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The Deep Space Network tracking system is described. Revisions of subsystem Mark III-75 are briefly outlined, and the currently used multimission support subsystem Mark III-77 is described. Tracking functions performed are given as well.
A water vapor radiometer (WVR) was developed which measures the atmospheric noise temperature at two different frequencies. These noise temperatures are used in empirical-theoretical equations which yield tropospheric range delay, in centimeters, through the atmosphere along the beam of the WVR. This range correction is then applied to measurements concerning spacecraft range and to very long baseline interferometry determinations.
The current plane to provide radio science real-time display capability in response to multimission radio science requirements is described. Topics discussed include the display of Doppler frequency and high-resolution graphical display of all closed-loop radio metric parameters, and spectrum displays of open-loop receiver output.
The data system created to collect the functions performed by the Deep Space Network in support of spacecraft radio science experiments is described. Some of the major functional requirements presently being considered for the system are delineated.
The Deep Space Network command Mark III-78 data processing system includes a capability for a store-and-forward handling method. The functions of (1) storing the command files at a Deep Space station; (2) attaching the files to a queue; and (3) radiating the commands to the spacecraft are straightforward. However, the total data processing capability is a result of assuming worst case, failure-recovery, or nonnominal operating conditions. Optional data processing functions include: file erase, clearing the queue, suspend radiation, command abort, resume command radiation, and close window time override.
A functional description of the ground communications facility and its relationships with other elements of the Deep Space network and the world-wide NASA communications network (NASCOM) is presented together with development activities and goals and comments on implementation activities in support of flight projects.
The Deep Space Network is in the process of fielding high-density digital instrumentation recorders for support of the Pioneer Venus 1978 entry experiment and other related tasks. It has long been obvious that these recorders would also serve well as the recording medium for very long base interferometry (VLBI) experiments with relatively weak radio sources, provided that a suitable correlation processor for these tape recordings could be established. The overall design and current status of a VLBI correlator designed to mate with these tape recorders are described.
System performance tests are required to evaluate system performance following initial system implementation and subsequent modification, and to validate system performance prior to actual operational usage. Non-real-time end-to-end Radio Science system performance tests are described that are based on the comparison of open-loop radio science data to equivalent closed-loop radio metric data, as well as an abbreviated Radio Science real-time system performance test that validates critical Radio Science System elements at the Deep Space Station prior to actual operational usage.
The system performance test software is currently being modified to include additional capabilities and enhancements. Additional software programs are currently being developed for the Command Store and Forward System and the Automatic Total Recall System. The test executive is the main program. It controls the input and output of the individual test programs by routing data blocks and operator directives to those programs. It also processes data block dump requests from the operator.
Effects of weather on Deep Space Network system performance at X-band are examined by comparing a record of 64 meter system noise temperatures with weather observations taken at approximately the same times and places.
The functional characteristics of a subsystem for support of radio science data acquisition requirements are described. The factors that were of major importance in the design and implementation approach are considered.
The use of level 4 prepass readiness tests (load and go pretrack preparation) to increase in Network productivity is described. Application of this method of operation for Voyager support, so that increased tracking could be provided to all projects during a period of continued interproject conflicts, is discussed.
The RF performance is studied for large reflector antenna systems (100 meters) when using the high efficiency dual shaped reflector approach. An altered phase was considered so that the scattered field from a shaped surface could be used in the JPL efficiency program. A new dual band (X-S) microwave feed horn was used in the shaping calculations. A great many shaping calculations were made for various horn sizes and locations and final RF efficiencies are reported. A conclusion is reached that when using the new dual band horn, shaping should probably be performed using the pattern of the lower frequency
Design and test data on portable zero delay assemblies are reported. These assemblies are field-use delay standards to periodically calibrate the block 4 translator ranging paths at each 64-m antenna Deep Space Station.
Future tracking requirements and advantages over earth based stations justify the design of an orbiting, free flying very long base interferometry system to provide high resolution maps of celestial radio sources. Moderate technology development is required for the following: 30 meter to 60 meter diameter deployable parabolic antennas with less than 2 millimeters surface tolerance; a momentum wheel attitude control system with few arc/second accuracy; solar power design; a hydrogen maser atomic frequency standard; and the cryogenic receivers. The system must meet current Deep Space tracking capabilities as a minimum, and the technology must be compatible with system performance growth in the future. System lifetime must be ten years without major refurbishing.
A water vapor radiometer (WVR) was developed that measures the atmospheric noise temperature at two different frequencies near 22 GHz. These noise temperature are used in empirical-theoretical equations that yield tropospheric range delay, in centimeters, through the atmosphere along the beam of the WVR. This range correction is then applied, as needed, to measurements concerning spacecraft range and to VLBI baseline determinations. The WVR design and calibration techniques are discussed.
A description of the Deep Space Network Telemetry System, Mark III-77, and the recent improvements are provided. Telemetry functions and performance are identified.