LUNAR INDUSTRIAL RESEARCH BASE
DESCRIPTION Lunar Industrial Research Base is one of global, expensive, scientific and labor intensive projects which is to be implemented by the humanity to meet the needs of mankind for the resources and colonization of the solar system. The base is to be gradually and sequentially created checking and approving every step, each mission in order to ensure all of its elements operation to be highly reliable. Lunar Industrial Research Base is a complex of hermetic and nonhermetic modules being integrated into the full design after delivery to the surface of the Moon by separate launches.
SEQUENCE OF LUNAR BASE CREATION Phase 1 Preparatory phase: establishment of the international cooperation for development of the Moon, exploration of the Moon with the use of drones, creation of Earth-Moon-Earth Lunar Space Transportation System and components of the Lunar Base infrastructure Phase 2 Base minimum configuration: delivery of the base first modules, preparation of the take-off and landing area, checking and testing of the base systems Phase 3 Base expansion: re-equipment of the Lunar Base with required modules and hardware, exploration of the lunar surface Phase 4 Transition to production: creation of a closed-loop life-sustaining system, production base and lunar observatory Phase 5 Permanent Base: ensuring of permanent human presence and habitation on the Moon
Phase 2 Base Minimum Configuration Phase 3 Base Expansion Phase 5 Permanent Base
SYSTEMS AND COMPONENTS Main technical systems and components are being developed under the project: Launch vehicles and space transportation vehicles Lunar Base operation infrastructure Lunar orbital facilities
LAUNCH VEHICLES AND SPACE TRANSPORTATION VEHICLES Super-heavy Cripton ILV is created on the basis of middle-class Mayak-C3.9 ILV Technical Characteristics Maximum lift-off mass, t 2374 Propellants kerosene + liquid oxygen Number of stages 2 + 4 liquid boosters Lift-off thrust of engines, tf 3770 Length, m maximum 78 Diameter of stages/fairing body, m 3.9 / 6.2 Payload mass in LEO, t 91.5 Payload mass in lunar 30.5 (with upper stage) trajectory, t Payload mass on the surface of the Moon, t Landing mass, t Payload mass, t 10 10.5 8 8.5
LAUNCH VEHICLES AND SPACE TRANSPORTATION VEHICLES RD 815 engine is a single-chamber dual-mode engine with single burn. It operates on liquid oxygen and kerosene as well as is designed by the scheme of staged combustion of oxidizing generator gas. The engine chamber gimbaling provides thrust vector control. Technical Characteristics Propellants liquid oxygen + kerosene Thrust, tf: - at the sea level 51.3 - in vacuum 274.5 Specific pulse, sec: - at the sea level - in vacuum 306.7 335 Engine mass, kg 3300
LAUNCH VEHICLES AND SPACE TRANSPORTATION VEHICLES RD 835 engine is being developed by Yuzhnoye SDO for prospective Mayak ILV family. The engine is a single-chamber dual-mode engine with dual burn. It operates on liquid oxygen + kerosene and is designed by the scheme of staged combustion of oxidizing generator gas. The engine chamber gimbaling provides thrust vector control. Technical Characteristics Propellants liquid oxygen + kerosene Thrust in vacuum, tf 50.0 Specific pulse in vacuum, sec 355 Mixture ratio 2.6 Engine mass, kg 830
LAUNCH VEHICLES AND SPACE TRANSPORTATION VEHICLES RD 809К engine operates on kerosene and liquid oxygen. The one-chamber dual-burn closed-loop engine is being developed on the basis of series-produced RD-8 engine which is used in the second stage of Zenit LV. The main engine is designed by the scheme of staged combustion of oxidizing generator gas. Technical Characteristics Total mass without payload, t 67.8 Propellants liquid oxygen + kerosene Engine thrust, tf 2 10.0 Length, m ~22 Diameter, m 3.9
LAUNCH VEHICLES AND SPACE TRANSPORTATION VEHICLES RD861K engine, one-chamber multiple-burn engine for upper stages, is developed for the upper stage of Cyclone 4 LV and passed the full cycle of tests. Technical Characteristics Nominal thrust of engine, tf 7.916 Mass of propellant to be filled, t ~11 Number of liquid propellant thrusters 10 Nominal thrust of liquid propellant thrusters, kgf 3 Block diameter, m 3.98 Block length, m 3.98
LAUNCH VEHICLES AND SPACE TRANSPORTATION VEHICLES The configuration of Space Transportation System (STS) to be used to deliver the crew to the Moon and their further return to the Earth is as follows: lunar spaceship includes: assembly compartment of lunar spaceship (AC); lunar spaceship cabin with crew (LS); Earth-Moon propulsion system (EM-PS) is to ensure flight from near-earth orbit (NEO) to near-lunar orbit (NLO); Moon-Earth propulsion system (ME-PS) is to ensure flight from NLO to NEO; landing platform provides departure from NLO, descent and soft landing of Yuzhnoye lunar cabin on the Moon; SDO proprietary take-off module (TM) is to ensure delivery of lunar cabin from the Moon surface to NLO. The reusable orbital spaceplane is used to return people from NEO to the Earth surface. It is injected into NEO by middle-class launch vehicle with payload capacity of 13 14 tons.
LAUNCH VEHICLES AND SPACE TRANSPORTATION VEHICLES Space Transportation System 1 landing platform; 2 take-off module; 3 lunar spaceship cabin; 4 assembly compartment of lunar spaceship; 5 Moon-Earth propulsion system; 6 Earth-Moon propulsion system
LAUNCH VEHICLES AND SPACE TRANSPORTATION VEHICLES Orbital Spaceplane Technical Characteristics Lift-off mass maximum 13000 kg Injected payload mass maximum 2000 kg Recovery payload mass maximum 1000 kg Maximum height of circular orbit 500 km Number of cosmonauts maximum 4 persons Duration of autonomous flight maximum 5 days Maximum lateral maneuver when disorbiting maximum 500 km Landing as a plane Maximum number of flights 50
LAUNCH VEHICLES AND SPACE TRANSPORTATION VEHICLES Landing Platform for delivery of the Lunar Base components to the Moon surface Landing platform is designed to deliver the Lunar Base components from near lunar circular orbit to the Moon surface. Technical Characteristics Propulsion system, t 0.3 Systems of control, measurement, power supply, navigation, communication, 0.4 thermal control, landing, t Structure, t 0.7 Propellant, t 8.6 Total mass, t 10
LUNAR BASE OPERATION INFRASTRUCTURE Lunar Base Modules When creating the Lunar Base, it is assumed to use pressurized cylindrical modules of two main types: vertical and horizontal. The modules are to be developed taking into account the previously-developed diameters of tanks and dry compartments of LVs produced in Ukraine and Europe: The horizontal module Pressurized modules represents a welded aluminum structure composed of cylindrical shell, mating rings and torispherical bottoms. The vertical module is a two-level welded aluminum structure composed of cylindrical shell, mating rings and torispherical bottoms.
LUNAR BASE OPERATION INFRASTRUCTURE Pressurized modules The horizontal module represents a welded aluminum structure composed of cylindrical shell, mating rings and torispherical bottoms. The vertical module is a two-level welded aluminum structure composed of cylindrical shell, mating rings and torispherical bottoms. On the basis of lunar module typical structure the following modules can be developed: airlock module accommodation module storage module production-and-maintenance module command module scientific-and-experimental module vivarium module Typical Module Characteristics horizontal Mass, t 2.9 Length, m 6 Diameter, m 3 vertical Mass, t 4.8 Length, m 6 Diameter, m 5
LUNAR BASE OPERATION INFRASTRUCTURE Airlock Module The airlock module is to connect the base indoor premises with lunar surface while providing personnel passage and movement of different cargoes (equipment). All equipment required for Moonwalking, returning and preparation of the next walks including maintenance of space suits is stored in the airlock module.
LUNAR BASE OPERATION INFRASTRUCTURE Accommodation Module The accommodation module is designed for leisure, recreation, as well as necessary sanitary-and-living needs of the crew members.
LUNAR BASE OPERATION INFRASTRUCTURE Production-and-maintenance Module The production-andmaintenance module is designed to perform repairs and maintenance of lunar equipment.
LUNAR BASE OPERATION INFRASTRUCTURE Vertical Command Module The vertical command module is a module for operation control, checking of all other modules and downlinking. The community room for the crew is on the first level, the working places are on the second level.
LUNAR BASE OPERATION INFRASTRUCTURE Power Plant The solar power plant (SPP) is to provide the Lunar Base with electrical power and represents a source of electrical power generated by means of direct conversion of solar power. SPP includes: solar batteries primary electrical power source electrochemical generator secondary electrical power source heat recovery systems accumulator chemical batteries backup electrical power source complex of automatic control units control, regulation and monitoring of power plant Parameter Value Output capacity of power plant, kw: typical mode (during 10 lunar day); sleeping mode (during lunar night); 1 2 adaptive mode (lunar sunsets and sunrises) 1 10 SPP total mass, kg 4110
LUNAR BASE OPERATION INFRASTRUCTURE Research Rover The research rover is meant for research expeditions of the crew on the lunar surface. Main Characteristics Name Value Total mass, kg maximum 8000 Scientific equipment mass, maximum 1000 kg Average velocity, km/h maximum 20 Duration of one mission, days 14 7 Crew, persons 2 4
LUNAR BASE OPERATION INFRASTRUCTURE Lunar Transportation Vehicle The lunar transportation vehicle consists of one and more basic modules which provide the required load-carrying capacity of the transportation vehicle depending on the number of modules. The structure of transportation vehicle is to equip it with installable mounted equipment. The range of transportation vehicles could unload, shift cargoes (including lunar modules) and perform groundworks.
LUNAR BASE OPERATION INFRASTRUCTURE Range of transportation vehicles General view of basic transportation vehicle Number of axles of transportation vehicle Chassis type Equipped mass, t Total mass, t Load-carrying capacity, t Swivel wheels 2 3х2 1.2 in different modifications 3.2 2 forward axle 4х4 2 6 4 forward axle forward axle 3 6х6 3 9.6 (8.4) 6.6 (5.4) (forward and rear axles) 4 8х8 4 12(9.6) 8(5.6) forward and rear axles (all axles) 5 10х1 0 5 15.6 (13) 10.6 (7) forward and rear axles (all axles)
LUNAR ORBITAL FACILITIES Lunar Orbital Station The lunar orbital station is designed to enable the effective remote surface exploration, solving of control issues, performance of experiments, relieving of cargo and passenger traffic. Main Characteristics Name Value Orbit altitude, km 100 5500 Orbit inclination, degrees ~ 87 Power capacity of power supply system, kw maximum 22 Crew, persons 2-4
LUNAR ORBITAL FACILITIES Lunar orbital communication satellite constellation It is designed for continuous connection between satellites, acquisition stations and users. The number of satellites in the constellation is 4. Technical characteristics Total mass, kg ~400 Payload mass, kg ~65 Circular orbit parameters: altitude, km ~1000 inclination, degrees ~70 Maximum power, W 500 Retransmitter: receiver transmitter L-range Ka-range Active service life, years minimum 2
LUNAR ORBITAL FACILITIES Lunar navigation orbital satellite constellation It is necessary to provide the users with continuous data about three dimensional positioning with high accuracy. The number of satellites in the constellation is 12. Main Сharacteristics Total mass, kg ~400 Payload mass, kg ~65 Circular orbit parameters: altitude, km ~1000 inclination, degrees ~70 Maximum power, W 500 Retransmitter: receiver transmitter L-range Ka-range Active service life, years minimum 2
LUNAR ORBITAL FACILITIES Orbital constellation of lunar remote sensing satellites It is designed for on-line receipt of digital images of lunar surface in visible and radar bands of electromagnetic waves lengths and transmission of the received images data to the Ground Control Complex. The number of satellites in the constellation is 4: to meet the challenges of detailed mapping and creation of lunar surface 3D-model. The constellation consists of two spacecraft with optical payload. Main Сharacteristics Total mass ~ 600 kg Payload mass ~ 200 kg Circular orbit parameters: altitude 100 ± 4 km inclination 90 ± 0.03 Ground resolution in nadir ~ 1.2 m Swath width Provided ground imagery to the left and to the right from the track Active service life ~ 35 km ± 85 km minimum 2 years
LUNAR ORBITAL FACILITIES Orbital constellation of lunar remote sensing satellites to meet the challenges of reconnaissance and analysis of lunar samples. The constellation consists of two spacecraft with radar payload. Main Сharacteristics Total mass, kg ~ 600 Payload mass, kg ~ 160 Circular orbit parameters: altitude, km 250 ± 4 km inclination, degrees 90 ± 0.03 Ground resolution in nadir: ~ 1.2 m in spot imaging mode 2 2 m in strip imaging mode 6 10 m in overview mode 20 20 m Ground images dimensions (by azimuth in lateral direction) in spot imaging mode 8 6 km in strip imaging mode 100 12 m in overview mode 100 30 m Active service life minimum 2 years