (Chief Designer I S Prudnikov).

The expeditionary and transport craft consisted of:

  • LEK (Lunar Expeditionary Spacecraft). As in the original LK lunar lander, this would be taken to near zero velocity near the lunar surface by the Vulkan Block V 'lunar crasher' rocket stage. It would then descend to the lunar surface using a landing stage nearly identical to the American lunar module descent stage. This landing stage however would primarily provide propulsion of the upper Ascent/earth recovery stage to a trans-earth trajectory. The Ascent/earth recovery stage consisted of a re-entry capsule in the shape of but larger than the Soyuz descent module, encapsulated in a larger pressurized volume providing crew quarters and equipment storage.

  • LZhM (Laboratory-Residence Module) for three men as the home base for living and working during the expedition. This used a simpler descent stage with minimal propellant for the soft landing on the moon following separation from its Block V lunar crasher stage.

The equipment of the permanent base station consisted of:

  • Lunokhod - a large manned wheeled mobile pressurized laboratory with a working radius of up to 200 km from the base. The Lunokhod would also be used for loading and unloading operations, and had a grader for burying the nuclear reactors which would power the complex and the laying out of 'streets' and protective berms for the base itself.

  • LZM (Laboratory-Factory Module) provided biological and physics laboratories in two lobes. In the other was a factory for production of oxygen from the lunar soil. This used the same simple descent module as the LZhM.

  • Nuclear power stations to power all of the modules of the lunar base. Each




    Photo Gallery

    Zond 5 Reaches MoonZond 5 Reaches Moon
    Zond 5 rounds the Moon and heads for Earth after the first Lunar Circumnavigation
    Credit: © Mark Wade


    LOK Lunar OrbiterLOK Lunar Orbiter
    The Soyuz 7K-LOK lunar orbiter spacecraft to be used in the L3 lunar landing project complex.
    Credit: © Mark Wade


    L1-1963L1-1963
    Cutaway view of 1963 L1 circumlunar spacecraft.


    LK Lunar LanderLK Lunar Lander
    LK lunar lander.


    Early LK Test ModelEarly LK Test Model
    Dynamic Test Model of Early LK Concept.
    Credit: © Mark Wade


    L2-1963L2-1963
    1963 L2 robot lunar rover spacecraft. L2 configuration speculative based on early Ye-8 rover design studies at OKB-1.


    DLB Stow/UnstowedDLB Stow/Unstowed
    View of DLB Soviet lunar base modules as they would appear in short transport configuration and in inflated, telescoped deployed configuration.


    Zvezda / DLB baseZvezda / DLB base
    Zvezda / DLB long-tern lunar base
    Credit: Spetsmash


    Zvezda / DLB moduleZvezda / DLB module
    Basic module for Zvezda / DLB long-tern lunar base


    L3 -1963L3 -1963
    1963 L3 manned lunar lander using earth-orbit rendezvous method. Configuration based on description and lander configuration of early L3M design.


    Mars TrainMars Train
    Elements of Mars Train and Zvezda Lunar Base Support Craft. From left: two LK landers; Marsokhod with manipulator arms; Mars Train with reactor, ascent stage, and forward living module; another Marsokhod with manipulator arms.
    Credit: © Mark Wade


    DLB Module DeployedDLB Module Deployed
    View of the DLB Soviet lunar base modules as they would appear deployed on the lunar surface.


    L4 -1963L4 -1963
    1963 L4 manned lunar orbiter.


    Mars TrainMars Train
    Elements of Mars Train and Zvezda Lunar Base Support Craft. From left: two LK landers; Marsokhod with manipulator arms; Mars Train with reactor, ascent stage, and forward living module; another Marsokhod with manipulator arms.
    Credit: © Mark Wade


    L3M - Cutaway ViewL3M - Cutaway View
    Cutaway views of early and later L3M manned lunar lander designs.


    L3ML3M
    External views of early and later L3M manned lunar lander designs.


    Vulkan LVVulkan LV
    Vulkan Launch Vehicle
    Credit: © Mark Wade


    L5 -1963L5 -1963
    1963 L5 manned lunar rover. Drawing based on model at Tsniimash museum.


    LEK Lunar LanderLEK Lunar Lander
    Lunar lander of the Lunar Expeditionary Complex (LEK).


    LEK ModelLEK Model
    Model of LEK in Energia museum - unusual re-entry capsule or subsidiary module at its top.
    Credit: Andy Salmon


    LEK Lunar LanderLEK Lunar Lander
    LEK LK moon lander Vulkan-launched
    Credit: © Mark Wade


    LZhM lunar habitatLZhM lunar habitat
    LZhM Laboratory-Residence Module
    Credit: © Mark Wade


    Lunokhod LEKLunokhod LEK
    Credit: © Mark Wade


    Cutaway of N1Cutaway of N1
    Credit: RKK Energia


    LZM lunar factoryLZM lunar factory
    Credit: © Mark Wade


    N1-L3 TowerN1-L3 Tower
    Detail of tower of N1-L3 7L
    Credit: RKK Energia


    N1 6L lift-offN1 6L lift-off
    Credit: RKK Energia


    N1 5L ExplosionN1 5L Explosion
    Final explosion of N1 5L, destroying pad.
    Credit: RKK Energia


    2 N1s Mounted on Pad2 N1s Mounted on Pad
    Credit: RKK Energia


    N1 5L Falls BackN1 5L Falls Back
    Having just cleared the tower, N1 5L falls back onto the pad at a 45 degree angle.
    Credit: RKK Energia


    N1 5L clears towerN1 5L clears tower
    N1 5L Clears the tower but falters as the KORD system incorrectly shuts down engines.
    Credit: RKK Energia


    N1 5L lift-offN1 5L lift-off
    Engine ignition of N1 5L.
    Credit: RKK Energia


    N1 7L lift-offN1 7L lift-off
    N1 7L rises over the apartment blocks of the workers that built it
    Credit: RKK Energia


    N1 subassembliesN1 subassemblies
    N1 tank sections were built in Samara, then shipped to Baikonur for assembly of the launch vehicle.
    Credit: RKK Energia


    N1 stagesN1 stages
    N1 stages in the assembly hall
    Credit: RKK Energia


    N1 tank assemblyN1 tank assembly
    Subassemblies from Samara were built up into stage bulkheads on assembly jigs at Baikonur.
    Credit: RKK Energia


    N1 boattail assemblyN1 boattail assembly
    Base of N1 first stage in assembly jig
    Credit: RKK Energia


    Energia-launched LOKEnergia-launched LOK
    LOK Lunar Orbiter (Energia-launched)
    Credit: © Mark Wade


    N1 engineersN1 engineers
    N1 engineers study drawing
    Credit: RKK Energia


    N1 Engine firedN1 Engine fired
    N1 Engine fired on test stand
    Credit: RKK Energia


    N1 Upper StageN1 Upper Stage
    N1 Upper Stage firing on test stand
    Credit: RKK Energia


    N1 6L Lift-offN1 6L Lift-off
    Credit: RKK Energia


    N1 6L ignitionN1 6L ignition
    Credit: RKK Energia


    N1 6L Engine StartN1 6L Engine Start
    Credit: RKK Energia


    N1 7L Lift-offN1 7L Lift-off
    Credit: RKK Energia


    N1 MIK Assembly HallN1 MIK Assembly Hall
    CIA's National Intelligence Estimate of March 1967
    Credit: RKK Energia


    N1 Model TestN1 Model Test
    Credit: RKK Energia


    N1 Wind Tunnel TestN1 Wind Tunnel Test
    Credit: RKK Energia


    LEK LK moon landerLEK LK moon lander
    LEK LK moon lander Energia-launched
    Credit: © Mark Wade


    N1 Subscale ModelN1 Subscale Model
    Credit: RKK Energia


    Model of N1 padModel of N1 pad
    Credit: RKK Energia


    N1 RolloutN1 Rollout
    N1 Rollout - base of booster
    Credit: RKK Energia


    N1 RolloutN1 Rollout
    N1 Rollout - view from inside MIK
    Credit: RKK Energia



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