INTEGRATED TRUSS STRUCTURE

The 'Integrated Truss Structure' forms the backbone of the International Space Station, with mountings for unpressurized logistics carriers, radiators, solar arrays, and other equipment.
In the initial Space Station Freedom plans, a variety of designs for the truss were used, all of them intended to be shipped up as girders where they would be assembled and their equipment installed by astronauts on spacewalks once it had been launched. After the 1991 redesign, NASA switched to shorter, prefabricated pieces that would require minimal installation.

Contents

Truss components

Z1 truss

S0 truss

P1, S1 trusses

P2, S2 trusses

P3/P4, S3/S4 truss assemblies

P5, S5 trusses

P6, S6 trusses

Truss subsystems

Solar arrays

Solar Alpha Rotary Joint

Power Conditioning and Storage

Truss and solar array assembly sequence

See also

References

External links

Truss components

Z1 truss

The first truss piece, the Z1 truss, launched aboard STS-92 in October 2000 is being used as a temporary mounting position for the P6 truss and solar array, attached on the subsequent shuttle flight, STS-97. Though not a part of the main truss, the Z1 truss was the first permanent lattice-work structure for the ISS, very much like a girder, setting the stage for the future addition of the station's major trusses or backbones. It contains the control moment gyroscope (CMG) assemblies, electrical wiring, communications equipment, and two plasma contactors designed to neutralize the static electrical charge of the space station. It is unpressurized, but features two Common Berthing Mechanism docking ports for easy connecting and data communications. One port is used to connect the Z1 truss to the zenith port of ''Unity''. The other port was used to temporarily store PMA-3. Once P6 is moved, the Z1 truss will not be used for connecting other elements in the future, but will solely house the CMGs, communications and the plasma contractors.

S0 truss

The S0 truss, (also called the ''Center Integrated Truss Assembly Starboard 0 Truss'') forms the center backbone of the Space Station. It was attached on the top of the Destiny Laboratory Module during STS-110 in April 2002. S0 is used to route power to the pressurized station modules and conduct heat away from the modules to the S1 and P1 Trusses. The S0 truss is not docked to the ISS, but is connected with four Module to Truss Structure (MTS) struts.

P1, S1 trusses

The P1 and S1 trusses (also called the ''Port and Starboard Side Thermal Radiator Trusses'') are attached to the S0 truss, and contain carts to transport the Canadarm2 and astronauts to worksites along the space station. They each flow 290 kg (637 lb) of anhydrous ammonia through three heat rejection radiators. However, currently only one radiator on each truss is in use, as there is no room to deploy the others until the solar panels of Zarya are retracted; this is scheduled to take place during STS-120. The S1 truss was launched on STS-112 in October 2002 and the P1 truss was launched on STS-113 in November 2002. Detailed design, test and construction of the S1 and P1 structures was conducted by McDonnell Douglas (now Boeing) in Huntington Beach, CA. First parts were cut for the structure in 1996, and delivery of the first truss occurred in 1999.

P2, S2 trusses

The P2 and S2 trusses were planned as locations for rocket thrusters in the original design for Space Station Freedom. Since the Russian parts of the ISS also provided that capability, the reboost capability of the Space Station Freedom design was no longer needed at that location. So P2 and S2 were canceled.^[1]

P3/P4, S3/S4 truss assemblies

The P3/P4 truss assembly was installed by the Space Shuttle ''Atlantis'' STS-115 mission, launched September 9, 2006, and attached to the P1 segment. The P3 and P4 segments together contain a pair of solar arrays, a radiator and a rotary joint that will aim the solar arrays, and connects P3 to P4. Upon its installation, no power was flowing across the rotary joint, so the electricity generated by the P4 solar array wings was only being used on the P4 segment, and not the rest of the station. Then in December of 2006 a major electrical rewiring of the station by STS-116 routed this power to the entire grid. The S3/S4 truss assembly -- a mirror-image of P3/P4 -- was installed on June 11, 2007 also by Space Shuttle ''Atlantis'' during flight STS-117, mission 13A and mounted to the S1 truss segment.
Major P3 and S3 subsystems include the Segment-to-Segment Attach System (SSAS), Solar Alpha Rotary Joint (SARJ), and Unpressurized Cargo Carrier Attach System (UCCAS). The primary functions of the P3 truss segment are to provide mechanical, power and data interfaces to payloads attached to the two UCCAS platforms; axial indexing for solar tracking, or rotating of the arrays to follow the sun, via the SARJ; movement and work site accommodations for the Mobile Transporter. The P3/S3 primary structure is made of a hexagonal shaped aluminum structure and includes four bulkheads and six longerons. STS-115 Press kit The S3 truss also supports EXPRESS Logistics Carrier locations, first to be launched and installed in the 2009 time frame.
Major subsystems of the P4 and S4 Photovoltaic Modules (PVM) include the two Solar Array Wings (SAW), the Photovoltaic Radiator (PVR), the Alpha Joint Interface Structure (AJIS), and Modified Rocketdyne Truss Attachment System (MRTAS), and Beta Gimbal Assembly (BGA).

P5, S5 trusses

The P5 and S5 trusses are connectors which will support the P6 and S6 trusses, respectively. The P3/P4 and S3/S4 truss assemblies' length was limited by the cargo bay capacity of the Space Shuttle, so these small connectors are needed to extend the truss. The P5 truss was installed on December 12, 2006 during the first EVA of Space Shuttle mission STS-116. The S5 truss was brought into orbit by mission STS-118 and installed on August 11, 2007.

P6, S6 trusses

The P6 truss was the second truss segment to be added, because it contains a large Solar Array Wing (SAW) that generated essential electricity for the station, prior to activation of the SAW on the P4 truss. It is currently mounted to the Z1 truss but it will be moved far along the port side main truss and mounted on the P5 truss during assembly mission 10A, STS-120. A later assembly mission (the out of sequence STS-119) will mount the S6 truss on the starboard side and provide a fourth set of solar arrays and radiators.

Truss subsystems

Solar arrays

The International Space Station's main source of energy is from two of the four large U.S.-made photovoltaic arrays currently on the station, sometimes referred to as the ''Solar Array Wings'' (SAW). The first pair of arrays are attached to the P6 truss segment, which was launched and installed late 2000 during STS-97. The second pair was launched and installed in September 2006 during STS-115, but they didn't provide electricity until STS-116 in December 2006 when the station got an electrical rewiring. A third pair of arrays was installed during STS-117 in June 2007. A final pair is planned to arrive on STS-119. More solar power was to have been available via the Russian-built Science Power Platform, but it was cancelled.
Each of the Solar Array Wings are 34 m (112 ft) long by 12 m (39 ft) wide, and are capable of generating nearly 32.8 kW of DC power.^[2] They are split into two photovoltaic blankets, with the deployment mast in between. Each blanket has 16,400 silicon photovoltaic cells, grouped into 82 active panels, each consisting of 200 cells, and each cell is 8 cm² with 4,100 diodes.

close-up view of solar array folded like an accordion.

Each pair of blankets is folded like an accordion for compact delivery to space. Once in orbit, the deployment mast between each pair of blankets unfolds the array to its full length. Gimbals, known as the ''Beta Gimbal Assembly'' (BGA) are used to rotate the arrays so that they face the Sun to provide maximum power to the Space Station.

Solar Alpha Rotary Joint

One Solar Alpha Rotary Joint (SARJ) is located between the P3 and P4 truss segments and the other is located between the S3 and S4 truss segments. When in operation, these joints continuously rotate to keep the solar array wings on the outboard truss segments oriented towards the Sun. Each SARJ is 10 feet in diameter, weighs approximately 2,500 pounds and can be rotated continuously using bearing assemblies and a servo control system. On both the port and starboard sides, all of the power flows through the Utility Transfer Assembly (UTA) in the SARJ. Roll ring assemblies allow transmission of data and power across the rotating interface so it never has to unwind. The SARJ was designed, built and tested by Lockheed Martin and its subcontractors.

Power Conditioning and Storage

The Sequential Shunt Unit (SSU) is designed to coarsely regulate the solar power collected during periods of insolation – when the arrays collect power during sun-pointing periods . A sequence of 82 separate strings, or power lines, leads from the solar array to the SSU. Shunting, or controlling, the output of each string regulates the amount of power transferred. The regulated voltage setpoint is controlled by a computer located on the IEA and is normally set to around 140 volts. The SSU has an overvoltage protection feature to maintain the output voltage below 200 V DC maximum for all operating conditions. This power is then passed through the BMRRM to the DCSU located in the IEA. The SSU measures 32” by 20” by 12” and weighs 185 pounds.
The power storage system consists of a Battery Charge/Discharge Unit (BCDU) and two battery assemblies.
The BCDU serves a dual function of charging the batteries during solar collection periods, and providing conditioned battery power to the primary power busses (via the DCSU) during eclipse periods. The BCDU has a battery charging capability of 8.4 kW and a discharge capability of 6.6 kW. The BCDU also includes provisions for battery status monitoring and protection from power circuit faults. Commanding of the BCDU is from the IEA computer.
Each battery assembly consist of 38 lightweight Nickel Hydrogen cells and associated electrical and mechanical equipment. Two battery assemblies connected in series are capable of storing a total of 8 kW of electrical power. This power is fed to the ISS via the BCDU and DCSU respectively. The batteries have a design life of 6.5 years and can exceed 38,000 charge/discharge cycles at 35% depth of discharge. Each battery measures 40” by 36” by 18” and weighs 375 pounds.
http://www.shuttlepresskit.com/STS-97/payload81.htm

Truss and solar array assembly sequence

Main articles: ISS assembly sequence


★ 'Truss segments in orbit'

★ Truss segments pending a Shuttle launch

'Element'	'Flight'	'Launch date'	'Length (m)'	'Diameter (m)'	'Mass (kg)'
'Z1 truss'	3A – STS-92	October 11,2000	4.9	4.2	8,755
'P6 truss – solar array'	4A – STS-97	November 30,2000	73.2	10.7	15,824
'S0 truss'	8A – STS-110	April 8,2002	13.4	4.6	13,971
'S1 truss'	9A – STS-112	October 7,2002	13.7	4.6	14,124
'P1 truss'	11A – STS-113	November 23,2002	13.7	4.6	14,003
'P3/P4 truss – solar array'	12A – STS-115	September 9, 2006	73.2	10.7	15,824
'P5 truss'	12A.1 – STS-116	December 9, 2006	3.37	4.55	1,864
'S3/S4 truss – solar array'	13A – STS-117	June 8, 2007	73.2	10.7	15,824
'S5 truss'	13A.1 – STS-118	August 8, 2007	3.37	4.55	1,818
P6 truss – solar array (relocation)	10A – STS-120	no earlier than October 20, 2007	–	–	–
S6 truss – solar array	15A – STS-119	July, 2008	73.2	10.7	15,824

See also

★ ISS assembly sequence

★ List of manned spaceflights to the ISS

References

1. Ask The Mission Team - Question and Answer Session
2. Spread Your Wings, It's Time to Fly

External links

★ NASA Flash ITS Interactive