Abstract: A machine learning (“ML”) model may be used to detect a presence of an object in one or more frames received from a camera sensor. The ML model may insert bounding boxes around the object and annotate the bounding boxes with one or more attributes of the object. The one or more frames and the annotated bounding boxes may be stored in a database configured to be searchable by at least one attribute of the one or more attributes. It may be determined whether the object is true positive (“TP”) event or a false positive (“FP”) event. The ML model may be re-trained using one or more of the database and the determination. If the object is a TP event, an alert may be transmitted to one or more devices with a location of the object that is based off of location information received from the camera sensor.

Abstract: An absolute vector gravimeter and method of use is provided. The absolute vector gravimeter includes one or more single axis accelerometers, each capable of pointing in at least two directions and calculating an estimated gravity component. Further embodiments provide for estimating a bias in the single axis accelerometer, as well as measuring non-ballistic accelerations along multiple axes and calculating estimated gravity components for each. A resultant non-ballistic acceleration vector can be calculated. Examples for reducing the RMS error in the estimated gravity components are also provided.

Abstract: A cryogenic coil assembly including a coil substrate with a flat surface, and a number of radial channels cut into a region of the flat surface. The cryogenic coil assembly also includes a spiral coil covering the radial channels, and a chemical bonding agent for bonding the spiral coil to the coil substrate. The chemical bonding agent is present within the radial channels.

Abstract: The use of an accelerometer for inertial navigation of a low thrust spacecraft undergoing acceleration wherein the inaccuracy of the accelerometer is less than the uncertainty in the accuracy of a modeled non-gravitational component of the acceleration that the spacecraft is undergoing is disclosed. A method of navigating a spacecraft having a low thrust propulsion system is also disclosed. The method comprises engaging the low thrust propulsion system, measuring the acceleration of the spacecraft using an accelerometer with an inaccuracy less than the uncertainty in the acceleration imparted by the low thrust propulsion system and acquiring a trajectory estimate using the measured acceleration. The trajectory estimate may be updated using an external reference navigation sensor.

Abstract: A system and method for protecting an electronics module on a spacecraft in space are described. The system includes a non-radiation hardened electronics module electrically connected to a power supply, with a switch connected between the power supply and the electronics module. The switch can disconnect the electronics module from the power supply in response to an event signal. A sensor which is capable of detecting a solar proton event is connected to the switch. The sensor emits the event signal upon detection of the solar proton event.

Abstract: A cryogenic coil assembly including a coil substrate with a flat surface, and a number of radial channels cut into a region of the flat surface. The cryogenic coil assembly also includes a spiral coil covering the radial channels, and a chemical bonding agent for bonding the spiral coil to the coil substrate. The chemical bonding agent is present within the radial channels.

Abstract: A cryogenic coil assembly including a coil substrate with a flat surface, and a number of radial channels cut into a region of the flat surface. The cryogenic coil assembly also includes a spiral coil covering the radial channels, and a chemical bonding agent for bonding the spiral coil to the coil substrate. The chemical bonding agent is present within the radial channels.

Abstract: The use of an accelerometer for inertial navigation of a low thrust spacecraft undergoing acceleration wherein the inaccuracy of the accelerometer is less than the uncertainty in the accuracy of a modeled non-gravitational component of the acceleration that the spacecraft is undergoing is disclosed. A method of navigating a spacecraft having a low thrust propulsion system is also disclosed. The method comprises engaging the low thrust propulsion system, measuring the acceleration of the spacecraft using an accelerometer with an inaccuracy less than the uncertainty in the acceleration imparted by the low thrust propulsion system and acquiring a trajectory estimate using the measured acceleration. The trajectory estimate may be updated using an external reference navigation sensor.

Abstract: An absolute vector gravimeter and method of use is provided. The absolute vector gravimeter includes one or more single axis accelerometers, each capable of pointing in at least two directions and calculating an estimated gravity component. Further embodiments provide for estimating a bias in the single axis accelerometer, as well as measuring non-ballistic accelerations along multiple axes and calculating estimated gravity components for each. A resultant non-ballistic acceleration vector can be calculated. Examples for reducing the RMS error in the estimated gravity components are also provided.

Abstract: A system and method for protecting an electronics module on a spacecraft in space are Described. The system includes a non-radiation hardened electronics module electrically connected to a power supply, with a switch connected between the power supply and the electronics module. The switch can disconnect the electronics module from the power supply in response to an event signal. A sensor which is capable of detecting a solar proton event is connected to the switch. The sensor emits the event signal upon detection of the solar proton event.

Abstract: A quadrupole responder for an OQR-type gravity gradiometer comprises a housing, and a mass quadrupole positioned within the housing. The mass quadrupole has a pair of sides, and also has a center of mass between the sides. At least a pair of torsion spring flexures are provided by pins connecting said side of said mass quadrupole to the housing. The torsion spring flexures provide an axis of rotation which passes through the center of mass of the mass quadrupole and through both spring flexures. The pins are integral with the mass quadrupole.

Abstract: A cryogenic coil assembly including a coil substrate with a flat surface, and a number of radial channels cut into a region of the flat surface. The cryogenic coil assembly also includes a spiral coil covering the radial channels, and a chemical bonding agent for bonding the spiral coil to the coil substrate. The chemical bonding agent is present within the radial channels.

Abstract: Systems and methods for determining a bias-corrected value of at least one component of a gravity gradient tensor using a gravity gradiometer and a measurement bias of the gravity gradiometer wherein the measurement bias varies with time, by taking at least three measurements with the gravity gradiometer positioned in at least two orientations. Any gravity gradiometer can be used, including a Cross-Component Gravity Gradiometer (CCGG), an Orthogonal Quadrupole Responder (OQR), an In-Line Responder (ILR), a Diagonal-Component Gravity Gradiometer, or a Multi-Component Gravity Gradiometer (MCGG).

Abstract: A quadrupole responder for an OQR-type gravity gradiometer comprises a housing, and a mass quadrupole positioned within the housing. The mass quadrupole has a pair of sides, and also has a center of mass between the sides. At least a pair of torsion spring flexures are provided by pins connecting said sideof said mass quadrupole to the housing. The torsion spring flexures provide an axis of rotation which passes through the center of mass of the mass quadrupole and through both spring flexures. The pins are integral with the mass quadrupole.

Abstract: Systems and methods for determining a bias-corrected value of at least one component of a gravity gradient tensor using a gravity gradiometer and a measurement bias of the gravity gradiometer wherein the measurement bias varies with time, by taking at least three measurements with the gravity gradiometer positioned in at least two orientations. Any gravity gradiometer can be used, including a Cross-Component Gravity Gradiometer (CCGG), an Orthogonal Quadrupole Responder (OQR), an In-Line Responder (ILR), a Diagonal-Component Gravity Gradiometer, or a Multi-Component Gravity Gradiometer (MCGG).

Abstract: A quadrupole responder for an OQR-type gravity gradiometer comprises a housing, and a mass quadrupole positioned within the housing. The mass quadrupole has a pair of sides, and also has a center of mass between the sides. At least a pair of torsion spring flexures are provided by pins connecting said side of said mass quadrupole to the housing. The torsion spring flexures provide an axis of rotation which passes through the center of mass of the mass quadrupole and through both spring flexures. The pins are integral with the mass quadrupole.

Abstract: A quadrupole responder for an OQR-type gravity gradiometer comprises a housing, and a mass quadrupole positioned within the housing. The mass quadrupole has a pair of sides, and also has a center of mass between the sides. At least a pair of torsion spring flexures are provided by pins connecting said side of said mass quadrupole to the housing. The torsion spring flexures provide an axis of rotation which passes through the center of mass of the mass quadrupole and through both spring flexures. The pins are integral with the mass quadrupole.

Abstract: A gravity gradiometer having quadrupole responders in which a mass quadrupole is supported by a torsional spring forming a flexure allowing rotation of the mass quadrupole about its center of mass. The flexure can be a pair of spaced apart posts. The flexure can be made from glassy metal having at room temperature a high elastic limit, high stiffness, high strength and low internal damping. The flexure can alternatively be a web made of glassy metal.

Abstract: A gravity gradiometer having quadrupole responders in which a mass quadrupole is supported by a torsional spring forming a flexure allowing rotation of the mass quadrupole about its center of mass. The flexure can be a pair of spaced apart posts. The flexure can be made from glassy metal having at room temperature a high elastic limit, high stiffness, high strength and low internal damping. The flexure can alternatively be a web made of glassy metal.