Attachment_A_-_Statement_of_Work.pdf

ATTACHMENT A

STATEMENT OF WORK (SOW)

Statement of Work (SOW) for the Space Geodesy Project (SGP) VGOS

Antenna

Table of Contents

Section 1 Overview

1.1 Introduction

1.2 Background

1.3 Scope

Section 2 VGOS Antenna Requirements

2.1 Environmental Conditions

2.2 Physical Characteristics

2.3 Functional Requirements

2.4 Performance Requirements

Section 3 External Interface Requirements

3.1 Field System (VLBI System Controller) Interface Requirements

3.2 Signal Chain Interface Requirements

3.3 Network Interface Requirements

3.4 Timing Interface Requirements

3.5 Electrical Interface Requirements

3.6 Antenna Foundation Requirements

3.6 Human Interface Requirements

Section 4 Reliability/Maintainability/Availability Requirements

Section 5 Safety Requirements

5.1 Safety Training and Certification

5.2 Safety-Guidance

5.3 Safety-Operations

5.4 Safety-Occupational

5.5 Safety-Markings and Labels

Section 6 Security Requirements

6.1 Security Guidance

Section 7 Functions to be performed by the Vendor

7.1 Project Management

7.2 Quality Assurance and Workmanship

7.3 Design, Development, and Deployment

7.4 System/Product Support

Section 1 Overview

1.1 Introduction

This Statement of Work (SOW) is for the construction, deployment, and commissioning of up to three Very Long Baseline Interferometer (VLBI) antennas that will be part of a new NASA Space

Geodesy Network (NSGN) and the VLBI2010 Global Observing System (VGOS).

One of the main objectives of the Space Geodesy Project (SGP) is to produce the necessary observations for realization of the Terrestrial Reference Frame (TRF). Scientific objectives dictate the desire for an ITRF definition with accuracy of 1 mm and stable to 0.1mm/yr. (millimeters per year), including geocenter and with a scale accurate to 0.1ppb (parts per billion), and stable to 0.01 ppb/yr. (Source: Gross et al., 2009). This is a factor of 10-20 beyond current capability.

The NASA SGN will comprise integrated, multi-technique next generation space geodetic observing systems, as the core NASA contribution to a global network designed to produce the higher quality data required to maintain the ITRF and provide information essential for fully realizing the measurement potential of the current and coming generation of Earth Observing spacecraft. It is anticipated that to achieve the desired level of accuracy and stability the SG sites will co-locate and use in unison several key techniques of observation, including VLBI, Satellite

Laser Ranging (SLR), Global Navigation Satellite Systems (GNSS) and Doppler Orbitography and Radiopositioning Integrated by Satellite (DORIS).

1.2 Background

The SGP is responsive to two important reports from the National Research Council (NRC): 1)

"Earth Science and Applications from Space: National Imperatives for the Next Decade and

Beyond", a.k.a. the "Earth Science Decadal Survey"; and 2) "Precise Geodetic Infrastructure, National Requirements for a Shared Resource". These reports highlight the importance of maintaining and enhancing the geodetic infrastructure that enables modern geodesy and supports

NASA's Earth Science missions.

The global geodetic infrastructure, with its terrestrial- and space-based assets, enables the realization of the Terrestrial Reference Frame (TRF), the foundation for virtually all airborne, space-based and ground-based Earth observations. Through its tie to the Celestial Reference Frame

(CRF) by time-dependent Earth orientation parameters, it is also fundamentally important for interplanetary spacecraft tracking and navigation. The TRF determined by geodetic measurements is the indispensable foundation for all geo-referenced data used by society. Furthermore, modern geodetic measurements are making fundamental contributions to mitigating the impact of geo-hazards such as earthquakes, volcanic eruptions, debris flows, landslides, land subsidence, sea level change, tsunamis, floods, storm surges, hurricanes and extreme weather. Geodesy is also at the heart of present day ocean studies and contributes to atmospheric science and hydrological studies.

In 2006, The International VLBI Service for Geodesy and Astrometry (IVS) defined the requirements for a next generation network (VGOS) of broadband VLBI antennas as described in technical memorandum number 2006-022v01 found on the IVS website at http://ivscc.gsfc.nasa.gov/publications/memos/index.html. NASA recently implemented the first broadband antenna in this new network at the Goddard Geophysical and Astronomical

Observatory (GGAO) in Greenbelt, MD. NASA is also currently building a second station at the

Kokee Park Geophysical Observatory (KPGO) on Kauai, HI in partnership with the United States

Naval Observatory. Future NASA stations will be based upon the design of the KPGO station with only minor modifications that take into account advances in technology.

The SGP has selected the McDonald Observatory (MCD) located near Fort Davis, TX as a NASA core geodetic site. This contract is to fabricate, ship, and install a VGOS radio antenna at MCD with the option to develop and deploy up to an additional two (2) antennas at international sites yet to be determined. Current sites under consideration by NASA are in Tahiti, Brazil and

Colombia. Additional information on the SGP, the prototype site, and the VGOS stations can be found on the SGP website at http://space-geodesy.nasa.gov.

1.3 Scope

This SOW documents the project management, engineering development, system build, documentation and delivery of one to three VGOS antennas to NASA, and the deployment of the first system to MCD and the following optional two to international sites selected by NASA at a future date. Acceptance testing at the vendor’s facility and at the final location are included in this work, as are periodic reviews of the engineering design, system development, documentation and system performance. The vendor shall be responsible for the deployment of each system to its final location, including shipping and system setup. There shall be a commissioning period at each final location where the vendor demonstrates the operational system performance after all system elements has been integrated with the antenna.

Deliverables include the VGOS antenna and all associated subsystems, spares for critical parts, test instrumentation needed to maintain the system, documentation, system analysis, drawings and models, all data collected during Functional and Acceptance Testing, all data collected during commissioning, and all software source code and firmware code developed under this contract and used in the system (with the exclusion of any proprietary licenses that were purchased as commercial-off-the-shelf).

A notional timeline for the first SGP VGOS antenna is to design, fabricate, install and test the first

VGOS antenna between 18 to 24 months. The programmatic milestones for the notional timeline follows:

Month 0 Contract Award (CA) -

Month 1 Contract Kick Off CA+30 days

Month 2 Preliminary Design Review (PDR) CA+60 days

Month 4 Critical Design Review (CDR) CA+120 days

Month 15 Factory Acceptance Test (FAT) CA+450 days

Month 18 Ship/Installation/Test CA+540 days

Month 20 VLBI System Integration Support and Commissioning

CA+600 days http://space-geodesy.nasa.gov/

Section 2 VGOS Antenna Requirements The VGOS radio antenna consist of a main reflector, a secondary reflector, feedtube, counterweights, a turning head, a pedestal, antenna drives and a control system. The VGOS radio antenna interfaces with several interfaces that include interfaces to the site foundation, electrical power, signal chain, VLBI system controllers, timing, networks and human interfaces.

VGOS radio antenna has precise technical specifications necessary to achieve the desired observational data quality. This statement of work (SOW) includes physical characteristics, performance characteristics, interface requirements, safety requirements, for each of the (3) VGOS radio antennas to operate within the environmental conditions defined for this SOW.

2.1 Environmental Conditions

2.1.1 Primary Operating Conditions (Full performance of the antenna):

2.1.1.1 Temperature.

The antenna shall be capable of operating at temperatures from 20°F to 90°F.

2.1.1.2 Relative Humidity.

The antenna shall be capable of operating at relative humidity between 0–100 percent.

2.1.1.3 Wind Speed.

The antenna shall be capable of operating at wind speeds < 32 km/hr. (20 mi. /hr.) sustained.

2.1.1.4 Rainfall.

The antenna shall be capable of withstanding rain rates of up to 50 mm/hr. (2 in/hr.) without structural damage.

2.1.2 Secondary Operating Condition (Degraded performance of the antenna):

2.1.2.1 Temperature.

The antenna secondary operating temperature shall be 10°F to 100°F.

2.1.2.2 Relative Humidity.

The antenna secondary operating relative humidity shall be 0-100%.

2.1.2.3 Wind Speed.

The antenna secondary operating wind speed shall be < 100 km/hr. (62 mph.) sustained (or <

99.5-percentile wind speed, if higher).

2.1.2.4 Rainfall.

The antenna secondary operating temperature shall be rainfall :< 100 mm/hr. (4 in/hr.).

2.1.3 Survival Conditions at Stow with negligible structural damage

2.1.3.1 Temperature.

The antenna survival temperature shall be 10°F to 100°F

2.1.3.2 Relative Humidity.

The antenna survival humidity shall be between 0-100 percent.

2.1.3.3 Wind Speed.

The antenna shall be able to withstand wind speed of < 200 km/hr. (124 mph) sustained.

2.1.3.4 Rainfall.

The antenna be able to withstand rainfall of < 100 mm/hr.

2.1.3.5 Hail.

The antenna shall survive one-inch diameter hail in winds of 48 km/hr. (30 mph) without structural damage.

2.1.3.6 Ice.

The antenna shall be capable of withstanding 19 mm (0.75 in) of ice in winds of 48 km/hr. (30 mph) without structural damage.

2.1.3.7 Seismic.

The VLBI system shall be designed to International Building Code (IBC) Seismic Design

Category (SDC) C and shall not be damaged by earth movement consistent with Seismic Design

Category C events.

2.1.3.8 Snow.

The antenna for elevation angles = 20 degrees shall be capable of withstanding a ground snow load of 30 pounds per square foot (psf) without structural damage or performance degradation

2.2 Physical Characteristics

2.2.1 Diameter.

The antenna diameter shall be ≥ 12.0 m.

2.2.2 Antenna Type.

The antenna reflector/sub reflector type shall be Cassegrain.

2.2.3 Antenna Mount.

The antenna mount shall be a standard azimuth-elevation (az-el) type mount.

2.2.4 Mount Materials.

The antenna mount materials shall be composed of steel-galvanized and painted to NASA specifications and/or industry best practices.

2.2.5 Antenna Reflector Panel Materials.

The antenna reflector panel materials shall be composed of Aluminum and painted to NASA specification and/or industry best practices.

2.2.6 Antenna Optics.

The antenna optics shall give maximum sensitivity with the quad-ridge flared horn (QRFH) feed.

2.2.7 Antenna Subreflector Subtended Angle.

The antenna optics shall support a QRFH feed having a 50-60 degree subtended half angle.

2.2.8 Antenna Reference Point.

The geodetic reference point, or “invariant point”, is the intersection point between the fixed rotation axis and the plane that contains the moving axis and is perpendicular to the fixed axis.

For an elevation-over-azimuth mount, the fixed and moving axes are the azimuth and elevation axes, respectively. If the offset between the rotation axes is zero, the reference point is the point where the axes intersect. The vendor shall provide the location of the antenna reference point to an accuracy of less than 0.3 mm RSS.

2.2.9 Antenna Reference Point Stability.

Relative to a local geodetic network external to the antenna and its foundation, the antenna 3-

Dimensional position of the reference point shall be either stable or able to be modeled, as a function of elevation and temperature (and possibly other parameters), to less than 0.3 mm RSS.

2.2.10 Antenna Reference Point Measurement and Monitoring.

The vendor shall accurately determine the location of the antenna reference point, through direct measurement and/or modeling, and model the changes based upon temperature, motion of the telescope, time and any other factors that will change this value more than 0.3 mm.

2.2.11 Antenna Reference Point Survey Target Interface.

The antenna shall provide an external precise survey target interface to the antenna reference point with known offset dimensions accurate to 0.3 mm RMS.

2.2.12 Sky Coverage-Azimuth.

The antenna shall have an azimuth travel range of +/- 270° with no constraints on location or direction of travel within this range.

2.2.13 Sky Coverage-Elevation

The antenna shall have an elevation travel range from +5 degrees above the horizon to 90 degrees.

2.2.14 Antenna Cable Wrap Range of Motion.

The antenna cable wrap shall have a range of motion of -270 degrees to +270 degrees relative to the center of the range of motion.

2.2.15 Antenna Cable Wrap-Hose and Cable Size Constraint.

The antenna cable wrap shall be able to accept, route and operate network (Ethernet-CAT5/6) cables, electrical cables (AWG 6), fiber optics cables, and helium hoses without any damage to the cable wrap and/or cables. These cables and hoses can be up to 1 inch in diameter in the azimuth cable wrap and up to 1.75 inch diameter in the elevation cable wrap.

2.2.16 Antenna Cable Wrap.

The antenna shall have a cable routing mechanism (i.e., antenna cable wrap) to route and manage cables.

2.2.17 Antenna Cable Wrap Compliance with IVS Memorandum.

The antenna cable wrap shall comply with IVS Memorandum 2009-003v02, August 04, 2015.

2.2.18 Mounting Provisions.

The antenna shall make provisions to mount geodetic instrumentation, such as reflectors or corner cubes, on the antenna primary and secondary reflectors and around the feed to allow measurements of path length variations for different pointing directions.

2.2.19 Heating, Ventilation and Air Conditioning (HVAC).

The antenna shall be outfitted with a heating, ventilation, and air conditioning and (HVAC) system to maintain the antenna pedestal environmental condition that is optimum for safe operations of people and equipment inside the antenna.

2.2.20 Materials to Reduce Heat in the Antenna Interior Compartments.

The antenna shall have materials to reduce heating of the antenna interior.

2.2.21 Limit Switches, Emergency Stops and Brakes.

The antenna limit switches, emergency stop buttons, and failsafe brakes shall be installed to ensure the safety of personnel and equipment in the case of equipment failure or malfunction

2.2.22 Antenna Movement Disable Switch (Emergency Stop Switch).

The antenna shall have a movement disable switch provided at the base of the antenna pedestal.

The switch shall allow for quick access to disable the antenna in an emergency situation. Any interlock shall be indicated on both local and remote antenna status displays.

2.2.23 Antenna Stop Protection.

The antenna shall be protected with software, hardware, and hard stops or equivalent protection to prevent damage to antenna in both azimuth and elevation.

2.2.24 Inhibit-Failsafe.

The antenna shall prevent uncontrolled movement of system components in the event of a system fault or failure.

2.2.25 Inhibit-Hazardous Energy.

The antenna hazardous energy shall be capable of being isolated and locked when maintenance or service is required to protect personnel and equipment.

2.2.26 Dust and Dirt.

The antenna shall be designed to preclude the intrusion of dirt and dust.

2.2.27 Infestation Prevention.

The antenna shall be designed to prevent infestation by insects, birds and vermin.

2.2.28 Materials and Finishes.

The antenna materials, finishes, and seals shall be suitable for the environment conditions.

2.2.29 Water Accumulation.

The antenna shall be designed to prevent accumulation of water on any active surface.

2.2.30 Leakage.

The antenna shall be designed to prevent any leakage into any exposed equipment or into the antenna interior due to rain.

2.3 Functional Requirements

2.3.1 Slew

The antenna shall be capable of performing rapid slew rates in azimuth and elevation.

2.3.2 Slew-Antenna Movement-Discontinuity Target Trajectories.

The antenna shall slew smoothly when a discontinuity in the target trajectories occurs.

2.3.3 Slew-Accelerations and Decelerations.

The antenna shall manage the accelerations, decelerations and settling of the antenna for all types of modes of operations to include large slews of greater than ten degrees, small slews of 1 to 10 degrees and calibration slews of less than 1 degree.

2.3.4 Manual Movement of Antenna.

The antenna shall have a safe mechanism for manual movement of the antenna by an operator.

2.3.5 Antenna Stowage System.

The antenna shall be outfitted with a system to safely secure and stow the antenna during power outages and/or severe weather.

2.3.6 Track-Trajectory Commands.

The antenna shall track smoothly when the antenna receives consistent trajectory commands regardless of the interval between them.

2.3.7 Antenna Temperature Monitoring.

The antenna shall be capable of monitoring and logging the temperature of the structure at various points of the antenna structure.

2.3.8 Antenna Tilt Monitoring.

The antenna shall be capable of monitoring and logging the tilt of the antenna structure. This tilt data shall be able to be accessed by the VLBI system controller and by operators. The temperature data shall be able to be electronically accessed by the VLBI system controller and by operators.

2.3.9 Antenna Controller Data Log.

The antenna shall be capable of logging antenna controller unit commands/transactions. The log shall include transactions/operations performed by operators that involve movement of the antenna.

2.3.10 Antenna Controller Data Log Archival.

The antenna controller data log shall be maintained for up to 30 days and can be viewed and retrieved by operators.

2.4 Performance Requirements

2.4.1 RF Frequency Range.

The antenna structure frequency range shall be 2–32 GHz and 2-14 GHz for the feed and Low

Noise Amplifiers (LNAs).

2.4.2 Aperture Efficiency.

The antenna aperture efficiency shall be greater than 50.0 % (over 2-14 GHz) instantaneously.

2.4.3 Antenna Blind Pointing Accuracy.

The antenna blind pointing accuracy shall be < 0.1 half-power beam width (HPBW) at 32 GHz

(equivalent to < 20 arc sec ) for primary operating conditions; 0.3 HPBW at 32 GHz (equivalent to < 1 arc min) for secondary operating conditions. These limits apply both to pointing to an arbitrary position on the sky and to tracking at a specified rate.

2.4.4 Encoder Angular Accuracy.

The antenna encoder angular accuracy shall be 10.0 % (of the required pointing accuracy).

2.4.5 Antenna Path Length.

The vendor shall define the antenna path length. The antenna path length shall be the difference between the arrival times (converted to length by multiplying by the speed of light) of a plane wave front at the reference point and at the feed after passing through the antenna optics.

2.4.6 Antenna Path Length Stability.

The antenna path length difference shall be stable or able to be modeled, as a function of elevation and temperature, to less than 0.3 mm RMS for all pointing directions under primary operating conditions.

2.4.7 Antenna Surface Accuracy.

The antenna surface accuracy shall be <0.2 mm RSS combined error for primary and secondary reflectors for all pointing directions under the primary operating conditions.

2.4.8 Adjustments of Reflector Panels.

Provision shall be made for adjusting the height and tilt of the reflector panels if the surface accuracy cannot be guaranteed for 20 years without adjustment.

2.4.9 Slews per Day.

The antenna mount, drives, and antenna shall be able to withstand nearly continuous operation with more than 2,500 slews per day.

2.4.10 Antenna Slew Rate.

The antenna slew rate shall be greater than or equal to 12°/s (minimum) in azimuth and 6°/s

(goal) / 3.5°/s (minimum) in elevation.

2.4.11 Antenna Slew Accelerations.

The antenna slew acceleration shall be 3°/s/s (goal) / 2.5°/s/s (minimum).

2.4.12 Antenna Settling Time.

The antenna settling time shall be < 2 second from a maximum slew rate to a specified pointing accuracy for all modes of operations to include large slews of up to tens of degrees, small slews of 1 to 10 degrees and calibration scans of fractions of a degree. For all modes of operations, the antenna structural behavior shall not include any unnecessary jitter, vibration and/or oscillations.

2.4.13 Antenna Tilt Monitor Angular Range.

The antenna tilt monitor shall continuously monitor antenna tilt within an angular range of +/- 3 degrees with a resolution of 0.0001 degrees (repeatability 0.0003 degrees). The 0.0001 degree resolution is appropriate for our application (less than 0.1 mm in equivalent horizontal displacement).

Section 3 External Interface Requirements The external interfaces for the antenna are to the field system, signal chain, the VLBI network and the timing system. The antenna also interfaces with site specific items such as the antenna foundation that has an adaptor to interface the antenna to the foundation. There are also conduits that run data and power cables through the foundation from a services trench.

3.1 Field System (VLBI System Controller) Interface Requirements

SGP is adopting a new architecture where a centralized command center will be the hub for monitoring and control of the SGP geodesy systems including VLBI. Within the new paradigm it is conceivable that the VLBI system controller would reside within the command center. The

VLBI system controller would handle the processing of the IVS schedules, load the antenna commands into the antenna and execute the session remotely over a network connection.

Currently, the NVI Field System (FS) acts as the VLBI system controller for VLBI data acquisition hardware. The FS is used to change hardware settings and monitor hardware status by using Standard Notation for Astronomical Procedures (SNAP) commands. SNAP is a line-based command language which gives access to low-level data acquisition hardware. The FS interacts with the antenna controller and other antenna peripheral equipment such as an antenna temperature logger and a tilt meter. During a VLBI session the FS is in continuous communications with the antenna controller exchanging positioning (coordinates, cross-elevation, elevation, time and speed) commands and antenna position data. After the antenna has settled on a quasar source the field system interacts with the antenna controller to track the quasar while energy is collected by the antenna and the signal chain.

FS calibration tools are used to calibrate antenna pointing and gain. During calibration the antenna is commanded to make small slews (i.e., less than 1 degree) to measure gain and properly position the antenna to calibrate the antenna/signal chain using a signal source. During this mode of operation, the antenna controller will need to accelerate and settle the antenna to allow effective calibration of the source signal.

3.1.1 Transfer of Configuration, Control and Status Commands.

The antenna shall interface with a VLBI system controller to transfer configuration, control and status commands.

3.1.2 Transfer of Antenna Equipment Parameters.

The antenna shall interface with a VLBI system controller to provide critical component parameters such as temperature, tilt meter readout, and encoder readouts.

3.1.3 Antenna Control Calibration Tools.

The antenna shall interface with VLBI system controller calibrations tools to calibrate antenna pointing and gain.

3.1.4 Antenna Natural Coordinates.

The antenna shall accept, process and execute VLBI system controller epoch, position, and rate commands. These commanded values define a target trajectory for the antenna to follow. The commanded position is the target position at the commanded epoch. The target position evolves

(to or from the commanded position) at the commanded rate.

3.1.5 Software Limit Controls.

The antenna shall be protected in case the VLBI system controller commands the antenna to move past the antenna structural limits.

3.1.6 Encoder Status Command Precision.

The antenna shall accept sufficient precision for the commands from the VLBI system controller to cover at least the full resolution of the encoders and not lose precision in the propagation of the coordinates at that level.

3.1.7 Tracking When Disconnected from Control Interface.

The antenna shall continue to track according to the last command if the interface to the VLBI system controller is disconnected and/or reconnected.

3.1.8 Azimuth - Position of the Antenna.

The antenna shall identify azimuth positions of the antenna to the VLBI system controller.

3.1.9 Antenna Cable Wrap-Dead Man Switch.

The antenna shall command to enable/disable a “Dead Man Switch” (DMS) to take action if loss of positive control is detected by the antenna.

3.1.10 Antenna Cable Wrap-Time-Out Interval.

The time-out (interval) for detecting loss of control shall be settable to a value of a few seconds to a few tens of seconds, but typically a fixed value of about 30 seconds is useful. The actions available on timeout will minimally include “stop”, and “stow”.

3.1.11 Antenna Temperature Monitor Interface.

The antenna shall be capable of monitoring structure temperature. The temperature monitor shall have a RJ45 interface to connect to the VLBI system controller to transfer structure temperature data. As a minimum, the temperature data shall include time, location of the sensor, temperature and status of the sensor.

3.1.12 Antenna Tilt Monitor Interface.

The antenna shall be capable of monitoring antenna structure tilt. The tilt monitor shall have a

RJ45 interface to connect to the VLBI system controller to transfer tilt data.

3.2 Signal Chain Interface Requirements

The Signal Chain consists of the frontend, backend, noise and phase calibration, and cable delay measurement systems. The high performance cryogenic receiver front ends are based on the quad-ridge flared horn (QRFH), a dual linearly-polarized radio telescope feed and cryogenically cooled low noise amplifiers (LNAs). The signal chain interface is described in detail in SGP-VLBI-ICD-

002 Signal Chain Frontend Interface Control Document.

3.2.1 Signal Chain Interface Compatibility.

The antenna shall interface with the signal chain equipment as defined in the Signal Chain

Frontend Subsystem Interface Control Document (SGP-VLBI-ICD-0002). These signal chain interfaces include the signal chain feed, payload positioning assembly, cryogenics, electrical power, monitoring and control and signal chain frontend installation apparatus/procedures. Any proposed changes to this interface must be approved by NASA.

3.2.2 Payload Interface.

The antenna shall interface with the signal chain QRFH feed to transfer collected radio frequency

(RF) energy from quasar sources.

3.2.3 Feed Cone

NASA will supply the receiver as defined in the Signal Chain Frontend Subsystem Interface

Control Document (SGP-VLBI-ICD-0002), but an appropriate feed cone will be the responsibility of the vendor.

3.2.4 Subreflector Distance to the QRFH Feed Mating Plate.

The vendor shall provide the exact distance from the bottom mating plate (for the QRFH feed) to the antenna subreflector. The combination of the subreflector to mating plate distance and the mating plate to focal plane distance equals the antenna focal length.

3.2.5 Payload Assembly Interface.

The antenna shall provide a physical (i.e., mechanical and power) connections to the signal chain payload positioning assembly as defined in the Signal Chain Frontend Subsystem Interface

Document

3.2.6 Signal Chain Electrical Power.

The antenna shall provide an interface to connect power to the payload positioning assembly and signal chain frontend equipment that will be located in the hub and will be positioned inside the antenna feed tube.

3.2.7 Helium Compressor Electrical Power Connection.

The antenna shall provide an electrical interface to connect power to the compressor and supply a 220/480 VAC 3 phase delta 40/20 amperes source of power. This power connection shall be provided on a separate power and shall not be on the same feed as signal chain electronics, data communications equipment and antenna components.

3.2.8 Helium Compressor Mount.

The antenna shall mount and house the helium compressor. The signal chain helium compressor used at KPGO is a M700 Austin Scientific Cryopump Helium Compressor and is mounted on the antenna turning head. The helium compressor will be decided on by CDR.

3.2.9 Feed Wiring and Cryogenics Interface.

The antenna shall provide an interface to transfer helium hoses and data communications cables from the helium compressor to the signal chain frontend providing no obstruction to connect the helium compressor. The signal chain cryogenic subsystem is located in the hub and is positioned inside the antenna feed tube for operations.

3.2.10 Mounting of Signal Chain Equipment in Antenna.

The antenna shall provide space inside the antenna hub to mount signal chain equipment.

3.3 Network Interface Requirements

The VGOS VLBI network element provides the connectivity between the antenna and the operations building where the backend, cable calibration, VLBI system controller and timing equipment resides. The network allows for high speed connectivity to the correlator facilities and a lower speed connection to the internet to allow maintenance personnel to remotely access antenna equipment, access to data archives and remote command centers. The network also allows connectivity to other geodesy equipment like Satellite Laser Ranging (SLR) through a vector tie connection.

3.3.1 Data Communications Needs.

The vendor shall define the network interfaces to include protocol, connector type and data rates required for antenna operations.

3.3.2 Data Communication Equipment Mount.

The antenna shall provide space to mount data communications equipment inside the antenna.

The space shall accommodate network, power supplies, patch panels and UPS.

3.3.3 Data Communication Equipment Power.

The antenna shall provide power for the data communication equipment that is inside the antenna pedestal.

3.4 Timing Interface Requirements

The VGOS VLBI timing element provides timing across the entire VLBI system. The timing element consist of an atomic clock and GPS time. It provides Network Time Protocol (NTP), Simple Network Time Protocol which is distributed over the network to synchronize time for

VLBI system elements. The timing element provides 1 PPS, 5 MHz and 10 MHz timing sources as a time references.

3.4.1 Timing Needs.

The vendor shall define the timing requirements for antenna operations.

3.5 Electrical Interface Requirements

3.5.1 Facility Power Grid Interface.

The antenna shall provide an electrical power interface to the facility electrical power grid.

3.5.2 Power Distribution.

The antenna shall distribute electrical power to all antenna components and other equipment, including the signal chain and data communications equipment that resides in the antenna.

3.5.3 Electrical Power Outlets.

The antenna shall be outfitted with electrical power receptacles to accommodate power connections for data communications equipment, test equipment, laptops and signal chain equipment in the pedestal, antenna hub and on the external surface of the antenna.

3.5.4 Antenna Interior Lighting.

The antenna shall be outfitted with lights to illuminate the interior of the antenna pedestal and hub to enable personnel to safely perform activities inside the antenna.

3.5.5 Electrical Power Monitoring.

The antenna shall be capable of monitoring power quality and consumption of the power that is being distributed through the antenna’s electrical distribution panels.

3.5.6 Electrical Power Generator.

The antenna shall be capable of operating with an electrical generator to switch from battery power to generator power or local electrical power for up to 5 minutes.

3.5.7 System-Grounding Design.

The antenna shall be outfitted with a grounding system. Elements of the grounding system (i.e., cable trays and conduit for signal, power, or control cables) shall be installed and connected in accordance with industry best practices.

3.5.8 Lightning Protection.

The antenna shall be equipped with lightning rods and lightning ground conductors to protect the antenna. The lightning rods and ground conductors shall interface with the site’s grounding system.

3.6 Antenna Foundation Requirements

3.6.1 Construction Foundation Calculations

The vendor shall be responsible for the technical performance approval of the construction foundation calculations; drawings and integration of the antenna hardware.

3.6.2 Antenna to Foundation Connection.

The vendor shall provide an adaptor to connect the antenna pedestal to the antenna foundation.

3.6.3 Antenna Stowage.

The vendor shall provide physical connections on the antenna to secure and stow the antenna during periods of severe weather and/or power outage.

3.6.4 Antenna Foundation Needs.

Taking into account a NASA provided location-specific geotechnical report, the vendor shall specify requirements for its foundation, including footing depth, foundation materials, height above grade, minimum foundation area, grouting, etc.

3.6.5 Electrical Power and Data Conduits.

The antenna shall interface with the foundation to align the location of power and data conduits through the foundation to the pedestal in an optimum location to enable connection to power distribution panels, data communication equipment and routing of cables through cable trays, chases and cable wraps.

3.6 Human Interface Requirements

3.6.1 Personnel Interface.

The antenna shall provide an interface for maintenance and operations personnel to safely maintain and operate the antenna from within the antenna, external to the antenna-in close proximity and remotely.

3.6.2 Personnel Access.

The antenna shall provide an interface to include ladders, hatches, and equipment access panels for personnel to safely access the antenna and perform maintenance on antenna components, structure and signal chain equipment.

3.6.3 Signal Chain Installation and Maintenance.

The antenna shall provide an interface for maintenance personnel to safely install and maintain signal chain components.

3.6.4 Antenna Control Interface-Operations.

The antenna shall provide a graphical user interface (GUI) for the antenna control interface

(ACI) that allows operators to monitor antenna operations.

3.6.5 Antenna Control Interface-Activity Logs

The antenna shall provide an interface to access to antenna activity logs.

3.6.6 Antenna Control Interface-Diagnostic Tools

The antenna shall provide LRU-level diagnostic tools remotely and from within the antenna pedestal.

3.6.7 Antenna Control Interface-Remote Access

The antenna shall provide software to allow secure remote access to the antenna control unit and all antenna monitor/control software through the site’s network infrastructure for remote maintenance, troubleshooting and operations.

Section 4 Reliability/Maintainability/Availability Requirements

4.1.1 Reliability and Maintainability.

The vendor shall be compliant with NPD 8720.1, NASA Reliability and Maintainability (R&M)

Program Policy, NPD 8730.5, NASA Quality Assurance Program Policy and Software

Assurance and Software Safety per NASA-STD-8739.8, NASA Software Assurance Standard.

4.1.2 Lifetime.

The antenna mechanical structure and components aside from the motors and gearboxes shall have a useful lifetime of 20.0 years based on 365 days per year of operations.

4.1.3 Mean Time Between Failures (MTBF).

The antenna components shall have MTBF of 2 years or greater.

4.1.4 Mean Time to Repair (MTTR).

The antenna components shall have a MTTR of 1 day for components that have spares stored on site and 2 weeks for components that do not have spares onsite.

4.1.5 Downtime

The antenna shall have calculated downtime for repair and maintenance of less than 21 days per year.

4.1.6 Annual Maintenance Cost

The antenna shall have calculated annual maintenance cost of less than 10% of the capitol cost.

4.1.7 Spares Plan.

The vendor shall provide a spares lists that identify the recommended spares, the MTBF and

MTTR for item in the list and a recommendations as to the spare part/s that would be held locally at the site.

4.1.8 Maintenance Plan.

The vendor shall provide a recommended maintenance plan/procedures including maintenance periodicity for all antenna components.

4.1.9 Reliability and Maintainability Report.

The vendor shall provide a reliability and maintainability report for the proposed antenna down to the line replaceable unit (LRU). The report shall indicate the top level as well as the LRU, the

MTBF and the MTTR for each. Methods for the calculations shall be based upon MILHDBK-

217F, Notice 2.

http://www.sre.org/pubs/Mil-Hdbk-217F.pdf http://www.sre.org/pubs/Mil-Hdbk-217F.pdf

Section 5 Safety Requirements

5.1 Safety Training and Certification.

The vendor shall provide applicable safety training or certifications as required and requested.

Examples include Crane Operator, Qualified Rigger documentation, Aerial Platform or Powered

Industrial Truck Operator certifications, and Fall Protection End User.

5.1.1 Safety Data Sheets.

The vendor shall provide a copy of all safety data sheets and receive approval prior to bringing products onsite.

5.2 Safety-Guidance.

5.2.1 Federal, State and Local Regulations.

The vendor shall comply with federal, state, and local environmental regulations in the design and installation of antenna system.

5.2.2 NASA Safety Regulations.

The vendor shall comply with NASA Safety guidance per NPR 8715.3, NASA General Safety

Program Requirements and NASA-STD-8719.13C, NASA Software Safety Standard.

5.2.3 Lifting Devices and Equipment.

The vendor shall meet the requirements of 29 CFR 1926 -Subpart N – Cranes, Derricks, Hoists, Elevators, and Conveyors.

5.2.4 Pressure Vessel Systems -Safety Requirements.

All antenna related pressure vessel systems shall be designed in accordance with NASA-STD-

8719.17, NASA Requirements for Ground Based Pressure Vessels and Pressurized Systems. (if applicable)

5.2.5 System-Photo Documentation of Key Assemblies.

The vendor shall produce closeout photographic documentation of all (key) assemblies during the manufacturing process and of the final integrated configuration.

5.3 Safety-Operations

5.3.1 Control Panel Surface Safe Operating Temperature.

The antenna shall operate at an ambient temperature of 77 degrees Fahrenheit (°F), surface temperature of the control panels and operating controls shall be less than or equal to 113°F.

http://nodis3.gsfc.nasa.gov/displayDir.cfm?Internal_ID=N_PR_8715_003C_&page_name=main http://nodis3.gsfc.nasa.gov/displayDir.cfm?Internal_ID=N_PR_8715_003C_&page_name=main http://www.hq.nasa.gov/office/codeq/doctree/NS871913C.pdf https://www.osha.gov/pls/oshaweb/owastand.display_standard_group?p_toc_level=1&p_part_number=1926 http://www.hq.nasa.gov/office/codeq/doctree/871917.htm http://www.hq.nasa.gov/office/codeq/doctree/871917.htm

5.3.2 Aircraft Warning Lights.

The antenna shall have aircraft warning lights and other markings shall be installed. The location shall be at the highest point on the antenna structure and shall be distributed around the outside edge of the primary reflector not interfering with the RF path.

5.3.3 Warning Light-Antenna Start Up.

The antenna shall have warning light installed to notify personnel of antenna activation.

5.3.4 System-Operational Safety-Audible Alarm-Antenna Start Up.

The antenna shall have an audible alarm to notify personnel of antenna start-up.

5.4 Safety-Occupational

5.4.1 Safety Guards.

The antenna guards shall be installed for use as a cover or barrier to prevent access to hazardous equipment so there can be no contact with hazardous voltages, currents, high temperature, moving machinery, etc., during either operation, service, or maintenance.

5.4.2 Sharp Objects.

The antenna equipment shall have no sharp projections on cabinets, doors, and similar parts.

5.4.3 Voltage, Current, Thermal and Physical Hazards.

The antenna shall eliminate or control potential hazards that could result in personnel injury and/or damage to components or facilities through personnel error, component failure, or a combination of the two. For the purposes of this paragraph, specific hazards are defined as voltage, current, thermal, or physical hazards.

5.4.4 Fall Protection.

The antenna shall be designed to protect personnel from falls where working at heights is required. Anchor points and other fall protection engineering shall be installed in accordance with applicable ANSI Z359 Series.

5.5 Safety-Markings and Labels

5.5.1 Markings and Labels.

The antenna guards, barriers, access doors, covers, or plates shall be marked to indicate the hazard that may be reached upon removal of such devices.

5.5.2 Markings and Labels-Danger/Caution Signs.

The antenna shall have danger or caution signs, labels, and markings installed or attached to warn of specific hazards.

https://foiaelibrary.gsfc.nasa.gov/_assets/doclibBidder/tech_docs/41)%20GPR%208715.8.pdf https://foiaelibrary.gsfc.nasa.gov/_assets/doclibBidder/tech_docs/41)%20GPR%208715.8.pdf https://foiaelibrary.gsfc.nasa.gov/_assets/doclibBidder/tech_docs/41)%20GPR%208715.8.pdf https://foiaelibrary.gsfc.nasa.gov/_assets/doclibBidder/tech_docs/41)%20GPR%208715.8.pdf

5.5.3 Markings and Labels-Electrical Panels.

The antenna electrical panels shall be labeled and marked in accordance with NFPA 70 National

Electrical Code and NFPA 70E, Standard for Electrical Safety in the Workplace.

Section 6 Security Requirements

6.1 Security Guidance.

The antenna shall adhere to the technical security control requirements specified in NASA

Procedural Requirements (NPR) 2810.1A, Security of Information Technology.

6.1.1 Access Control.

The antenna shall restrict access to antenna related software, information and functions to authorized users.

6.1.2 Password.

The antenna shall require user id and password for access to antenna related software, functions and data.

Section 7 Functions to be performed by the Vendor

7.1 Project Management

7.1.1.1 Project Management Plans and Controls

The vendor shall establish and maintain management processes and controls required to deliver the contract items on schedule and in compliance with the contract requirements.

7.1.2 Project Management Plan (PMP)

The vendor shall prepare, deliver, and maintain a Project Management Plan (PMP). The MP shall serve as the authoritative document providing the management procedures for all activities necessary to meet the requirements of the SOW. The PMP shall describe the following at a minimum:

Vendor’s organization and internal lines of communication, Assignment of management and engineering responsibilities and duties, Project management structure, policies, and procedures, Resources plan for contract implementation, http://nodis3.gsfc.nasa.gov/displayDir.cfm?t=NPR&c=2810&s=1A http://nodis3.gsfc.nasa.gov/displayDir.cfm?t=NPR&c=2810&s=1A

7.1.3 Management Reporting

7.1.3.1 Bi-Weekly Meetings

The vendor shall support bi-weekly status and Project Milestone reviews with the SGP Team, via teleconference, for the life of each antenna production.

7.1.3.2 Monthly Status Reports

In addition the vendor shall support supplementary status reviews as designated by NASA and shall provide written monthly status reports that include: issues, risks and mitigation plans, progress against the established schedule, courses of action to correct schedule departures and problems, and near-term project plans.

7.1.3.3 Technical Interchange Meetings (TIM)

For each antenna, the vendor shall support Technical Interchange Meetings (TIM) between NASA technical personnel and vendor personnel. The TIMs shall be conducted within one month of each task award. The primary purpose of the TIM is to review the system design and resolve and issues concerning the development and delivery of the antenna. While not a formal Review, the TIM is where the vendor presents their ideas for antenna design and an open exchange between the vendor and the Government takes place.

7.1.4 Reviews

The vendor shall be responsible for planning, scheduling and conducting design reviews.

7.1.4.1 Preliminary Design Reviews (PDR)

A PDR shall be held after the first system’s TIM when the system design is ready for presentation but is not completely mature. The vendor shall present a clear, consistent design that addresses all of the VGOS antenna requirements and demonstrates that the system meets all requirements.

A PDR is only required for the first system.

7.1.4.2 Critical Design Review (CDR)

The CDR shall be held prior to the build of the first antenna system with delta CDRs held for each of the other systems. The vendor shall present a clear, consistent design that addresses all of the

VGOS antenna requirements and demonstrates that the system meets all requirements.

7.1.4.3 Factory Acceptance Test (FAT) and Review (FATR)

The FAT shall be performed at the vendor’s factory, by vendor personnel with the vendor’s test equipment. A formal Acceptance Test Plan (ATP) shall be generated by the vendor with NASA input that will specify each test to be performed, what is required to pass, and who performs the test based on the SOW requirements. The ATP must be approved by NASA prior to the beginning of FAT. A NASA representative must be present for a majority of FAT testing. NASA concurrence will be required to determine pass/fail on each FAT according to criteria in the FAT

Plan. At the FAT, the antenna capabilities shall be tested with a load that represents the mass characteristics of the SGP signal chain.

A FAT Review (FATR) will be held after the FAT on each antenna and NASA SGP personnel have had time to review the test results (approximately one week).

7.1.4.4 Pre-Ship Review (PSR)

A PSR will be held after the FATR on each antenna prior to shipment of the antenna to the SGP site. Any open actions identified at the FATR should be closed by the PSR or have a NASA approved plan for closure.

7.1.4.5 Initial Site Acceptance Testing (SAT) and Site Acceptance Test Review (SATR)

After passing the PSR, the vendor shall transport and install the antenna system to the corresponding SGP site. The vendor shall perform SAT verification with NASA support after installation of each antenna system delivery at each SGP site.

Any updates to the ATP must be approved by NASA prior to the beginning of SAT. The ATP shall specify each SAT to be performed, what is required to pass, and who performs the test based on the SOW requirements. A NASA representative must be present for a majority of SAT testing.

NASA concurrence will be required to determine pass/fail on each SAT according to criteria in the ATP.

The SAT is expected to be a subset of the tests demonstrated at the FAT. The vendor shall conduct the SAT verification testing and provide NASA with the data and their analysis of the system performance. At the SAT, the antenna capabilities shall be tested with a load that represents the mass characteristics of the SGP signal chain. Any antenna requirements that require the signal chain installed to be demonstrated shall be verified during the commissioning period.

A SATR will be held after the SAT on each antenna and NASA SGP personnel have had time to review the test results (approximately one week). The SATR represents the formal handover of the antenna to NASA, but final acceptance occurs after the commissioning period.

7.1.4.6 Operational Readiness Review (ORR)

NASA will begin integration with the signal chain after the successful completion of the SATR.

The vendor shall provide support on an as needed basis to complete the integration with the signal chain and end-to-end system testing as part of the commissioning period that is expected to last 3-

6 months. During this period, any remaining antenna requirements verification that require the signal chain will be performed according to the ATP. These tests may be performed by NASA personnel, the vendor, or both as described and agreed to in the ATP. NASA concurrence will be required to determine pass/fail on each commissioning test according to criteria in the ATP.

In addition, the vendor shall complete any open issues identified at the SATR and provide support for the resolution of any identified antenna related issues during commissioning.

A ORR will be held after successful completion of the commissioning period and represents the final NASA acceptance of the antenna.

7.1.5 Risk Management

7.1.5.1 Risk Identification.

The vendor shall identify programmatic, schedule and technical risks and describe how they will effectively manage/mitigate these risks on an ongoing basis throughout contract performance.

7.1.5.2 Risk Quantification

The vendor shall quantify risks with respect to the impact on development, production, integration, testing, performance, delivery, and schedule.

7.1.5.3 Risk Prioritization

The vendor shall assign a priority to identified risks and develop risk mitigation plans for risks considered medium or high priority.

7.1.5.4 Risk Reporting

The vendor shall report on the status and risk mitigation plans in the weekly status reviews and the written monthly reports.

7.1.6 Schedule and Cost Management

The vendor shall provide their plans and approach for the development and delivery of the task products complying with the major schedule milestones for each task. The vendor schedule shall be provided in either Microsoft Project format or a format compatible with Microsoft Project.

7.1.7 Logistics and Export Control

The vendor shall be responsible for the all aspects of the export process, including but not limited to the following:

A plan identifying export licenses required for performance, and exemptions and exceptions that apply

Determining what items (equipment, software, documentation, information, etc.) require an export license

Coordinating with the proper government agencies to ensure compliance with the appropriate US export control laws and/or regulations

Obtaining the required export licenses and Technical Assistance Agreements

Retaining all required export documentation for the required period of time after exportation

A status report of licenses obtained, including copies of licenses

A status report of…