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The International Space Station (ISS) Flight Systems Make up the Core Functional Infrastructure of the On-Orbit ISS

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The International Space Station (ISS) Flight Systems Make up the Core Functional Infrastructure of the On-Orbit ISS The International Space Station (ISS) flight systems make up the core functional infrastructure of the on-orbit ISS. The ISS flight systems consist of Habitation; the Crew Health Care System (CHeCS); systems Extravehicular Activity (EVA); the Environmental Control and Life Support System (ECLSS); Computers and Data Management; Propulsion; Guidance, Navigation, and Control; Communications; the Thermal Control System (TCS); and the Electrical Power System (EPS). These flight systems provide a safe, livable, and comfortable environment in which crewmembers perform scientific research. Payloads, hardware, software, and crew support items on the ISS operate within the capabilities of these flight systems. INTERNATIONAL SPACE STATION GUIDE SYSTEMS 49 INTEGRATED TRUSS ASSEMBLY 5 31 10 5 15 31 9 Integrated Truss Assembly 25 6 15 10 32 12 37 37 The truss assemblies provide attachment points for the solar arrays, thermal control radiators, and 37 external payloads. Truss assemblies also contain electrical and cooling utility lines, as well as the mobile 5 15 transporter rails. The Integrated Truss Structure (ITS) is made up of 11 segments plus a separate com- 24 10 37 ponent called Z1. These segments, which are shown in the figure, will be installed on the Station so that 11 4 5 4 they extend symmetrically from the center of the ISS. 6 32 41 At full assembly, the truss reaches 108.5 meters (356 feet) in length across the extended solar arrays. 22 31 42 30 12 ITS segments are labeled in accordance with their location. P stands for “port,” S stands for “star- 22 26 37 37 board,” and Z stands for “Zenith.” 37 38 15 Initially, through Stage 8A, the first truss segment, Zenith 1 (Z1), was attached to the Unity Node 37 37 17 20 zenith berthing mechanism. Then truss segment P6 was mounted on top of Z1 and its solar arrays and 29 4 16 4 radiator panels deployed to support the early ISS. Subsequently, S0 was mounted on top of the U.S. 37 36 1 22 27 7 9 Lab Destiny, and the horizontal truss members P1 and S1 were then attached to S0. As the remaining 37 27 30 P6 members of the truss are added, P6 will be removed from its location on Z1 and moved to the outer 2 16 10 31 end of the port side. 8 10 39 P5 11 36 29 27 7 35 39 37 10 P4 39 34 37 7 28 19 3 18 39 23 41 14 13 2003–06 configuration, 10 21 16 looking from nadir. 17 10 P3 5 15 14 1 37 9 37 40 17 39 U.S. Lab 20 5 P1 39 19 Outboard Lower Camera 23 40 18 20 Photovoltaic Radiator 37 3 28 21 Pump Flow Control Assembly 17 33 35 S0 31 10 22 Pump Flow Control Subassembly 10 37 39 21 27 39 7 8 Charged Particle Directional Spectrometer 23 Pump Module 30 9 Direct Current Switching Unit (DCSU) 24 PVR Controller Unit 9 17 19 5 10 DC-to-DC Converter Unit (DDCU) 25 PVR Grapple Fixture Bar 15 5 6 4 S1 1 Solar Array Alpha Rotary Joint 11 Deployed Thermal System Radiator 26 Radiator Beam Valve Module S3 2 Ammonia Tank Assembly 12 Grapple Fixture 27 Remote Power Control Modules 3 Assembly Contingency 13 Inboard Lower Camera 28 Rotary Joint Motor Controller Baseband Signal Processor 14 Main Bus Switching Units 29 S-Band Antenna 4 Batteries S4 15 Mast Storage Canister 30 Solar Array Alpha Rotary Joint Drive 31 5 Battery Charge Discharge Unit Lock Assembly 12 16 Mobile Transporter Rails 6 Beta Gimbal Assemblies 31 Solar Array Wing 4 17 Multiplexer/De-Multiplexers 7 Cable Trays 32 Stowed Photovoltaic Radiator 20 18 Nitrogen Tank Assembly (interior to truss) S5 33 Struts 6 34 Thermal Control System Radiator Beam 35 Thermal Radiator Rotary Joint with Flex Manual Hose Rotary Coupler S6 Berthing Space to Ground Mechanism Antenna (SGANT) Z1 S0 36 Transponder Z1-to-U.S. Lab 37 Trunnion Umbilical U.S. 38 UHF Antenna Z1-to-U.S. Lab Airlock Umbilical 39 Umbilical Mechanism Assemblies 31 40 Umbilicals 20 41 Unpressurized Cargo Carrier Attachment Z1-to-S0 Node 1 U.S. Lab Node 2 42 Wireless Video System Antenna 2003–06 configuration, looking from aft. S-Band Antenna Umbilical Structural Assembly (SASA) Mounting locations of truss eLeMents view of top/forward/starboard on Node 1 and U.S. Lab, starboard side vieW INTERNATIONAL SPACE STATION GUIDE SYSTEMS HABITATION 50 Habitation Haircut in SM. The habitable elements of the International Space Station are mainly a series of cylindrical modules. Many of the primary accommodations, including the waste management compartment and toilet, the galley, individual crew sleep compartments, and some of the exercise facilities, are in the Service Module (SM). A third sleep compartment is located in the U.S. Lab, and additional exercise equipment is in the U.S. Lab and the Node. Additional habitation capabilities for a crew of six will be provided prior to completion of ISS assembly. Preparing meal in galley. Playing keyboard in U.S. Lab. Shaving in SM. soyuz service module fgb node/airlock u.s. lab U.S./Joint Airlock U.S. Lab Computer U.S. Lab Temporary Workstation Sleep Station (TSS) SM mid compartment and treadmill. SM forward compartment. Stowage container in FGB. Node Passageway Stowed Food Trays in FGB SM Sleep Remote Docking SM Transfer Compartment Control Station Compartment Russian water containers. Microgravity Science Glovebox in U.S. Lab FGB Corridor and Stowage Stowage in Node 1 Toilet in Waste Management Crewmembers Exercise on U.S. Lab Window SM Treadmill Compartment Crewmembers with Orlan Suits in Pirs INTERNATIONAL SPACE STATION GUIDE SYSTEMS 51 CREW HEALTH CARE SYSTEM Crew Health Care System (CHeCS)/ Integrated Medical System The Crew Health Care System (CHeCS)/Integrated Medical System is a suite of hardware on the ISS that provides the medical and environmental capabilities necessary to ensure the health and safety of crewmembers during long-duration missions. CHeCS is divided into three subsystems: Leroy Chiao uses RED. Crew uses medical restraint and defibrillator. soyuz service module fgb node/airlock u.s. lab Volatile Organics Analyzer (VOA) Blood Sample Reflotron Bonner Ball Neutron Treadmill Vibration CHeCS Rack Particle Detector and Isolation System (TVIS) Water Sampling Phantom Torso for radiation Resistive Exercise and Analysis measurement experiments. Device (RED) Water Samples (taken for ground Saliva Sample Kit analysis of contamination) Countermeasures System (CMS)—The CMS provides the equipment and protocols for the perfor- mance of daily and alternative regimens (e.g., exercise) to mitigate the deconditioning effects of living in a microgravity environment. The CMS also monitors crew- CardioCog From left to right: members during exercise regimens, reduces vibrations Intravehicular Charged Particle Directional during the performance of these regimens, and makes Spectrometer (IV-CPDS) periodic fitness evaluations possible. Microbial Surface Sampling Cycle Ergometer with Vibration (gold box) and Tissue Isolation System (CEVIS) Equivalent Proportional Counter (TEPC) detector environmental Health System (eHS)—The EHS (gold cylinder). monitors the atmosphere for gaseous contaminants (i.e., from nonmetallic materials off-gassing, combustion prod- ucts, and propellants), microbial contaminants (i.e., from crewmembers and Station activities), water quality, acoustics, and radiation levels. Health Maintenance System (HMS)—The HMS provides in-flight life support and resuscitation, medical Potable water Crew Medical Defibrillator. care, and health monitoring capabilities. sampler. Acoustics measurement kit. Atmosphere Grab Restraint System Microbial air sampler. Velo-Ergometer Sampler Container. (CMRS). INTERNATIONAL SPACE STATION GUIDE Temp. & Air ISS SYSTEMS Humidity U.S. Regenerative Environmental Control and Life Support System (eCLSS) CO2 ENVIRONMENTAL CONTROLECLSS 52 Control Air Re turn Oxygen Generation Water Recovery Water Recovery CO 2 1 Catalytic Reactor 12 Reactor Health Sensor System (OGS) Rack System Rack 1 (WRS-1) System Rack 2 (WRS-2) Removal 2 Deionizer Beds 13 Storage Tanks H Waste Cabin Air Cabin Return 2 Trace Mgmt. 3 Digital Controller 14 Urine Processor Contaminant Pumps 2 8 14 3 Control 4 Distillation Assembly 15 Waste Products Air Subassembly 15 Volume reserved for 5 Electrolysis Cell Stack later CO2 Reduction 14 12 C O System 17 Urine 2 6 Gas Separator 6 o 11 Environmental Control and n Urine d Recovery 16 Water Processor e 7 Multifiltration Beds 13 n Oxygen s O /N Delivery Pump a Control2 2 1 te Generation 8 Particulate Filter Life Support System (ECLSS) Processed Urine 17 Water Processor 18 N 2 9 Power Supply 3 Pump & Separator 3 ater ter 10 Product Water Tank t W Potable Wa 18 Water Processor c uct du Water Prod ro Wastewater Tank P Processing 11 Pumps & Valves 4 Earth’s natural life-support system provides the air we breathe, the water we drink, and other 9 5 7 r 16 e =Process Water t a Regenerative environmental = Oxygen 10 conditions that support life. For people to live in space, however, these functions must be w te as =Urine W control life support in the U.S. =Hydrogen performed by artificial means. The ECLSS includes compact and powerful systems that provide segment of the ISS. (vented overboard) =Brine Crew System the crew with a comfortable environment in which to live and work. =Potable Water =Humidity Condensate Potable Water Hand Wash/ System Shaving progress service module fgb node/airlock u.s. lab shuttle CWC Bags (used by astronauts to carry water from the Shuttle to the ISS) Vozdukh (absorbs carbon dioxide from crew) elektron (produces oxygen Lithium Hydroxide (LiOH) Contingency Water Container (CWC) bag. from water through elec- cartridge used for eliminating trolysis; vents hydrogen out CO from air, backup system. Fuel Cells (make 2 Lithium Hydroxide of the Station) Cartridges (absorb electricity and carbon dioxide) water from oxygen Russian eDVs used to store and and hydrogen) CO2 transport water.
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