Abstract: An ammunition cartridge including a case, an ignitable material within the case and an optical primer for igniting the ignitable material. The optical primer includes a conductive cylindrical cup electrically coupled to the case and a circular conductive button including a top button portion positioned in the cup and a bottom button portion extending through an opening in the cup, where the button and the cup are electrically isolated. The optical primer further includes a first bracket electrically coupled to the button, a second bracket electrically coupled to the cup, and a pair of laser diodes electrically coupled in a reverse parallel direction and being electrically coupled to the first and second brackets, where one of the laser diodes generates a laser beam that ignites the ignition material in response to a current flow in either direction through the case, the cup and the button.

Abstract: One example includes an Ising machine system. The system includes a plurality of ring oscillators that are each configured to propagate an oscillation signal. Each of the ring oscillators can be cross-coupled with at least one other of the ring oscillators via a respective one of the oscillation signals to provide a respective phase coupling between the respective cross-coupled ring oscillators. The system also includes an Ising machine controller configured to generate control signals corresponding to parameters of an Ising problem and including a plurality of delay selection signals. The Ising machine controller can provide at least one of the delay selection signals to each of the ring oscillators. The delay selection signal can be configured to set a variable propagation delay of the ring oscillator to control the relative phase coupling of each of the ring oscillators to each of the at least one other of the ring oscillators.

Abstract: One example includes a switch system. The system includes a first signal port and a second signal port. The system also includes a first switching path arranged between the first and second signal ports. The first switching path includes at least one first switch and at least one of the at least one first switch being configured as a high-speed switching device. The system further includes a second switching path arranged between the first and second signal ports in parallel with the first switching path. The second switching path includes at least one second switch and at least one of the at least one second switch being configured as a high-performance switching device.

Abstract: A transmitter for a chaos communications system employing chaotic symbol modulation that perform auto-indexing, temporal gain control, increased path diversity and sequence lock up prevention. The transmitter includes a symbol mapper that converts a series of information bits to a series of bit symbols, and a chaos modulator providing chaotic spreading modulation of the bit symbols. The chaos modulator includes a plurality of chaos generators, one for each bit symbol, providing a chaos sequence for the bit symbols. Each chaos modulator includes a RAM/ROM that provides auto-indexing where a chaos sequence output from the RAM/ROM is fed back to an input of the RAM/ROM from which a chaos sequence at a next address in the RAM/ROM is selected as the output of the modulator.

Abstract: A containerized cross-domain solution (CDS) is disclosed herein. In some examples, a first network interface container can be executed on a server to run a first network interface application to receive a data packet that includes data generated by a first process executing at a first security domain. A filter container can be executed on the server to run a data filter to evaluate a data content of the data to determine whether the data content violates a set of data rules. A second network interface container can be executed on the server to run a second network interface application. The data packet can be provided to the second network interface application in response to determining that the data content does not violates the set of data rules. The second network interface application can provide the data packet to a second security domain for a second process executing therein.

Abstract: In an example, a synchronization signal can be transmitted to a plurality of synchronizers. The plurality of synchronizers can include a plurality of upstream synchronizers and a downstream synchronizer. Each synchronizer of the plurality of upstream synchronizers can be caused to count from a respective count value until a predetermined end count sequence value in response to receiving the synchronization signal. The respective count value stored at each synchronizer can be representative of a difference in time between a respective upstream synchronizer of the plurality of upstream synchronizers receiving the synchronization signal and the downstream synchronizer receiving the synchronization signal. A respective processing element of a plurality of processing elements can be caused to start a respective function or operation in response to a respective upstream synchronizer reaching the predetermined end count sequence value.

Abstract: One example describes a superconducting XOR-gate system. The system includes a pulse generator configured to generate a decision pulse. The system also includes an input superconducting XOR-2 gate that receives a first superconducting logic input signal and a second superconducting logic input signal and is configured to perform a logic XOR function based on the decision pulse on a given phase of a clock signal to provide an intermediate superconducting logic output signal. The system also includes an output superconducting XOR-2 gate that receives the intermediate superconducting logic output signal and a third superconducting logic input signal and is configured to perform a logic XOR function based on the decision pulse on the given phase of the clock signal to provide a superconducting logic output signal.

Abstract: A LIDAR system that scans a beam in a full 360° FOV without any moving parts. The system includes a transmitter sub-system having a tunable laser beam source, an SPPR responsive to the laser beam, and a conical mirror receiving the output beam and directing the output beam into a desired FOV. The system also includes a receiver sub-system responsive to a reflected beam that is reflected off of an object that receives the output beam from the mirror, where the receiver sub-system includes a plurality of detector modules each including a receiver detector and arranged so that at least one detector module receives the reflected beam from any direction. The system further includes a signal processor sub-system that tunes the frequency of the laser beam generated by the laser source to change the angle orientation of the output beam and scan the output beam in the 360° FOV.

Abstract: One example includes an isochronous receiver system. The system includes a pulse receiver configured to receive an input data signal from a transmission line and to convert the input data signal to a pulse signal. The system also includes a converter system comprising a phase converter system. The phase converter system includes a plurality of pulse converters associated with a respective plurality of sampling windows across a period of an AC clock signal. At least two of the sampling windows overlap at any given phase of the AC clock signal, such that the converter system is configured to generate an output pulse signal that is phase-aligned with at least one of a plurality of sampling phases of the AC clock signal based on associating the pulse signal with at least two of the sampling windows.

Abstract: A method of forming a superconductor structure is disclosed. The method comprises forming a superconductor line in a first dielectric layer, forming a resistor with an end coupled to an end of the superconductor line, and forming a second dielectric layer overlying the resistor. The method further comprises etching a tapered opening through the second dielectric layer to the resistor, and performing a contact material fill with a normal metal material to fill the tapered opening and form a normal metal connector coupled to the resistor.

Abstract: A method of integrating a phase change switch (PCS) into a Bipolar (Bi)/Complementary Metal Oxide Semiconductor (CMOS) (BiCMOS) process, comprises providing a base structure including BiCMOS circuitry on a semiconductor substrate, and forming on the base structure a dielectric contact window layer having metal through-plugs that contact the BiCMOS circuitry. The method includes constructing the PCS on the contact window layer. The PCS includes: a phase change region, between ohmic contacts on the phase change region, to operate as a switch controlled by heat. The method further includes forming, on the contact window layer and the PCS, a stack of alternating patterned metal layers and dielectric layers that interconnect the patterned metal layers, such that the stack connects a first of the ohmic contacts to the BiCMOS circuitry and provides connections to a second of the ohmic contacts and to the resistive heater.

Abstract: A machine learning maneuver model can be programmed to generate maneuver data identifying a plurality of flight paths for maneuvering an aerial vehicle through an adverse weather condition and a flight path confidence score for each flight path of the plurality of flight paths based on at least weather sensor data characterizing the adverse weather condition. The flight path confidence score can be indicative of a probability of successfully maneuvering the aerial vehicle through the adverse weather condition according to a respective flight path. A maneuver decision engine can be programmed to evaluate each flight path confidence score for each flight path relative to a flight path confidence threshold to identify a given flight path of the plurality of flight paths through the adverse weather condition that poses a least amount of structural risk to the aerial vehicle.

Abstract: One example includes a flux switch system. The system includes an input stage configured to provide an interrogation pulse. The system also includes a plurality of flux loops configured to receive an input current. Each of the flux loops includes a Josephson junction configured to trigger to generate an output pulse in response to a first polarity of the input current and to not trigger to generate no output pulse in response to a second polarity of the input current opposite the first polarity. The system further includes an output stage configured to propagate the output pulse to an output of the flux switch system.

Abstract: A system and method for vaporizing space debris in space. The system includes a spacecraft body, a primary solar concentrator mounted to the spacecraft body that collects and focuses solar flux from the sun, and a secondary solar concentrator positioned at a focal point of the primary solar concentrator that refocuses the focused solar flux. A manipulator arm coupled to the spacecraft body grabs the space debris in space and positions it at a location where the refocused solar flux vaporizes the debris. The secondary solar concentrator can be a point-source concentrator, the primary solar concentrator can be a parabolic mirror, a Fresnel lens or a light focusing element or assembly, and the space debris can be a retired spacecraft or launch vehicle upper stage or component.

Abstract: Spacecraft servicing devices or pods and related methods may be configured to be deployed from a carrier spacecraft and include at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft. The spacecraft servicing devices may be configured to be transported from an initial orbit to another orbit after the spacecraft servicing device is deployed from the carrier spacecraft.

Abstract: A hybrid metal composite (HMC) structure comprises tiers comprising fiber composite material structures, and additional tiers longitudinally adjacent one or more of the tiers and comprising perforated metallic structures and additional fiber composite material structures laterally adjacent the perforated metallic structures. Methods of forming an HMC structure, and related rocket motors and multi-stage rocket motor assemblies are also disclosed.

Abstract: An in-flight refueling assembly for an aircraft to be refueled by a fuel dispensing aircraft includes a refueling probe extending from the aircraft and having an electromagnet with an energized condition and a non-energized condition. A refueling probe receptacle is connected to the fuel dispensing aircraft. A superconductor is connected to the receptacle such that the refueling probe becomes aligned with the receptacle when the electromagnet is placed in the energized condition.

Abstract: Cubic BAs is used in semiconductors to improve the thermal characteristics of a device. The BAs is used in device layers to improve thermal conductivity. The BAs also provides thermal expansion characteristics that are compatible with other semiconductors and thereby further improves reliability. The substrates of the semiconductors may also include vias that contain BAs. The BAs in the vias may contact the BAs in the device layers. Some vias may have a surface area to volume ratio of greater than 10 to better assist with device heat dissipation.

Abstract: One example includes a flux switch system. The system includes an input stage configured to provide an interrogation pulse. The system also includes a plurality of flux loops configured to receive an input current. Each of the flux loops includes a Josephson junction configured to trigger to generate an output pulse in response to a first polarity of the input current and to not trigger to generate no output pulse in response to a second polarity of the input current opposite the first polarity. The system further includes an output stage configured to propagate the output pulse to an output of the flux switch system.

Abstract: A load testing apparatus can include a plurality of vertical load structures arranged on a flight control surface to provide torque on the control surface and reacted by a control rod of the flight control surface. The load testing apparatus can also include a plurality of fore/aft load structures arranged to provide tensile and/or compressive force in a direction intersecting a hinge line of the flight control surface. Each of the plurality of fore/aft load structure can include a first rubber pad having a surface extending in a first plane that is arranged to contact a lower surface of the flight control surface. Each of the plurality of fore/aft load structures can also include a first rubber pad having a surface extending in a second plane that is arranged to contact an upper surface of the flight control surface, wherein the first plane and the second plane are non-parallel planes.