Mission Objectives

Overview The primary objective of STS-98, International Space Station Assembly Mission 5A, is to deliver and install the U.S. Destiny Laboratory onto the ISS. The centerpiece of research on this world-class scientific orbiting outpost, this workshop in space will support experiments and studies in cancer, diabetes and materials, just to name a few. The aluminum U.S. laboratory module is 28 feet long and 14 feet wide. It is comprised of three cylindrical sections and two endcones that contain the hatch openings through which astronauts will enter and exit the module. Destiny will be mated to the forward port of Unity. In Destiny are five systems racks that will provide life-sustaining functions on board including electrical power, cooling water, air revitalization, and temperature and humidity control. Each rack weighs about 1,200 pounds. Six additional racks will be flown to Destiny on STS-102. Four standoffs provide raceways for module utilities—interfaces for ducting, piping, and wiring to be run to/from the individual racks and throughout the Lab. Twelve racks that will provide platforms for a variety of scientific experiments will follow on subsequent missions. In total, Destiny will hold 23 racks – six each on the port and starboard sides and overhead, and five on the deck. Astronauts will work inside the pressurized facility to conduct research in numerous scientific fields. Scientists throughout the world will use the results to enhance their studies in medicine, engineering, biotechnology, physics, materials science, and Earth science. The Boeing Co. began construction of the 16-ton, state-of-the art research laboratory in 1995 at the Marshall Space Flight Center in Huntsville, Ala. Destiny was shipped to the Kennedy Space Center in Florida in 1998 and was turned over to NASA for pre-launch preparations in August 2000. Destiny’s Laboratory Structure Internal to the laboratory are racks, rack standoffs, and vestibule jumpers. The lab racks house the system hardware in removable modular units. The rack standoffs provide a volume for ducting, piping and wiring to be run to/from the individual racks and throughout the Lab. The racks interface to the piping and wiring in the standoff via outlets and ports located in the standoffs at the base end of each rack location. Jumpers in the vestibule, the area between Unity and Destiny, connect the piping and wiring between the two. Grounding straps between Unity and Destiny will be installed. One side of the grounding strap will be connected to the Active Common Berthing Mechanism (ACBM) on Unity, while the other end will be connected to the Passive Common Berthing Mechanism (PCBM) on Destiny. Some of the mechanisms on Destiny are the CBMs (passive and active), hatches, and the laboratory window shutter. The ACBM is in the forward port of the laboratory. It will be attached to the PCBM in Pressurized Mating Adapter 2 (PMA 2) when the PMA is berthed to the forward port of Destiny at the conclusion of the mission. Destiny’s ACBM cannot be operated until the laboratory is activated. The PCBM on Destiny is located in the laboratory’s aft port. The ACBM in Unity’s forward port will be latched to the laboratory’s PCBM to berth Destiny to Unity. Each of the two berthing ports on Destiny contains a hatch. The aft hatch (hatch to Unity) will be opened and will remain open (unless a situation arises requiring a module to be isolated). The forward hatch will be used as the main access to the orbiter on future missions until Node 2 arrives. Each hatch has a window. The hatches can be opened or closed from either side. The hatches have a pressure interlock feature, which prevents the hatch from being opened if there is a negative pressure across the hatch (higher pressure on the outside of the hatch). Destiny has an optical quality window (principally for Earth science observations) and a window shutter to protect the window from potential micrometeoroid and orbital debris strikes during the life of the ISS. The crew manually opens the shutter to use the window. The shutter will be installed during the third scheduled space walk. Installation and Activation Mission Specialist Marsha Ivins will use the shuttle’s robotic arm to attach Destiny to the forward port of Unity. Over the course of three scheduled space walks, Mission Specialists Tom Jones and Bob Curbeam will perform external outfitting and connect umbilical cables to provide power and data capability between Destiny and the space station. Following Destiny’s installation to Unity, Ivins will once again use the robot arm to relocate Pressurized Mating Adapter 2 (PMA-2), which was moved to a temporary location to allow the installation of Destiny. She then will remove PMA-2 from its temporary location on the Z1 Truss and attach it to Destiny’s forward Common Berthing Mechanism (CBM). At that point, Commander Ken Cockrell will issue a series of computer commands from the aft flight deck of Atlantis to command the final latching and berthing operations. Lab installation activities will begin on Flight Day 4 with the first space walk. Key activities include connecting all of the critical power and fluid umbilicals between the Z1 Truss and the lab. The ISS crew will complete Unity-to-Destiny vestibule outfitting toward the end of the space walk. Together these connections will permit the lab activation upon completion of the space walk. The activation sequence of events is as follows: Lab Activation Sequence of Events Step Rationale Executed by 1 Activates the converters in the Lab DDCUs to provide secondary power to the Lab systems Orb crew 2-3 Once the DDCUs are on, there is no need to have the Node 1 MDMs be the bus controllers on the CB GNC-1 and CB GNC-2.  The Config 9 command is sent to each of the Node 1 MDMs so that once power is applied to the C&C MDM, it will not see any BCs on the GNC buses, and it will automatically transition to Primary. Orb crew 4-5 The configuration command sent to the Primary Node 1 MDM will likely cause a loss of connection with the EPCS as well as the OIU.  These interfaces are reestablished so the procedure can continue. Orb crew 6 The RPCs are closed that provide power to the C&C1 MDM.  It should initialize and transition to Primary in approximately 4 minutes. Orb crew 7-8 The status of the C&C1 MDM is checked to verify that it is nominal.  The ISS crew will have direct connectivity through a PCS machine once the C&C1 MDM transitions to Primary, providing extra insight to the orbiter crew. Orb/ISS crew 9 The ISS crew can then perform the procedures to reestablish LDR S-band which was lost during the vestibule connections made on FD-5. ISS crew 10 The N1-1 MDM is commanded to be an RT on the LB SYS-LAB 1 bus since it no longer needs to be BC, and the INT MDM will be expecting to find no BC on that bus when it is powered up. Orb crew 11 The INT2 MDM is powered up by closing the appropriate RPCs that allow power to the MDM.  The N1-2 MDM must become an RT on the LB SYS-LAB 2 bus within 2 minutes of powering on the INT2 MDM so that the INT2 MDM will transition to the Operational mode. Orb crew 12-13 The configuration command sent to the Primary Node 1 MDM will likely cause a loss of connection with the EPCS as well as the OIU.  These interfaces are reestablished so the procedure can continue. Orb crew 14 The status of the INT2 MDM is checked after the approximate 4-minute initialization time.Once again, the ISS crewmember through the PCS machine has a little more insight into the status of the MDM than the orbiter crew. Orb/ISS crew 15 The Node 1 MDMs should already be synced to the broadcast time coming from the C&C1 MDM. Orb crew 16 The pass-thru interface is commanded that will allow the C&C1 MDM to be the recipient of all commands from the orbiter AFD PCS, and will also flow telemetry from the C&C1 MDM to the OIU and AFD PCS through the Node 1 MDMs. Orb crew 17 The OIU format is reloaded to accept the data stream coming from the C&C1 MDM rather than the Node 1 MDM. Orb crew 18 The orbiter crew must now set up a PCS machine in the AFD to communicate with the C&C1 MDM. Orb crew 19-21 The LA MDMs are powered on.  After the 2-minute initialization is complete, their status is verified. Orb crew 22 Bus communication is enabled to the RPCMs to prepare for closing various RPCs. Orb crew 23-26 RPCs are closed applying power to various pieces of MTL and LTL equipment in preparation for IATCS startup. Orb crew After Destiny is activated and active cooling has been established to avionics, the ground will take over activation of the laboratory systems. The Pressure Control Assembly (PCA) will be activated, followed by smoke detectors. Then the Common Cabin Air Assembly will be started to provide air circulation and scrubbing of the atmosphere inside the laboratory. The Guidance, Navigation and Control Multiplexer/Demultiplexers (MDMs) will then be activated and loaded with the appropriate software. Destiny’s Power Management Controller Unit MDMs will be checked out as well. The ground will then command the Emergency Egress Lighting batteries to begin charging, followed by activation of the laboratory’s interior lights. The condensation (shell) heaters will be activated, and the survival heaters will be deactivated. The ground will also activate and check out much of the audio equipment in the laboratory. The Control Moment Gyros (CMGs) will also be prepared for spinup, which will occur the following day. Upon successful activation of Destiny’s systems, both the STS-98 crew and the Expedition One crewmembers will enter Destiny on Flight Day 5 and begin outfitting the lab. During the second space walk scheduled for Flight Day 6, PMA-2 will be moved to Destiny’s forward port. The spacewalkers will then work together to remove the laboratory Power Data Grapple Fixture (PDGF) from the orbiter sidewall and install the PDGF on Destiny. The PDGF will be used by the Space Station Remote Manipulator System, the new station robotic arm that will arrive on Mission 6A. The third space walk is scheduled for Flight Day 8. Key activities planned include moving the spare S-Band Antenna Support Assembly from the orbiter to the ISS stowage site, installing the window shutter on the lab and connecting PMA-2 umbilicals to the lab. Deferred Activation and Checkout The ISS crew and/or ground controllers will perform some activation and checkout tasks of the laboratory after the orbiter crew ingress is complete. The ground will command a checkout of the Internal Video Distribution Subsystem Orbital Replacement Units (ORUs). As there is no video capability on this mission, this will be a functional checkout of the equipment to verify that it survived launch in good shape. The ground also will perform a health and status check of the Ku-band radio frequency group. Once again, this will be a health check of the ORUs because there will not be any Ku-band capability until Mission 5A.1. The ISS crew will inspect the wastewater tank in Destiny to verify there are no leaks. Other activation procedures that will be performed by the ISS crew after Atlantis leaves, include the activation and checkout of the water vent system, inhibiting the water vent system, and activation and checkout of the vacuum vent system. The ISS crew will also install a Pressure Control System extension duct to assist the flow of air through the PCA. Systems Destiny will provide the following for the International Space Station: Environmental Control and Life Support System, or ECLSS (temperature and humidity control; fire detection and suppression; atmosphere control and supply; wastewater, recovery and management; vacuum system); Thermal Control System (active thermal control system, passive thermal control system); Guidance, Control and Navigation; Extravehicular Activity; Extravehicular Robotics; Flight Crew Support; Communication and Tracking (audio system, video system, space-to-space communication system, Ku-band and S-band systems); Electrical Power System (EPS); Command and Data Handling; Structures and Mechanism; and Payload Capability. The Command and Data Handling system gains 11 MDMs with the arrival of the lab. These MDMs are used to control the U.S. on-orbit segment systems including payloads. The Communication and Tracking system activates high-data rate S-band to replace the early com system. The audio system comes online and the hardware for Ku-band, UHF and the video distribution system are delivered but not activated until future missions. The ECLSS maintains a pressurized habitable environment within the ISS by supplying correct amounts of oxygen and nitrogen, controlling the temperature and humidity, removing carbon dioxide and other atmospheric contaminants, and monitoring the atmosphere for the presence of combustion products. The system also collects, processes, and stores water removed from the ISS atmosphere. The ECLSS receives equipment in the laboratory that will be used during most of the assembly stages. The atmosphere control and supply subsystem contains the pressure control assembly, vent relief assembly, and manual pressure equalization valves and gas lines. A complete rack of atmosphere revitalization equipment arrives, and the Sample Delivery System lines launched in the Destiny and Unity are connected to the major constituent analyzer in Destiny. The temperature and humidity control subsystem sees the arrival of two common cabin air assemblies and more intermodule ventilation equipment, as well as avionics air assemblies in several racks. The standard fire detection and suppression equipment is launched with Destiny, as are the water recovery and management condensate tank, water vent assembly and waste and fuel cell water lines. The electrical power system, which manages, controls, and distributes electrical power to the U.S pressurized modules, receives all the new electrical loads in the laboratory. Power is brought to the Destiny from the P6 array through the Z1/laboratory umbilical tray. The power is brought to two DC-to-DC converter units in the laboratory and is distributed to the secondary power distribution assemblies and downstream loads. The Motion Control System takes a major step with this mission. The U.S. segment begins contributing to the attitude control of the ISS with the CMGs. The U.S. segment Guidance, Navigation and Control System takes control of the ISS with state vector and attitude inputs from the Russian segment. The Russian segment propulsive capability is still needed for joint attitude control during CMG desaturation and for reboost. Mission 5A delivers the systems that will assume station management and control from the Zvezda Service Module. The Motion Control System becomes integrated between Zvezda and Destiny’s computers. The Thermal Control System activates the early external and internal thermal control systems to accommodate the addition of Destiny’s thermal loads. The Russian segment continues to manage its own modules while interfacing with the U.S. segment Motion Control System for certain data and operations. The Node 1 MDM Node control software continues to provide closed-loop control of environmental, heater, thermal systems and power for Unity, the PMAs, and truss segments. Destiny’s MDM architecture controls the rest of the U.S. on-orbit segment. Mission 5A adds the additional capability of high-rate S-band and internal audio to the U.S. on-orbit segment. The S-band high-rate capability is the major communications and tracking addition to the ISS for Mission 5A. The S-band system provides two-way communications with the ISS and the Mission Control Center via the Tracking and Data Relay Satellite System for commands and system telemetry, voice and file transfer. The internal audio subsystem allows crewmembers to communicate with other crewmembers aboard the ISS. Science The centerpiece of research on the International Space Station, the U.S. Laboratory Destiny will support experiments and studies that may contribute to research toward cures for diseases like cancer and diabetes. Destiny is the primary research laboratory for U.S. payloads. It will support experiments in microgravity research, human life science, fundamental biology and ecology, Earth observations, space science and commercial applications. By Flight 5A.1 (STS-102), the Destiny will support Earth photography and the Human Research Facility in which radiation measurements, psychological evaluations, and neural response experiments will be conducted. In 2002, shuttle flights will deliver the Minus Eighty Laboratory Freezer for ISS, Microgravity Science Glovebox and Window Observational Research Facility. Eventually, Destiny will house up to 13 payload racks with experiments in human life science, materials research, Earth observations and commercial applications. The results of these experiments will allow scientists to better understand our world and ourselves and prepare us for future missions, perhaps to the Moon and Mars. Destiny will be joined by laboratory modules sponsored by the National Space Development Agency of Japan, European Space Agency and Rosaviakosmos.

Crew
Commander:	Kenneth D. Cockrell
Pilot:	Mark L. Polansky
Mission Specialist 1:	Robert L. Curbeam
Mission Specialist 2:	Marsha S. Ivins
Mission Specialist 3:	Thomas D. Jones

Launch
Orbiter:	Atlantis OV104
Launch Site:	Kennedy Space Center Launch Pad 39A
Launch Window:	2.5 to 5 Minutes
Altitude:	173 Nautical Miles
Inclination:	51.6 Degrees
Duration:	10 Days 19 Hrs. 28 Min.

Vehicle Data
Shuttle Liftoff Weight:	4,520,235 lbs.
Orbiter/Payload Liftoff Weight:	254,694 lbs.
Orbiter/Payload Landing Weight:	198,909 lbs.

Software Version:

OI-28

Space Shuttle Main Engines: (1 MB pdf)
SSME 1:  2052	SSME 2:  2044	SSME 3:  2047

External Tank:   ET-106A   ( Super Light Weight Tank)

SRB Set:  BI-105PF

Shuttle Aborts

Abort Landing Sites    RTLS:  Kennedy Space Center Shuttle Landing Facility    TAL:    Zaragoza    AOA:   Edwards Air Force Base, California

Shuttle Abort History

Landing
Landing Date:	02/18/01
Landing Time:	12:56 PM (eastern time)
Primary Landing Site:	Kennedy Space Center Shuttle Landing Facility