Abstract: An improved spacecraft actuator wheel is provided which can be operated as a momentum wheel, a reaction wheel or a gimbal. The actuator wheel has a central cavity. One or more battery modules are located within the actuator wheel's central cavity. The battery modules supply power to one or more electronic components affixed to the actuator wheel or mounted on the spacecraft frame via an electrical harness. In addition, the actuator wheel's central cavity is pressurizeable for storing spacecraft propellant which can be controllably diverted to the spacecraft's thrusters through conduits and flow valves.

Abstract: A method is provided for realigning or relieving mechanical stress in a spacecraft frame. The process includes providing a spacecraft which includes at least two frame subsections connected by a mechanical connector. The mechanical connector provides both a soft dock connection which mechanically connects the two frame subsections but allows relative movement between the two frame sections and a hard dock connection which mechanically connects the two frame subsections but does not allow relative movement between the two frame sections. Once in space, a controller causes the mechanical connector to transition from a hard dock connection to a soft dock connection, which is maintained for a predetermined time period to realign or relieve stress within the spacecraft frame. Thereafter, the controller causes the mechanical connector to transition from the soft dock connection back to the hard dock connection.

Abstract: A method is provided for realigning or relieving mechanical stress in a spacecraft frame. The process includes providing a spacecraft which includes at least two frame subsections connected by a mechanical connector. The mechanical connector provides both a soft dock connection which mechanically connects the two frame subsections but allows relative movement between the two frame sections and a hard dock connection which mechanically connects the two frame subsections but does not allow relative movement between the two frame sections. Once in space, a controller causes the mechanical connector to transition from a hard dock connection to a soft dock connection, which is maintained for a predetermined time period to realign or relieve stress within the spacecraft frame. Thereafter, the controller causes the mechanical connector to transition from the soft dock connection back to the hard dock connection.

Abstract: A spring ring circuit assembly is provided for transmitting electricity between a first structure and a second structure which rotates relative to the first structure. The spring ring circuit assembly includes a spring ring which is affixed to and concentrically positioned around a spindle. The spring ring circuit assembly further includes a circular band concentrically positioned around the spring ring so as to create an annular space between the spring ring and circular band. The spring ring circuit assembly further includes an inner set of rollers positioned around and engaging the spring ring, and an outer set of rollers positioned within and engaging the circular band. The spring ring, rollers and circular band are made of electrically conductive materials so as to allow electricity to transmit between the spring ring and the circular band which is capable of rotating around the spring ring.

Abstract: A method for providing thermal balance of spacecraft electronics is provided. The spacecraft includes two or more electronic units wherein each electronic unit is capable of performing the same spacecraft operational task. The method for balancing the temperature of spacecraft electronics further includes providing each of the two or more electronic units with a temperature sensor for determining the temperature of that electronics unit. The electronic units and their respective temperature sensors are connected to a controller. In the event that the controller determines that the temperature of an activated first electronics unit has reached or exceeded a predetermined threshold, and the controller has determined that the temperature of a second deactivated electronics unit is below a predetermined threshold, the controller automatically deactivates the first electronics unit and activates the second electronics unit to perform the task previously being performed by the first electronics unit.

Abstract: A method for providing thermal balance of spacecraft electronics is provided. The spacecraft includes two or more electronic units wherein each electronic unit is capable of performing the same spacecraft operational task. The method for balancing the temperature of spacecraft electronics further includes providing each of the two or more electronic units with a temperature sensor for determining the temperature of that electronics unit. The electronic units and their respective temperature sensors are connected to a controller. In the event that the controller determines that the temperature of an activated first electronics unit has reached or exceeded a predetermined threshold, and the controller has determined that the temperature of a second deactivated electronics unit is below a predetermined threshold, the controller automatically deactivates the first electronics unit and activates the second electronics unit to perform the task previously being performed by the first electronics unit.