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Deep Space One Telecommunication Development M.I • • SSC98-IV-l • Deep Space One Telecommunication Development M.I. Herman, S. Valas, W. Hatch, C.C. Chen, S. H. Zingales, R. P. Scaramastra, L.R. Amaro, • and M. D. Rayman Jet Propulsion Laboratory • California Institute of Technology 4800 Oak Grove Drive • Pasadena, CA 91109 m1s 161-213 818-354-8541 • [email protected] • Abstract. Deep Space One (DS1) is the first of the New Millennium Program deep space technology validation missions, to be launched October 1998. This paper focuses on the • Telecommunication Subsystem architecture, technology developments, as well as the test results. Technical factors that influenced the subsystem architecture were the ability to command the • spacecraft and downlink telemetry data in cruise and emergency situations, and the need to provide radiometric data. Additional challenges included the requirement to demonstrate new • telecommunication technology, enable the validation of other system technologies (for example solar electric propulsion, autonomous navigation, and beacon monitor operation), and at the same time utilize a single string system design. From a programmatic perspective we had to accomplish • these goals within a budget and workforce load that was at least a factor 2 less than the Mars • Pathfinder Project. The Small Deep Space Transponder (SDST), a new technology developed by Motorola, is the • heart of the Telecommunication Subsystem and is a result of a JPL multimission sponsored competitive award. The SDST provides the functionality normally associated with 4-5 individual • subassemblies at less than half the mass (2.95 kg). Another new technology to be validated on DS1 is a 2.5W Ka-band solid state amplifier developed by Lockheed Martin (under their own funding). This technology not only extends the robustness of the system design (augmenting the • X-band downlink) but also provides the capability to characterize ~-band deep space • communication links. • Infusion of new technologies did not allow for the traditional subsystem integration and test program due to the additional lead time required for the technology developments. Working with the Project, we defined a test plan that was consistent with the spacecraft integration timeline while • still providing enough characterization to ensure confidence of the subsystem's functionality in • flight. Introductionl programs affordable, it is anticipated that • small spacecraft, launched on low-cost launch vehicles and with highly focused • Overview of New Millennium objectives, will be used for many of the missions. To prevent the loss of capability • that may be expected in making spacecraft "NASA's plans for its space and Earth smaller and less expensive, the introduction science programs in the early years of the of new technologies is required. • next century call for many exciting, scien­ • tifically compelling missions. To make such 1 • M. Hennan 12th AIAAlUSU Conference on Small Satellites • SSC98-IV-l • With many spacecraft carrying out its Astro, Inc. as the industry partner for programs of scientific exploration, NASA spacecraft development. Planned for launch • would accept a higher risk per spacecraft; the in October 1998, DS l' s payload consists of loss of anyone spacecraft would represent a 12 technologies. The primary requirements of relatively small loss to the program. the mission are the validations of four of • Nevertheless, the use of new technologies in these: space science missions forces the first users • solar electric propulsion (SEP), • to incur higher costs and risks. The implemented on DS 1 as the ion concomitant diversion of project resources propulsion system (IPS); from the focused objectives of the science • solar concentrator arrays, supplied • missions can be avoided by certification of to DS 1 as solar conCentrator arrays the technologies in a separate effort. using refractive linear element • technology (SCARLET); • autonomous on-board navigation • The principal goal of the New Millennium (AutoNav); and program (NMP) is to validate selected high­ • an integrated panchromatic visible risk, high-benefit technologies in order to imager and infrared and ultraviolet • reduce the risks and the costs future missions imaging spectrometers, would experience in their use. NMP implemented on DS 1 as the • comprises dedicated deep space and Earth miniature integrated camera orbiting missions focused on the validation of spectrometer (MICAS). these technologies. As each mission is • flown, the risk of using the technologies that formed its payload should be substantially To assist in the validation of SEP, DS 1 • reduced, both because of the knowledge includes IPS diagnostic sensors (IDS), gained in the incorporation of the new composed of instruments to quantify • capability into the spacecraft, ground system, magnetic and electric fields, ion and electron and mission design as well as, of course, the densities, and surface contamination. quantification of the performance during the • mission. DS 1 also has level 1 goals which include the • validation of eight more technologies: By their very nature, NMP missions are high • a small deep space transponder risk. The key technologies that form the (SDST); • basis for each mission are the ones which • a Ka-band solid state power require validation to reduce the risk of future amplifier (KAPA) and associated • missions. Still, the failure of a new experiments in ~ -band technology on an NMP mission, even if it telecommunications; • leads to the loss of the spacecraft, does not • an integrated ion and electron necessarily mean the mission is a failure. If spectrometer, known as plasma the nature of the problem with the technology experiment for planetary • can be diagnosed, the goal of preventing exploration (PEPE); future missions from accommodating the risk • a remote agent experiment (RAX) • can be realized. Showing that a technology architecture for autonomous needs modification before it is appropriate for onboard planning and execution; use on science missions would be a useful • a beacon monitor operations • result of an NMP flight." experiment (BMOX) for autonomous onboard health and • status summarization and request Overview of DSl1 for ground assistance; • • a set of low power electronics (LPE); "Deep Space 1 (DS 1) is the first mission of • a high-packaging-density smart • NMP, It is being led by JPL, with Spectrum power switch, known as a power • 2 1 M. Herman 12 " AIAAIUSU Conference on Small Satellites • • • • SSC98-IV-l activation and switching module Table 1. New Millennium Deep Space 1 • (PASM); and Telecom Hardware Summary • a multifunctional structure (MFS) experiment combining electronics DC Power Notes ITEM Mass Dissipation • and thermal control in a structural (kg) (W) • element. SDST 2.95 New .... ····T1:·6 ........ .. ~~~~g,~lY·· .. ' .. ~.. 9.~.. y. .... Details on each technology (and further ......... 1'3':'3......... RX, X- • background on the project) are presented Exciter elsewhere." 2.3 ........ ·1·5:·2····· .. · • "RX~"'K~'''~' ........ T6:·9·· .... ·· Exciter The level 1 goals specify that DS 1 encounter "RX~"""'X~' • & Ka - an asteroid (1992 KD). In one extended mission scenario, DS 1 could encounter the Exciters • comet Borrelly. X-SSPA 1.61 59 MPF Spare • Ka-SSPA 0.66 20 New DSI Telecom Architecture Design Diplexer 0.37 MPF • Spare The telecommunication subsystem for DS 1 is DAM 0.20 0.30 New • single string (see Figure 1) as mandated by Design the project. The primary communication link WTS 0.78 Cassinil • is on Channel 19 at X -band for both uplink (2 of MPF and downlink ( 7.168 GHz and 8.421 GHz, them) Heritage respectively). As part of the technology MiscHW 5.25 (wiring • demonstration we have an auxiliary Ka -band harness, downlink (32.155 GHz). A major departure wvgd, • from a science driven mission to a technology brackets, driven one is that we are capabilities versus J..lwave requirement driven. This played a major role • comps in how components were selected as well as etc.) what our communication capabilities would • be. RFE 11.82 TOTAL • MPF Table 1 presents a detailed summary of the HGA 1.2 telecommunication subsystem mass and Spare • power for the NM DS 1 mission. LGA L08 Cassinil (3 of MPF • them) HeritaKe HGA 0.04 New • Radome Design Ka-band 0.80 New Hom Design • Antenna 3.11 • TOTAL TOTAL 14.9 Allocated • TELECOM mass= • 16.5 kg 3 • M. Herman 12th AIAAlUSU Conference on Small Satellites • SSC98-IV-l • Radio Frequency Electronics (RFE) This single unit which replaces 4 components used in past designs provides new • capabilities never considered before as part of The Radio Frequency Electronics (includes a transponder. Details about this unit will be all components except the antennas) was a described later in this paper. • combination of new technology insertion and the use of low-cost space heritage • components. From the Mars Pathfinder Without a functional SDST, the spacecraft (MPF) program we procured a flight spare would not be able to communicate with High Gain Antenna (HGA), diplexer, and Earth. In addition, other key DS 1 • 12.5 W RF X-band Solid State Power technologies depend on the SDST Amplifier (XPA). Implicit in this strategy functionality and include: • was that MPF would not require their spare hardware before launch in December 1996. • Ka -band communications: The SDST • Following the MPF launch, if DSI provides the Ka -band RF drive as experienced any failures (of these well as the modulation/encoding and components) there would not be any spares ranging for Ka -band.
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