GPS-2A (Global Positioning System) or Navstar-2A (Navigation System using Timing And ranging) are improved satellites of the second generation of the GPS navigation system.

The Block IIA satellites were improved operational GPS satellites based on the GPS 2 series. They were designed to provide 180 days of operation without contact from the control segment. During the 180 day autonomy, degraded accuracy is evident in the navigation message.

In 1983 Rockwell was awarded a contract to build 28 Block II/IIA satellites.

The spacecraft was 3-axis stabilized, nadir pointing using reaction wheels. Two solar arrays supplied 710 Watts (EOL). S-Band (SGLS) communications were used for control and telemetry. A UHF channel provided cross-links between spacecraft. A hydrazine propulsion system was used for orbital correction. The payload included two L-Band navigation signals at 1575.42 MHz (L1) and 1227.60 MHz (L2). Each spacecraft carried 2 rubidium and 2 cesium clocks. Also carried as a secondary payload were nuclear detonation detection sensors (NDS).

SEDS (Small Expendable Deployer System) were two piggyback missions of tether-in-space technology demonstrations. They deployed end-masses from Delta-7925 second stages after the primary deployment mission was conducted.