Mission Robotic Vehicle

Northrop Grumman / SpaceLogistics.

Overview

The Mission Robotic Vehicle is a geosynchronous satellite servicing spacecraft operated by SpaceLogistics, a Northrop Grumman company. It is a servicing bus developed from the technologies and lessons of the Mission Extension Vehicle, adding an advanced robotic capability to the proven MEV design [2], [4]. The robotic payload comes from DARPA and was developed by the US Naval Research Laboratory as part of the Robotic Servicing of Geosynchronous Satellites program [2]. In the capability taxonomy that NASA’s on-orbit servicing surveys use, robotic manipulation is one area among several, alongside rendezvous and capture, relocation, repair and refueling, and MRV is a rendezvous-and-capture vehicle that adds a manipulation payload to that base rather than a manipulator-first design [9].

The commercial mission is pod installation. Mission Extension Pods are compact propulsion augmentation devices carried to a client by the MRV and attached to it, each providing six years of extended GEO stationkeeping [1]. A pod launches on a commercial rideshare and operates as a free flier until it reaches GEO, where the MRV captures it and installs it on the client.

Specifications

Parameter	Value	Source
Bus	developed from MEV technologies and lessons	[2], [4]
Robotic arms	2 dexterous manipulators, DARPA/NRL supplied	[2]
Arm heritage	FREND, 1.8 m reach, 7 DOF, first use 2007	[2], [5]
Cameras	21 individual cameras across the vehicle	[1]
Long-range imagers	2 Malin ECAM-P50 visible cameras	[1]
Orbital maneuvering	electric propulsion	[2]
Design life	more than 10 years	[1]
MEP life extension	6 years of extended GEO stationkeeping	[1]
Client type	cooperative and non-cooperative	[2]

The SpaceLogistics program page describes the robotic payload as a single seven-degree-of-freedom arm designated RAS-1, built by the US Naval Research Laboratory under the DARPA Robotic Servicing of Geosynchronous Satellites program [6], where the retrieved literature describes two dexterous manipulators of the same FREND design [2].

Mission profile

Parameter	Value	Source
Launch	21 July 2026, Falcon 9 from Cape Canaveral Space Force Station	[8], [6]
Co-manifested payload	3 Mission Extension Pods	[8]
Mission Extension Pods scheduled for launch in summer 2026	3	[6]
Expected clients over the mission life	dozens	[1]
Time allocation on orbit	rendezvous, proximity operations and docking a fraction of the time, the remainder phasing between GEO slots	[1]

Mobility

The MRV maneuvers between geostationary slots under electric propulsion [2].

Manipulation is performed by two dexterous robotic arms supplied by DARPA and built by the Naval Research Laboratory [2]. The arm design is FREND, a seven degree of freedom arm of 1.8 m reach capable of autonomous grapple and manipulation, first used in 2007 and driven by the MOOG Rikishi Electronics Unit, which drives up to nine separate joints. The same design was carried into NASA’s OSAM-1 servicing arm [2], [3], and was already recorded as feeding both OSAM-1 and RSGS in 2022 [5]. Grasping a client without a purpose-built grapple fixture is the point of the design: MRV serves unprepared clients, docking to non-standard interfaces without a prebuilt docking mechanism on the client [2]. Capturing an uncooperative target this way spans the phases a broader review of on-orbit servicing manipulators identifies as generic to the problem: observation and motion estimation of the target, final approach and path planning, capture, and post-capture stabilization of the combined stack [10].

Power and energy

Propulsion is electric for orbit maneuvering [2], which sets the power scale of the bus. No array output, battery capacity or thermal design has been published.

Compute and avionics

No processor, memory or data handling specification has been published. The vehicle carries an onboard GPS receiver to maintain knowledge of its own ephemeris without ground ranging, which also provides a precision time reference, and high-precision star trackers maintain attitude knowledge at all times [1]. Vehicle state from both is attached as metadata to captured images along with camera configuration parameters.

Autonomy

Approach guidance draws on visible, infrared and lidar sensing [7], and capture is a soft capture guided by the sensors before a lance is inserted into the client apogee engine nozzle. That capture method is inherited from MEV, whose target features, the liquid apogee engine nozzle and the launch adapter ring, are present on most GEO satellites without having been designed as servicing interfaces. A lance-and-cone capture of this kind has a demanding accuracy floor: ground work on a comparable free-flyer docking port found that the relative sensor feeding the final approach had to deliver better than 1 cm of linear and 2 degrees of angular accuracy immediately before contact for the capture to have any chance of success, with repeated captures observed only below about 1 cm/s of closing velocity [11].

The attitude control system supports precise pointing for fixed-vector observation and rastered scan patterns over wider areas, with multiple exposures at a specified attitude or at each point in a search pattern [1].

Communications

No link budget, band allocation or data rate has been published. Raw sensor data is stated to be made available to US government and other approved customers for their own post-processing [1].

Payload and instruments

The vehicle carries 21 individual cameras, designed both for long-range tracking and for zero-range high-precision robotic operations [1].

Long-range detection and tracking uses a pair of Malin ECAM-P50 cameras. Each has a 1 inch format global-shutter focal plane behind a low-distortion radiation-hardened optic, with a 22 mm effective focal length imaging a 32 by 25 degree swathe per frame [1]. The camera shares components with units flown on Mars 2020 and RRM3.

Detection performance is modeled against on-orbit data collected by MEV-1 and MEV-2, whose imagery incidentally captured resident space objects during proximity operations and so validated the analytical camera models [1]. Taking a 13 dB signal to noise ratio as a conservative single-frame detection threshold, corresponding to apparent magnitude 6.4, the MRV camera system detects 1 square meter objects to about 600 km, 2 square meter objects to about 1200 km and 3 square meter objects to about 1800 km, modeling the targets as 20 percent Lambertian and sunlit. Those figures are described as extremely conservative because customers can apply their own post-processing.

The MEV sensor suite from which this derives comprises a visible sensor system of six cameras in two optical trains, a long-wave infrared camera set and a scanning lidar in the near infrared, tracking clients from beyond 50 km [4]. The visible narrow-field cameras resolved Intelsat 10-02 for classification and tracking from beyond 30 km, with a handover to the wide-field set at about 15 m during terminal approach.

The Mission Extension Pod is the primary carried payload. Pods are compact propulsion augmentation devices using electric propulsion, launched with the MRV or separately, captured by the MRV as free flyers and installed on a client [1], [2]. Repair tools beyond the arms are not part of the current pod design, with tools planned for the future [2].

Modes of operation

The recurring operational sequence is rendezvous with and capture of a free-flying Mission Extension Pod, phasing to the customer vehicle, and installation of the pod for life extension [1]. That operation is expected four to five times a year across a mission life of more than ten years, with each pod rendezvous and installation taking no longer than four weeks of dedicated event sequencing. The remaining time is available for secondary missions.

Space domain awareness data collection is the declared secondary mission [1]. Observing from inside the GEO belt, the vehicle produces a high concentration of data in the regime of greatest operational interest, is not subject to weather outages, and generally observes other GEO residents along the in-track axis, orthogonal to the ground and therefore in the direction in which ground-based passive sensors are weakest.

Ground operations

Operations are conducted by SpaceLogistics. No description of the control room, planning cycle or teleoperation latency for the robotic arms has been published.

Technologies developed

MRV is the first flight of dexterous robotic manipulation in geosynchronous orbit [1]. It carries the FREND arm design from a 2007 demonstration into operational use, the same design line NASA adopted for the OSAM-1 servicing arm [2], [3]. Where OSAM-1 was canceled in 2024, MRV continues the unprepared-client servicing capability: it began offering services to unprepared clients from 2026, inspecting and servicing GEO satellites with its dual arms and installing pods attached to the client apogee engine, giving satellites with depleted propellant or inoperable propulsion up to six years of life extension through electric propulsion [2].

The pod-carrier architecture is a different economic model from the MEV one. MEV docks to a client and flies it, so one servicer serves one client at a time [3]; the MRV installs a pod and departs, so one vehicle can serve many clients in sequence [1]. That economics rests on how much of the GEO fleet the docking interface actually fits: the vendor’s own MEV fact sheet claims compatibility with nearly 80 percent of GEO satellites on orbit, a figure given with no stated basis or definition of compatibility [12], and no independent figure for MRV’s own addressable fleet fraction has been published.

What is not established

No mass, power, propellant load, delta-v or thermal design for MRV has been published in any source held on the vehicle. The vehicle’s own manufacturer is the sole source for the docking lance dimensions, the RAS-1 arm designation, and the “six years” and “more than 10 years” lifetime figures, and the two Northrop Grumman channels disagree with each other on transit time, pod life extension and even which agency supplied the arms [6], [7], [8]. The camera detection ranges in the specifications table are model outputs computed before launch against an assumed 20 percent Lambertian, sunlit target, not measurements, and the only on-orbit evidence available for the sensor suite before MRV’s own launch was qualitative: three unresolved objects in a single MEV-2 frame [1], [4]. No navigation accuracy, capture-approach velocity, or docking outcome has yet been reported for MRV itself; the accuracy floor and closing-velocity threshold given here for lance-and-cone capture come from a ground and reduced-gravity test campaign on a different, smaller free-flyer, not from MRV or any GEO servicing vehicle [11]. The NASA capability surveys that describe the wider OSAM landscape share verbatim text across their editions and carry no independent evidence grading of their own [2], [5], [9].

References