X-band Solid-state Power Amplifier Research Articles

AIR-COOLED 350 W X-BAND SOLID-STATE POWER AMPLIFIER

In this paper we present the results of the design and production of an air-cooled X-band solid-state power amplifier based on AlGaN/GaN/SiC Schottky FET. The power amplifier includes: preliminary power amplifier, output power amplifiers, set of secondary power supplies, digital control unit, monitoring system for the power amplifier performance, set of microwave power waveguide combiners.

An implementation of 60W X-band Cascade SSPA for Marine Radar System

In this paper, An X-band solid state power amplifier(SSPA) for pulse compressed microwave signal with 60Watt power and power added efficiency(PAE) above 30% is described. Designed 60Watt high power amplifier(HPA) was implemented by cascade coupled amplifiers, and it is consisted on three stage drive amplifiers with internally matched GaAs FET and one stage main power amplifier with an internally matched GaN HEMT. The designed SSPA has performance with more than total power gain 37dB and output power 48dBm(60-W) in condition of frequency range , pulse period width under 1ms and duty cycle under 10%. The implemented SSPA can apply to high quality digital marine radar applications with pulse compression technique.

Telecommunications system technologies for the near spacecraft

The launch of the Near Earth Asteroid Rendezvous (NEAR) spacecraft on February 17, 1996 was the first in NASA's series of Discovery-class missions. The spacecraft is designed to rendezvous with and eventually orbit the asteroid 433 Eros. The spacecraft telecommunications system is centered about two redundant X-band transponder systems that provide the command, telemetry, and tracking functions. Despite a very tight development schedule, a significant amount of new technology has been used in the system. Included in the design are the most recent developments in transponder hardware, an X-band solid state power amplifier (a deep space “first”), and efficient microstrip patch antennas. During spacecraft emergencies, a microstrip fanbeam antenna is used as part of a unique earth acquisition algorithm. Potential areas for future technology improvements are also discussed.

Hermes Global Orbiter spacecraft system design

The Hermes Global Orbiter (HGO) mission was one of the eleven DISCOVERY NASA HQ Code SL projects funded for study in FY’93. It proposes to launch a spacecraft to Mercury in the 1999 launch opportunity, with multiple encounters at Venus and Mercury, to reduce the launch and Mercury Orbit Insertion energy requirements. This mission design strategy results in an interplanetary cruise of 3.44 earth years and with a Mercury orbit lifetime of 1 earth year. The project proposes to maintain total run out to launch plus 30 days cost at less than 150 M$ (1991 FY $) with launch vehicles being excluded from this cap. The spacecraft uses a great deal of heritage from prior TRW spacecraft developments. The key elements are the Lightsat avionics being used for the TRW Advanced Bus, the TRW dual mode Liquid Apogee Engine, TRW graphite fiber wrapped tanks, the JPL/TRW X-band Solid State Power Amplifier, TRW heat pipe technology and the TRW Gallium Arsenide solar array technology.