Abstract: A conical scanning method and system is provided for orienting a spacecraft with respect to a source. The system includes a spacecraft and an incidence angle sensor secured to the spacecraft to sense a signal from a source. The incidence angle sensor has a boresight that is canted with respect to the principal axis. A processor communicates with actuators on the spacecraft to adjust an attitude of the spacecraft based on information received from the incidence angle sensor and to thereby align a principal axis of the spacecraft with a direction from the spacecraft to the source. The method and system can also rely on information received from source presence sensors. The source may be the Sun, or a non-solar signal source.

Abstract: A new approach for rapid slew and settle of small satellites is based on four single degree-of-freedom control moment gyroscopes with variable speed flywheels (or reaction wheels) in a pyramid configuration, combined with path and endpoint constraint time-optimal control. The path and endpoint constrained time-optimal control can be augmented with momentum management without the use of additional actuators.

Abstract: A conical scanning method and system is provided for orienting a spacecraft with respect to a source. The system includes a spacecraft and an incidence angle sensor secured to the spacecraft to sense a signal from a source. The incidence angle sensor has a boresight that is canted with respect to the principal axis. A processor communicates with actuators on the spacecraft to adjust an attitude of the spacecraft based on information received from the incidence angle sensor and to thereby align a principal axis of the spacecraft with a direction from the spacecraft to the source. The method and system can also rely on information received from source presence sensors. The source may be the Sun, or a non-solar signal source.

Abstract: A new approach for rapid slew and settle of small satellites is based on four single degree-of-freedom control moment gyroscopes with variable speed flywheels (or reaction wheels) in a pyramid configuration, combined with path and endpoint constraint time-optimal control. The path and endpoint constrained time-optimal control can be augmented with momentum management without the use of additional actuators.

Abstract: A communication system is provided. The communication system includes a directional antenna, an antenna steering system to steer the directional antenna, a memory, and one or more processors coupled to the memory, the directional antenna, and the antenna steering system. The one or more processors are configured to identify a communication target and state information associated with the communication target, instruct the antenna steering system to steer the at least one directional antenna towards the communication target based on the state information, instruct the antenna steering system to perform a received power scan within a scan area to determine a maximum received power direction associated with a signal transmitted from the communication target, and track the maximum received power direction.

Abstract: An optical system for use in an Earth-orbiting satellite includes a plurality of image sensors disposed on a focal plane having a reference axis orthogonal thereto, optics configured to focus incident light onto the image sensors, a piezoelectric actuator coupled to the image sensors and configured to translate the image sensors in at least two axes each orthogonal to the reference axis, and at least one controller operably coupled to the plurality of image sensors and the piezoelectric actuator. The image sensors are configured to generate at least one image frame from light detected by the plurality of image sensors, the image frame including a target star and at least one guide star. The controller is configured to stabilize the position of the target star by adjusting the position of the piezoelectric actuator based on the changes in the position of the guide star.

Abstract: An optical system for use in an Earth-orbiting satellite includes a plurality of image sensors disposed on a focal plane having a reference axis orthogonal thereto, optics configured to focus incident light onto the image sensors, a piezoelectric actuator coupled to the image sensors and configured to translate the image sensors in at least two axes each orthogonal to the reference axis, and at least one controller operably coupled to the plurality of image sensors and the piezoelectric actuator. The image sensors are configured to generate at least one image frame from light detected by the plurality of image sensors, the image frame including a target star and at least one guide star. The controller is configured to stabilize the position of the target star by adjusting the position of the piezoelectric actuator based on the changes in the position of the guide star.