Moog METEORITE Satellite Bus

History

The Moog METEORITE is an ESPA-class satellite bus developed and manufactured by Moog Inc. for small spacecraft missions. The flight-proven platform is designed primarily for low Earth orbit and can be modified for missions in geostationary orbit and beyond.

METEORITE uses avionics derived from Moog's wider Space Vehicle family, a modular power architecture, three-axis stabilization, and an integrated propulsion system. Moog positions the platform for pathfinder constellation missions, disaggregated spacecraft architectures, and missions requiring substantial orbital maneuvering.

In 2026, Moog announced a High Delta-V configuration intended to increase thrust and propellant capacity for propulsion-intensive missions. The configuration was described for high-energy transfers, large orbital-plane changes, frequent station-keeping, tactical intelligence, surveillance and reconnaissance missions, and space domain awareness.

Development and production

The baseline METEORITE was already flight-proven when Moog announced the High Delta-V configuration in 2026. Moog states that several METEORITE buses are on orbit supporting national security space missions. The manufacturer's METEORITE product page describes the standard spacecraft as an ESPA-class platform for missions in low Earth orbit, including high LEO altitudes of 1,000 to 1,200 km, with modifications possible for GEO and missions beyond Earth orbit.

The High Delta-V configuration was announced as an adaptation of the existing METEORITE architecture rather than a completely new spacecraft. According to reporting based on Moog's announcement, increased thrust and propellant mass were incorporated without requiring a lengthy new development and qualification program. ASDNews reported that the propulsion system is developed at Moog's Niagara Falls, New York, propulsion facility, where dedicated clean-room space was being expanded by more than 80 percent to increase assembly, integration, and testing capacity.

Final bus integration takes place at Moog's facility in the greater Denver area. The company states that this facility can integrate dozens of spacecraft per year. Separate reporting by SatNews described the High Delta-V version as using higher-volume liquid-propulsion modules and thruster-gimbal hardware while retaining the standardized ESPA-class platform.

Design

Structure and payload accommodation

The baseline METEORITE uses a simple all-aluminum structure that provides radiation shielding and accommodates different payload configurations. Moog lists the bus dry mass as 120 kg and the supported payload mass as 220 kg. The basic bus envelope is approximately 55.9 × 71.1 × 60.1 cm, corresponding to 22 × 28 × 23.65 inches. Its flat payload deck measures approximately 55.9 × 71.1 cm and can support payload installations up to approximately 76.2 cm high for an ESPA launch, with greater dimensions possible when a dedicated small launch vehicle is used.

The platform is compatible with ESPA rideshare missions and dedicated small launch vehicles. Its modular architecture is intended to allow adaptation of electrical power and mission equipment without redesigning the complete spacecraft.

Avionics and guidance

METEORITE uses avionics based on Moog's BRE440 radiation-hardened processor. Flight software is configurable for different payloads and missions. The spacecraft is three-axis stabilized using reaction wheels and torque rods. Moog describes its guidance, navigation and control sensor suite as single-string but layered to provide resiliency.

For the baseline configuration, Moog specifies orbital position knowledge better than 4 m, attitude-knowledge telemetry accuracy better than 40 arc-seconds at one sigma, pointing accuracy better than 60 arc-seconds at one sigma, and pointing jitter below 10 arc-seconds. Velocity accuracy is listed as 0.1 m/s. Maximum slew rate is 2.5 degrees per second and maximum point-to-point slew acceleration is 0.3 degrees per second squared.

Power and payload interfaces

The electrical system uses a modular power architecture that can be expanded according to mission requirements. Moog lists approximately 150 W of OAP payload power and 2 kW peak payload power as example values, with actual capability dependent on orbit and mission. Payload power is supplied through an unregulated 28 VDC bus with a stated 25 to 33 V operating range and multiple 1.2 A switches.

Payload data interfaces include two SpaceWire connections, four discrete interfaces, and one GPS one-pulse-per-second interface using LVDS.

Propulsion

The standard METEORITE uses a green propulsion system intended to simplify launch integration while providing sufficient maneuvering capability for deorbiting from high LEO. Moog also identifies the relatively high thrust of the system as suitable for collision avoidance and other rapid orbital changes. The manufacturer lists baseline delta-v capability above 175 m/s for a configuration stated with 200 kg dry mass.

The High Delta-V configuration announced in 2026 increases available thrust and propellant capacity for missions requiring more extensive maneuvering. SatNews reported integration of Moog's Model-S Thruster Gimbal Assembly with liquid thrusters and feed-control hardware. The supplied sources do not provide a numerical delta-v value for the High Delta-V configuration.

Operational history

Moog states that several baseline METEORITE buses are operating in orbit in support of national security space missions. The supplied material does not identify individual spacecraft, launch dates, operators, or mission designations.

The High Delta-V configuration was announced in 2026 as an expanded version for future propulsion-intensive missions. The supplied material does not establish that this configuration had entered operational service at the time of the announcement.

Variants

• METEORITE: Flight-proven baseline ESPA-class satellite bus designed primarily for missions from 500 to 1,200 km altitude and adaptable for GEO and missions beyond.
• High Delta-V METEORITE: Configuration announced in 2026 with increased thrust and propellant capacity for high-energy transfers, large plane changes, frequent station-keeping, space domain awareness, and other maneuver-intensive missions. The supplied sources do not provide a confirmed operational-service date.

Specifications (baseline METEORITE)

General characteristics

• Orbit: 500 to 1,200 km
• Mission life: 2 to 5 years, depending on orbit
• Bus dry mass: 120 kg
• Payload mass: 220 kg
• Bus dimensions: approximately 55.9 × 71.1 × 60.1 cm (22 × 28 × 23.65 in)
• Payload deck: approximately 55.9 × 71.1 cm (22 × 28 in), with payload height up to approximately 76.2 cm (30 in) for ESPA launch
• Radiation tolerance: 25.5 kRad total dose with approximately 5.08 mm (0.200 in) aluminum shielding
• Radiation-effects availability: greater than 99 percent over one year for single-event upset effects, as stated by Moog

Power and interfaces

• Example payload power: approximately 150 W OAP payload power
• Peak payload power: 2 kW
• Payload power interface: 28 VDC unregulated bus, 25 to 33 V range, with multiple 1.2 A switches
• Payload data interfaces: two SpaceWire, four discrete interfaces, and one GPS 1PPS interface via LVDS

Guidance and performance

• Orbital position knowledge: better than 4 m
• Attitude knowledge telemetry accuracy: better than 40 arc-seconds, one sigma
• Pointing accuracy: better than 60 arc-seconds, one sigma
• Pointing jitter: less than 10 arc-seconds
• Velocity accuracy: 0.1 m/s
• Maximum slew rate: 2.5 degrees per second
• Maximum slew acceleration: 0.3 degrees per second squared, point-to-point
• Delta-v: greater than 175 m/s for the 200 kg dry-mass configuration stated by Moog