Abstract: Discussed herein are devices, systems, and methods for improved trajectory planning. A method can include providing two of (i) a first value indicating a change in velocity to alter an orbit of a first object to a transfer orbit; (ii) a second value indicating a range between the first object and a second object; or (iii) a third value indicating an altitude of the first object relative to a celestial body around which the first and second objects are orbiting as input to a machine learning (ML) model, receiving, from the ML model, a holdout value, the holdout value a prediction of the value, of the first value, the second value, and the third value, that was not provided to the ML model, and providing the holdout value to an orbital planner.

Abstract: Disclosed herein is a panel assembly configured to form a mullion joint. The panel assembly can comprise a panel composed of a material substrate that, in some examples, can be transparent to radio frequency signals. The panel assembly can further comprise a first bezel configured to frame a perimeter of the panel on a first side of the panel. The panel assembly can comprise a second bezel configured to frame the perimeter of the panel on a second side of the panel opposite of the first side, the second bezel comprising cogs formed on a first edge of the second bezel. The cogs of the second bezel can be configured to receive and join with cogs of a bezel of a second panel assembly to form a mullion joint. The mullion joint can be transparent, opaque, or partially transparent to radio frequency signals and/or visible light.

Abstract: A digital measuring device implemented on a photonic integrated circuit, the digital measuring device including a laser source implemented on the photonic integrated circuit configured to provide light, a first waveguide structure implemented on the photonic integrated circuit configured to direct a first portion of light from the laser source at a moving object and receive light reflected from the moving object, a second waveguide structure implemented on the photonic integrated circuit configured to combine a second portion of light from the laser source with the light reflected from the moving object to produce a measurement beam, a first multiplexer implemented on the photonic integrated circuit configured to split the measurement beam into a plurality of channels, and a plurality of detectors implemented on the photonic integrated circuit configured to detect an intensity value of each channel to measure a distance between the digital measuring device and the moving object.

Abstract: Dry ice cooling systems and methods of making dry ice cooling systems are disclosed. According to embodiments, dry ice cooling systems include a compression container including compressed liquid carbon dioxide. The dry ice cooling systems include a dry ice container coupled to the compression container to receive the liquid carbon dioxide and house dry ice as it forms. The dry ice container includes a liquid coolant. Further, the dry ice cooling system includes a heat exchanger to couple a heat-generating source to the dry ice container.

Abstract: A system includes a pair of chassis, a housing, and a cooling module. Each chassis including multiple rails with adjacent rails defining card slots. The housing connected to the chassis in first card slots on the pair of chassis and formed to contain electronic components including a heat generating component. The cooling module connected to the chassis in second card slots on the pair of chassis and formed to contact the heat generating component through an aperture in the housing.

Abstract: A semiconductor-based imaging device and method of manufacture. A direct bond hybridization (DBH) structure is formed on a top surface of a read out integrated circuit (ROIC). A silicon-based detector is bonded to the ROIC via the DBH structure. A non-silicon-based detector is bonded to the DBH structure located on the top of the ROIC using indium-based hybridization.

Abstract: A mechanism for attachment and detachment of a fixed or controllable airfoil to an airframe includes a base adapted for attachment to a root of the airfoil and a slot beam adapted for attachment along the airframe (e.g., parallel to the longitudinal X-axis of the airframe). The base includes a plurality of pins spaced along and held between parallel rails. The slot beam includes a plurality of slots arranged along the beam. Each slot has a lead-in portion to receive one of the plurality of pins and a longitudinally-oriented tapered portion (e.g., parallel to the longitudinal X-axis with a taper between 1 and 5 degrees) to engage the pin so that the base is seated in the slot beam to position the airfoil against the airframe in an XY plane. A pre-load mechanism is configured to apply a force along the X-axis to press the plurality of pins into the respective tapered portions to fix the base relative to the slot beam in six degrees of freedom (6 DOF).

Abstract: An apparatus includes a deformable mirror. The deformable mirror includes a reflective surface configured to reflect a high-energy laser (HEL) beam and to focus the HEL beam on a target. The deformable mirror also includes multiple actuators configured to adjust a shape of the reflective surface in order to maintain focus of the HEL beam on the target over a specified range of distances between the deformable mirror and the target. At least one portion of the reflective surface is configured to be adjusted by the actuators and obtain convex, flat, and concave shapes.

Abstract: Systems and methods for VIIRS image processing. The method can include receiving image data of immediately adjacent VIIRS image scans including a first image scan and a second image scan. The first image scan and the second image scan provide a partially overlapping view of a geographic area. The method can further involve resampling columns of pixels of the first image scan and the second image scan. The resampling can include selecting, in the first image scan and the second image scan, a subset of pixel values in each column that correspond to a specified geographic distance. The method can further involve upsampling the selected pixels to an equal number of pixels in each column resulting in upsampled pixel values and interpolating the upsampled pixel values to produce modified first and second image scans.

Abstract: A system for restraining one or more control surfaces of a tactical flight vehicle includes a retaining frame secured at an aft end of the tactical flight vehicle and a cover plate releasably coupled to the retaining frame with a resilient lock ring. The resilient lock ring is disposed between the retaining frame and the cover plate and is deformable between a locking configuration and an unlocking configuration. A control surface restraining ring is releasably coupled to the cover plate and has control surface restraints configured to engage respective control surfaces. The resilient lock ring is configured to deform from the locking configuration to the unlocking configuration upon a launch of the tactical flight vehicle such that the cover plate becomes uncoupled from the retaining frame and may be jettisoned from the tactical flight vehicle after the launch.

Abstract: An aerospace mirror having a reaction bonded (RB) silicon carbide (SiC) mirror substrate, and a SiC cladding on the RB SiC mirror substrate forming an optical surface on a front side of the aerospace mirror. A method for manufacturing an aerospace mirror comprising obtaining a green mirror preform comprising porous carbon, silicon carbide (SiC), or both, the green mirror preform defining a front side of the aerospace mirror and a back side of the aerospace mirror opposite the front side; removing material from the green mirror preform to form support ribs on the back side; infiltrating the green mirror preform with silicon to create a reaction bonded (RB) SiC mirror substrate from the green mirror preform; forming a mounting interface surface on the back side of the aerospace mirror from the RB SiC mirror substrate, and forming a reflector surface of the RB SiC mirror substrate on the front side of the aerospace mirror.

Abstract: An optics system includes a convex catching mirror located within respect to the concave primary mirror to form an optical path for a field of view. A conical volume is formed with respect to the concave primary mirror and the convex catching mirror, the optical path not obstructed by the conical volume. A component within the conical volume.

Abstract: A modular cable assembly for use with a system including a first system device and a second system device is provided. The first system device is configured to produce a first electronic communication protocol. The second system device is configured to produce a second electronic communication protocol. The modular cable assembly includes a first connector, a second connector, a cable body, and a communication control assembly. The communication control assembly includes a communication translation module (CTM). The CTM includes a protocol storage submodule configured to store a plurality of predetermined system device protocols (PSDPs) and a processor in communication with the protocol storage submodule storing instructions, which instructions when executed cause the processor to identify the second system device using a second selected PSDP of the plurality of PSDPs and translate at least a portion of the second electronic communication protocol into the first electronic communication protocol.

Abstract: A system/device, such as a gradiometer probe for detecting RF signals, or for example for explosive detection, has the shape of the coils in its adjustment mechanism that minimizes the cross-talk between the receiver probe (Rx) and the transmitting antenna (Tx) in such a way as to minimize (or reduce) the areas where the distance between the coils during the adjustment is the smallest. Moving coils along the plain of the coils is one mechanism of achieving it. Having the coils of different shapes, e.g., circular receiver and oval transmitter coils, is another. Many shapes are possible, including circular, oval, elliptical, and polygonal, to give a few examples. In some embodiments both of these methods/approaches are combined in a single device.

Abstract: A system includes a high energy laser (HEL) configured to transmit a HEL beam and a beacon illumination laser (BIL) configured to transmit a BIL beam. The system also includes at least one fast steering mirror (FSM) configured to steer the BIL beam to be offset from the HEL beam. The system further includes at least one Coudé path FSM configured to correct for atmospheric jitter of the HEL beam and the BIL beam while maintaining the offset of the BIL beam from the HEL beam.

Abstract: A phased antenna array calibration station comprising an enclosure comprising a first rectangular interior room comprising at least one exterior door, a power source device, a cooling device, and a controller device configured to control power, cooling, and testing within a second interior room and an antenna under test (AUT); and the second rectangular interior room comprising at least one interior door abutting the first interior room, an opening in one wall of the second interior room, a radio frequency (RF) absorbing material covering all interior surfaces of the second interior room, and at least one movable electromagnetic interference (EMI) shield configured to form an EMI seal around the opening and active elements of AUT aligned with opening; and support fixture configured to support AUT and align active elements of AUT with opening to second interior room comprising cooling and electronic unit (CEU) configured to cool AUT and operate AUT.

Abstract: A method including: receiving, at a given satellite, a target list, the target list identifying a plurality of targets; identifying a plurality of satellites of which the given satellite is part; generating, at the given satellite, a plurality of satellite-target pairs, each satellite-target pair including a respective one of the plurality of targets and a respective one of the plurality of satellites; identifying a plurality of costs, each of the plurality of costs corresponding to a different one of the plurality of satellite-target pairs; identifying, by the given satellite, a plurality of assignment pairs, the plurality of assignment pairs being identified based on the plurality of satellite-target pairs and the plurality of costs, each of the plurality of assignment pairs including a respective one of the plurality of targets and a respective one of the plurality of satellites that is assigned to track the respective target.

Abstract: An optical sensor comprises foreoptics configured to receive an image signal, an image optic operable to focus the image signal, at least one focal plane array (FPA) configured to detect the image signal, and a jitter stabilization system. The jitter stabilization system can comprise a transmitter configured to transmit a jitter source signal to the foreoptics and a position sensor configured to receive a jitter return signal. The position sensor can be positioned at a shared focus with the at least one FPA. The optical sensor further comprises a diffraction grating operable to reflect and diffract at least a portion of the jitter source signal. The jitter return signal received at the position sensor comprises at least a portion of the reflected and diffracted jitter source signal.

Abstract: A method includes receiving, using a first graphical user interface, information associated with a request for proposal, quote, bid, or information (RFX) to be generated and provided to a supplier. The method also includes identifying one of multiple acquisition scenarios associated with the RFX to be generated based on the received information. The method further includes generating the RFX based on the received information and the identified acquisition scenario. The method also includes receiving, using a second graphical user interface, an RFX response from the supplier. The method further includes identifying multiple requirements associated with the RFX response based on the identified acquisition scenario and comparing contents of the RFX response to the identified requirements. In addition, the method includes automatically informing the supplier of one or more identified requirements for which the RFX response is non-compliant.

Abstract: A hinge includes internal on-axis stopping mechanisms that cause the hinge to shear and break at an on-axis weakened region of the hinge when rotation of the hinge reaches a predetermined angle with a specified torsional load. The on-axis configuration is compact, has minimal impact on the outer mold line (OML) of the object to which it is mounted both pre and post detachment and allows for accurate tailoring of the torsional load that will detach the hinge.