Abstract: A method of monitoring a curing process for fiber reinforced composite materials that includes positioning an actuator on uncured composite material at a first location. At least one sensor is positioned at a second location that is spaced apart from the first location. The actuator excites waves in the composite part at the first location. At least one sensor is positioned at a second location that is spaced apart from the first location. The actuator excites waves in the composite part at the first location. The waves propagate through the composite part due to internal reflection. At least one wave metric is measured at the second location utilizing the sensor. At least one parameter of the curing process may be adjusted based, at least in part, on a wave metric measured by the sensor.

Abstract: The present disclosure is directed to a nuclear thermionic avalanche cell (NTAC) systems and related methods of generating energy comprising a radioisotope core, a plurality of thin-layered radioisotope sources configured to emit high energy beta particles and high energy photons, and a plurality of NTAC layers integrated with the radioisotope core and the radioisotope sources, wherein the plurality of NTAC layers are configured to receive the beta particles and the photons from the radioisotope core and sources, and by the received beta particles and photons, free up electrons in an avalanche process from deep and intra bands of an atom to output a high density avalanche cell thermal energy through a photo-ionic or thermionic process of the freed up electrons.

Abstract: A non-etched gap is introduced along the length of an integrated Bragg grating with etched grooves such that the coupling coefficient, K, of the grating is reduced by the non-etched gap. In this way, multiple grating K values may be defined within a photonic integrated circuit using a single lithography and etch step. Additionally, the non-etched gap width may be varied along the length of a single grating to implement a chirped grating.

Abstract: Light is projected through a grid (e.g., a Ronchi ruling) and onto a background, where it forms an image of the ruling. The light from this projected image is then reflected back onto the same grid, with a polarizing refractor (e.g., a Rochon polarizing prism) imparting a small offset between the projected and reflected light, and then on to an imaging camera. Thus, a separate source and cutoff grid is not needed, resulting in a focusing schlieren system that is compact and easy to construct and align. In some embodiments, translation of the polarizing refractor along the instrument axis provides a sensitivity adjustment of the resulting schlieren images. Manipulation of the polarization state of the light through the system allows the projected and reflected light to be coincident, maintaining a small footprint for the system, which can be mounted to the front of the imaging camera.

Abstract: A method of recycling a polymer structure includes converting a first polymer structure into feedstock. The first polymer structure comprises particles that are bonded to one another by chemical click bonds to form a first shape. The first polymer structure is converted into feedstock particles by breaking the click bonds. The feedstock particles are formed into a second shape, and the feedstock particles are chemically click-bonded together to form a second polymer structure having a second shape. Breaking the click bonds may include heating the particles. The structures may be formed by causing first particles having dienes to chemically bond to dienophiles of second particles.

Abstract: Various aspects include electric generators configured to boost electrical output by leveraging electron avalanche generated by a high energy photon radiation source. In various aspects, an electric generator includes a stator and a rotor positioned within the stator, wherein the stator and rotor are configured to generate electric current when the rotor is rotated, and a high energy photon source (e.g., a gamma ray source) positioned and configured to irradiate at least a portion of conductors in the rotor or stator. In some aspects, the stator generates a magnetic field when the electric generator is operating, and the rotor includes armature windings configured to generate electric current when the rotor is rotated. In some aspects, the high energy photon source includes cobalt-60 and/or cesium-137.

Abstract: Systems, methods, and devices of the various embodiments may provide Automated Tape (or Tow) Placement (ATP) systems including machine-based parts that support prepreg tape laying processes to build composite parts. Various embodiments may be applied to materials that may be consolidated during fabrication and/or may be used to fabricate parts that may require post processing steps.

Abstract: A motion damper for structures includes a housing coupled to a structure such that the housing moves in correspondence with the structure. The housing includes a wall with a vent, and has an air chamber therein in fluid communication with the vent. A piston is sealed within the housing for one-dimensional motion therein. A rigid plate is disposed within the housing's air chamber. The plate is disposed between the piston and the vent, and is spaced apart from and fixedly coupled to the piston such that the plate moves in correspondence with the one-dimensional motion of the piston. At least one spring is mounted in the housing and is coupled to the plate for applying a force thereto that is in opposition to the one-dimensional motion of the piston.

Abstract: The present invention relates to a modular architecture for a resilient extensible SmallSat (MARES) command and data handling (C&DH) device used in a spacecraft, the modular architecture which conforms to a 1U CubeSat board area form factor, including: a C&DH processor card disposed on a backplane of the form factor; a C&DH processor card disposed on a backplane of the form factor; a fault tolerant field programmable gate array (FPGA) disposed on the C&DH processor card, the FPGA including an embedded fault tolerant memory controller, and a soft-core processor which runs core flight software on a real-time executive for a multiprocessor operating system; and a C&DH auxiliary card disposed on the backplane and used in conjunction with the C&DH processor card, to provide processing capability for the spacecraft, the auxiliary card which contains peripheral interface drivers and read electronics for monitoring a health and safety of the spacecraft.

Abstract: A motion damping system includes a tank compartmentalized to have a first compartment having a first opening, a second compartment having a second opening, and a third compartment disposed between the first and second compartments. The third compartment is in fluid communication with the first and second openings. A first piston is movably sealed within the first compartment and is in fluid communication with its first opening. A second piston is movably sealed within the second compartment and is in fluid communication with its second opening. A liquid fills the third compartment, a portion of the first compartment up to the first piston, and a portion of the second compartment up to the second piston. A coupling fixedly attached to the first and second pistons moves in correspondence with the first and second pistons. Motion damper(s) coupled to the coupling resist movements of the first and second pistons.

Abstract: A ruggedized miniaturized infrared camera system for harsh environments has an infrared camera module that is connected to a ruggedized camera mount. The camera mount has a body and a lens clamp that clamps the camera lens to the body. The camera mount and military-spec fasteners cooperate to mechanically secure the camera module from vibrations. An interface bracket is attached to the camera mount and has a central opening. A signal connector is attached to the exterior side of the bracket and configured to carry USB2 signals. Conductive pins of the signal connector extend through the central opening and are electrically coupled to a circuit board that is adjacent to the interior side of the bracket. An electrically non-conductive spacer is within the central opening and interposed between the signal connector and circuit board. Heat-conductive epoxy secures the circuit board from vibrations and creates thermal bonds that passively remove heat.

Abstract: A frequency-tunable vibration damper includes a first container having rigid wall regions and compliant wall regions. A second container is coupled to the first container such that a wall region of the second container includes one of the compliant wall regions. A fluid fills the first container and a gas fills the second container. A flow restrictor is included in the second container and is spaced-apart from the one of the compliant wall regions included with the second container.

Abstract: A radiation shielded vault structure includes a rigid outer structure comprising a plurality of rigid structural components that are interconnected at elongated joints to define an interior space. The structural components include a layer of lower atomic number (Z) material such as aluminum alloy and one or more layers of higher atomic number (Z) material titanium and/or tantalum. The vault structure may include radiation shield members extending along the elongated joints to provide radiation shielding at the elongated joints. The shield members comprise a higher atomic number (Z) material such as titanium or tantalum. The rigid structural components may comprise plate members that are interconnected along side edges thereof. End plates may be attached to the plate members to close off the interior space.

Abstract: The presently disclosed embodiments relate to vertical takeoff and landing (VTOL) aircraft that have the capability of hovering in both a “nose forward” and a “nose up” orientation, and any orientation between those two. The disclosed aircraft can also transition into wing born (non-hovering) flight from any of the hovering orientations. In addition, certain of the disclosed embodiments can, if desired, use only vectored thrust control to maintain stable flight in both hover and forward flight. No control surfaces (e.g. ailerons, elevators, rudders, flaps) are required to maintain a stable vehicle attitude. However, the disclosure contemplates aircraft both with and without such control surfaces.

Abstract: The present invention relates to a novel rotator for a standardized coarse azimuth-pointing system for a balloon-borne platform—either zero pressure or Super Pressure Balloons (SPB)—with a maximum suspended payload of 5,500 lbs. The 5.5K Rotator novel shaft design, bearings, motor, and housing, result in a weight of the rotator being decreased by 33% from existing legacy rotators. The present invention achieved a 24% parts reduction from existing legacy rotators, and has the advantages of lighter weight, reusability, cost-effectiveness, machinability, and ease of assembly.

Abstract: A pneumatically adjustable lifting apparatus utilizes inflatable spring devices for lifting and precisely positioning a load at a desired location. Variations in the forces produced by the load cause the inflatable spring devices to expand or compress thereby allowing soft mating between components that need to be connected together, such as assembling or disassembling large threaded connections. Pneumatic pressure in the inflatable spring devices may be adjusted depending upon the particular load. The pneumatically adjustable lifting apparatus provides lightly damped vertical travel with a substantially linear force profile over a relatively wide displacement range. Recirculating linear ball bearings cooperate with the linear loading characteristics of the inflatable spring devices to minimize the vertical motion damping of the pneumatically adjustable lifting apparatus.

Abstract: A dark mirror optical stack, particularly a low emittance, high absorbance dark mirror optical stack is provided. The dark mirror optical stack includes a polyimide substrate containing carbon filler, an aluminum layer on the polyimide substrate, a first silicon oxide layer on the aluminum layer, a chromium layer on the first silicon oxide layer, and a second silicon oxide layer on the chromium layer. In a particularly exemplary embodiment, the aluminum layer has an average thickness of 600 to 2000 Angstroms, the first and second silicon oxide layers have average thicknesses of 500 to 1000 Angstroms, and the chromium layer has an average thickness of 40 to 100 Angstroms.

Abstract: System and method for in-process cure monitoring of a material utilizes one or more sensors such as fiber Bragg gratings (FBGs) or phase-shifted FBGs (PS-FBGs) and at least one optical line fiber connected to the sensor(s). The sensor(s) and the optical line may be embedded in the material prior to curing the material may comprise a fiber reinforced polymer. Waves are excited into the material during curing thereof to form guided waves that propagate through the material. At least one wave metric of the guided waves is measured utilizing the sensor(s).

Abstract: The present invention relates to a single-board processor card configured for use in a 1U CubeSat payload form-factor multi-purpose architecture, including: a field-programmable-gate-array (FPGA) which is reconfigurable in flight; wherein a configuration memory of the FPGA can be scrubbed in flight to correct errors or upsets; and a radiation-hardened monitor (RHM) which provides radiation mitigation and system monitoring of the single-board processor card, and which reconfigures said FPGA during flight, scrubs the configuration memory, and monitors a health of the FPGA. The 1U CubeSat payload form-factor multi-purpose architecture includes a backplane having a plurality of slots, one of the plurality of slots which accommodates the single-board processor card, wherein the backplane routes signals to a plurality of standard-sized processor cards, interchangeably disposed in any of the plurality of slots.

Abstract: The present disclosure is directed to nuclear thermionic avalanche cell (NTAC) systems and related methods of generating energy from captured high energy photons. Huge numbers of electrons in the intra-band of atom can be liberated through bound-to-free transition when coupled with high energy photons. If a power conversion process effectively utilizes these liberated electrons in an avalanche form through a power conversion circuit, the power output will be drastically increased. The power density of a system can be multiplied by the rate of high energy photon absorption. The present disclosure describes a system and methods built with multilayers of nuclear thermionic avalanche cells for the generation of energy. The multilayer structure of NTAC devices offers effective recoverable means to capture and harness the energy of gamma photons for useful purposes such as power systems for deep space exploration.