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Exam Number : HP0-512
Exam Name : Replication Solutions for the HP StorageWorks EVA
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HP EVA testing
space Station consumer's ebook | HP0-512 Practice Test and Test Prep
ISS aspects: Z1 Truss segmentsource: Shuttle Press kit
The Z1 is the bottom structure for the U.S. solar array. This Truss segment changed into launched on the STS-92/ISS-3A mission in November 2000.
The Z1 Truss section contains two plasma contactors, two DC-to-DC converter instruments (DDCUs), 4 control moment gyro (CMG) assemblies, part of 1 string of the S-band communications gadget, one Ku-band communications device, primary and secondary power distribution, thermal handle device hardware, mechanical interfaces, and EVA/extravehicular robotics (EVR) hardware.
Command and monitoring Subsystem
S-Band Communications gadget. The S-band communications gadget contains two redundant strings, each of which includes three on-orbit replaceable contraptions (ORUs) and two antennas, the baseband sign processor (BSP), the monitoring and statistics Relay satellite tv for pc equipment (TDRSS) transponder, and the antenna RF group, which comprises a low-benefit antenna and a excessive-gain directional antenna.
The radio frequency community (RFG) has two main services. It amplifies and filters the radio signal and receives and radiates the signal, presenting the interface with free area. It additionally controls antenna switching and pointing.
The RFG unit has two antennas. The excessive-profit antenna (HGA) can assist the excessive-rate statistics link, nevertheless it requires TDRSS pointing updates which are generated by way of the suggestions, navigation, and control (GN&C) pointing function (which usually are not obtainable unless the GN&C multiplexer/demultiplexer [MDM] was activated on Mission 5A). The low-gain antenna (LGA) is fastened in place and desires no pointing facts.
The RFG is launched on the Z1 starboard bulkhead. due to the fact that this is the DDCU warmth pipe (HP) setting up area, the RFG have to be relocated briefly during EVA1 to the stowage bracket.
The BSP is the heart of the S-band system. It gives facts and voice processing for downlink and uplink. A voice line connects directly to the BSP to supply voice communications.
The TDRSS transponder, which turned into delivered on Mission 4A, receives downlink guidance from the BSP and modulates the RF service for transmission to the floor. The transponder receives the uplink suggestions from the RF group, demodulates the sign, and routes it to the BSP for tips separation and distribution.
The downlink output of the BSP is a relentless-expense facts movement of either 192 kbps or 12 kbps, as exact by means of a configuration command.
To support the uplink, the BSP inputs a digital bit circulate from the regular TDRSS transponder at either seventy two or 6 kbps counting on whether the BSP is configured for the high or low records rate. The statistics is processed with the aid of decryption, CCSDS header validation, and demultiplexing services. If uplink audio channel facts is latest, it's multiplied to 192 kbps per channel for interface to the AUAIU and is routed to the applicable output port. The uplink core information channel packets are passed to the 1553 interface for switch to the command and manage processor.
Ku-Band Communications device. The Ku-band system is the basic return link for overseas space Station (ISS) video and payload facts transmitted in digital layout to the ground. The area-to-floor antenna (SGANT) could be relocated and connected to the one-beam boom of the current Ku-band antenna on EVA1.
The Ku-band gives a 50-Mbps fixed-fee downlink with as much as 4 video indicators or up to forty three-Mbps excessive-price information with 7 Mbps overhead. A communication outage recorder data payload information within the zone of exclusion and all the way through structural blockage outages. There are 12 logical channels (four video and 8 payload) within the Ku-band downlink.just like the S-band device, the Ku-band equipment doesn't inspect the facts passing through it.
The ISS transmits at a continuing price of fifty Mbps. Of this, 43 Mbps is attainable to the user.
The video channels may also be configured to downlink full-movement video or cease-action video, which incorporates skipping video frames. consistently, the carrier is configured on the ground and commanded in the course of the S-band uplink to the on-board C&DH, which routes instructions by way of the 1553 native bus to the Ku-band.
The on-board Ku-band machine includes a single string of four avionics contraptions-the video baseband sign processor (VBSP), excessive-rate frame multiplexer (HRFM), high-price modem (HRM), and the transmit/receive controller (TRC)-plus an erectable, steerable antenna. Video alerts must be processed by using the VBSP before they're routed to the HRFM for interleaving with high-rate records (HRD). HRD comes from the payload patch without delay to the HRFM for processing and interleaving with the video signal. The HRFM builds the downlink transfer frames and routes the statistics move to the HRM for modulation on an S-band interface (I/F) frequency for routing to the TRC for translation to the Ku-band frequency. The information circulate is power amplified and routed to the steerable antenna for transmission throughout the TDRSS to the ground. An uplink carrier is received and processed by way of the TRC to hold antenna autotracking most effective.
Video channels are directed to the VBSP for processing. The VBSP has 4 audio and four video input channels and 4 video plus audio output channels. Connectors are additionally offered for power and 1553 bus and i/F statistics out. The 4 video plus audio output channels are directed to the HRFM. The VBSP performs audio and video analog-to-digital (A/D) format conversions, packet formatting, built-in examine (BIT), and ORU manage features. The VBSP converts incoming analog signals to digital, codecs them for the chosen mode of operation, and forwards them to the HRFM for interleaving with excessive-price payload records.
Electrical vigor Subsystem
The Z1 truss meeting has a few power distribution accessories. These consist of two initialization diode assemblies (IDAs), two secondary energy distribution assemblies (SPDAs), two plasma contactor instruments (PCUs), two DDCUs, and two patch panels.
The IDAs deliver diode-protected power from the shuttle meeting vigour conversion unit (APCU) to P6 for module initialization on Mission 4A. They also deliver a connection direction from P6 to the lab DDCUs from Mission 5A until Mission 12A, when the P4 module could be delivered.
The SPDAs consist of faraway energy controller modules (RPCMs), vigour and information connections (important utility rail), and a cold plate. They control, deliver protection to, and isolate secondary distribution strains. The SPDAs settle for secondary power from the DDCUs and distribute this vigour to RPDAs or downstream hundreds. The SPDA cold plates switch heat from the RPCMs via radiant fins.
The critical utility rail gives energy connections from the DDCU energy feed to the RPCMs and records connections by the use of redundant 1553B facts buses. because the DDCUs should not lively all through Mission 3A, SPDAs Z1-3B and Z1-4B will obtain power directly from Russian-American conversion instruments (RACUs) 5 and 6, respectively.
RPCMs are electronic switches that handle, offer protection to, and isolate secondary distribution lines. There are six styles of RPCMs, which fluctuate of their rated output existing, variety of switches per module, and go back and forth services.
The PCU emits electrons through a self-generated plasma and is self-regulating. The PCUs control the voltage between the house plasma and the ISS constitution. PCUs installed on the Z1 truss hold the constitution talents of the ISS within forty volts of the plasma potential. A vital aspect of every PCU is the hole cathode assembly (HCA), which emits up to 10 amps of electron existing to the ambient plasma. The PCU actively emits when the ISS is in daylight. with out the PCUs, the ISS might attain structure potentials of approximately -a hundred and fifty volts.
Two DDCUs, which are launched attached to cargo coping with interface adapters (CHIAs), may be delivered on Mission 3A. The DDCUs might be removed from the CHIAs and connected to the starboard facet of Z1 all through EVA1. The contraptions convert energy from simple (one hundred fifteen to 173 volts DC) to secondary (123 to 126 volts DC). They usually are not activated unless Mission 4A, when P6 energy comes on line.
Two patch panels on the port aspect of Z1 enable the Z1 enter energy source to be changed. On the outside of the panels are a set output and three interchangeable enter connectors. To trade the panel configuration, an umbilical is easily demated and mated to a special connector on the patch panel. The launch configuration of the patch panels provides Russian phase (RS) vigor to Z1 add-ons for retain-alive functions. The panels could be reconfigured during Mission 4A to put together for the transition to U.S. vigour by the use of P6.
Extravehicular pastime Subsystems
The Z1 truss section is fitted with a number of spacewalk aids: Two EVA device stowage gadgets (ETSDs), 22 worksite interface (WIF) sockets, 1 flight-releasable grapple fixture (FRGF), 11 trusses, 2 tray launch restraints, numerous commonplace handholds and handrails, and a couple of customized handles.
movement handle Subsystem
The motion manage subsystem (MCS) hardware launched as part of the Z1 aspect contains the CMGs and the CMG assemblies. This hardware are not activated unless Mission 5A, when the GN&C MDM may be activated with the U.S. Lab.
The CMG assembly contains four CMGs and a micrometeorite/orbital debris defend. The 4 CMGs, to be able to manage the angle of the ISS, have a spherical momentum storage ability of 14,000 toes-lb/sec, the scalar sum of the particular person CMG wheel moments. The momentum kept in the CMG system at any given time equals the vector sum of the particular person CMG momentum vectors.
To hold the ISS within the favored attitude, the CMG system ought to cancel, or take up, the momentum generated via the disturbance torques performing on the station. If the usual disturbance torque is nonzero, the resulting CMG output torque is also nonzero, and momentum builds up within the CMG device. When the CMG system saturates, it's unable to generate the torque required to cancel the disturbance torque, which consequences in the lack of attitude control.
The CMG equipment saturates when momentum vectors have turn into parallel and best momentum vectors change. When this occurs, manage torques perpendicular to this parallel line are possible, and controllability about the parallel line is misplaced.
Russian phase thrusters are used to desaturate the CMGs.
An ISS CMG incorporates a huge flat wheel that rotates at a continuing speed (6,600 rpm) and develops an angular momentum of three,500 feet-lb/sec about its spin axis. This rotating wheel is mounted in a two-degree-of-freedom gimbal gadget that can aspect the spin axis (momentum vector) of the wheel in any path.
as a minimum two CMGs are needed to deliver attitude control. The CMG generates an output reaction torque it really is applied to the ISS via inertially changing the route of its wheel momentum. The CMG's output torque has two components, one proportional to the price of exchange of the CMG gimbals and a 2d proportional to the inertial body expense of the ISS as sensed on the CMG base. because the momentum along the direction of the spin axis is fastened, the output torque is limited to lie in the plane of the wheel. that's why one CMG can't provide the three-axis torque necessary to control the angle of the ISS.
each and every CMG has a thermostatically managed survival heater to preserve it within thermal limits before the CMGs are activated on Mission 5A. the warmers are rated at one hundred twenty watts and have an working temperature latitude of -42 to -35°F.
buildings and Mechanisms
Mechanical interfaces are provided between Z1 and the P6 lengthy spacer on the Z1 zenith face, between Z1 and Node 1 on the Z1 nadir face, between Z1 and PMA-2 on the Z1 ahead face, and throughout a cable tray from the Z1 ahead face to the U.S. Lab.
A manual berthing mechanism (MBM) on the forward face of Z1 enables temporary stowage of PMA-2. The machine is similar to the one used on the Spacelab pallet to stow PMA-three on this flight (however devoid of the perimeter bolts).
A hinged cable tray on the forward face of Z1 offers a direct interface for power, information, and coolant strains to the U.S. Lab. Mission 3A EVA crew members will installation the tray to expose the MBM and should unencumber 32 bolts on the four coolant traces.
The Z1 truss structure is designed to maximize part packaging and assist load paths throughout launch and on orbit. a superior plate beneath the CMG face provides additional protection from micrometeorites and orbital particles for the CMGs and different Z1 add-ons. The structural framework beam and shell facets are aluminum 2219-T851. The trunnion and keel pin beam elements are INCO 718, and the Ku-band antenna growth beam aspects are metal.
Thermal manage Subsystem
The Z1 truss assembly contains here points of the early external active thermal control system (EEATCS): 4 accumulators, ammonia, and 12 brief disconnects and linked plumbing. The accumulators cost the EEATCS with ammonia on orbit, accommodate thermal enlargement within the fluid, and hold the device's operating power. The brief disconnects facilitate the connection of ammonia transfer strains between P6 and Z1 and between Z1 and the U.S. Lab.
