A2100

A2100 is a highly successful and versatile satellite bus platform designed and manufactured by Lockheed Martin for geostationary communications missions. First launched in the mid-1990s, the platform has become a cornerstone for commercial, military, and governmental operators globally, known for its reliability, power capacity, and flexible design. Its longevity and continuous evolution have made it one of the most prolific commercial satellite buses in history, supporting a wide array of telecommunications, broadcasting, and secure communications payloads.

Overview

The A2100 series was developed by Lockheed Martin following its acquisition of the satellite division of General Electric, building upon heritage technology from earlier programs like the HS 601. It was designed to compete directly in the commercial market against contemporary platforms from Space Systems/Loral and Boeing Satellite Systems. The bus introduced significant advancements in modularity and electrical power systems, allowing it to be scaled for missions ranging from medium to very high power. Key early customers included AT&T Corporation, Telesat, and SES S.A., establishing its reputation for robust performance in geostationary orbit.

Design and Development

The design philosophy of the A2100 emphasized commonality and flexibility, utilizing a modular architecture where subsystems could be tailored for specific mission requirements without a complete redesign. Its structure is based on a central thrust tube and employs lightweight composite materials, contributing to a high mass efficiency for payload. The electrical system pioneered the use of a standardized 100-volt bus, which provided greater power scalability compared to earlier 28-volt or 50-volt systems used on satellites like the Intelsat VI. The platform also integrated advanced propulsion options, including both bipropellant systems and, on later models, electric propulsion for station-keeping, influenced by technology from programs like the Milstar constellation. Development and integration primarily occurred at Lockheed Martin's facilities in Sunnyvale, California and Denver, Colorado.

Operational History

The inaugural launch of the A2100 platform was the AMC-1 satellite for SES Americom in 1996, launched aboard an Atlas IIA rocket from Cape Canaveral Space Force Station. This began an extensive operational history that spans decades and includes numerous high-profile missions. The platform has been launched on a variety of vehicles including the Ariane 5, Proton-M, Falcon 9, and Atlas V. It forms the backbone of many critical satellite fleets, such as those operated by Intelsat, Eutelsat, and the United States Space Force for the Advanced Extremely High Frequency (AEHF) secure communications system. Notably, several A2100-based satellites, like GOES-16, have been adapted for meteorological observation by NASA and the National Oceanic and Atmospheric Administration. The platform has demonstrated exceptional on-orbit longevity, with many satellites exceeding their 15-year design lives.

Variants

The A2100 platform has been produced in several major variants, differentiated primarily by payload power and mission capability. The A2100A was the initial model, designed for medium-power missions. The more common A2100AX and A2100AXS variants offered enhanced power and flexibility for high-throughput communications. The A2100M is a militarized version developed for specialized U.S. government missions, featuring components from the TRW Inc. supply chain and enhanced radiation hardening. The most powerful variant is the A2100SAT, or "A2100 Space and Air Team," which supports very high-power payloads exceeding 20 kilowatts. Each variant maintains the core architectural principles while incorporating lessons learned from programs like the DSCS III and commercial demand for more transponders.

Specifications

The A2100 is a three-axis stabilized bus designed for operations in geostationary orbit. Its dry mass typically ranges from 1,800 to 3,000 kilograms depending on the variant and configuration. The platform can support payload masses from 500 to over 1,000 kilograms and provide payload power ranging from 5 kilowatts to more than 20 kilowatts for the largest models. It utilizes a standardized 100-volt unregulated power bus, with power generated by dual-junction or triple-junction gallium arsenide solar arrays. Propulsion systems typically include a liquid apogee engine for orbit insertion and monopropellant or electric thrusters for north-south and east-west station-keeping. The bus is designed to accommodate a wide spectrum of communications payloads, including Ku-band, Ka-band, C-band, X-band, and UHF transponders, as well as specialized military payloads for protected communications. Category:Communications satellite buses Category:Lockheed Martin satellites Category:Satellites introduced in 1996