urn:nasa:pds:context:instrument:rss.near 1.0 1.7.0.0 Product_Context 2016-10-01 1.0 extracted metadata from PDS3 catalog and modified to comply with PDS4 Information Model urn:nasa:pds:context:instrument_host:spacecraft.near::1.0 instrument_to_instrument_host Anderson, J.D., J.W. Armstrong, and E.L. Lau, Upper Limits for Gravitational Radiation from Supermassive Coalescing Binaries, Astrophysical Journal, 408, 287-292, 1993. reference.ANDERSONETAL1993 Asmar, S.W., and R.G. Herrera, Radio Science Handbook, JPL D-7938, Volume 4, Jet Propulsion Laboratory, Pasadena, CA, 22 January 1993. reference.ASMAR-HERRERA1993 Asmar, S. W., N. A. Renzetti, The Deep Space Network as an instrument for radio science research, NASA Technical Reports Server, 1993STIN...9521456A, 1993. reference.ASMAR-RENZETTI1993 Asmar, S.W., R.G. Herrera, and T. Priest, Radio Science Handbook, JPL D-7938, Volume 6, Jet Propulsion Laboratory, Pasadena, CA, 1995. reference.ASMARETAL1995 Deep Space Network / Flight Project Interface Design Book, Document 810-5, Jet Propulsion Laboratory, Pasadena, CA. reference.DSN810-5 Estabrook, F.B., and H.D. Wahlquist, Response of Doppler Spacecraft Tracking to Gravitational Radiation, Gen. Rel. Grav., 6, 439-447, 1995. reference.ESTABROOKETAL1995 DSN Geometry and Spacecraft Visibility, Document 810-5, Rev. D, Vol. 1, DSN/Flight Project Interface Design, Jet Propulsion Laboratory, Pasadena, CA, 1987. reference.GEO-10REVD Mars Global Surveyor Project, Telecommunications System Operations Reference Handbook, Version 2.1 (MGS 542-257), JPL Document D-14027, Jet Propulsion Laboratory, Pasadena, CA, 1996. reference.JPLD-14027 Tyler, G.L., G. Balmino, D.P. Hinson, W.L. Sjogren, D.E. Smith, R. Woo, S.W. Asmar, M.J. Connally, C.L. Hamilton, and R.A. Simpson, Radio Science Investigations with Mars Observer, Journal of Geophysical Research, 97, 7759-7779, 1992. reference.TYLERETAL1992 Woo, R., Spacecraft Radio Scintillation and Solar System Exploration, Wave Propagation in Random Media (Scintillation), Society of Photo-Optical Instrumentation Engineers, Bellingham, WA, 1993. reference.WOO1993 RADIO SCIENCE SUBSYSTEM Atmospheric Sciences not applicable not applicable Instrument Overview =================== The Near-Earth Asteroid Rendezvous (NEAR) Radio Science investigations utilized instrumentation with elements on the spacecraft and at the NASA Deep Space Network (DSN). Much of this was shared equipment, being used for routine telecommunications as well as for Radio Science. The performance and calibration of both the spacecraft and tracking stations directly affected the radio science data accuracy, and they played a major role in determining the quality of the results. The spacecraft part of the radio science instrument is described immediately below; that is followed by a description of the DSN (ground) part of the instrument. Instrument Specifications - Spacecraft ====================================== The Near-Earth Asteroid Rendezvous spacecraft telecommunications subsystem served as part of a radio science subsystem for investigations of asteroids 253 Mathilde and 433 Eros. Many details of the subsystem are unknown; its 'build date' is taken to be 1995-02-01, the date on which acceptance testing began at Motorola. Instrument Id : RSS Instrument Host Id : NEAR Pi Pds User Id : UNK Instrument Name : RADIO SCIENCE SUBSYSTEM Instrument Type : RADIO SCIENCE Build Date : 1995-02-01 Instrument Mass : UNK Instrument Length : UNK Instrument Width : UNK Instrument Height : UNK Instrument Manufacturer Name : Motorola Instrument Overview - Spacecraft ================================ The spacecraft radio system was constructed around a redundant pair of X-band Cassini Transponders. Other components included two redundant power amplifiers, two redundant diplexers, two redundant microstrip patch low-gain antennas (LGA), one microstrip patch medium-gain antenna (MGA) providing a fan beam and one high-gain antenna (HGA) dish with a diameter of 1.5 m. The X-band capability reduced plasma effects on radio signals by a factor of 10 compared with previous S-band systems, but absence of a dual-frequency capability (both S- and X-band) meant that plasma effects could not be estimated and removed from radio data. The spacecraft was capable of X-band uplink commanding and simultaneous X-band downlink telemetry. The transponder generated a downlink signal in either a 'coherent' or a 'non-coherent' mode, also known as the 'two-way' and 'one-way' modes, respectively. When operating in the coherent mode, the transponder behaved as a conventional transponder; its transmitted carrier frequency was derived coherently from the received uplink carrier frequency with a 'turn-around ratio' of 880/749. The nominal coherent and noncoherent downlink frequencies were 8438.1 MHz and 8435 MHz respectively. The HGA was a 1.5 m diameter dish of a Cassegrain design that was directed in the spacecraft's +Z direction. The gain was 40 dBic at 8.4 GHz (on Z axis). The 3 dB beamwith was 1.7 degrees. The MGA had a maximum gain of 18 dBic at 8.4 GHz (on Z axis) with a 3 dB beamwith of 8 x 40 degrees. The two LGAs were mounted forward and aft with their axes pointing in the +Z and -Z directions respectively. These LGAs had a gain of +5 to -10 dBic at 8.4 GHz over the hemispheric field of view. The MGA had a single polarization while the HGA and the two LGAs had dual, selectable, circular polarizations. NEAR telemetry data were sent to Earth at rates between 9 bits per second (bps) and 26.5 kilobits per second (kbps). Uplink data rates were either 7 or 125 bps. Science Objectives ================== The science objectives of this investigation were to determine the mass of Eros to better than 0.1%, to determine the bulk density of Eros to an accuracy level commensurate with the accuracy of the volume determination (~1%), and to investigate the interior homogeneity of the asteroid by determining high order gravity fields from the shape models and comparing these models with those determined directly from the spacecraft tracking data. Additional science objectives included the determination of the asteroid's moment of inertia matrix and its rotation state, placing upper limits upon any outgassing that may have occurred during its 100- year observational history, and determining the masses and orbits of any satellites discovered in orbit about Eros. During the 1997 June 27 NEAR spacecraft flyby of asteroid 253 Mathilde, the Doppler and range tracking data was used to solve for the mass of this asteroid. In combination with the volume estimate provided by the imaging team, the asteroid's bulk density (1.3 g/cm3) was determined [YEOMANSETAL1997]. The radio science objectives of this mission were more extensive than traditional gravity science for large solar system bodies and there were additional challenges to be overcome to meet those objectives. For example, the figure of Eros was very irregular and traditional spherical harmonics were no longer the obvious choice for gravity field analyses. In addition, the rotation state of the asteroid was not well known prior to the spacecraft's arrival and the spacecraft orbits about the asteroid were often near the plane-of-sky as seen from the Earth, thus limiting the power of the Doppler data to define the gravity field of Eros. Because of these technical challenges and additional ones dictated by the short lead time before launch and the modest budget associated with Discovery class missions, the NEAR radio science team relied upon experienced personnel who had already been tasked with navigating the NEAR spacecraft during the approach and orbiting phases of the mission. The success with which the NEAR Radio Science Team met its objectives depended upon a very close cooperative effort with the JPL Navigation Team. Operational Considerations - Spacecraft ======================================= Descriptions given here are for nominal performance. The spacecraft transponder system comprised redundant units, each with slightly different characteristics. As transponder units age, their performance changes slightly. Their performance also depends upon factors which were not always under the control of the NEAR Project. Calibration Description - Spacecraft ==================================== No information available. Platform Mounting Descriptions - Spacecraft =========================================== The spacecraft +Z axis vector was aligned with the HGA boresight perpendicular to the top surface of the spacecraft. The +Y axis vector ran through the power switching electronics box and the +X axis completed the orthogonal, right-handed, rectangular coordinate system. The axes of the two low gain antennas were in the +Z and -Z directions. The MGA boresight was along the +Z axis. Investigators ============= Team Leader for the NEAR Radio Science Team was D.K. Yeomans of the Jet Propulsion Laboratory (JPL). Members of the Team included Jon D. Giorgini (JPL), Alex Konopliv (JPL) and Jean-Pierre Barriot (CNES, France). Addition collaborative efforts were provided by members of the JPL navigation team including B.G. Williams, J.K. Miller, P. Antreasian, C. Helfrich, J.D. Giorgini and mission design personnel from the Johns Hopkins University's Applied Physics Laboratory (R. Farquhar, D. Dunham, and J. McAdams). Instrument Section / Operating Mode Descriptions - Spacecraft ============================================================= The NEAR radio system consisted of two sections, which could be operated in the following modes: Section Mode ------------------------------------------- Oscillator two-way (coherent) one-way (non-coherent) RF output low-gain antenna (choice from two) medium-gain antenna high-gain antenna Instrument Overview - DSN ========================= Three Deep Space Communications Complexes (DSCCs) (near Barstow, CA; Canberra, Australia; and Madrid, Spain) comprise the DSN tracking network. Each complex is equipped with several antennas [including at least one each 70-m, 34-m High Efficiency (HEF), and 34-m Beam WaveGuide (BWG)], associated electronics, and operational systems. Primary activity at each complex is radiation of commands to and reception of telemetry data from active spacecraft. Transmission and reception is possible in several radio-frequency bands, the most common being S-band (nominally a frequency of 2100-2300 MHz or a wavelength of 14.2-13.0 cm) and X-band (7100-8500 MHz or 4.2-3.5 cm). Transmitter output powers of up to 400 kW are available. Ground stations have the ability to transmit coded and uncoded waveforms which can be echoed by distant spacecraft. Analysis of the received coding allows navigators to determine the distance to the spacecraft; analysis of Doppler shift on the carrier signal allows estimation of the line-of-sight spacecraft velocity. Range and Doppler measurements are used to calculate the spacecraft trajectory and to infer gravity fields of objects near the spacecraft. Ground stations can record spacecraft signals that have propagated through or been scattered from target media. Measurements of signal parameters after wave interactions with surfaces, atmospheres, rings, and plasmas are used to infer physical and electrical properties of the target. Principal investigators vary from experiment to experiment. See the corresponding section of the spacecraft instrument description or the data set description for specifics. The Deep Space Network is managed by the Jet Propulsion Laboratory of the California Institute of Technology for the U.S. National Aeronautics and Space Administration. Specifications include: Instrument Id : RSS Instrument Host Id : DSN Pi Pds User Id : N/A Instrument Name : RADIO SCIENCE SUBSYSTEM Instrument Type : RADIO SCIENCE Build Date : N/A Instrument Mass : N/A Instrument Length : N/A Instrument Width : N/A Instrument Height : N/A Instrument Manufacturer Name : N/A Subsystems - DSN ================ The Deep Space Communications Complexes (DSCCs) are an integral part of Radio Science instrumentation, along with the spacecraft Radio Frequency Subsystem. Their system performance directly determines the degree of success of Radio Science investigations, and their system calibration determines the degree of accuracy in the results of the experiments. The following paragraphs describe the functions performed by the individual subsystems of a DSCC. Each DSCC includes a set of antennas, a Signal Processing Center (SPC), and communication links to the Jet Propulsion Laboratory (JPL). The general configuration is illustrated below; antennas (Deep Space Stations, or DSS -- a term carried over from earlier times when antennas were individually instrumented) are listed in the table. -------- -------- -------- -------- -------- : DSS 25 : : DSS 27 : : DSS 14 : : DSS 15 : : DSS 16 : :34-m BWG: :34-m HSB: : 70-m : :34-m HEF: : 26-m : -------- -------- -------- -------- -------- : : : : : : v v : v : --------- : --------- --------->:GOLDSTONE:<---------- :EARTH/ORB: : SPC 10 :<-------------->: LINK : --------- --------- : SPC :<-------------->: 26-M : : COMM : ------>: COMM : --------- : --------- : : : v : v ------ --------- : --------- : NOCC :<--->: JPL :<------- : : ------ : CENTRAL : : GSFC : ------ : COMM : : NASCOMM : : MCCC :<--->: TERMINAL:<-------------->: : ------ --------- --------- ^ ^ : : CANBERRA (SPC 40) <---------------- : : MADRID (SPC 60) <---------------------- GOLDSTONE CANBERRA MADRID Antenna SPC 10 SPC 40 SPC 60 -------- --------- -------- -------- 26-m DSS 16 DSS 46 DSS 66 34-m HEF DSS 15 DSS 45 DSS 65 34-m BWG DSS 24 DSS 34 DSS 54 DSS 25 DSS 26 34-m HSB DSS 27 DSS 28 70-m DSS 14 DSS 43 DSS 63 Developmental DSS 13 Subsystem interconnections at each DSCC are shown in the diagram below, and they are described in the sections that follow. The Monitor and Control Subsystem is connected to all other subsystems; the Test Support Subsystem can be. ----------- ------------------ --------- --------- :TRANSMITTER: : : : TRACKING: : COMMAND : : SUBSYSTEM :-: RECEIVER/EXCITER :-:SUBSYSTEM:-:SUBSYSTEM:- ----------- : : --------- --------- : : : SUBSYSTEM : : : : ----------- : : --------------------- : : MICROWAVE : : : : TELEMETRY : : : SUBSYSTEM :-: :-: SUBSYSTEM :- ----------- ------------------ --------------------- : : : ----------- ----------- --------- -------------- : : ANTENNA : : MONITOR : : TEST : : DIGITAL : : : SUBSYSTEM : :AND CONTROL: : SUPPORT : :COMMUNICATIONS:- ----------- : SUBSYSTEM : :SUBSYSTEM: : SUBSYSTEM : ----------- --------- -------------- DSCC Monitor and Control Subsystem ---------------------------------- The DSCC Monitor and Control Subsystem (DMC) is part of the Monitor and Control System (MON) which also includes the ground communications Central Communications Terminal and the Network Operations Control Center (NOCC) Monitor and Control Subsystem. The DMC is the center of activity at a DSCC. The DMC receives and archives most of the information from the NOCC needed by the various DSCC subsystems during their operation. Control of most of the DSCC subsystems, as well as the handling and displaying of any responses to control directives and configuration and status information received from each of the subsystems, is done through the DMC. The effect of this is to centralize the control, display, and archiving functions necessary to operate a DSCC. Communication among the various subsystems is done using a Local Area Network (LAN) hooked up to each subsystem via a network interface unit (NIU). DMC operations are divided into two separate areas: the Complex Monitor and Control (CMC) and the Link Monitor and Control (LMC). The primary purpose of the CMC processor for Radio Science support is to receive and store all predict sets transmitted from NOCC such as Radio Science, antenna pointing, tracking, receiver, and uplink predict sets and then, at a later time, to distribute them to the appropriate subsystems via the LAN. Those predict sets can be stored in the CMC for a maximum of three days under normal conditions. The CMC also receives, processes, and displays event/alarm messages; maintains an operator log; and produces tape labels for the DSP. Assignment and configuration of the LMCs is done through the CMC; to a limited degree the CMC can perform some of the functions performed by the LMC. There are two CMCs (one on-line and one backup) and three LMCs at each DSCC The backup CMC can function as an additional LMC if necessary. The LMC processor provides the operator interface for monitor and control of a link -- a group of equipment required to support a spacecraft pass. For Radio Science, a link might include the DSCC Spectrum Processing Subsystem (DSP) (which, in turn, can control the SSI), or the Tracking Subsystem. The LMC also maintains an operator log which includes operator directives and subsystem responses. One important Radio Science specific function that the LMC performs is receipt and transmission of the system temperature and signal level data from the PPM for display at the LMC console and for inclusion in Monitor blocks. These blocks are recorded on magnetic tape as well as appearing in the Mission Control and Computing Center (MCCC) displays. The LMC is required to operate without interruption for the duration of the Radio Science data acquisition period. The Area Routing Assembly (ARA), which is part of the Digital Communications Subsystem, controls all data communication between the stations and JPL. The ARA receives all required data and status messages from the LMC/CMC and can record them to tape as well as transmit them to JPL via data lines. The ARA also receives predicts and other data from JPL and passes them on to the CMC. DSCC Antenna Mechanical Subsystem --------------------------------- Multi-mission Radio Science activities require support from the 70-m, 34-m HEF, and 34-m BWG antenna subnets. The antennas at each DSCC function as large-aperture collectors which, by double reflection, cause the incoming radio frequency (RF) energy to enter the feed horns. The large collecting surface of the antenna focuses the incoming energy onto a subreflector, which is adjustable in both axial and angular position. These adjustments are made to correct for gravitational deformation of the antenna as it moves between zenith and the horizon; the deformation can be as large as 5 cm. The subreflector adjustments optimize the channeling of energy from the primary reflector to the subreflector and then to the feed horns. The 70-m and 34-m HEF antennas have 'shaped' primary and secondary reflectors, with forms that are modified paraboloids. This customization allows more uniform illumination of one reflector by another. The BWG reflector shape is ellipsoidal. On the 70-m antennas, the subreflector directs received energy from the antenna onto a dichroic plate, a device which reflects S-band energy to the S-band feed horn and passes X-band energy through to the X-band feed horn. In the 34-m HEF, there is one 'common aperture feed,' which accepts both frequencies without requiring a dichroic plate. In the 34-m BWG, a series of small mirrors (approximately 2.5 meters in diameter) directs microwave energy from the subreflector region to a collection area at the base of the antenna -- typically in a pedestal room. A retractable dichroic reflector separates S- and X-band on some BWG antennas or X- and Ka-band on others. RF energy to be transmitted into space by the horns is focused by the reflectors into narrow cylindrical beams, pointed with high precision (either to the dichroic plate or directly to the subreflector) by a series of drive motors and gear trains that can rotate the movable components and their support structures. The different antennas can be pointed by several means. Two pointing modes commonly used during tracking passes are CONSCAN and 'blind pointing.' With CONSCAN enabled and a closed loop receiver locked to a spacecraft signal, the system tracks the radio source by conically scanning around its position in the sky. Pointing angle adjustments are computed from signal strength information (feedback) supplied by the receiver. In this mode the Antenna Pointing Assembly (APA) generates a circular scan pattern which is sent to the Antenna Control System (ACS). The ACS adds the scan pattern to the corrected pointing angle predicts. Software in the receiver-exciter controller computes the received signal level and sends it to the APA. The correlation of scan position with the received signal level variations allows the APA to compute offset changes which are sent to the ACS. Thus, within the capability of the closed-loop control system, the scan center is pointed precisely at the apparent direction of the spacecraft signal source. An additional function of the APA is to provide antenna position angles and residuals, antenna control mode/status information, and predict-correction parameters to the Area Routing Assembly (ARA) via the LAN, which then sends this information to JPL via the Ground Communications Facility (GCF) for antenna status monitoring. During periods when excessive signal level dynamics or low received signal levels are expected (e.g., during an occultation experiment), CONSCAN should not be used. Under these conditions, blind pointing (CONSCAN OFF) is used, and pointing angle adjustments are based on a predetermined Systematic Error Correction (SEC) model. Independent of CONSCAN state, subreflector motion in at least the z-axis may introduce phase variations into the received Radio Science data. For that reason, during certain experiments, the subreflector in the 70-m and 34-m HEFs may be frozen in the z-axis at a position (often based on elevation angle) selected to minimize phase change and signal degradation. This can be done via Operator Control Inputs (OCIs) from the LMC to the Subreflector Controller (SRC) which resides in the alidade room of the antennas. The SRC passes the commands to motors that drive the subreflector to the desired position. Pointing angles for all antenna types are computed by the NOCC Support System (NSS) from an ephemeris provided by the flight project. These predicts are received and archived by the CMC. Before each track, they are transferred to the APA, which transforms the direction cosines of the predicts into AZ-EL coordinates. The LMC operator then downloads the antenna predict points to the antenna-mounted ACS computer along with a selected SEC model. The pointing predicts consist of time-tagged AZ-EL points at selected time intervals along with polynomial coefficients for interpolation between points. The ACS automatically interpolates the predict points, corrects the pointing predicts for refraction and subreflector position, and adds the proper systematic error correction and any manually entered antenna offsets. The ACS then sends angular position commands for each axis at the rate of one per second. In the 70-m and 34-m HEF, rate commands are generated from the position commands at the servo controller and are subsequently used to steer the antenna. When not using binary predicts (the routine mode for spacecraft tracking), the antennas can be pointed using 'planetary mode' -- a simpler mode which uses right ascension (RA) and declination (DEC) values. These change very slowly with respect to the celestial frame. Values are provided to the station in text form for manual entry. The ACS quadratically interpolates among three RA and DEC points which are on one-day centers. A third pointing mode -- sidereal -- is available for tracking radio sources fixed with respect to the celestial frame. Regardless of the pointing mode being used, a 70-m antenna has a special high-accuracy pointing capability called 'precision' mode. A pointing control loop derives the main AZ-EL pointing servo drive error signals from a two- axis autocollimator mounted on the Intermediate Reference Structure. The autocollimator projects a light beam to a precision mirror mounted on the Master Equatorial drive system, a much smaller structure, independent of the main antenna, which is exactly positioned in HA and DEC with shaft encoders. The autocollimator detects elevation/cross- elevation errors between the two reference surfaces by measuring the angular displacement of the reflected light beam. This error is compensated for in the antenna servo by moving the antenna in the appropriate AZ-EL direction. Pointing accuracies of 0.004 degrees (15 arc seconds) are possible in 'precision' mode. The 'precision' mode is not available on 34-m antennas -- nor is it needed, since their beamwidths are twice as large as on the 70-m antennas. DSCC Antenna Microwave Subsystem -------------------------------- 70-m Antennas: Each 70-m antenna has three feed cones installed in a structure at the center of the main reflector. The feeds are positioned 120 degrees apart on a circle. Selection of the feed is made by rotation of the subreflector. A dichroic mirror assembly, half on the S-band cone and half on the X-band cone, permits simultaneous use of the S- and X-band frequencies. The third cone is devoted to R&D and more specialized work. The Antenna Microwave Subsystem (AMS) accepts the received S- and X-band signals at the feed horn and transmits them through polarizer plates to an orthomode transducer. The polarizer plates are adjusted so that the signals are directed to a pair of redundant amplifiers for each frequency, thus allowing simultaneous reception of signals in two orthogonal polarizations. For S-band these are two Block IVA S-band Traveling Wave Masers (TWMs); for X-band the amplifiers are Block IIA TWMs. 34-m HEF Antennas: The 34-m HEF uses a single feed for both S- and X-band. Simultaneous S- and X-band receive as well as X-band transmit is possible thanks to the presence of an S/X 'combiner' which acts as a diplexer. For S-band, RCP or LCP is user selected through a switch so neither a polarizer nor an orthomode transducer is needed. X-band amplification options include two Block II TWMs or an HEMT Low Noise Amplifier (LNA). S-band amplification is provided by an FET LNA. 34-m BWG Antennas: These antennas use feeds and low-noise amplifiers (LNA) in the pedestal room, which can be switched in and out as needed. Typically the following modes are available: 1. downlink non-diplexed path (RCP or LCP) to LNA-1, with uplink in the opposite circular polarization; 2. downlink non-diplexed path (RCP or LCP) to LNA-2, with uplink in the opposite circular polarization 3. downlink diplexed path (RCP or LCP) to LNA-1, with uplink in the same circular polarization 4. downlink diplexed path (RCP or LCP) to LNA-2, with uplink in the same circular polarization For BWG antennas with dual-band capabilities (e.g., DSS 25) and dual LNAs, each of the above four modes can be used in a single-frequency or dual-frequency configuration. Thus, for antennas with the most complete capabilities, there are sixteen possible ways to receive at a single frequency (2 polarizations, 2 waveguide path choices, 2 LNAs, and 2 bands). DSCC Receiver-Exciter Subsystem ------------------------------- The Receiver-Exciter Subsystem is composed of three groups of equipment: the closed-loop receiver group, the open-loop receiver group, and the RF monitor group. This subsystem is controlled by the Receiver-Exciter Controller (REC) which communicates directly with the DMC for predicts and OCI reception and status reporting. The exciter generates the S-band signal (or X-band for the 34-m HEF only) which is provided to the Transmitter Subsystem for the spacecraft uplink signal. It is tunable under command of the Digitally Controlled Oscillator (DCO) which receives predicts from the Metric Data Assembly (MDA). The diplexer in the signal path between the transmitter and the feed horn for all three antennas (used for simultaneous transmission and reception) may be configured such that it is out of the received signal path (in listen-only or bypass mode) in order to improve the signal-to-noise ratio in the receiver system. Closed Loop Receivers: The Block V receiver-exciter at the 70-m stations allows for two receiver channels, each capable of L-Band (e.g., 1668 MHz frequency or 18 cm wavelength), S-band, or X-band reception, and an S-band exciter for generation of uplink signals through the low-power or high-power transmitter. The closed-loop receivers provide the capability for rapid acquisition of a spacecraft signal and telemetry lockup. In order to accomplish acquisition within a short time, the receivers are predict driven to search for, acquire, and track the downlink automatically. Rapid acquisition precludes manual tuning though that remains as a backup capability. The subsystem utilizes FFT analyzers for rapid acquisition. The predicts are NSS generated, transmitted to the CMC which sends them to the Receiver-Exciter Subsystem where two sets can be stored. The receiver starts acquisition at uplink time plus one round-trip-light-time or at operator specified times. The receivers may also be operated from the LMC without a local operator attending them. The receivers send performance and status data, displays, and event messages to the LMC. Either the exciter synthesizer signal or the simulation (SIM) synthesizer signal is used as the reference for the Doppler extractor in the closed-loop receiver systems, depending on the spacecraft being tracked (and Project guidelines). The SIM synthesizer is not ramped; instead it uses one constant frequency, the Track Synthesizer Frequency (TSF), which is an average frequency for the entire pass. The closed-loop receiver AGC loop can be configured to one of three settings: narrow, medium, or wide. It will be configured such that the expected amplitude changes are accommodated with minimum distortion. The loop bandwidth (2BLo) will be configured such that the expected phase changes can be accommodated while maintaining the best possible loop SNR. Open-Loop Receivers: The Radio Science Open-Loop Receiver (OLR) is a dedicated four channel, narrow-band receiver which provides amplified and downconverted video band signals to the DSCC Spectrum Processing Subsystem (DSP); it sometimes goes by the designation 'RIV'. The OLR utilizes a fixed first Local Oscillator (LO) frequency and a tunable second LO frequency to minimize phase noise and improve frequency stability. The OLR consists of an RF-to-IF downconverter located at the feed , an IF selection switch (IVC), and a Radio Science IF-VF downconverter (RIV) located in the SPC. The RF-IF downconverters in the 70-m antennas are equipped for four IF channels: S-RCP, S-LCP, X-RCP, and X-LCP. The 34-m HEF stations are equipped with a two-channel RF-IF: S-band and X-band. The 34-m BWG stations vary in their capabilities. The IVC switches the IF input among the antennas. The RIV contains the tunable second LO, a set of video bandpass filters, IF attenuators, and a controller (RIC). The LO tuning is done via DSP control of the POCA/PLO combination based on a predict set. The POCA is a Programmable Oscillator Control Assembly and the PLO is a Programmable Local Oscillator (commonly called the DANA synthesizer). The bandpass filters are selectable via the DSP. The RIC provides an interface between the DSP and the RIV. It is controlled from the LMC via the DSP. The RIC selects the filter and attenuator settings and provides monitor data to the DSP. The RIC could also be manually controlled from the front panel in case the electronic interface to the DSP is lost. RF Monitor -- SSI and PPM: The RF monitor group of the Receiver-Exciter Subsystem provides spectral measurements using the Spectral Signal Indicator (SSI) and measurements of the received channel system temperature and spacecraft signal level using the Precision Power Monitor (PPM). The SSI provides a local display of the received signal spectrum at a dedicated terminal at the DSCC and routes these same data to the DSP which routes them to NOCC for remote display at JPL for real-time monitoring and RIV/DSP configuration verification. These displays are used to validate Radio Science Subsystem data at the DSS, NOCC, and Mission Support Areas. The SSI configuration is controlled by the DSP and a duplicate of the SSI spectrum appears on the LMC via the DSP. During real-time operations the SSI data also serve as a quick-look science data type for Radio Science experiments. The PPM measures system noise temperatures (SNT) using a Noise Adding Radiometer (NAR) and downlink signal levels using the Signal Level Estimator (SLE). The PPM accepts its input from the closed-loop receiver. The SNT is measured by injecting known amounts of noise power into the signal path and comparing the total power with the noise injection 'on' against the total power with the noise injection 'off.' That operation is based on the fact that receiver noise power is directly proportional to temperature; thus measuring the relative increase in noise power due to the presence of a calibrated thermal noise source allows direct calculation of SNT. Signal level is measured by calculating an FFT to estimate the SNR between the signal level and the receiver noise floor where the power is known from the SNT measurements. There is one PPM controller at the SPC which is used to control all SNT measurements. The SNT integration time can be selected to represent the time required for a measurement of 30K to have a one-sigma uncertainty of 0.3K or 1%. DSCC Transmitter Subsystem -------------------------- The Transmitter Subsystem accepts the S-band frequency exciter signal from the Receiver-Exciter Subsystem exciter and amplifies it to the required transmit output level. The amplified signal is routed via the diplexer through the feed horn to the antenna and then focused and beamed to the spacecraft. The Transmitter Subsystem power capabilities range from 18 kw to 400 kw. Power levels above 18 kw are available only at 70-m stations. DSCC Tracking Subsystem ----------------------- The Tracking Subsystem primary functions are to acquire and maintain communications with the spacecraft and to generate and format radiometric data containing Doppler and range. The DSCC Tracking Subsystem (DTK) receives the carrier signals and ranging spectra from the Receiver-Exciter Subsystem. The Doppler cycle counts are counted, formatted, and transmitted to JPL in real time. Ranging data are also transmitted to JPL in real time. Also contained in these blocks is the AGC information from the Receiver-Exciter Subsystem. The Radio Metric Data Conditioning Team (RMDCT) at JPL produces an Archival Tracking Data File (ATDF) which contains Doppler and ranging data. In addition, the Tracking Subsystem receives from the CMC frequency predicts (used to compute frequency residuals and noise estimates), receiver tuning predicts (used to tune the closed-loop receivers), and uplink tuning predicts (used to tune the exciter). From the LMC, it receives configuration and control directives as well as configuration and status information on the transmitter, microwave, and frequency and timing subsystems. The Metric Data Assembly (MDA) controls all of the DTK functions supporting the uplink and downlink activities. The MDA receives uplink predicts and controls the uplink tuning by commanding the DCO. The MDA also controls the Sequential Ranging Assembly (SRA). It formats the Doppler and range measurements and provides them to the GCF for transmission to NOCC. The Sequential Ranging Assembly (SRA) measures the round trip light time (RTLT) of a radio signal traveling from a ground tracking station to a spacecraft and back. From the RTLT, phase, and Doppler data, the spacecraft range can be determined. A coded signal is modulated on an uplink carrier and transmitted to the spacecraft where it is detected and transponded back to the ground station. As a result, the signal received at the tracking station is delayed by its round trip through space and shifted in frequency by the Doppler effect due to the relative motion between the spacecraft and the tracking station on Earth. DSCC Spectrum Processing Subsystem (DSP) ---------------------------------------- The DSCC Spectrum Processing Subsystem (DSP) located at the SPC digitizes and records the narrowband output data from the RIV. It consists of a Narrow Band Occultation Converter (NBOC) containing Analog-to-Digital Converters (ADCs), a ModComp CLASSIC computer processor called the Spectrum Processing Assembly (SPA), and several magnetic tape drives. Magnetic tapes containing DSP output are known as Original Data Records (ODRs). The DSP was originally operated through the LMC. During 1996-97 a remote operations capability was developed by the JPL Radio Science systems Group so that the DSP could be operated from JPL. Using the SPA-Radioscience (SPA-R) software, the DSP allows for real-time frequency and time offsets (while in RUN mode) and, if necessary, snap tuning between the two frequency ranges transmitted by the spacecraft: coherent and non-coherent. The DSP receives Radio Science frequency predicts from the CMC, allows for multiple predict set archiving (up to 60 sets) at the SPA, and allows for manual predict generation and editing. It accepts configuration and control data from the LMC (or remote operations console), provides display data to the LMC (or remote operations console), and transmits the signal spectra from the SSI as well as status information to NOCC and the Project Mission Support Area (MSA) via the GCF data lines. The DSP records the digitized narrowband samples and the supporting header information (i.e., time tags, POCA frequencies, etc.) on 9-track magnetic tapes in 6250 or 1600 bpi GCR format and/or on a local disk for later transmission to JPL. Through the DSP-RIC interface the DSP controls the RIV filter selection and attenuation levels. It also receives RIV performance monitoring via the RIC. In case of failure of the DSP-RIC interface, the RIV can be controlled manually from the front panel. All the RIV and DSP control parameters and configuration directives are stored in the SPA in a macro-like file called an 'experiment directive' table. A number of default directives exist in the DSP for the major Radio Science experiments. Operators can create their own table entries. Items such as verification of the configuration of the prime open-loop recording subsystem, the selection of the required predict sets, and proper system performance prior to the recording periods will be checked in real-time at JPL via the NOCC displays using primarily the remote SSI display at NOCC and the NRV displays. Because of this, transmission of the DSP/SSI monitor information is enabled prior to the start of recording. The specific run time and tape recording times will be identified in the Sequence of Events (SOE) and/or DSN Keyword File. The DSP can be used to duplicate ODRs. It also has the capability to play back a certain section of the recorded data after conclusion of the recording periods. DSCC Frequency and Timing Subsystem ----------------------------------- The Frequency and Timing Subsystem (FTS) provides all frequency and timing references required by the other DSCC subsystems. It contains four frequency standards of which one is prime and the other three are backups. Selection of the prime standard is done via the CMC. Of these four standards, two are hydrogen masers followed by clean-up loops (CUL) and two are cesium standards. These four standards all feed the Coherent Reference Generator (CRG) which provides the frequency references used by the rest of the complex. It also provides the frequency reference to the Master Clock Assembly (MCA) which in turn provides time to the Time Insertion and Distribution Assembly (TID) which provides UTC and SIM-time to the complex. JPL's ability to monitor the FTS at each DSCC is limited to the MDA calculated Doppler pseudo-residuals, the Doppler noise, the SSI, and to a system which uses the Global Positioning System (GPS). GPS receivers at each DSCC receive a one-pulse-per-second pulse from the station's (hydrogen maser referenced) FTS and a pulse from a GPS satellite at scheduled times. After compensating for the satellite signal delay, the timing offset is reported to JPL where a database is kept. The clock offsets stored in the JPL database are given in microseconds; each entry is a mean reading of measurements from several GPS satellites and a time tag associated with the mean reading. The clock offsets provided include those of SPC 10 relative to UTC (NIST), SPC 40 relative to SPC 10, etc. Optics - DSN ============ Performance of DSN ground stations depends primarily on size of the antenna and capabilities of electronics. These are summarized in the following set of tables. Note that 64-m antennas were upgraded to 70-m between 1986 and 1989. Beamwidth is half-power full angular width. Polarization is circular; L denotes left circular polarization (LCP), and R denotes right circular polarization (RCP). DSS S-Band Characteristics 70-m 34-m 34-m Transmit BWG HEF -------- ----- ----- ----- Frequency (MHz) 2110- 2025- N/A 2120 2120 Wavelength (m) 0.142 0.142 N/A Ant Gain (dBi) 62.7 56.1 N/A Beamwidth (deg) 0.119 N/A N/A Polarization L or R L or R N/A Tx Power (kW) 20-400 20 N/A Receive ------- Frequency (MHz) 2270- 2270- 2200- 2300 2300 2300 Wavelength (m) 0.131 0.131 0.131 Ant Gain (dBi) 63.3 56.7 56.0 Beamwidth (deg) 0.108 N/A 0.24 Polarization L & R L or R L or R System Temp (K) 20 31 38 DSS X-Band Characteristics 70-m 34-m 34-m Transmit BWG HEF -------- ----- ----- ----- Frequency (MHz) 8495 7145- 7145- 7190 7190 Wavelength (m) 0.035 0.042 0.042 Ant Gain (dBi) 74.2 66.9 67 Beamwidth (deg) N/A 0.074 Polarization L or R L or R L or R Tx Power (kW) 360 20 20 Receive ------- Frequency (MHz) 8400- 8400- 8400- 8500 8500 8500 Wavelength (m) 0.036 0.036 0.036 Ant Gain (dBi) 74.2 68.1 68.3 Beamwidth (deg) 0.031 N/A 0.063 Polarization L & R L & R L & R System Temp (K) 20 30 20 NB: X-band 70-m transmitting parameters are given at 8495 MHz, the frequency used by the Goldstone planetary radar system. For telecommunications, the transmitting frequency would be in the range 7145-7190 MHz, the power would typically be 20 kW, and the gain would be about 72.6 dB (70-m antenna). When ground transmitters are used in spacecraft radio science experiments, the details of transmitter and antenna performance rarely impact the results. Electronics - DSN ================= DSCC Open-Loop Receiver (RIV) ----------------------------- The open loop receiver block diagram shown below is for the RIV system at 70-m and 34-m HEF and BWG antenna sites. Input signals at both S- and X-band are mixed to approximately 300 MHz by fixed-frequency local oscillators near the antenna feed. Based on a tuning prediction file, the POCA controls the DANA synthesizer, the output of which (after multiplication) mixes the 300 MHz IF to 50 MHz for amplification. These signals in turn are down converted and passed through additional filters until they yield output with bandwidths up to 45 kHz. The Output is digitally sampled and either written to magnetic tape or electronically transferred for further analysis. S-Band X-Band 2295 MHz 8415 MHz Input Input : : v v --- --- --- --- : X :<--:x20:<--100 MHz 100 MHz-->:x81:-->: X : --- --- --- --- : : 295: :315 MHz: :MHz v v --- -- 33.1818 --- --- : X :<--:x3:<------ MHz ------>:x11:-->: X : --- -- :115 : --- --- : :MHz : : : : : : 50: 71.8181 --- --- :50 MHz: MHz->: X : : X :<-10MHz :MHz v --- --- v --- ^ ^ --- : X :<--60 MHz : : 60 MHz-->: X : --- : approx : --- : 9.9 : 43.1818 MHz : 9.9 : : MHz ------------- MHz : : : ^ : : 10: v : v :10 MHz: --- ---------- --- :MHz :------>: X : : DANA : : X :<------: : --- :Synthesizr: --- : : : ---------- : : v v ^ v v ------- ------- : ------- ------- :Filters: :Filters: ---------- :Filters: :Filters: :3,4,5,6: : 1,2 : : POCA : : 1,2 : :3,4,5,6: ------- ------- :Controller: ------- ------- : : ---------- : : 10: :0.1 0.1: :10 MHz: :MHz MHz: :MHz v v v v --- --- --- --- 10 MHz -->: X : : X :<------ 0.1 MHz ------->: X : : X :<-- --- --- --- --- : : : : : 10 MHz v v v v Output Output Output Output Reconstruction of the antenna frequency from the frequency of the signal in the recorded data can be achieved through use of one of the following formulas. Filters are defined below. FSant=3*SYN+1.95*10**9+3*(790/11)*10**6+Frec (Filter 4) =3*SYN+1.95*10**9+3*(790/11)*10**6-Fsamp+Frec (Filters 1-3,5,6) FXant=11*SYN + 7.940*10**9 + Fsamp - Frec (Filter 4) =11*SYN + 7.940*10**9 - 3*Fsamp + Frec (Filters 1,2,3,6) where FSant,FXant are the antenna frequencies of the incoming signals at S and X bands, respectively, SYN is the output frequency of the DANA synthesizer, commonly labeled the readback POCA frequency on data tapes, Fsamp is the effective sampling rate of the digital samples, and Frec is the apparent signal frequency in a spectrum reconstructed from the digital samples. NB: For many of the filter choices (see below) the Output is that of a bandpass filter. The sampling rates in the table below are sufficient for the bandwidth but not the absolute maximum frequency, and aliasing results. The reconstruction expressions above are appropriate ONLY when the sample rate shown in the tables below is used. Filters - DSN ============= DSCC Open-Loop Receiver (RIV) ----------------------------- Nominal filter center frequencies and bandwidths for the RIV Receivers are shown in the table below. Recommended sampling rates are also given. S-Band X-Band ------------------------ ------------------------- Output 3 dB Sampling Output 3 dB Sampling Filter Center Band Rate Center Band Rate Freq Width Freq Width (Hz) (Hz) (sps) (Hz) (Hz) (sps) ------ ------ ------ -------- ------ ------ -------- 1 150 82 200 550 82 200 2 750 415 1000 2750 415 1000 3 3750 2000 5000 13750 2000 5000 4 1023 1700 5000 3750 6250 15000 5 75000 45000 100000 275000 45000 100000 6 37500 20000 50000 137500 20000 50000 Detectors - DSN =============== DSCC Open-Loop Receivers ------------------------ Open-loop receiver output is detected in software by the radio science investigator. DSCC Closed-Loop Receivers -------------------------- Nominal carrier tracking loop threshold noise bandwidth at both S- and X-band is 10 Hz. Coherent (two-way) closed-loop system stability is shown in the table below: integration time Doppler uncertainty (secs) (one sigma, microns/sec) ------ ------------------------ 10 50 60 20 1000 4 Calibration - DSN ================= Calibrations of hardware systems are carried out periodically by DSN personnel; these ensure that systems operate at required performance levels -- for example, that antenna patterns, receiver gain, propagation delays, and Doppler uncertainties meet specifications. No information on specific calibration activities is available. Nominal performance specifications are shown in the tables above. Additional information may be available in [DSN810-5]. Prior to each tracking pass, station operators perform a series of calibrations to ensure that systems meet specifications for that operational period. Included in these calibrations is measurement of receiver system temperature in the configuration to be employed during the pass. Results of these calibrations are recorded in (hard copy) Controller's Logs for each pass. The nominal procedure for initializing open-loop receiver attenuator settings is described below. In cases where widely varying signal levels are expected, the procedure may be modified in advance or real-time adjustments may be made to attenuator settings. Open-Loop Receiver Attenuation Calibration ------------------------------------------ The open-loop receiver attenuator calibrations are performed to establish the output of the open-loop receivers at a level that will not saturate the analog-to-digital converters. To achieve this, the calibration is done using a test signal generated by the exciter/translator that is set to the peak predicted signal level for the upcoming pass. Then the output level of the receiver's video band spectrum envelope is adjusted to the level determined by equation (3) below (to five-sigma). Note that the SNR in the equation (2) is in dB while the SNR in equation (3) is linear. Pn = -198.6 + 10*log(SNT) + 10*log(1.2*Fbw) (1) SNR = Ps - Pn (SNR in dB) (2) Vrms = sqrt(SNR + 1)/[1 + 0.283*sqrt(SNR)] (SNR linear) (3) where Fbw = receiver filter bandwidth (Hz) Pn = receiver noise power (dBm) Ps = signal power (dBm) SNT = system noise temperature (K) SNR = predicted signal-to-noise ratio Operational Considerations - DSN ================================ The DSN is a complex and dynamic 'instrument.' Its performance for Radio Science depends on a number of factors from equipment configuration to meteorological conditions. No specific information on 'operational considerations' can be given here. Operational Modes - DSN ======================= DSCC Antenna Mechanical Subsystem --------------------------------- Pointing of DSCC antennas may be carried out in several ways. For details see the subsection 'DSCC Antenna Mechanical Subsystem' in the 'Subsystem' section. Binary pointing is the preferred mode for tracking spacecraft; pointing predicts are provided, and the antenna simply follows those. With CONSCAN, the antenna scans conically about the optimum pointing direction, using closed-loop receiver signal strength estimates as feedback. In planetary mode, the system interpolates from three (slowly changing) RA-DEC target coordinates; this is 'blind' pointing since there is no feedback from a detected signal. In sidereal mode, the antenna tracks a fixed point on the celestial sphere. In 'precision' mode, the antenna pointing is adjusted using an optical feedback system. It is possible on most antennas to freeze z-axis motion of the subreflector to minimize phase changes in the received signal. DSCC Receiver-Exciter Subsystem ------------------------------- The diplexer in the signal path between the transmitter and the feed horns on all antennas may be configured so that it is out of the received signal path in order to improve the signal-to-noise ratio in the receiver system. This is known as the 'listen-only' or 'bypass' mode. Closed-Loop vs. Open-Loop Reception ----------------------------------- Radio Science data can be collected in two modes: closed- loop, in which a phase-locked loop receiver tracks the spacecraft signal, or open-loop, in which a receiver samples and records a band within which the desired signal presumably resides. Closed-loop data are collected using Closed-Loop Receivers, and open-loop data are collected using Open-Loop Receivers in conjunction with the DSCC Spectrum Processing Subsystem (DSP). See the Subsystems section for further information. Closed-Loop Receiver AGC Loop ----------------------------- The closed-loop receiver AGC loop can be configured to one of three settings: narrow, medium, or wide. Ordinarily it is configured so that expected signal amplitude changes are accommodated with minimum distortion. The loop bandwidth is ordinarily configured so that expected phase changes can be accommodated while maintaining the best possible loop SNR. Coherent vs. Non-Coherent Operation ----------------------------------- The frequency of the signal transmitted from the spacecraft can generally be controlled in two ways -- by locking to a signal received from a ground station or by locking to an on-board oscillator. These are known as the coherent (or 'two-way') and non-coherent ('one-way') modes, respectively. Mode selection is made at the spacecraft, based on commands received from the ground. When operating in the coherent mode, the transponder carrier frequency is derived from the received uplink carrier frequency with a 'turn-around ratio' typically of 240/221. In the non-coherent mode, the downlink carrier frequency is derived from the spacecraft on-board crystal-controlled oscillator. Either closed-loop or open-loop receivers (or both) can be used with either spacecraft frequency reference mode. Closed-loop reception in two-way mode is usually preferred for routine tracking. Occasionally the spacecraft operates coherently while two ground stations receive the 'downlink' signal; this is sometimes known as the 'three-way' mode. DSCC Spectrum Processing Subsystem (DSP) ---------------------------------------- The DSP can operate in four sampling modes with from 1 to 4 input signals. Input channels are assigned to ADC inputs during DSP configuration. Modes and sampling rates are summarized in the tables below: Mode Analog-to-Digital Operation ---- ---------------------------- 1 4 signals, each sampled by a single ADC 2 1 signal, sampled sequentially by 4 ADCs 3 2 signals, each sampled sequentially by 2 ADCs 4 2 signals, the first sampled by ADC #1 and the second sampled sequentially at 3 times the rate by ADCs #2-4 8-bit Samples 12-bit Samples Sampling Rates Sampling Rates (samples/sec per ADC) (samples/sec per ADC) --------------------- --------------------- 50000 31250 25000 15625 12500 10000 10000 6250 5000 5000 4000 3125 2500 2000 1250 1000 1000 500 400 250 200 200 Input to each ADC is identified in header records by a Signal Channel Number (J1 - J4). Nominal channel assignments are shown below. Signal Channel Number Receiver Channel --------------------- ------------- J1 X-RCP J2 S-RCP J3 X-LCP J4 S-LCP Location - DSN ============== Station locations are documented in [GEO-10REVD]. Geocentric coordinates are summarized here. Geocentric Geocentric Geocentric Station Radius (km) Latitude (N) Longitude (E) --------- ----------- ------------ ------------- Goldstone DSS 13 (34-m R&D) 6372.125125 35.0660185 243.2055430 DSS 14 (70-m) 6371.993286 35.2443527 243.1104638 DSS 15 (34-m HEF) 6371.966540 35.2403133 243.1128069 DSS 24 (34-m BWG) 6371.973553 35.1585349 243.1252079 DSS 25 (34-m BWG) 6371.983060 35.1562594 243.1246384 DSS 26 (34-m BWG) 6371.993032 35.1543411 243.1269849 Canberra DSS 34 (34-m BWG) 6371.693561 -35.2169868 148.9819620 DSS 43 (70-m) 6371.689033 -35.2209234 148.9812650 DSS 45 (34-m HEF) 6371.675906 -35.2169652 148.9776833 Madrid DSS 45 (34-m BWG) 6370.025429 40.2357708 355.7459008 DSS 63 (70-m) 6370.051221 40.2413537 355.7519890 DSS 65 (34-m HEF) 6370.021697 40.2373325 355.7485795 Measurement Parameters - DSN ============================ Open-Loop System ---------------- Output from the Open-Loop Receivers (OLRs), as sampled and recorded by the DSCC Spectrum Processing Subsystem (DSP), is a stream of 8- or 12-bit quantized voltage samples. The nominal input to the Analog-to-Digital Converters (ADCs) is +/-10 volts, but the precise scaling between input voltages and output digitized samples is usually irrelevant for analysis; the digital data are generally referenced to a known noise or signal level within the data stream itself -- for example, the thermal noise output of the radio receivers which has a known system noise temperature (SNT). Raw samples comprise the data block in each DSP record; a header record (presently 83 16-bit words) contains ancillary information such as: time tag for the first sample in the data block RMS values of receiver signal levels and ADC outputs POCA frequency and drift rate Closed-Loop System ------------------ Closed-loop data are recorded in Archival Tracking Data Files (ATDFs), as well as certain secondary products such as the Orbit Data File (ODF). The ATDF Tracking Logical Record contains 150 entries including status information and measurements of ranging, Doppler, and signal strength. ACRONYMS AND ABBREVIATIONS - DSN ================================ ACS Antenna Control System ADC Analog-to-Digital Converter AGC Automatic Gain Control AMS Antenna Microwave System APA Antenna Pointing Assembly ARA Area Routing Assembly ATDF Archival Tracking Data File AUX Auxiliary AZ Azimuth bps bits per second BWG Beam WaveGuide (antenna) CDU Command Detector Unit CMC Complex Monitor and Control CNES Centre National d'Etudes Spatiales CONSCAN Conical Scanning (antenna pointing mode) CRG Coherent Reference Generator CUL Clean-up Loop DANA a type of frequency synthesizer dB deciBel dBic dB relative to isotropic, circularly polarized radiator dBm dB relative to one milliwatt DCO Digitally Controlled Oscillator DEC Declination deg degree DMC DSCC Monitor and Control Subsystem DOR Differential One-way Ranging DSCC Deep Space Communications Complex DSN Deep Space Network DSP DSCC Spectrum Processing Subsystem DSS Deep Space Station DTK DSCC Tracking Subsystem E east EIRP Effective Isotropic Radiated Power EL Elevation FET Field Effect Transistor FFT Fast Fourier Transform FTS Frequency and Timing Subsystem GCF Ground Communications Facility GHz Gigahertz GPS Global Positioning System HA Hour Angle HEF High-Efficiency (as in 34-m HEF antennas) HEMT High Electron Mobility Transistor (amplifier) HGA High-Gain Antenna HSB High-Speed BWG IF Intermediate Frequency IVC IF Selection Switch JPL Jet Propulsion Laboratory K Kelvin Ka-Band approximately 32 GHz KaBLE Ka-Band Link Experiment kbps kilobits per second kHz kiloHertz km kilometer kW kilowatt LAN Local Area Network LCP Left-Circularly Polarized LGA Low-Gain Antenna LGR Low-Gain Receive (antenna) LGT Low-Gain Transmit (antenna) LMA Lockheed Martin Astronautics LMC Link Monitor and Control LNA Low-Noise Amplifier LO Local Oscillator m meters MCA Master Clock Assembly MCCC Mission Control and Computing Center MDA Metric Data Assembly MGA Medium Gain Antenna MHz Megahertz MON Monitor and Control System MSA Mission Support Area N north NAR Noise Adding Radiometer NBOC Narrow-Band Occultation Converter NEAR Near-Earth Asteroid Rendezvous NIST SPC 10 time relative to UTC NIU Network Interface Unit NOCC Network Operations and Control System NRV NOCC Radio Science/VLBI Display Subsystem NSS NOCC Support System OCI Operator Control Input ODF Orbit Data File ODR Original Data Record ODS Original Data Stream OLR Open Loop Receiver OSC Oscillator PDS Planetary Data System POCA Programmable Oscillator Control Assembly PPM Precision Power Monitor RA Right Ascension REC Receiver-Exciter Controller RCP Right-Circularly Polarized RF Radio Frequency RIC RIV Controller RIV Radio Science IF-VF Converter Assembly RMDCT Radio Metric Data Conditioning Team RMS Root Mean Square RSS Radio Science Subsystem RTLT Round-Trip Light Time S-band approximately 2100-2300 MHz sec second SEC System Error Correction SIM Simulation SLE Signal Level Estimator SNR Signal-to-Noise Ratio SNT System Noise Temperature SOE Sequence of Events SPA Spectrum Processing Assembly SPC Signal Processing Center sps samples per second SRA Sequential Ranging Assembly SRC Sub-Reflector Controller SSI Spectral Signal Indicator TID Time Insertion and Distribution Assembly TLM Telemetry TSF Tracking Synthesizer Frequency TWM Traveling Wave Maser TWNC Two-Way Non-Coherent TWTA Traveling Wave Tube Amplifier UNK unknown USO UltraStable Oscillator UTC Universal Coordinated Time VCO Voltage-Controlled Oscillator VF Video Frequency X-band approximately 7800-8500 MHz