Module "Zvezda"

Launch, orbit & landing data: Designation  26400 / 00037A Launch date - time  12 Jul 2000 - 04:56:36 UT Launch site  Baikonur, LC81/23 Launch vehicle  Proton-K (nº398-01) OKB name - S/Nº  77KSM nº 128-01 Mass (kg)  19 050 kg (20295 kg?) Docking date - time  26 Jul 2000 - 00:45 UT Target spacecraft/port  Zarya rear port Orbital parameters on Jul 26, 2000 (.14):    - Perigee / Apogee  351 x 368 km    - Inclination  51.58°    - Period  91.73 min Descent date - time  Still in orbit - ISS Flight Duration (d:hr:min)   Nbr orbits

Zvezda service module with a Progress docked on the left and the Zarya FGB docked on the right. (NASA)

Spacecraft specifications:

Summary:

Mission details:

• ISS Zvezda is a Russian service module for the International Space Station. Its name is from the Russian Звезда, meaning 'star'. The eighth civilian Salyut-class space station 17KSM No. 128-1, was successfully launched on Jul 12 at 0456 UTC. The three stage Krunichev Proton-K rocket reached orbit at 0505 UTC. This was the fifth Proton launch in a month. Zvezda's initial orbit was 179 x 332 km x 51.6 deg. On Jul 14 the orbit was raised to 288 x 357 km. ISS is in a 365 x 372 km orbit.
• Docking with the Zarya/Unity on July 26 at 00:45 UT. The basic structural frame was initially built in the mid 1980's and designed to be the core of the Mir 2 space station, which the ISS replaced, and, in fact, was labeled as "Mir-2" for quite some time in the factory. Zvezda is outwardly almost identical to the Mir core module launched in 1986, and the main structure is similar to all the civilian DOS orbital stations launched since 1971 built by the Krunichev company and developed and operated by Energiya.

• Due to Russian financial problems, Zvezda was launched with no backup and no insurance. Due to this risk, NASA had constructed an Interim Control Module in case it was delayed significantly or destroyed on launch. However, without the Service Module, it would be several more flights before the ISS would be able to support a permanent crew.

• Zvezda is the structural and functional center of the Russian portion of the ISS -- the Russian Orbital Segment and the early core of the station. Zvezda provided early living quarters, a life support system, a communication system, electrical power distribution, a data processing system, a flight control system, and a propulsion system. These quarters and systems are to be supplemented or replaced by future ISS components.

  Zvezda consists of a cylindrical "Work Compartment" where the crews work and live, a cylindrical "Transfer Chamber" which has one docking port, an unpressurised "Assembly Compartment" surrounding the Transfer Chamber, and a spherical "Transfer Compartment" with three docking ports.

  The Transfer Compartment attaches currently to the Zarya module and has docking ports intended for the Science Power Platform and the Universal Docking Module. However, currently the lower port contains the Russian Docking Compartment and the other is empty. It can be used as an airlock, however, if the hatch fails, it will be impossible to travel to the rest of the station, so that capability has never been used.

  The Assembly compartment holds external equipment such as thrusters, antennas, and propellant tanks.

  The Transfer Chamber is equipped with automatic docking equipment and is used to service Soyuz and Progress spacecraft.

  Zvezda contains sleeping quarters for two astronauts, A NASA-provided treadmill and a bicycle for exercise, toilet and other hygiene facilities, a galley with a refrigerator and freezer. It contains the primary Russian computers for guidance and navigation. It has a total of 14 windows -- three 9-inch diameter windows in the forward Transfer Compartment, a 16-inch in the Working Compartment, a window in each crew compartment, and several more. It also contains the Elektron system that uses condensed humidity and waste water, electrolyzes it, and provides hydrogen and oxygen. The hydrogen is exhausted into space and the oxygen is used for breathing air. The condensed water and the waste water can be used for drinking in an emergency, but ordinarily other fresh water from Earth is used. There are 16 small thrusters and two large thrusters for propulsion and eight batteries for storing power.

  The Elektron system has required significant maintenance work, having failed several times and requiring the astronauts to use Solid Fuel Oxygen Generator canisters (commonly called "Oxygen Candles"), which were the cause of a fire on Mir, when it has been broken for extended amounts of time. It also contains the Vozdukh system to remove Carbon Dioxide from the atmosphere. It was criticized for being excessively noisy inside of the Zvezda and, in fact, Astronauts have been observed wearing earplugs inside of it.

Description:

Zvezda Service Module, : Zvezda is the core of the ISS, providing living quarters and life support for the crew. It was originally intended for the Mir-2 space station, but when this was cancelled after the fall of the Soviet Union, it was amalgamated into the ISS instead.

Zvezda is a cylinder divided into two main compartments:

• PKhO, transfer compartment: this spherical compartment at the forward end provides 5 docking ports and also serves as a back-up airlock if no specialized airlock is attached.
• Working Compartment: contains life support systems, instruments and crew quarters. It is two cylinders joined together:
  • Instrument Compartment: the smaller section aft of the PKhO contains the Station command post (central computer) and related equipment. 
  • Habitable Compartment: behind this, in the larger cylinder, contains crew life support and two cabins (kayuti). The kayuti each has a measurement of 0.73 x 0.85 x 1.89 m.

Diagrams:

Zvezda internal layout: Transition piece Transfer hatch TORU manual docking controls Gas mask Vozdukh atmosphere regenerator Solid oxygen generators Cabin (1 of 2) Sanitary compartment (the loo!) Intermediate camera Transfer hatch Fire extinguisher Service module Treadmill installation site Dust collector Table Bicycle ergometer installation site Windows Central command post (Novosti Kosmonavtiki)

Zvezda has 14 windows, most downward-facing. There is one window in each kayuta (n° 1 port, and 2 starboard - not shown here), and 6 set into the floor of the Working Compartment (n° 3-8), plus one 40 cm-diameter Observation Window (n° 9) set into the flared skirting between the Working and Living Compartments. There are 3 22.8 cm windows in the Forward Transfer Compartment for viewing docking activities, and one set into the rear docking port. Window 7 has a shade; window 4 a vertical sight.

Official Module Zvezda

Novosti Kosmonavtiki n°9, 2000

The official module Zvezda (article 17KSM, n°12801) is the foundation of the ISS Russian segment. The Service Module provides support for up to 6 crew members and enables control of the ISS during its construction and changing configuration. In the ISS development stage, Zvezda is the core module of the Station and provides the basis for life support and crew activity. It is thus the most complex module of the Russian segment, with the most equipment.

Basic functions of the Service Module

1. Guarantee of conditions of work and leisure of crew;
2. control of the work of major portions of the orbital complex;
3. supply of complex by electric power;
4. guarantee of a two-way radio system of crew with the ground-based complex of control;
5. method and the transmission of television information;
6. transfer in NKU of telemetry data about the state of crew and onboard systems;
7. method of controlling on-board information systems;
8. orientation of complex relative to the Station's center of mass;
9. correction of the orbit of complex;
10. guarantee of the approach and docking of other objects to the complex;
11. maintenance of the assigned temperature and humidity regime of habitable volume, elements of construction and equipment;
12. guaranteing of suitable conditions for cosmonauts' spacewalks - the fulfillment of works on maintenance and repair on the external surface of station;
13. conducting scientific and applied research and experiments with the use of specialized equipment;
14. possibility of achieving two-way onboard communication of all ISS modules.

The official module is the first completely Russian module, which will become part of the International Space Station. The head developer of the SM Zvezda is RKK Energiya (named after Academician S. P. Korolyov). Basic subcontractor was GKNPTs Khrunichev: also involved were KB Salyut (design and designing), the rocket-space plant (production of housing, assembling, the part of the tests), plant on the operation of rocket-space technology (prelaunch servicing procedure, launching) and many others.

Construction of the module

Structurally, SM Zvezda consists of four sections: three airtight-transition pieces, working compartment (PO, RO) and intermediate chamber (IIpK, PrK), and also the non-hermetic service module (AO, AO), in which is placed the united engine installation. The housing of airtight sections is made from the aluminum-magnesium alloy AMr-6 and is of welded construction, which consists of blocks of cylindrical, conical and spherical shape.

The transitional section, is intended for the provision for transfer of crew members between the CM and other ISS modules. It also fulfils the functions of an airlock on exiting of crew members into open space (i.e. spacewalks), for which on the lateral cover on the number II (starboard) plane there is a dump valve.

The PkhO's structure is the combination of a sphere with the diameter of 2.2 m and truncated cones with the diameters of the bases of 1.35 m and 1.9 m. The length of the PkhO is 2.78 m; airtight volume - 6.85 m. With the conical part (large diameter) PkhO is attached to the RHO. On the spherical part of the PkhO are established three hybrid passive docking assemblies - SSVP-M G8000, CCBP-MT 800 (one axial and two lateral). To the axial knot of the PkhO will be joined the FGB Zarya. On the upper knot of the PkhO is planned the installation of the Science & Power Platform. To the lower attachment point of the PkhO must first be moored docking module n°1 (Pirs), and then universal docking module (USM).

On the external surface of the PkhO are brackets, on which the handrails are fixed, three sets of the antennas (AR-VKA, 2AP-VKA and 4AO-VKA) of system Kurs for three butt are main, docking targets, aggregates CTP , STR, the block of refueling DU; television camera, aircraft navigation lights and other equipment. External surface is closed with panels EVTI and antimeteorite screens. In the PkhO there are four illuminators.

The working compartment section, is intended for containing the major portion of SM onboard systems and equipment, for life support and crew activity. The housing of the (working compartment) consists of two cylinders of different diameters (2.9 m and 4.1 m), connected together by a conical adapter. The length of the cylinder of small diameter is 3.5 m; greater: 2.9 m. The front and back plates are spherical. The overall length of the RO is 7.7 m; the airtight volume with the equipment: 75.0 m³; the volume of the crew-inhabited section: 35.1 m³. The panels of the interior separate habitable zone from the instrument section, and also from the housing of the RO. In the RO there are eight illuminators/lights, one of which (n°9) with a diameter of 420 mm, is supplied with a cover, and two illuminators stand in the individual cabins.

The living quarters of the RO are equipped with the means of crew life support. In the zone of the small diameter of the RO is located the Station central control post, with the control blocks and the emergency-warning panels. Here is provided a place for the installation of the TORU teleoperator control equipment. In the zone of the large diameter of the RO are two personal cabins (by volume 1.2 m³ each), a sanitary section with a wash-stand and the toilet (volume of 1.2 m³), a kitchen with a refrigerator-freezer, a fixed working table, medical equipment, physical exercise equipment, a small airlock for the department of containers with the withdrawals and small KA and so forth, etc.

Outside, the hull of the RO is sealed with a multilayer shield-vacuum heat insulation (EVTI). On the cylindrical parts the radiators, which fulfill also the functions of antimeteorite screens, are attached. The sections not protected by radiators are sealed with carbon plastic screens of honeycomb construction. On the external surface of the RO are fixed handrails, which the members of crew can use for fastening tethers during their work in open space. On the left and starboard there are two brackets (duct) of fastening nose fairing. On them it is planned to subsequently establish telescopic cargo booms (Strela cranes). On the II and IV planes of the small diameter of the RO are two niches, in which are established the SB drives (B16). Furthermore, outside the small diameter of the RO are established the sensors of the system of control of motion and navigation (SUDN) for the orientation by the sun (two DK-31M and two 251K2) and to the Earth (three 256K), four sensors of orientation system SB (B12M), two stellar units (star sensors) AB-2, two antennas of system Tranzit-B, aircraft navigation lights and so forth, etc.

At the ends of the solar batteries are established two antennas AKR-VKA of the Kurs system, two antennas of the Regul-OS system, one television antenna, one antenna of the BITS2-12 system, and aircraft navigation lights.

The intermediate chamber, is intended for the provision for transfer of the cosmonauts between the SM and the Soyuz spacecraft or Progress, attached to the stern docking assembly. The shape of the PrK is cylindrical with a diameter of 2.0 m and with a length of 2.34 m. The internal volume is 7.0 m³. The PrK is supplied with one passive docking assembly SSVP G4000 (analogous to the attachment points on BB of the Mir space station), located along the longitudinal axis SM. Knot is intended for dockings of cargo and transport spacecraft, including of Russian ships Soyuz TM, Soyuz TMA, Progress M; and Progress M2, and also the European automatic ship (ATV). For the external observation into PrK there are two illuminators, and a television camera is attached to the outside.

The assembly compartment, is intended for positioning the units of the united engine installation (ODU). Aft of the AO are two corrective engines, while on the side four blocks of the orientation engines. Outside on the rear frame of the AO is fixed a rod of the highly directional antenna (IT) for the onboard radio-technical system Lira. Furthermore, on the housing of the AO are three antennas (AR-VKA, AP-VKA and 2AP-VKA) of the Kurs system, four antennas of the radio-technical system for control and communications Regul-OS (including antennas AR-1 and AR-2 with the phased lattices), two antennas of television system, six antennas of the system of telephone-telegraph communications, two antennas of equipment of the radio control of orbit, two antennas of the BITS2-12 system, four antennas of the Tranzit-B system, two rods of the antennas of system Kurs. Also on AO are SUDN fixed sensors for the orientation by the sun (four DK-31M and two 251K2), four sensors of orientation system SB (B12M), aircraft navigation lights and so forth, etc.

The AO has a cylindrical form. At the end it is sealed by the multilayer shield-vacuum heat insulation EVTI. The external surface of the AO is closed with an antimeteorite protective housing and EVTI. The handrails and antennas are fixed on the external surface, and there are hatchways for servicing of equipment, located inside the AO.

During launch, the small diameter RNO, with the folded solar arrays (SB) and PkhO, is protected by the nose fairing (GO). The SM is attached to the RN rocket launcher through an intermediate section, which is discarded with the 3rd stage of the rocket separation.

It is necessary to add that the significant equipment component was not loaded on the SM because of the limitations on the RN launch rocket's load capacity. It will be delivered later aboard the transport ships of both Russia and USA. Thus, for instance, part of the equipment and devices for Zvezda has already been carried into orbit during the flights of shuttles STS-88, -96 and -101, and are awaiting their hour in the cargo sections of the FGB Zarya (among them the bicycle ergometer and treadmill).

Service module systems

The onboard control complex (Bortovoi Kompleks Upravleniya) consists of the Service Module and other ISS modules, united into a single controlling complex.

The BKU includes the following SM systems:

• the motion control system;
• onboard computing system;
• onboard radio complex;
• the onboard measurements system;
• the onboard complex control system;
• the teleoperator mode control equipment (TORU) of approaching and docking automatic cargo spacecraft (i.e. Progress).

The motion control system:

• enables ISS orientation stabilization in any regime of attitude control with the aid of the jet engines, and also the power gyroscopes (after their arrival to the ISS Russian segment);
• the execution of programmed rotations in any of the regimes of attitude control;
• the calculation of the current onboard navigation information with the aid of the autonomous equipment for satellite navigation;
• conducting of unloading the accumulated moment of momentum (desaturation) of power gyroscopes with the aid of the jet engines;
• conducting the correction of orbit with the aid of the SM's corrective engines and the approach-corrective engine of cargo ship Progress; also with the use of the SM's orientation engines and for cargo ship, and subsequently the engines of Science & Power Platform;
• conducting of docking and undocking of the Soyuz spacecraft, Progress and shuttle with the ISS;
• the control of the consumption of fuel, production of resource by instruments and by executing agencies;
• attitude control solar batteries of the SM and FGB, and also the radiator of the temperature control system of the Science & Power Platform;
• controlling of the attitude of the Lira pencil-beam antenna and the attitude of the impulse phased antenna cascade of the Regul system, which supports connection with the relay satellite;
• the control of the fitness for work of instruments and other equipment in the control loop.

In the composition of the SUD SM, the Station's attitude is determined by the gyroscopic gauge of angular velocities (GIVUS), wide-angle view-finder with the precise vertical line (VSHTV), six sensors of the eclipse of the sun DK-31M, four sensors of the measurement of the coordinates of the sun of 251K2 (DIKS2), three sensors of the determination of the coordinates of the Earth 256K (11M39), two magnetometers CM-8M (17M23), two starry instruments AIS-9E with the stellar units AB-2, equipment of the system of navigation ASN, Al'fa. For the observation of space surrounding the SM are a pilot view-finder, VP-2 (240K) and a movable view-finder (PUMA). For control of the parameters of the motion of station at the central station post, two orientation control knobs (RUO) and one motion control knob (RUD).

In the composition of the SUD SM is also the Kurs equipment for the measurement of the parameters of relative motion, utilized for automatic approach & docking of other modules with Zvezda and transport ships. Kurs consists of the unit K2-VKA-02, antennas 4AO-VKA, 2AP-VKA, AP-VKA, AKP-VKA, and other electronic components.

Furthermore, on the exterior of the SUD of the module Zvezda are external aircraft navigation lights and targets for docking.

The onboard computer system is the basis of the BKU SM and serves as the SM's control onboard system and for coordinating all modules of the ISS Russian segment, solves the problems of long-term planning and automatic preset control, and also ensures connection with the American segment's onboard equipment control system.

The SM's central element BVS, is the data processing system of the DMS-R (Data Management System of the Russian Service Module). It was developed and produced in Europe by an industrial group under the management of DaimlerChrysler Aerospace (DASA) in Bremen (Germany) on the contract of the directorate of manned space flights and micro-gravity EKA (Directorate of Manned Spaceflight and Microgravity) (Noordvik, the Netherlands). The creation of the DMS-R project was achieved within the framework of agreement of the collaboration between EKA and Rosaviakosmos. The system includes: two failure-resistant computers (Fault Tolerant Computer, FTC); central computer (Control Computer, the CC) and terminal computer (Terminal Computer, TC); two control stations (Control Post, CP) for the delivery by the crew of commands and fulfilment of control through DMS-R, and also for conducting of experiments and operations with the European Manipulator, ERA.

The DMS-R system architecture and its interfaces with the entire ISS include ten mains MIL-STD, which ensure the connection between different ISS elements and equipment. Furthermore, in the composition of the BVS CM are the Simbol-TsM, display, two other displays, and devices of docking and nourishment.

Onboard radio complex

The onboard radio complex (BRK, Bortovoi Radiokompleks) ensures two-way oral communication, exchange of digital command-programs, telemetric and television information through the Russian ground-based complexes or through the relay satellite located in geostationary orbit.

The SM consists of five systems:

1. the radio-technical system for control and communications (RSUS) Regul-OS with two antennas AR-1 and AR-2 with phased lattices and four-bolt omnidirectional antennas VNA;
2. the television system (TVS) with the block of commutation KL-160, three antennas, electronic components and two cameras 140ST-M (into PkhO and PrK) (remaining TV equipment, including the television camera KL-103B, long-distance receiver KL-123-01 and TV transmitter KL-108-A, will be delivered later);
3. the system of telephone-telegraph communications (STTS), which includes different electronic components, loudspeakers, sets of low it is noise without the noise reduction, six antennas (on two antennas AM-6, AM-7, AM-9), telegraphic equipment (it is reached more lately) and equipment of internal wireless connection inside the station Sphere (it is reached more lately);
4. the system of the radio control of orbit (RKO) with the transceiver 38G6 and two antennas;
5. onboard radio-technical system (BRTS) Lira, with semidirectional antenna MNA, pencil-beam antenna ONA precise bearing and antenna of the approximate bearing (all three antennas they cost on the rod ONA). BRTS Lira includes the subsystem of automatic control of drives ONA.

Onboard measurement system

The onboard measurement system (Sistema Bortovykh Izmerenii) is intended for obtaining, working, storing and transmission to the Earth of information about state and work of systems, scientific equipment and status of the health of crew members. In the SBI enter onboard measuring telemetric system, communications collection equipment, which ensures the transfer of the parameters from FGB Zarya, and also the devices of the measurement of temperature aboard the attached Soyuz spacecraft. The SBI consists of onboard transmitters, different electronic components for the collection, working and delivering of the data, large number of switchboards. For the collection of information in SBI also enter the accelerometers, the gauges of angular velocities, pressure sensors, magnetometers. Partly SBI also will become the reached later system Resource for the observation of the state of housing SM and its fatigue strength.

Also structurally in SBI enters the radiotelemetry system (RTS) Tranzit-B, intended for the radiotelemetric control of crew members during spacewalks. It consists of two onboard receivers SHA346 and SHA346B and two input units; and signal forming TA739M and TA739MB.

Control system of the onboard complex

Control system of onboard equipment (SUBK) is intended for control, monitoring and diagnostics of the state of onboard systems SM. On the module there is about 2700 units of equipment and instruments with a general mass of 2.5 T. of them it connects order 3000 cables (overall mass BKS: 2990 kg). SUBK functions on the basis of the use of output data of the signals of sensors, functional outputs of command radio link SM, relay outputs BVS, SM control panels and onboard systems. SUBK consists of:

• the subsystem of the distribution of electric power supply and control of pyro-means;
• the subsystem of logical processing of commands;
• the manager of information complex with the subsystem of time, SPL-BSV;
• the means of manual control of onboard systems (33 different panels, panels and control panels).

Electrical power supply system

Electric power supply system (SEP) ensures the continuous feed of direct current to onboard instruments of the SM. Furthermore, SEP SM provides nourishment and possibility of the booster charge of the attached to the ISS, Soyuz spacecraft and Progress. It is also possible to obtain electrical power, if necessary, from the power supply system of the ISS American segment, and from the NEP also of universal docking module. Prior to the arrival of the Science & Power Platform, the SEP SM ensures the nourishment of the remaining elements of Russian segment, with the exception of the FGB.

The basic electric power source are two solar batteries (СБ, SB) each massing 580 kg. Their area, occupied with photoelectric converters for each of them, composes 38 m². The photoelectric cells are protected from both sides by a transparent glass coating. The SB are turned by their surface areas towards the sun. Each SB consists of 12 independent generators, which in turn consist of the series-connected silicone photoelectric converters.

The solar arrays were constructed so that additional solar panels ( DPSB) could be added to them in orbit. The delivery of the DPSB to orbit is planned TKG Progress, and the installation of these on the basic SB will be done by crew during a space walk. A complete set of DPSB for the SM was being prepared in the Khrunichev center during October 1999. During July 2000, photoelectric converters were installed on them. During September 2000 DPSB will be transmitted in RKK Energiya for the preparation of their sending in orbit.

The attitude control of the solar arrays can be achieved automatically with the use of an SB orientation system (SOSB), which consists of eight B12 sun sensors, two B16M drives, control units B14M and other electronic components. Also, the orientation of the solar arrays can be manually controlled by crew with the aid of the onboard computers.

Storage of electric power and constant electric power supply on the SM is provided by eight 800A storage batteries (AB). Five of them were included on the SM with its launch and three more will be delivered later. Each of the batteries contains 22 hermetically isolated nickel-cadmium storage batteries which are serially connected. At the output AB is supported stress 28.5 V. kazhdaya it is supplied with current control, with converter of current PTAB-YM, with control unit of the converter of current BUPT-Y.

Furthermore, in the composition of the SEP SM are two current regulators ST-25, four stabilizers of voltage and current SNT-50M, the filter unit. The SEP structurally includes also the means of illumination, which include 23 stationary and two movable lamps (two additional stationary lamps will be delivered later and installed by the crew).

United engine installation

The united engine installation (ОДУ, ODU) is intended for fulfilling the following functions:

• the guarantee of ISS attitude control;
• the correction of orbit altitude with the aid of the corrective engines ODU;
• the guarantee of ISS stabilization with the spinup of power gyroscopes;
• power unloading gyroscopes;
• the guarantee of a possibility of refueling the ISS;
• the guarantee of supply of fuel from the tanks ODU CM to the engines CM, the Science & Power Platform, to the engines of roll control of universal docking module and engines of the Progress cargo ship;
• the guarantee of supply of fuel from the Progress tanks into the engines ODU CM.

The ODU Zvezdi (Stars) includes two corrective engines (KD) C5.79 with a thrust of 315 kg (mass of one = 38.5 kg) and 32 engines for orientation (DO) 11D428A with a thrust of 13.3 kg (mass of one = 1.2 kg) for the channels of pitch, yaw and roll. KD C5.79 are the regenerative cooled engines, established at an angle of 15° to the longitudinal axis of the SM. Each of the KD are supplied with gimbal suspension, which makes possible for them to be turned to ±5° along two axes. The exterior of the KDs are protected by removable covers. DO 11D428A are grouped into two collections of 16 engines.

Also included in the composition of the ODU:

• bellows-type four tanks (mass of one 65.0 kg), which contain to 558 kg of oxidizer (nitric tetraoxide) and of 302 kg four tanks bellows
• eight balloons with compressed nitrogen (mass of balloon = 7.6 kg, the mass of servicing with nitrogen = 37.0 kg);
• the pneumo-hydrosteel framework of tanks;
• controlling-starting hydroapparatus;
• servicing hydro-steel framework from the side AO PkhO;
• the pneumo-steel framework of high and low pressure;
• the block of compressors (mass = 115 kg);
• the conduits (with overall mass of 100 kg), neck, sensors and so forth, etc.

The ODU SM tanks can be primed by fuel from the cargo ship Progress, and also by transit through SM can be primed the fuel tanks of the FGB Zarya.

Thermal control system

The system for maintaining thermal conditions (COTP, SOTR) works independently of the SM's remaining systems and functions constantly. It has both active and passive thermal controls. The COTP provides the assigned temperature characteristics of the atmosphere of airtight sections and the corresponding thermal conditions for the functioning of equipment, elements of structure, blocks of the system of engines and docking assemblies. Also it governs ventilation and humidity of the crew compartments and instrument zone SM. In the crew compartments the temperature is maintained in the range of 18°C to 28°C. The active COTP is used by 262 of the heat-transfer agent with a mass of 303 kg.

The temperature control system, which includes, is the main element of the COTP:

• two cooling circuits, KOKh1 and KOKh2, with four panels of the radiative heat exchangers outside the small diameter RHO and six outside the large (heat-transfer agent PMS-1.5r with a mass of 40 kg);
• two internal outlines of heating, KOB1 and KOB2 (in them they enter, including and the airconditioning system SKV-1) (heat-transfer agent , Temp, with the mass of 170 kg);
• two intermediate circuits of connection PKS1 and PKS2 (heat-transfer agent PMS-1.5r with a mass of 10 kg);
• sensors, valves, main, conduits, other steel framework and so forth, etc.

Furthermore, into the composition of COTP they enter ventilation system (only 32 fans), the system of control COTP, etc. passive thermal control provides shield-vacuum heat insulation with the overall mass of 150 kg.

Life support system (SOZH)

SOZH consists of the following subsystems:

1. the system for assuring proper gas composition SOGS). It includes means of control and regulation of atmospheric pressure, means of pressure balance, equipment of decompression and supercharging the PkhO, gas-analytic equipment, the system of the removal of harmful impurities БМП, BMP, the Vozkukh system of the removal of carbon dioxide from the atmosphere and the means of cleaning the atmosphere. The SOGS provides the means of oxygen supply, which include the solid-propellant sources of oxygen (TIK) and the system of obtaining oxygen from the water ( Elektron VM) (this will be delivered onboard the SM later). The Service Module was launched with 120 kg of air and two solid-propellant generators of oxygen (TGK);
2. the means of water provision (SVO), used for collection, storage and the distribution of the water supplies on the ISS for the crew's needs. They consist of the system of the regeneration of water from the condensate SRV-K2M, the means of water provision on the supplies of water SVO-EV (distribution and preheating water), the water storage system Rodnik (Spring) (two tanks). With the launch of the SM there was 210 kg of drinking water onboard;
3. means of health and hygiene guarantee (SSGO). They include waste management system ASU-8AM, a wash-stand (this will be delivered to the SM later), containers for household trash, vacuum cleaner Raketa-7S (delivery later);
4. means of the guarantee of the nourishment (SPO), which includes two electric food heaters/warmers (one was included with launch, one will be delivered in the course of flight), two onboard refrigerators BKH-E (both to be brought later), the food serving facility, containers of food rations and secondary food rations. The SM was loaded with 96 kg of food prior to launch;
5. means of individual protection, which consist of two Orlan spacesuits with their equipment (everything will be delivered onboard after launch);
6. means of detection and signalling about the fire situation Signal-VM, which ensures the detection of smoke, the wear and tear of signalling and the automatic start of the fire extinguishing program, that insulate gas masks, fire extinguishers.

Medical support

The health of crew members - the maintenance of their normal fitness for work under the conditions of space flight - is one of the basic objectives of the ISS mission. On board the SM for these purposes there are special means which make it possible to check the status of the health of cosmonauts and to counteract the unfavorable influence of the factors of space flight on the human organism.

The means of medical control and inspection include complex Gamma-1M for the control and recording of physiological data for the purpose of the estimation of the state of cardiovascular system, the gauge of the body mass of the cosmonaut, the Reflotron analyzer for a biochemical study of the blood, the analyzer of urine Urolyuks, the volumeter of the shin of cosmonaut (i.e. measuring the dimensions of his calves), equipment Argument-A1-01, equipment of medkontrolya with the work in open space Output, complex Plasma, cardioregistrator. All this equipment, except that already included with the launching on CM complex Gamma-1M, will be delivered onboard in the course of flight.

The means of checking the purity of the atmosphere comprises two instruments: absorptive concentrator AK-Y, for evaluating the atmospheric content of toxic organic microcontaminants; and microbial sampler Ecosphere for the determination of the quantity of microorganisms in the Station's atmosphere.

There are various devices to help combat the unfavorable effects of weightlessness.

• the pneumo-vacuum suit PVK-Y Chibis (Lapwing - a species of bird) creates a negative pressure on the lower half of a cosmonaut's body, encouraging blood to circulate similar to the way it does in normal Earth gravity, thus helping prepare the wearer for return to Earth;
• the electrostimulator Tone-3, averts muscular atrophy;
• trainer (begushchaya dorozhka, treadmill) UKTF-4, bicycle ergometer (VELO, veloergometr) VB-5M for warning the muscular out-of-training state of legs and arms (it is also used during medical examinations);
• training-load suit TNK-U1, load suit Pengvin (Penguin) creates an incremental load on the supporting-motor apparatus of cosmonaut.

Besides equipment Tone-3, all this equipment will arrive onboard the SM after its launch, already in the course of flight.

Hygeine supplies on Zvezda include moist and dry napkins and towels, Aelita shampoo, a personal Komfort-1 hygiene equipment bag; a Kharkov razor*, sleeping equipment (sleeping bag with SPM-2MN insert/lining), and also sets of cotton-linen clothing, operator work suit and warm overalls (just in case).

[*Mark Shuttleworth mentioned in one of his ISS training diaries that the ISS-approved razor was the Gillette Sensor Excel.]

From the scientific gear on the SM thus far it is planned to deliver and to set up the Russian-French-Belgian atmospheric spectrometer MIRAS (Mir Infra-Red Atmospheric Spectrometer). Analogous equipment was also installed on the Spektr module of Mir. MIRAS consists of the external block MEX (spectrometer and heliostat, overall mass: 120 kg), the internal block of electronics EMIR and manager of computer. The instrument is intended for measuring the profiles of the concentration of low components of the atmosphere by the method of infrared absorptive spectroscopy during sunrise and sunset.

Photo gallery

	14 April 2003: "Attired in their Russian Sokol suits, the Expedition Six crewmembers pose for a crew photo in the Zvezda Service Module on the International Space Station (ISS)." This photo shows an aft view of the Service Module; starboard is to the left, port to right and the hatch leading to the docked Progress cargo ship is behind Expedition 6. The twin kayutas (cabins) are visible on either side. Photos of Yurii Gagarin and Konstantin Tsiolkovskii are attached to the panel above the rear hatch. - Credit: NASA.
	3 August 2003: "View down the length of the interior of the Zvezda Service module from the forward section to the aft end, as photographed by one of the Expedition 7 crewmembers." A sweeping view along Zvezda towards the Station's forward end, leading to Zarya. Laptops can be seen at the Command Post (TsP), providing an interface for the Russian segment's systems. - Credit: NASA.
	1 December 2003: "Cosmonaut Aleksander Y. Kaleri, Expedition 8 flight engineer representing Rosaviakosmos, eats a meal in the Zvezda Service Module on the International Space Station (ISS)." This view is further to the left (starboard in the photo), looking to Zvezda's aft, showing the Galley table and kayuta behind. - Credit: NASA.
	17 April 2005: "View of the interior of the Zvezda Service module from the forward section to the aft end, as photographed by one of the Expedition 10 crewmembers on the International Space Station (ISS)." A good view looking forward (toward Zarya), showing the Central Workstation with its four laptops. - Credit: NASA.

External links:

• Capcomespace: Module Zvezda. (in French)
• ENERGIA: Zvezda module.

Astrophilately covers:

Launch cancel Baikonur, special red cancel.

Launch cancel Baikonur, 4 different cancels. Credit: #402

Docking cancel Korolev, send registrated.