Abstract: A payload interposer (PIP) board provides an interface for hosting payloads on a space vehicle platform. Payload development may be performed via the PIP board in a manner that “abstracts” the hardware of the space vehicle from the payload developer. The PIP board may include a host side payload interface connector that connects to a space vehicle and a payload side payload interface connector that connects to a payload. Power, CDH, and other space vehicle functionality may thus be provided to the payload from the space vehicle via the PIP board.

Abstract: A compact SFS may can be deployed in small space vehicles. The SFS may have a small size, weight, and low power requirements. The hardware, software, catalogs, and calibration algorithm of the SFS provide highly accurate attitude information that can be used for pointing. For instance, accurate attitude determination may be provided that supports pointing of a deployable high gain helical antenna. A full “lost in space” attitude solution, accurate to about an arcminute, may be accomplished in under a minute. The SFS may be fully reprogrammable on orbit, allowing continued algorithm development and deployment after launch.

Abstract: A payload interposer (PIP) system and its control software provide an interface between a space vehicle and a payload. The PIP board facilitates power and communications between a command and data handler (CDH) of the space vehicle and the payload. A microcontroller of the PIP board may control operation of the payload, format messages between the space vehicle and the payload, and extract data from the payload for downlink via the space vehicle.

Abstract: An ADCS module may be configured to use coordinate data from 2D photodiodes in one or more sun sensors to determine a sun vector. The ADCS module may then use the sun vector in reference to its own body faced (BF) coordinate system to calculate a change in the orientation of the space vehicle. The change in orientation mechanism may be accomplished by reaction wheels, ion thrusters, or other orientation altering mechanisms. A miniature, intelligent star tracker may be included that improves satellite attitude determination and pointing accuracy. An improved reaction wheel assembly may be included that is more robust and suitable for inclusion in small space vehicles.

Abstract: An adaptable, modular, multi-purpose (AMM) space vehicle backplane may accommodate boards and components for various missions. The AMM backplane may provide a common hardware interface and common board-to-board communications. Components, connectors, test points, and sensors may be embedded directly into the backplane to provide additional functionality, diagnostics, and system access. Other space vehicle sections may plug directly into the backplane.

Abstract: An adaptable, modular, multi-purpose (AMM) space vehicle backplane may accommodate boards and components for various missions. The AMM backplane may provide a common hardware interface and common board-to-board communications. Components, connectors, test points, and sensors may be embedded directly into the backplane to provide additional functionality, diagnostics, and system access. Other space vehicle sections may plug directly into the backplane.

Abstract: An ADCS module may be configured to use coordinate data from 2D photodiodes in one or more sun sensors to determine a sun vector. The ADCS module may then use the sun vector in reference to its own body faced (BF) coordinate system to calculate a change in the orientation of the space vehicle. The change in orientation mechanism may be accomplished by reaction wheels, ion thrusters, or other orientation altering mechanisms. A miniature, intelligent star tracker may be included that improves satellite attitude determination and pointing accuracy. An improved reaction wheel assembly may be included that is more robust and suitable for inclusion in small space vehicles.