Abstract: The present invention relates to an apparatus including a self-regulating current source, which utilizes a switching regulator to provide high efficiency power conversion and a high-side current monitor, but instead of driving the feedback input with a voltage divider to set the output voltage, the self-regulating current source utilizes a high-side current sense resistor with an operational amplifier optimized for current sensing, to drive the feedback input to the switching regulator, thereby creating a self-regulating constant current source. By adjusting the gain of the operational amplifier, the user can directly set the optimized current needed for using the apparatus in a variety of deployment devices, including satellite and pyrotechnic applications.

Abstract: A microcontroller controlled altimeter includes a microcontroller, a digital altitude pressure sensor with a pressure indicating output coupled to the microprocessor, and at least one Form A solid state relay coupled to the microcontroller, where the microcontroller is configured to provide control signals to the at least one Form A solid state relay to provide an open circuit between normally open and common terminals of the at least one Form A solid state relay if the digital altitude pressure sensor output is less than, or equal to, a setpoint for the at least one Form A relay, and provide continuity between the normally open and common terminals of the at least one Form A solid state relay if the digital altitude pressure sensor output is greater than the setpoint for the at least one Form A relay.

Abstract: The invention disclosed herein includes various embodiments and components of a solid state analog altimeter switch useful for generating switching signals based on altitude determined from barometric pressure. Embodiments of the solid state analog altimeter switch disclosed herein are designed to be extremely accurate, small, robust and inexpensive to produce. Such solid state analog altimeter switches are particularly useful for generating switching events based on predetermined altitudes in sounding rockets.

Abstract: A microcontroller controlled altimeter includes a microcontroller, a digital altitude pressure sensor with a pressure indicating output coupled to the microprocessor, and at least one Form A solid state relay coupled to the microcontroller, where the microcontroller is configured to provide control signals to the at least one Form A solid state relay to provide an open circuit between normally open and common terminals of the at least one Form A solid state relay if the digital altitude pressure sensor output is less than, or equal to, a setpoint for the at least one Form A relay, and provide continuity between the normally open and common terminals of the at least one Form A solid state relay if the digital altitude pressure sensor output is greater than the setpoint for the at least one Form A relay.

Abstract: A system, method, and computer-readable storage devices for a 6U CubeSat with a magnetometer boom. The example 6U CubeSat can include an on-board computing device connected to an electrical power system, wherein the electrical power system receives power from at least one of a battery and at least one solar panel, a first fluxgate sensor attached to an extendable boom, a release mechanism for extending the extendable boom, at least one second fluxgate sensor fixed within the satellite, an ion neutral mass spectrometer, and a relativistic electron/proton telescope. The on-board computing device can receive data from the first fluxgate sensor, the at least one second fluxgate sensor, the ion neutral mass spectrometer, and the relativistic electron/proton telescope via the bus, and can then process the data via an algorithm to deduce a geophysical signal.

Abstract: A system, method, and computer-readable storage devices for a 6U CubeSat with a magnetometer boom. The example 6U CubeSat can include an on-board computing device connected to an electrical power system, wherein the electrical power system receives power from at least one of a battery and at least one solar panel, a first fluxgate sensor attached to an extendable boom, a release mechanism for extending the extendable boom, at least one second fluxgate sensor fixed within the satellite, an ion neutral mass spectrometer, and a relativistic electron/proton telescope. The on-board computing device can receive data from the first fluxgate sensor, the at least one second fluxgate sensor, the ion neutral mass spectrometer, and the relativistic electron/proton telescope via the bus, and can then process the data via an algorithm to deduce a geophysical signal.

Abstract: Miniature release mechanisms constrain objects, such as deployables during the launch of space vehicles, such as small satellites and nanosatellites, and enable the release of the objects once a desired destination is reached by the space vehicle. Constraint and release of the objects are achieved by providing a secure threaded interface that may be released by the release mechanisms. The release mechanisms include a housing structure; a release block can include a threaded interface; one or more retracting pins; one or more release springs; a breakable link, such as a plastic link; a cable harness clamp; and a circuit board. The release mechanism can be 0.1875 inches (approximately 4.8 mm) thick.