Abstract: Apparatus and methods for controlling a spacecraft for a transfer orbit. The spacecraft includes a propulsion subsystem with electric thrusters that are installed with two-axis gimbal assemblies. The spacecraft also includes a controller that identifies a target spin axis for the spacecraft, determines an actual spin axis for the spacecraft during the transfer orbit, determines gimbal angles for the electric thruster(s) that adjust the actual spin axis toward the target spin axis, and initiates a burn of the electric thruster(s) at the gimbal angles.

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.

Abstract: Apparatus and methods for controlling a spacecraft for a transfer orbit. The spacecraft includes a propulsion subsystem with electric thrusters that are installed with two-axis gimbal assemblies. The spacecraft also includes a controller that identifies a target spin axis for the spacecraft, determines an actual spin axis for the spacecraft during the transfer orbit, determines gimbal angles for the electric thruster(s) that adjust the actual spin axis toward the target spin axis, and initiates a burn of the electric thruster(s) at the gimbal angles.

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.

Abstract: A method and system for securing a flexible circuit to a mounting structure is disclosed. The system can include a surface-mount device, flexible circuit, stiffener, and bracket. The stiffener is used as an intermediate coupling device between the flexible circuit and bracket. The flexible circuit is coupled to the stiffener with a heat-activated adhesive. Next, the surface-mount device is mounted to the flexible circuit with surface-mounting techniques. A peripheral area of the stiffener is then welded to the bracket. The bracket in turn can be fastened to the enclosure of an electronic device.

Abstract: A method and system for securing a flexible circuit to a mounting structure is disclosed. The system can include a surface-mount device, flexible circuit, stiffener, and bracket. The stiffener is used as an intermediate coupling device between the flexible circuit and bracket. The flexible circuit is coupled to the stiffener with a heat-activated adhesive. Next, the surface-mount device is mounted to the flexible circuit with surface-mounting techniques. A peripheral area of the stiffener is then welded to the bracket. The bracket in turn can be fastened to the enclosure of an electronic device.