Abstract: A host satellite comprises a first memory segment for storing a mission operation lookup table having at least one mission operation identifier associated with mission parameter constraints, a target object type and object detection model parameters associated with the target object type. A first sensor provides satellite sensor data that represents orbital mission characteristics. A second sensor captures images. A mission operation selector is responsive to the orbital mission characteristics and the mission parameter constraints for selecting the at least one mission operation identifier. An object detector is responsive to the captured images and the object detection model parameters associated with the selected mission operation identifier for detecting objects from the captured images. An analytics generator is responsive to the detected objects, the orbital mission characteristics, and the mission operation identifier for creating a mission analytics packet.

Abstract: A device for data handling and communication may comprise a housing, and a communication hub carried by the housing. The communication hub may include a main controller, a transceiver controller, and a plurality of transceivers. The transceivers may be positioned in communication with the transceiver controller and with hardware devices. The transceiver controller may be operable to control communication between each of the transceivers to selectively route and bridge communication between each of the hardware devices, which may be based on a control signal received from the main controller.

Abstract: A light filtering system for use in a light sensor carried by an orbital device is provided. The light filtering system may comprise a light filter device that may be removably carried by the light sensor. The light filter device may be positioned between a lens and one or more of a sub-sensor carried by the light sensor. The light filter device may be operable to receive light passed through the lens defined as captured light. The light filter device may also be operable to pass the captured light therethrough to filter one or more wavelengths of light from the captured light to define a filtered light. The at least one wavelength of light filtered out by the light filter device may comprise one or more wavelengths of light that may be inversely associated with an absorption band of a substance.

Abstract: A modular satellite testing platform system having an upper and a lower member along with a plurality of support members, intermediate members, and lower bar members that are interconnected to the upper member and the lower member. The system further includes a plurality of shelf members that are attached to the support members. The satellite also includes a plurality of bottom cover members that are attached to the lower member by a plurality of hinge members that allow the cover members to selectively rotated about an axis to be rotatably translated between an opened position and a closed position. The system yet further includes a thermal control system to allow maintaining the thermals of the satellite as desired.

Abstract: A modular satellite system is provided comprising a main body member, one or more controllers, a communication system, a datastore, a power unit, and one or more orbital cameras. The controller(s) may be operable to perform a mission instruction. The communication system may be in communication with the controller(s) and with a client terminal. The datastore may store data accessible by the controller(s). The orbital camera(s) may be operable to capture one or more image(s) associated with the mission instruction, which may be defined as captured image(s). The controller(s) may be operable to detect and identify one or more predetermined object(s) in the one or more captured image(s). The controller(s) may generate a mission analytics packet, and the controller(s) may be operable to transmit the mission analytics packet to the client terminal.

Abstract: A cube satellite deployer system having a body plate, a communication unit, a power unit, and a control unit. The body plate is adapted to be connected to a space arm assembly. The communication unit and the power unit are attached to the body plate. Each of the communication unit, power unit, and the control unit are in communication with one another. The body plate is also adapted to receive one or more cube satellite housings. The cube satellite housings are adapted to house and selectively launch one or more of the cube satellites that are housed by the cube satellite housings.

Abstract: A test platform apparatus is provided. The apparatus may comprise a lower member, and upper member, and a plurality of side members that may extend between the lower member and the upper member. The apparatus may also include one or more material testers and a sensor system that may be in communication with a flight computer. The sensor system may comprise one or more of a passive remote sensor and an active remote sensor. The apparatus may also include one or more of a camera that may be in communication with the flight computer. The apparatus may also include a plurality of heatsinks.

Abstract: A modular satellite apparatus for testing materials in a space setting is provided. The apparatus includes a lower member and an upper member, as well as rear support members, medial support members, front support members, and side members that each extend between the lower member and the upper member. They apparatus also includes attachment members connected to an external surface of the lower member and configured to connect to an external platform. The apparatus further includes a plurality of mounting members on an internal surface of the lower member or the side members, and a plurality of heatsinks. The lower member includes a plurality of heatsink receiving holes formed therein to receive portions of the heatsinks to connect the heatsinks to the lower member.

Abstract: A three-dimensional print head apparatus comprising a hopper, a nozzle, a barrel, a heating system, a fume extraction system, a dry air purge system, and an agitator. The hopper may having a cavity and may have a lower aperture. The nozzle may have an upper aperture and may have a lower aperture. The heating system may be positioned along at least a portion of the barrel, which may defined a heated zone of the barrel. The dry air purge system may be in fluid communication with the hopper. The agitator may have at least one paddle.

Abstract: A cube satellite deployer system having a body plate, a communication unit, a power unit, and a control unit. The body plate is adapted to be connected to a space arm assembly. The communication unit and the power unit are attached to the body plate. Each of the communication unit, power unit, and the control unit are in communication with one another. The body plate is also adapted to receive one or more cube satellite housings. The cube satellite housings are adapted to house and selectively launch one or more of the cube satellites that are housed by the cube satellite housings.

Abstract: A three-dimensional print head apparatus including a hopper, a nozzle, a barrel, and a heating system. The apparatus may further include a fume extraction system and a dry air purge system. The hopper may have a cavity and a lower aperture. The nozzle may have an upper aperture and a lower aperture. The heating system may be positioned along the barrel, and the dry air purge system may be in fluid communication with the hopper.

Abstract: A three-dimensional print head apparatus may include a securing mechanism, a hopper, a nozzle, a heating system, and a fume extraction system. The securing mechanism may be adapted to secure to a wrist joint of a robotic arm. The hopper may have a cavity and a lower aperture and may be secured to the securing mechanism. The nozzle may have an upper aperture and a lower aperture. The heating system may be positioned along the barrel.

Abstract: A three-dimensional print head apparatus comprising a hopper, a nozzle, a barrel, a heating system, a fume extraction system, a dry air purge system, and an agitator. The hopper may having a cavity and may have a lower aperture. The nozzle may have an upper aperture and may have a lower aperture. The heating system may be positioned along at least a portion of the barrel, which may defined a heated zone of the barrel. The dry air purge system may be in fluid communication with the hopper. The agitator may have at least one paddle.

Abstract: A three-dimensional print head apparatus including a hopper, a nozzle, a barrel, and a heating system. The apparatus may further include a fume extraction system and a dry air purge system. The hopper may have a cavity and a lower aperture. The nozzle may have an upper aperture and a lower aperture. The heating system may be positioned along the barrel, and the dry air purge system may be in fluid communication with the hopper.

Abstract: A modular satellite apparatus for testing materials in a space setting is provided. The apparatus includes a lower member and an upper member, as well as rear support members, medial support members, front support members, and side members that each extend between the lower member and the upper member. They apparatus also includes attachment members connected to an external surface of the lower member and configured to connect to an external platform. The apparatus further includes a plurality of mounting members on an internal surface of the lower member or the side members, and a plurality of heatsinks. The lower member includes a plurality of heatsink receiving holes formed therein to receive portions of the heatsinks to connect the heatsinks to the lower member.

Abstract: A modular satellite testing platform system having an upper and a lower member along with a plurality of support members, intermediate members, and lower bar members that are interconnected to the upper member and the lower member. The system further includes a plurality of shelf members that are attached to the support members. The satellite also includes a plurality of bottom cover members that are attached to the lower member by a plurality of hinge members that allow the cover members to selectively rotated about an axis to be rotatably translated between an opened position and a closed position. The system yet further includes a thermal control system to allow maintaining the thermals of the satellite as desired.

Abstract: A filter unit is provided to retrofit within signal lines that couple analog cockpit gauges to transducers in rotorcraft systems. The filter unit may include a housing assembly and an electromagnetic interference (EMI) filter assembly housed therein. The filter assembly may include a printed circuit board (PCB) having conductive PCB traces and a signal line input connector configured to connect to multiple transducer signal lines. The filter assembly may also include a signal line output connector configured to connect to multiple analog cockpit gauge signal lines and a plurality of common mode chokes electrically connected between the signal line input connector and the signal line output connector. Each common mode choke may be positioned on the PCB so that it does not electrically/magnetically interfere with the other common mode chokes of the plurality of common mode chokes.

Abstract: A vacuum chamber may include an ambient side and a vacuum side. The vacuum chamber may be configured to carry a feedthrough that may include a hollow tube, a first O-ring captured by a first recess within the hollow tube and a rod extending through the hollow tube. The outer circumference of the rod may be configured to contact an entirety of an inner circumference of the first O-ring. A vacuum fitting having an inner circumference may be fixedly secured to the hollow tube. The rod may be operable to be linearly movable within the hollow tube and may be rotatably movable about an axis within the hollow tube. An object may be secured to the rod and may be linearly and rotatably moved within the vacuum chamber.

Abstract: A filter unit is provided to retrofit within signal lines that couple analog cockpit gauges to transducers in rotorcraft systems. The filter unit may include a housing assembly and an electromagnetic interference (EMI) filter assembly housed therein. The filter assembly may include a printed circuit board (PCB) having conductive PCB traces and a signal line input connector configured to connect to multiple transducer signal lines. The filter assembly may also include a signal line output connector configured to connect to multiple analog cockpit gauge signal lines and a plurality of common mode chokes electrically connected between the signal line input connector and the signal line output connector. Each common mode choke may be positioned on the PCB so that it does not electrically/magnetically interfere with the other common mode chokes of the plurality of common mode chokes.

Abstract: A feedthrough for use in a vacuum chamber is provided and includes a hollow tube having a length, an inner circumference, and a first recess located within the inner circumference. The feedthrough also includes a first O-ring captured by the first recess within the hollow tube. The feedthrough further includes a rod extending through an entirety of the length of the hollow tube. An outer circumference of the rod is configured to contact an entirety of an inner circumference of the first O-ring, and a vacuum fitting is fixedly secured to the hollow tube.