
MEP 1 [Northrop Grumman]
The MEP (Mission Extension Pod) is a compact in-orbit servicing spacecraft developed by Space Logistics to extend the operational life of geostationary satellites by providing propulsion augmentation. Based on technology developed for the company's Mission Extension Vehicle (MEV), the MEP is designed as a smaller and more economical servicing system that supplies electric propulsion for orbit raising and long-term station keeping after being installed on an existing satellite.
Unlike the larger MEV, which docks directly to a client satellite and remains attached while performing all propulsion functions, the MEP is delivered and installed by the Mission Robotic Vehicle (MRV). The robotic servicer captures the pod and mounts it onto the client's Liquid Apogee Engine (LAE) using an improved attachment mechanism. Because the MEP is considerably lighter than the MEV and does not require structural supports against the satellite's launch adapter ring, it is compatible with a wider range of geostationary spacecraft. Although the pod cannot detach independently after installation, the MRV can later remove it and transfer it to another satellite if required.
The spacecraft carries a redundant electric propulsion system used for Electric Propulsion Orbit Raising (EPOR) and station keeping. Following launch into geostationary transfer orbit, the MEP requires approximately ten months to reach geostationary orbit under its own propulsion. Once installed on a client satellite, it can provide about six years of full north-south and east-west station-keeping capability for spacecraft with a mass of up to 2,000 kg, significantly extending their operational lifetime without requiring replacement.
MEP-1 will launch together with MEP-2, MEP-3 and the first Mission Robotic Vehicle 1 (MRV 1).
| Nation: | USA |
|---|---|
| Type / Application: | Satellite servicing |
| Operator: | SpaceLogistics, Northrop Grumman Innovation Systems (NGIS) |
| Contractors: | SpaceLogistics, Northrop Grumman Innovation Systems (NGIS) |
| Equipment: | Docking adaptor |
| Configuration: | |
| Propulsion: | 2 electric propulsion modules |
| Power: | 2 deployable solar arrays, batteries |
| Lifetime: | 6 years |
| Mass: | ~500 kg |
| Orbit: | GEO |
| Satellite | COSPAR | Date | LS | Launch Vehicle | Remarks | |
|---|---|---|---|---|---|---|
| MEP 1 | 2026-167B | 21.07.2026 | CC SLC-40 | Falcon-9 v1.2 (Block 5)(ex) | with MRV 1, MEP 2, 3 | |
| MEP 2 | 2026-167C | 21.07.2026 | CC SLC-40 | Falcon-9 v1.2 (Block 5)(ex) | with MRV 1, MEP 1, 3 | |
| MEP 3 | 2026-167D | 21.07.2026 | CC SLC-40 | Falcon-9 v1.2 (Block 5)(ex) | with MRV 1, MEP 1, 2 |
