Space & Astronomy/Space and Astronomy (October 1993).iso/mac/TEXT/STATION/STFMEDEA.CN2

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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.