The Spectrum Astro SA-200 satellite bus provided a flexible platform for satellites launched by the Pegasus booster.

Spectrum Astro was acquired by General Dynamics C4 Division in 2006. Spectrum Astro's SA-200 family of satellites were marketed in three variants:

• The SA-200B provided an affordable platform for data collecting space missions at LEO, MEO, HEO, and GEO orbits. The spacecraft combining proven high-capability space components with an open architecture designed for concurrent development and early interface and functional test.
• The SA-200HP was a scaleable platform for missions ranging from remote-sensing operations requiring continuous "pushbroom" sensors in any low-earth orbit, to planetary missions demanding precision pointing and extended lifetimes. This platform provided a range of electric power and propulsion capabilities with provisions for complete redundancy, depending on mission need and cost constraints. The SA-200HP was sized to support payloads launched by Pegasus, Taurus, or Athena launch vehicles.
• The SA-200S was designed for missions with solar inertial, sun synchronous near-6am orbits, or missions that required duty-cycled, high-accuracy point tracking. It could be configured for a Pegasus, Athena, Delta, or Taurus launch. The bus provided a full capability monopropellant hydrazine RCS for orbit acquisition and precision control, and offered substantial pointing control and agility. Options for non-sun-synchronous orbits allowed payload operations for any sun orientation.

Mass: 500 kg (1,100 lb).

• 2000 July 19 - Mightysat 2.1 - Launch Site: Vandenberg. Launch Complex: SLC8. Launch Vehicle: Minotaur. Mass: 120 kg (260 lb). Perigee: 547 km (340 mi). Apogee: 581 km (361 mi). Inclination: 97.78 deg. Period: 95.86 min.
  Mightysat 2.1, also known as Sindri, used a Spectrum Astro SA-200B satellite bus. The spacecraft carried a hyperspectral imager for earth imaging and spectroscopy, as well as satellite technology experiments such as advanced solar arrays. An Aerospace Corp./DARPA picosatellite experiment, consisting of two small boxes connected by a deployable tether, was deployed later. Similar picosats were deployed on the previous Minotaur launch in January 2000.

• 2007 April 24 - NFIRE - Launch Site: Wallops Island. Launch Complex: LA0B. Launch Vehicle: Minotaur. Mass: 494 kg (1,089 lb). Perigee: 489 km (303 mi). Apogee: 497 km (308 mi). Inclination: 48.20 deg. Period: 94.50 min.
  Near Field Infrared Experiment conducted by the US Missile Defense Agency. Its Track Sensor Payload included visible and short, medium and long wave infrared sensors to observe missiles launched from the ground, and obtain basic data to distinguish between the missile and its hot rocket exhaust plume for application to anti-ballistic missile systems. Secondary payloads included Tesat, a German laser communications terminal, and its hydrazine propulsion system. This was used to maneuver the satellite from its initial 255 km x 465 km x 48.2 deg orbit to 489 km x 497 km by 18 May. The orbit was changed to 243 km x 487 km on 9 August and by 23 August was 219 km x 450 km. The satellite had a dry mass of 380 kg dry, was 2.7 m long and 1.3 m in diameter.

  The first major sensor test occurred when Minotaur II rocket TLV-7, was fired at 08:30 GMT on 23 August from Vandenberg in NFIRE Mission 2a. The Minotaur II was aimed to pass within 4 and 20 km of the NFIRE satellite while its third stage motor burning, to allow NFIRE to get a close look at the rocket and its exhaust. The Missile Defense Agency reported that the experiment was successful.