Lockheed Martin: A2100 / LM-2100

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AMC 8 (A2100A) [Lockheed Martin]

NSS 6 (A2100AXS) [Lockheed Martin]

Garuda 1 (A2100AXX) [Lockheed Martin]

HellasSat 4/SaudiGeoSat 1 (A2100 upgraded) [Lockheed Martin]

The Lockheed Martin A2100 geosynchronous spacecraft series is designed to meet a wide variety of telecommunications needs including Ka-band broadband and broadcast services, fixed satellite services in C-band and Ku-band payload configurations, high-power direct broadcast services using the Ku-band frequency spectrum, and mobile satellite services using UHF, L-band and S-band payloads. The A2100's modular design features a reduction in parts, simplified construction, increased on-orbit reliability and reduced weight and cost.

The company has standardized on this bus. Much of the R&D is directed toward increasing the power available on the satellite and the A2100 bus, which is capable of generating 15 kW in its standard configuration. This involves work on the integration of new, higher efficiency solar cells, onto the innovative solar "pleated shades," the use of high efficiency, radiation cooled TWTAs, the design of more efficient heat pipes and fold out radiators and improved design for thermal dissipation. Company engineers make extensive use of CAD tools and claim that they can deliver a satellite that uses the A2100 bus in 18 months after receipt of the order.

The A2100 series is modular and can be configured in three different sizes:

• A2100A = 1 to 4 kW
• A2100AX =4 to x kW
• A2100AXS: enhanced A2100AX
• A2100AXX: stretched version for mobile communications

Additionally there is a A2100M version, which fullfills military requirements.

Reliability:

Following failures of A2100 models have occured:

• EchoStar 4: 1998 - two of five panels on one solar array have not unfolded, later fuel system problems - partial loss
• Nimiq 2: 2003 - power loss - reduced performance
• Telkom 1: 1999 - solar array drive problems - no performance loss