Spin stabilization of a spacecraft for an orbit maneuver

US9963248B2 · kind B2 · utility

Assignee

• The Boeing Company · US

Inventors

• Qinghong W. Wang · Torrance, US
• Alexander Jacob Sobel · Los Angeles, US
• Gary E. Lemke · Grand Rapids, US
• Timothy S. Lui · Cupertino, US
• Kangsik Lee · Torrance, US
• Glenn N. Caplin · Manhattan Beach, US
• Troy Allen Fontana · Torrance, US

Key dates

• Filing date: Feb 4, 2016
• Grant date: May 8, 2018
• Expiry date: Feb 4, 2036

Classification

• Technology area (CPC B): Performing Operations; Transporting
• CPC primary: B64G1/369
• WIPO field: Transport
• WIPO sector: Mechanical engineering

Abstract

Apparatus and methods for controlling a spacecraft for a transfer orbit. The spacecraft includes a momentum subsystem that stores angular momentum relative to a center of mass of the spacecraft, and a propulsion subsystem that includes electric thrusters. A controller identifies a target spin axis for the spacecraft, determines gimbal angles for electric thruster(s) that so that thrust forces from the electric thrusters are parallel to the target spin axis, and initiates a burn of the electric thruster(s) at the gimbal angles. The controller controls the momentum subsystem to compensate for a thruster torque produced by the burn of the electric thrusters. The momentum subsystem is able to produce a target angular momentum about the center of mass, where a coupling between the target angular momentum and an angular velocity of the spacecraft creates an offset torque to counteract the thruster torque.