"6_10_7_4_3.TXT" (46916 bytes) was created on 08-11-89 Enter {V}iew, {X}MODEM, {Y}MODEM, ? for HELP, or {M}enu [V]... JOHNSON SPACE CENTER Traditional Center Roles and Responsibilities The history of the Johnson Space Center began in 1961 when it was announced that the new Manned Spacecraft Center would be established on a 1020-acre tract near Houston, Texas. The land, originally Humble Oil and Refining Company property that had been donated to Rice University, was transferred to the government by the university. Construction of facilities was begun in 1962 and the majority of buildings were completed by 1965. The name of the Center was changed to the Lyndon B. Johnson Space Center in 1974. The Johnson Space Center is located in Harris County, Texas, on a 1620-acre tract near Clear Lake. The site is approximately halfway between Houston and Galveston. JSC participated with other NASA installations in the Mercury, Gemini, and Apollo space programs which culminated in the first manned lunar landing in July 1969. The Skylab space station, controlled from JSC, provided the base for numerous scientific projects including the evaluation of manufacturing methods in space, the study of energy radiation from the Sun, and the study of the capability for space monitoring of the environment and resources on Earth. JSC participated in the joint U.S.-U.S.S.R. (Apollo-Soyuz) space mission in 1975, which has highlighted international cooperation in space to date. With the adoption of a national goal for development of a space transportation system, JSC has played a major role in this area. JSC serves as both the development center for the Space Shuttle and the Operations center for the evolving transportation system. Activities in the development of the Shuttle have included the successful completion of a number of research goals. The development of the power extension package will utilize deployable solar arrays, which are expected to triple the on-orbit stay time and double the available power compared to initial concepts. JSC has also demonstrated the feasibility of a three-man vehicle launched by the Shuttle which can potentially perform a wide variety of construction and service operations that would exploit the capabilities of man in space. Also, an analysis has been made by JSC of deployment, erection, fabrication, and assembly of very large structures in space. Research and development activities at JSC related to manned space flight include the following. 1.-The design, manufacture, testing, qualification, and delivery of systems such as space suits, extravehicular activity systems, crew provisions, and crew support equipment. 2.-The development of instrumentation, data management systems, and ground checkout systems used on manned spacecraft. 3.-The analysis, development, and evaluation of spacecraft structures, materials, and thermal protection systems. In addition to its role in the development of the Space Shuttle, JSC is involved in a wide range of research and technology activities in other areas. In lunar and planetary science, JSC scientists have led in the investigation of the ancient lunar crust. The tie of lunar and planetary studies to Earth has been strengthened. A new model has been developed for the origin of the Earth's continents. The environmental effects of space transportation are also being studied, from the standpoint both of the effects of launch and landing on the Earth environment and of the effects of the space environment on vehicles or structures in space. In the area of life sciences, research is being conducted to understand the effects of weightless spaceflight on the human body and to apply spaceflight-developed procedures and equipment to the solution of problems on Earth. JSC also functions as the lead organization for agricultural remote sensing. Other Earth observation responsibilities of JSC include soil moisture mapping, multicrop research, water mapping, forestry applications, and resources inventory with the State of Texas. JOHNSON SPACE CENTER Space Station Freedom Unique Activities Integrated Truss Assembly The integrated truss assembly provides the framework for the core base of the station. The transverse boom is 155 meters (508 feet) in length. It serves as the attachment point for the solar power arrays, as well as other systems, including experiments. It facilitates the movement of crew and equipment, and provides for distributed systems. Mobile Transporter The mobile transporter will enable the Canadian supplied Mobile Servicing Centre (MSC) to move along the truss. It provides the translation, rotation, and plane change mobility required by the MSC to support transportation, assembly, and payload operations. Resource Nodes - Design and Outfitting The four resource nodes, located at each end of the Habitation and U.S. Laboratory Modules, are small pressurized cylinders approximately 17 feet long and 14 feet in diameter. They are designed and outfitted to serve as command and control centers and as passage-ways to and from the various modules. A cupola will be attached to each of two nodes. Airlocks There are two types of airlocks planned for Space Station Freedom. There will be two standard airlocks and one hyperbaric airlock. The airlocks attached to a node, enable the transfer of crew and equipment between pressurized and unpressurized zones. The hyperbaric airlock has the capability for the treatment of decompression sickness. Distributed Systems There are a variety of systems which are fundamental to the operation of the space station in a safe and effective manner. They are the propulsion, data management, communications and tracking, guidance, navigation and control, thermal control, fluid management, mechanical, and electrical power systems. Man Systems Man Systems provide the crew with a safe environment and the necessities of life. Man Systems includes the health care system, hygiene system, crew quarters, galley, wardroom, food management, lighting, work-stations, EVA system, flight crew integration and training, restraints and mobility aids, housekeeping/trash management, portable emergency provisions, operational and personal equipment, and stowage. JOHNSON SPACE CENTER Elements and Systems Integrated Truss Assembly The truss assembly will give structural stiffness and dimensional stability to the entire space station. It also will provide the structure for integration and installation of all the elements and systems, including the modules, that make up the space station's manned base, or core. The integrated truss assembly for Space Station Freedom is the structural framework of tubular beams and columns which stiffen and stabilize the core base of the station. It has provisions for mounting and attaching modules, logistics carriers, external experiments, solar power arrays, and both Earth and astronomical viewing instruments. The truss also provides corridors and distributed systems for crew and equipment movement, and external lighting. The transverse boom, including solar arrays at each end, measures 155 meters (508 feet). The center section of 360 feet consists of a sequence of 5-meter (16.4 ft) cubic bays to secure the station elements and systems. It is erected in space, composed of longerons, battens and diagonal struts to form a latticework for structural stiffness and stability. Because of extreme temperatures as the station goes from the heat of the sun to the cold of the umbra, the tubular members are built of a composite material which reacts differently to heat and cold. A candidate material is an aluminum clad graphite epoxy which is light-weight and relatively stronger and stiffer than metal. Engineers at JSC weave graphite fibers through a convergence plate and into an aluminum tube. A second, smaller tube holds the strands together until resin can be injected around the fibers to form a structural member, ready for covering, corner fitting, launch, and assembly. Mobile Transporter System The primary function of the Mobile Transporter (MT) is to provide the Canadian-supplied Mobile Servicing Center (MSC) with mobility. It also provides the capability for movement of supplies, materials, and personnel independent of the MSC. The Mobile Transporter combined with the MSC comprises the Mobile Servicing System (MSS). The MT will will ride along rails mounted on truss providing mobility for the MSC. The MT will generate its own utilities and data, or will throughput station-distributed utilities and data. The base of the MT will measure approximately 4.9 x 6.1 meters (16 x 20 feet). The height has not yet been determined. The MSC will consist of a base structure mounted on the MT, a Remote Manipulator System (RMS), similar to the one on the orbiter, an Astronaut Positioning System, and a Special Purpose Dextrous Manipulator (SPDM) that acts as the "hands" of the system. The Astronaut Positioning System will be similar to the RMS, except that it will have additional restraints designed to interface with a suited astronaut. The SPDM will be designed to changeout space station orbital replacement units and attached payloads. Mechanical System The mechanical system consists of the solar alpha rotary joint, the thermal radiator rotary joint, umbilical mechanisms, and special end-effectors. The solar alpha rotary joint supports the outboard transverse booms and provides controlled rotation to point the power generation equipment towards the sun, while transferring power and data across this rotating interface. The thermal radiator rotary joint supports the control radiator panels and provides controlled rotation for aligning the panel edges to the sun. It transfers liquid/gaseous ammonia between the station and the panels. The umbilical mechanisms facilitate utility transfer between the station and the unpressurized logistics carrier, the mobile transporter, and the platform. Special end-effectors are provided for construction, assembly, maintenance, and repair. They are compatible with the other station manipulator systems. JOHNSON SPACE CENTER Elements and Systems Resource Node Design and Outfitting The JSC is responsible for the design and out-fitting of the resource nodes. The four resource nodes, located at each end of the Habitation and U.S. Laboratory modules, are designed to reduce the amount of EVA time required to assemble the station. The nodes are small, pressurized cylinders,approximately 14 feet in diameter and 17 feet long, that serve as command and control centers, and as pressurized passageways to and from the various modules. They, like the modules, have a primary and a secondary structure and contain accommodations for distributed systems. Certain nodes also contain berthing mechanisms for the temporary attachment of either the space shuttle or the logistics modules. Node 1 serves as a control center for the Communication and Tracking System, Data Management System, Guidance, Navigation and Control System, Propulsion System, Electrical Power System, Thermal Radiator Rotation, and the hyperbaric airlock. It is located between the Columbus (ESA) and U.S. Laboratory modules and attaches to the hyperbaric airlock and Node 2. Node 2 provides redundant control for the Propulsion System, Electrical Power System, Thermal Radiator Rotation, and the Communication and Tracking System. It also serves as the airlock control station. It is located between the JEM and the Habitation module. Node 3 is the primary command and control station for the pressurized areas of the station. It is located at the forward end of the U.S. Laboratory Module. It provides: the accommodation for a cupola interface and for a secondary docking port interface; a backup command and control station for the Mobile Servicing Centre and the Flight Telerobotic Servicer; backup guidance and navigation control; a secondary proximity operation for pressurized attached payload equipment. Node 4 is attached to the forward end of the Habitation module and is connected to Node 3. It serves as the primary docking port for the space shuttle, the primary control center for proximity operations, and the primary command and control center for the Mobile Servicing Center and the Flight Telerobotic Servicer. It also provides accommodations for interfacing with the cupola. Nodes 3 and Node 4 will be scarred for future growth. That is, both will contain the necessary hardware provisions to enhance the nodes as the station evolves. Cupolas There are two cupolas. One will be attached to resource Node 3 and the other to Node 4. One will face towards the earth while the other will face towards space. They facilitate the control of proximity operations and can be used simultaneously by two crew members with a work station available for each. From the cupola, they have a 360o field of view in azimuth and a complete hemispheric field of view in elevation. A restraint system enables the crew members to easily rotate for viewing through any of the 8 windows. The workstations can also be rotated to move to an optimum position for use by a crewmember. The workstations have a keyboard, two hand controllers, and a trackball. The following systems can be controlled by a crewmember in the cupola: the station manipulators (except the JEM manipulator), the mobile transporter, the telerobotic servicer, OMV piloting, external video cameras and lights and internal video monitors, international and external voice communications, and systems control functions via access to the DMS. When not in use the cupolas will be within a retractable, protective cover. Airlocks There are two types of airlocks: the hyperbaric airlock, and the airlock. The hyperbaric air-lock provides an effective and safe means for the transfer of crew and equipment between pressurized and unpressurized zones and provides a capability for the treatment of decompression sickness. The airlock is a separate element attached to a node by berthing/ docking mechanisms. The airlock serves the same function with the exception of the capability to treat decompression sickness. JOHNSON SPACE CENTER Elements and Systems Utility Distribution System In order to minimize EVA installation time, the number of joints, and fluid connector leakage potential, a unique concept of a rollout utility tray has been proposed. A 10-foot inside diameter (14.5-foot outside diameter) aluminum frame spool will provide a large bend radius. This will allow tray preintegration of long runs of stiff, yet lightweight, power cables and multi-insulation wrapped heat rejection and transport lines. During assembly, EVA crew members snap the trays into support fittings prebonded every 16.4 feet to the batten struts and make connections at distribution points. Aluminum covers provide protection from ultraviolet radiation, atomic oxygen, and meteroid-debris impact. Fluid Management System (FMS) The FMS handles the distribution of nitrogen, water, and waste fluids throughout the station. The integrated nitrogen system (INS) includes all of the hardware and software required to resupply, transfer, store, condition, distribute, control and monitor nitrogen for the station. The nitrogen logistics resupply subsystem includes the tankage, mounting hardware, condition, thermal control, transfer, monitoring and control hardware necessary to deliver the fluid to the station. It is located on the truss, as well as the tankage and associated equipment to store the nitrogen. The nitrogen distribution subsystem which transfers nitrogen from the resupply subsystem to the storage tanks and from the storage tanks to the user interface, is also located on the truss. The nitrogren distribution subsystem consists of two parts: --One part transfers nitrogen to the ECLSS and the integrated waste fluid system, and interfaces with the internal distribution systems located in Nodes 1 and 2, and --The other part transfers nitrogen to the integrated water system (IWS) and the laboratories. The integrated water system (IWS) is conceptually similar to the integrated nitrogen system. The storage system, located in the nodes, accepts water from the Space Shuttle orbiter's cargo bay, from the NSTS water scavenging system, and from the ECLSS. The integrated water fluid system (IWFS) consists of a collection/distribution subsystem, and a storage subsystem. These subsystems will contain all hardware and software required to provide fluid transfer, storage, conditioning, disposal, control, and monitoring to accommodate gas mixtures and water. The collection/distribution subsystem receives fluid discarded by the users and transfers them to the storage subsystem. Thermal Control System (TCS) The TCS is an integrated system which will maintain structures, systems, subsystems, equipment, and payloads within required temperature ranges. Twenty-five heat acquisition devices (HADs) will be used initially to collect waste heat from Habitation and Laboratory modules, resource nodes, and payload accommodation equipment. The heat will be transported by means of an ammonia/water loop from the HADs to a radiator located on the transverse boom. The radiator will be a 15.2m (50 ft) square which will be mounted on a rotary joint which permits the radiator to be turned away from the radiant heat of the Sun. The external thermal system provides cooling and heat rejection to control temperatures of electronics and other space station hardware located outside the modules and node. For truss attached payloads, thermal acquisition is provided at the payload attachment interface. Separate Attached Payload Accommodation Equipment (APAE) thermal loops transport waste heat to the central thermal bus heat exchangers. The APAE loop design is based upon a two-phase ammonia system. For pressurized payloads attached directly to nodes, thermal acquisition is through central thermal bus interface heat exchangers attached externally to the payload. JOHNSON SPACE CENTER Elements and Systems Propulsion Assembly The function of the propulsion assembly is to maintain the proper altitude, avoid collisions, and to provide backup attitude control. The propulsion assembly will provide thrust for orbital maintenance and 3-axis thrust for attitude stabilization and reorientation. Three-axis thrust will be used to desaturate the Control Momentum Gyroscopes, which are the primary attitude actuators of the Stabilization and Control System. The propulsion system consists of four propulsion modules, a tank farm, and a fuel distribution system. Each module contains fuel tanks, plumbing and valving, a fuel pump, and two types of jet actuators (hot gas and resistojets). The resistojets, used for vernier control, are fueled by waste fluids and produce a pound of thrust. The hot gas actuators are fueled by a hydrogen-oxygen mixture and produce 25 to 40 pounds of thrust. Communication and Tracking (C&T) This system provides for the transmission, reception, multiplexing, distribution and signal processing of telemetry, commands, user data, science data, computer data, and tracking data. C&T also provides for the raising, lowering and pointing of antennae on the station. C&T is comprised of six subsystems: --1) space to space, --2) space to ground, --3) audio, --4) video, --5) tracking, and --6) control and monitoring. The space-to-space subsystem provides communications with: astronauts performing EVA, the Space Shuttle, the Orbiting Maneuvering Vehicle, the Mobile Servicing Center, the Flight Telerobotic Servicer, and any compatible free-flying platforms in the vicinity of the manned base. Simultaneous communication can be carried out with up to four vehicles. The space-to-ground subsystem provides near continuous communications between the station and ground data networks through the TDRSS. The audio subsystem provides all of the voice communications on the space station. It is similar to a standard telephone system and permits voice communication between the crew inside the pressurized modules, the EVA crew, the crew of other manned vehicles, and compatible ground systems. The video subsystem provides all of the internal and external video capabilities on the space station by means of remotely controlled cameras. It includes closed circuit TV, storage, retrieval, compression, graphics, and special effects capabilities. The tracking subsystem consists of a Global Positioning System (GPS) receiver/ processor with provisions to accommodate future laser docking and radar requirements. The control and monitoring subsystem manages all C&T resources and distributes the C&T data. Guidance, Navigation & Control (GN&C) The GN&C performs two main functions: to control the manned base orbit and to control traffic around the space station. Periodically, the manned base portion of Space Station Freedom will decay in orbit. The GN &C, operated by sensors, star trackers and gyroscopes, will signal the propulsion assembly for a reboost for proper altitude and attitude. This system also supports the pivoting of the solar arrays and thermal radiator on the transverse boom to maximize the capture of the solar rays. Traffic management around the station is also critical. The GN&C controls all incoming, out-going and station keeping traffic; it also controls berthing and docking operations for the Space Shuttle. Finally, the GN&C monitors the trajectories of vehicles and objects that may intersect the orbit of the manned base and platforms. Such objects include meteoroids, some the size of a car, which are extremely rare in space. The more common micrometeoroids, ranging in size from a grain of sand to a marble and traveling at thousands of miles per hour, are too small to be tracked on radar. JOHNSON SPACE CENTER Elements and Systems Data Management System (DMS) The DMS is an onboard computer system with two main functions. First, the DMS includes all the hardware and software necessary for data processing and local communications among the onboard elements, systems and pay-loads. Secondly, the DMS provides an interface between human and machine for the operation and control of Space Station Freedom. The DMS provides database access, command and control, data transmission, data processing and handling, and human computer interfaces for the users and subsystems as well as interface for the onboard information systems of the international elements. It enables users and subsystems to initiate on-line capabilities such as command generation, data handling, graphics, health monitoring, planning, scheduling and training activities, display of performance and trend data, and monitoring of properly interfaced payloads. The Data Management System provides a family of compatible computers ranging from a single board computer suitable for use as an embedded controller, to a general purpose processor suitable for hosting system application software. Each processor has a compatible set, or subset, of the DMS operating systems tailored to its specific application. The DMS also includes a common assembly called the Multipurpose Application Console (MPAC). The MPAC is the electronic core of the space station workstations. It provides access into operational monitoring, training, testing, cautions and warning display, and crew operations. Some of the MPACs are fixed in place, while others are portable. The information and data management services provided will include data storage processing and handling presentation, and on-board networking services adequate to accommodate most user requirements. The Data Management System interfaces will be capable of supporting both Operations/ Administrative (O/A) traffic and payload traffic on a near continuous basis. O/A traffic can take priority over payload traffic in the event of emergencies or link failure which restricts link performance. Specifically, the Data Management System will exhibit the following features: 1)--Support the control of all onboard subsystems such as electrical power, thermal control, data management, communications, attitude control and orbit altitude maintenance of the station and platforms. 2)--Support normal, systems-management functions that ensure the station and platform systems continue to operate normally in a desired configuration. This function will be accessible by a ground controller or onboard crew members. 3)--Provide for onboard distribution of data between subsystems, payloads, and payload support equipment over DMS networks. 4)--Support real-time command and control. Commanding can be initiated by the system the crew, ground operations, or other payloads. 5)--Support the provision of orbit-position data of a selected reference point, attitude data, and navigation information. 6)--Provide the capability and warning and advisory information necessary to safely override, or inhibit manually, any automated functions. The DMS will provide a self-monitoring capability that will reduce recurring operations cost, reduce the crew and ground time devoted to configuration management, allow crew and ground controllers to quickly determine the health and status of all systems, and automatically give appropriate notification when checks should be made. There will be three primary configuration management functions: (1) hardware configuration management of space station elements, (2) software configuration management of station space elements, and (3) both system and customer data configuration management in the Data Management System. JOHNSON SPACE CENTER Elements and Systems Man Systems Johnson Space Center is responsible for managing the design, development, test and engineering of manned systems for the Habitation, U.S. Laboratory and Logistics modules. The manned systems include crew quarters restraints and mobility aids, health care, operational and personal equipment, portable emergency provisions, workstations, galley food management, personal hygiene, lighting, wardroom, stowage, and house-keeping/trash management. The Man Systems utilize a group of modular elements or "Functional Units" which enable partial or entire systems to be removed, replaced, and relocated as desired and at the time desired. The Habitation Module provides the living environment for eight crewmembers. Specifically it contains the crew quarters, galley, wardroom, general workstation, personal hygiene facility, crew emergency healthcare system, exercisers, and stowage. The crew quarters, perceived as a low activity area, are grouped at one end to minimize traffic and equipment operation disturbances while the crew members are resting. In addition, stowage racks are located between crew quarters and adjacent facilities to act as activity buffers and aid in sound absorption. The galley/wardroom is located at the opposite end of the module because of the high level of activity associated with meal preparations, consumption, and clean up. The personal hygiene facilities are located centrally to minimize the overlap of crew activities between the galley/ wardroom and crew quarter area. The layout of the module is designed to provide the most habitable and productive environment possible given the restricted available volume. The space station will provide private quarters for each of the eight crew members. Each crew quarter will serve as a bedroom, den, and living room, albeit on a smaller scale. At least 50 cubic feet will be provided within each compartment for sleeping. The crew quarter will provide stowage space for clothing and personal effects, a sleep restraint, a portable work-station linked to the space station data management system, audio/visual recording and playback equipment, and a communications panel. The interior decor of each crew quarter is made up of acoustical fabric panels, which are modular and easily removed. This allows crew members to personalize their quarters with colors and textures of their choice. Food preparation and stowage on the space station will be handled in the galley, or kitchen, located across from the wardroom area. Here the crew will be able to cook and dispense their daily meals using the galley's microwave and convection ovens, liquid/beverage dispensers and deployable preparation counters. After the crew is finished eating, the galley will also handle the clean-up with its trash collection/compaction unit, dishwasher, and handwasher. The galley provides bulk stowage for a 14-day supply of ambient, cold and frozen food stock. To make more efficient use of crew time, an integrated menu selection and inventory management system keeps track of the food used from the stock and tells the crew when it's time to resupply. The space station crew will need a place to eat their meals, have meetings and just relax. For these reasons a wardroom area has been set across from the galley. The wardroom will provide seating for up to eight crew members and support everything from meals to teleconferencing. The current concept features an integrated wardroom table and entertainment unit. The center bay is occupied by a single rack from which six of the eight worksurfaces are cantillevered. The remaining two worksurfaces are separate independent units that can be positioned anywhere in the Habitation Module via their compression posts. The rack also holds the monitor, playback equipment and 25 cubic feet of stowage. The entire wardroom can collapse into one rack space and then deploy to fit two to eight crew members. With extra independent worksurfaces, the wardroom area can accommodate up to 12 people. The integrated workstation system incorporates all on-board computer-based work-stations. It has operating displays and controls, and will interface with the Data Management System. The detailed workstation system design is presently under study. The crew hygiene system being proposed for the Space Station Freedom is composed of the entire body shower subsystem, the waste management subsystem and a partial body hygiene/grooming compartment. The mechanical, electrical, and human engineering aspects of the design of these subsystems must incorporate state-of-the-art technology. A research laboratory has been established at JSC to support all the development efforts and tests necessary for providing a personal hygiene system. The Space Station Crew Health Care System is an in-flight medical subsystem designed to maintain the health of the crew and provide treatment for illnesses and traumas that may be encountered during a mission. The subsystem is also responsible for monitoring the station's environment and assessing its impact on the crew's health. The Crew Health Care System is located in the Habitation Module and includes exercise equipment for crew conditioning, an analytical and microbiology lab, a restraint system for patient examination and treatment, a hyperbaric chamber, and a medical database. The purpose of the Health Care System is to ensure the safety of the crew and the mission by dealing with minor accidents or illnesses immediately, and thereby eliminating the necessity of early mission termination or emergency rescue. If a major emergency does arise, the Health Care System can provide a margin of safety by stabilizing injured or sick crew before transfer to Earth. The system also plays a major role in the prevention of accidents and illnesses by maintaining and monitoring the health of the crew and their environment. A computerized system will be used to keep track of crew condition, schedule , and track medical supplies. The system will also be linked to centers on the ground to increase the power and flexibility of the medical team. Photography and imagery systems will again be an integral part of the space station program. Photographic systems provide film imagery from modified, off-the-shelf hardware. They will consist of still photography cameras in the 35mm, 70mm, and 5-inch film format sizes and motion picture photography in the 16mm format size. The 35mm still and 16mm motion picture cameras will be used primarily for interior photography. All the systems will have typical characteristics and features of commercially available hardware. In addition to the film imagery, an electronic still camera system will be provided to support the necessity to return near photographic, high resolution quality data to the ground in a timely manner. The system will take the form of a hand-held camera in which the images are recorded electronically on memory media and then down-linked through a playback/ interface unit to the ground. Attachment Systems Devices are needed for Space Shuttle docking at the manned base. Johnson Space Center is responsible for these attachment systems, plus those needed for logistics supply modules. Devices to attach experiment packages and external hardware to the truss structure are also handled by JSC. EVA System The EVA system enables crew members to assemble, maintain, repair, inspect, and service the station and user systems. Until the Mobile Transporter is in place, assembly of the transverse boom is accomplished by extra-vehicular activity (EVA). The Johnson Space Center is responsible for EVA systems, including the extravehicular mobility unit (EMU), better known as the spacesuit, associated life support equipment, and support equipment. Inherent in the spacesuit are communication systems, a physiological monitoring system, and an autonomous life support system. The EVA system also includes mobility aides such as handrails, slide mechanisms, tethers, lighting, tools, and other support equipment. Flight Crew Integration JSC is responsible for providing the flight crew requirements across all space station systems and elements, as well as the standardization definition of crew interfaces for all systems and elements. The flight crew's training includes: space station distributed systems, such as power and life support, on-orbit operations, man systems; mobile servicing systems, on-orbit maintenance, ESA/JEM module systems, and EVA operations. Initially a classroom environment serves as the training forum, including workbooks, personal computers, and a computer assisted instructional trainer. Visits to factories, other NASA centers, and countries of participating partners for additional training, follow. The final aspect of the training program includes interfacing with both the Payload Operations Integration Center (POIC) and the Engineering Support Center (ESC). As an illustration of how these various training programs and facilities will interact to support station operations, consider the following hypothetical scenario: Career U.S. astronauts (station operators and scientists) who have been assigned to the manned base will commence with a series of training classes aimed at providing them with the proficiency necessary to operate the distributed systems on the station. This process will take about six months, conducted on a part-time basis, and will commence 24 months prior to launch. This training will occur at the SSTF or at other facilities at Johnson Space Center. Once a crew is assigned to a flight increment, they will begin a training regimen which will last approximately 18 months (i.e., will begin 18 months prior to launch). Payload Scientists will be added at this point to make up the complete increment crew complement. The first six months of increment-specific training will be accomplished as a team at the various user facilities associated with the team's projected flight increments. (Each team will be on-orbit for the duration of two increments.) Each individual payload investigator will be responsible for the training which the crew will receive while at a specific location. Scheduling coordination for the crew while taking part in this training will be the responsibility of the SSTCB located at JSC. The following six months of training will generally be based at the POIC or the Payload Training Facility (PTF) where the crew can work with the investigator's personnel and with PTF training people versed in the pay-load problems which have occurred on previous flight increments. At this point the crew will spend increasing time on individual experiments (including brief return trips to the laboratories). More and more time will be spent operating groups of experiments, which could be discipline groupings, or other sets of payloads which have some functional affinity. Increasingly, the crew will operate in concert with the personnel who will be in the POIC and the relevant DOC/ROCs during their flight increments. About six months before their flight, the crew begins to train in earnest in the PTF with a selected complement of experiments. These sessions are conducted on an integrated basis with the POIC and the applicable ROC/DOCs whenever possible. During this time the station operators and station scientists work on the skills they will require for EVAs planned during their increments, and will maintain their proficiency with MSCS and other manned base systems tasks they will have onboard. Three months before flight, the crew moves to JSC where their training continues in the SSTF and other JSC facilities. The concentration now is on ensuring that the crew comes together as a team, and that an affinity is also developing between the crew and the support personnel who will be on the ground during the first few weeks of their flight increment. It is at this point that the non-NASA crew-members will receive the habitability training they require. During this period, all of the crew will work to maintain the systems skills they will need. Beginning approximately ten weeks before launch, a small number of integrated simulations will be scheduled with a portion of SSSC personnel, along with personnel from the POIC and the users' ROC /DOCs. These simulations will be designed to ensure that the team building process has occurred properly and that the training for the increment about to launch is properly completed. Finally, after launch, "on-the-job" training and proficiency maintenance will occur throughout the duration of both increments. JOHNSON SPACE CENTER Elements and Systems Operational Activities A typical day's activity for the manned base will be analogous to the operation of a multi functional research and development complex on Earth. The major difference, of course, will be its location (in space and physically separated from its support facilities), including the unique requirements it places on those who maintain and use it. Typical operations activities for the manned base and unmanned platforms include: operations and utilization planning (determining who uses which resources and for what purposes, and planning for long term systems evolution); logistics operations support (the prelaunch activities associated with preparing the crew, consumables, and user instruments for launch to either the manned base or a platform, plus postlanding activities upon return); space operations (activities which transpire in orbit); and space operations support (ground-based activities which support or control manned base and platform on-orbit operations). During real-time operations, the Space Station Control Center (SSCC) (led by its Flight Director) is charged with maintaining manned base systems in working order and providing for the general health and welfare of the crew. SSCC responsibilities will include: space systems performance monitoring, resource availability assessments and projections, oversight of and support for increment changes, systems and user operations replanning, systems maintenance, housekeeping templates, crew safety assurance, extravehicular activity (EVA) scheduling and support, trajectory and altitude maintenance, and command and control zone operations support (in conjunction with the STS Mission Control Center). In the interests of system safety and clear communications paths to the station crew, the SSCC will perform overall management and control of the air-to-ground data and voice links, and will be responsible for coordination of space station systems flight data file uplinks to the crew (including checklists and crew timelines). The Payload Operations and Integration Center at MSFC (POIC) will be responsible for coordinating specific user operations of the data and voice links for payload operations, consistent with SSCC operations guidelines and constraints. The SSCC is also responsible for integration of all systems upgrade and sustaining engineering operations support provided by the various Engineering Support Centers (both domestic and partner-supplied). The SSCC will provide active support to the crew for at least one shift per day, with a minimum level of support consistent with safety requirements of the remainder of the time. Extensive use of automated monitoring capabilities will help to keep personnel requirements to a minimum. Other systems inputs are provided to the SSCC for logistics support requirements, and by the Platform Control Center (PCC) for any transfer operations scheduling requirements for servicing of the Co-Orbiting Platform (COP). These inputs are integrated into the real-time replanning effort, along with the user resource templates provided by the POIC to maximize systems performance, crew effectiveness, and user operations returns. JSC will provide an ongoing engineering support capability for sustaining the performance of systems acquired during the designing and fabrication program phases. This will include the provision of personnel and technical analysis capabilities to support routine space systems sustaining engineering activities, as well as "on call" support to the station execute teams for analysis of unanticipated situations onboard station elements. Space systems sustaining engineering includes systems maintenance engineering (engineering required to keep baselined space systems operating at peak performance); systems design engineering (engineering analyses performed in support of design modifications); and payload integration engineering (engineering in support of user payload operations and integration). JOHNSON SPACE CENTER Facilities Space Station Control Center (SSCC) The SSCC will provide for continuous real-time Space Station Freedom control and support, Manned Base Systems Integration/Support, Flight Activities Integration/Support, Flight Crew and Ground Support Personnel Integrated Training, Operations Planning and Preparation Support, Ground Applications Software Development and Operations Concept and Procedures Verification. A five story addition will be constructed at the southwest corner of the existing Mission Control Center (MCC). The addition will consist of approximately 106,000 square feet of floor for space station operations support and data processing/storage. The SSCC and MCC will share common skills, personnel, equipment, communications, and data. The facility will be fully operational approximately one year prior to launch of the first element, in order to conduct simulations. Space Systems Automated Integration and Assembly Facility (SSAIAF) The SSAIAF will provide an area for high fidelity dynamics simulation testing of manual and automated construction techniques and hardware, component attachment methods, and verification/inspection techniques for on-orbit space station structural assembly tasks and similar applications. It will provide required space for a large stationary simulator. A three story laboratory is required for a technician work and staging area. A 47,000 square foot addition will be constructed at the east end of the Systems Integration and Mockup Laboratory of Building 9. The addition consists of a 21,000 square foot high bay area and a 26,000 square foot, three story, laboratory support area. Space Station Training Facility (SSTF) This planned facility supports Ground Training Applications Software Development; Manned Base Training for Crew and Ground Support Personnel; Integrated Operations Training for Systems and Payloads; Flight and Ground Procedures Verification; Flight Software Verification; and Space Station Information System Network simulation. A three story addition will be constructed on the south side of the existing south wing high bay of building 5. The addition will include approximately 23,200 square feet of floor space. A variety of trainers needed for the unique Space Station systems will be housed in the facility. Neutral Buoyancy Laboratory (NBL) The NBL will be a large neutral buoyancy simulation facility which will provide the mandatory capability to support EVA activities associated with the large-scale on-orbit construction, verification, crew training, and mission operations. Products are Engineering Evaluations, Procedures Verifications, EVA Training, and Real Time Mission Support. The NBL building houses a pool which is 225 feet long, 125 feet wide, and 60 feet deep. The pool holds 12.6 million gallons of water. Two separate pressure suit exercises can be conducted simultaneously. JOHNSON SPACE CENTER Space Station Freedom Projects Office The Johnson Space Center is responsible for the design, development, verification, assembly and delivery of the Work Package 2 flight elements and systems. This includes the integrated truss assembly, propulsion assembly, mobile transporter, resource node design and outfitting, external thermal control, data management, operations management, communications and tracking, extravehicular systems, guidance, navigation and control systems, and the airlocks. JSC is also responsible for the attachment systems, the STS for its periodic visits, the flight crews, crew training and crew emergency return definition, and for operational capability development associated with operations planning. JSC will provide technical direction to the the Work Package 1 contractor for the design and development of all manned space subsystems. Johnson Space Center has established the Level III Space Station Freedom Projects office to manage and direct the various design, development, assembly, and training activities. This organization reports to the Space Station Freedom Program Office in Reston, Virginia. The Space Station Freedom Projects Office will develop a capability to conduct all career flight crew training. Experience has shown that integrated training, involving the flight crew and ground controllers using combined system and experiment trainers, is essential to mission success. The integrated training architecture will include the Space Station Control Center, and ultimately the Payload Operations and Integration Center when the station becomes permanently manned.