An ultra-lightweight high gain spacecraft antenna

• Main Authors: Schneider, W.A., Moore, J.L., Blakney, T.L., Smith, D.D., Vacchione, J.D.
• Format: Conference Proceeding
• Language: English
• Subjects: Aerospace engineering; Design engineering; Design optimization; Downlink; Feeds; Pluto; Radio frequency; Space technology; Space vehicles; Testing
• DOI: 10.1109/APS.1994.407960

A proof of concept telecommunications subsystem antenna (TSA) has been developed as part of the Pluto Fast Flyby Advanced Technology Insertion (ATI) program. The antenna was built to demonstrate the technology for an ultra-lightweight antenna which provides excellent RF performance. The Boeing antenna was designed to demonstrate the potential for significant weight reduction from the existing Viking 1.47 meter (58 inch) antenna. The Viking X-band uplink/X-band downlink antenna is a 5.8 kg (12.8 pound) subsystem. The Pluto antenna weight goal was 2.75 kg (6 pounds) or less. Further, it was desired that feasibility be established for the use of Ka-band downlink for the Pluto mission. The Boeing design was based on use of existing mandrels for the reflector shell and feed support struts from a previous reflector program. The feed design was scaled from Boeing's Mariner-Venus-Mercury (MVM) spacecraft. Trade studies and design optimizations refined the shell stiffening design. Details of the feed design were established interactively between the mechanical designer and RF engineer. High modulus, high strength graphite fibers were used within a cyanate ester matrix for overall high stiffness and strength and low thermal and moisture effects; all at minimum weight. Performance was verified by RF range testing at X-band and Ka-band. Weight measurements were completed, and a tap test was made to assess the stiffness modeling of the structure.< >