Northrop Grumman Systems Corporation

Northrop Grumman Innovation Systems, Inc.

Matthew Alan Michel

William A Llorens

John Francis Papayanopoulos

Michael Alfred Tosto

Kevin David Tebbe

Daisaku Inoyama

Michael Foster

Gregg A Herbert

Ronald Lynn Graham

Dewey Edwin Cochran

Christine A Agathon-Burton

David Michael Murphy

Michael Edward McEachen

Peter O Sorensen

Jeffrey Braden

Quentin Williams

Emmanuel Simpri

Jack Purcell

Christina Agathon-Burton

Peter O Sorenson

Jeffrey R Braden

Vehicle capture assemblies and related devices, systems, and methods include one or more probe assemblies for engaging with and securing the target vehicle. The one or more probe assemblies may include one or more attenuation features or movable joints to enable and/or dampen movement of the one or more probe assemblies relative to a capture vehicle.

Vehicle capture assemblies and related devices, systems, and methods

Vehicle capture assemblies and related devices, systems, and methods include one or more probe assemblies for passively engaging with and securing the target vehicle.

Movable platforms for use with a vehicle capture assembly of a capture vehicle and related devices, systems, and methods include floors with rotatable legs extending between the floors. The rotation of the legs relative to one or more of the floors enables the movable platform to move from an initial position to a displaced position as one or more of the floors move relative to each other.

Movable platforms for vehicle capture assemblies and related devices, assemblies, systems, and methods

Methods and systems for mitigating or reducing the risk of an electrostatic discharge due to static charge differentials between a first spacecraft and a second spacecraft as the first spacecraft approaches the second spacecraft may be accomplished using a passive electrostatic discharge mitigation device. In some embodiments, mitigation of static potential between the first spacecraft and the second spacecraft may be actively accomplished by an electric propulsion system provided on the first spacecraft. In some embodiments, mitigation may be provided by both actively and passively mitigating static potential between the first spacecraft and the second spacecraft.

Systems, assemblies, and methods for system for mitigating electrostatic discharge between space vehicles

Capture assemblies and compliant extension assemblies may be utilized for insertion into a nozzle of a liquid engine of a spacecraft. The capture assembly may include an apparatus such as a probe for insertion into the nozzle and an assembly at least partially enclosed in a forward portion of the probe. The assembly may include a plurality of actuated fingers for deploying outwardly from the probe when the probe is inserted into the nozzle. The compliant extension assembly may be at least partially enclosed in a housing connected to the capture assembly for axial movement of the probe. The compliant extension assembly may facilitate axial movement of the probe between a retracted position and an extended position, wherein the probe is extended forwardly, relative to the housing.

Systems for capturing a client vehicle

Electrostatic discharge mitigation for a first spacecraft operating in proximity to a second spacecraft

Growing community of inventors

Oak Hill, VA, United States of America

Matthew Alan Michel