Abstract: Systems and devices of the various embodiments may provide a low-drag, variable-depth acoustic liner having shared inlet volumes. Various embodiments may include a low-drag, variable-depth acoustic liner providing aircraft noise reduction. Acoustic liners according to the various embodiments may be used in engine nacelles and/or on external surfaces of an aircraft to reduce acoustic radiation. Acoustic liners according to various embodiments may provide increased broadband acoustic performance with less drag than conventional liners. Various embodiments may provide an acoustic liner with a reduced open area of the facesheet, and therefore reduced drag of the liner, when compared with conventional acoustic liners.

Abstract: The present invention relates to electromagnetic meta-material structures to serve as linear polarization sensitive mirrors. Two distinct classes have been developed, including: 1) a phase cohering reflector which maintains the phase of both polarization states with a controlled delay between polarization states, and 2) a phase de-cohering reflector which preserves the phase of one polarization state and destroys the coherence in the other. These reflective structures enable mitigation of spurious resonances in dual-polarization optical systems and phase compensation between polarization states. These polarization control structures have applications in absorber coupled detectors and receiver systems for space-borne and sub-orbital remote sensing applications.

Abstract: The present invention relates to a multi-functional platform, including: a printed circuit board (PCB) having a single chip integrated thereon; wherein the single chip includes a substrate having an environmental system disposed thereon, the environmental system including a plurality of three-dimensional (3D) printed, patterned and multi-layered nanostructures disposed on the substrate. The nanostructures include an on-chip heater, a power source, a wireless communication module, and a plurality of sensors, the sensors including at least one of a gas sensor, a pressure sensor, or a temperature sensor, each of which is directly deposited on the substrate and printed with a plurality of nanomaterials. The 3D patterned nanostructures use functionalized nanomaterials, which are patterned by a template using one of directed assembly or nano-offset printing, to deposit the nanostructures directly on the substrate of the single chip.

Abstract: A laser transmitter assembly for use in a Coherent Doppler Wind Lidar (“CDWL”) system includes a telescope/scanner assembly, a receiver, and a master oscillator crystal and a power amplifier crystal each constructed of Ho:YAG. The crystals are end-pumped to transmit an output beam through the telescope/scanner assembly with a high repetition rate of 200-300 Hz and 35 mJ of energy. As part of the CDWL system, a pump laser end-pumps the master oscillator and power amplifier crystals using a pump beam having a nominal wavelength of 1.905 ?m. A seed laser transmits a seeding beam into the master oscillator crystal at a nominal wavelength of 2.0965 ?m. The telescope/scanner assembly transmits the generated laser beam through an atmosphere toward a scene of interest, collects a backscattered return signal, and communicates the backscattered return signal to the receiver during operation of the CDWL system.

Abstract: A thrust chamber liner includes a metallic combustion chamber having an annular protrusion extending radially away from an exterior surface of the combustion chamber adjacent to its injector opening. A metallic nozzle is coupled to the combustion chamber at its throat opening. A composite material encases the exterior surface of the combustion chamber, but is only bonded to the annular protrusion.

Abstract: A self-reacting friction stir welding (SR-FSW) tool includes a crown shoulder having a central bore and a pin that extends through the crown shoulder's central bore. The central bore includes a first region at a first axial end of the crown shoulder, a second region axially adjacent to the first region, and a third region axially adjacent to the second region. The first region and third region have a diameter that provides sliding contact with the pin. The pin and crown shoulder have an annular gap there between at the second region of the central bore.

Abstract: The present invention relates to a phononic-isolated Kinetic Inductance Detector (KID) and a method of fabrication thereof. The KID is a highly sensitive superconducting cryogenic detector which can be scaled to very large format arrays. The fabrication process of the KID of the present invention integrates a phononic crystal into a KID architecture. The phononic structures are designed to reduce the loss of recombination and athermal phonons, resulting in lower noise and higher sensitivity detectors.

Abstract: A method for adaptive phase control of a distributed propulsion (DP) aircraft includes deriving an estimated source noise level of the aircraft's propulsors with respect to a designated low-noise area on the ground. Responsive to the estimated source noise level, a phase generator module estimates a ground noise level using the source noise level. The method includes determining an optimized set of relative azimuthal propulsor blade positions/phase angles, via the phase generator module, with such optimized phase angles being sufficient for reducing the estimated ground noise level. Phase control signals from a flight controller to the respective propulsors establishes the optimized set of relative phase angles, and thereby reduces community noise in the designated low-noise area. The DP aircraft includes an aircraft body, the flight controller, and the above-noted phase generator module.

Abstract: Embodiments of the present invention include systems for launching primary or secondary payloads or actuating other launch vehicle or payload or instrumentation devices. The system includes an adapter assembly and at least one sequencer mounted to the adapter assembly. The sequencer includes: controller boards, each of the controller boards having a controller for controlling deployment of the payloads and data files; output ports coupled to the controller boards and configured to transmit signals from the controller boards to dispensers therethrough, deployment mechanisms containing the payloads, the adapter assembly having channels for accommodating the dispensers; and a detector coupled to the controller boards and adapted to detect an external signal and, in response to the external signal, to send an initiation signal to the controller boards. The system also includes at least one power supply coupled to the sequencer and adapted to provide an electrical power to the sequencer.

Abstract: The present invention relates to a novel method and system for crater detection in planetary data based on marked point processes (MPP), effective for various object detection tasks in Earth observation, and for planetary image registration. The resulting spatial features are exploited for registration, together with fitness functions based on the MPP energy, on the mean directed Hausdorff distance, and on the mutual information. Two different methods—one based on birth-death processes and region-of-interest analysis, and the other based on graph cuts and decimated wavelets—are included within the present framework. Experimental results confirmed the effectiveness of the present invention in terms of crater detection performance and sub-pixel registration accuracy.

Abstract: Methods and systems for providing remote support and negotiating problem situations of autonomous operation of vehicles based on signal states and vehicle information are described. A system comprises a memory and a processor configured to execute instructions stored in the memory to: assign vehicles to support queues based on state data, generate a map display including locations of the vehicles, and generate a state display including the support queues, vehicle manager indicators corresponding to the support queues and state indicators corresponding to the state data.

Abstract: Systems, methods, and devices of the various embodiments may provide a mechanism to enable the growth of a rhombohedral epitaxy at a lower substrate temperature by energizing the atoms in flux, thereby reducing the substrate temperature to a moderate level. In various embodiments, sufficiently energized atoms provide the essential energy needed for the rhombohedral epitaxy process which deforms the original cubic crystalline structure approximately into a rhombohedron by physically aligning the crystal structure of both materials at a lower substrate temperature.

Abstract: A device for promoting healing of an injury in a living being is provided. Such device is based upon an injury covering portion, which portion comprises an electroactive polymer, such as poled polyvinylidine difluoride (PVDF) or a copolymer of PVDF. The electroactive polymer has either pyroelectric properties, piezoelectric properties, or both.

Abstract: An apparatus include one or more DACs and a resistor divider are configured to generate a variable bias voltage VBIAS with respect to a CM voltage VCM. The CM voltage VCM is applied to a cathode of one or more thermopiles or a negative input of one or more amplifiers to prevent saturation and over range of one or more low voltage readout amplifiers and one or more ADCs.

Abstract: A six-pole patch bandpass filter includes a dielectric substrate and six electrically-conductive isosceles-triangle patches disposed thereon. A first pair of the patches is an electrically connected pair. The first pair of patches is capacitively coupled to a first microstrip. A second pair of the patches is also an electrically connected pair. The second pair of patches is capacitively coupled to a second microstrip. A third pair of the patches are nested between and capacitively coupled to the first pair of patches and the second pair of patches.

Abstract: Provided are methods of preparing an electrically activated shape memory polymer composite capable of thermal shape reformation using electric power to heat the composite through its matrix glass transition temperature. The methods may include providing a polymer matrix component comprising a diglycidyl ether resin and at least one curing agent, adding into the polymer matrix component at least one nano-filler component, sonication and mixing the polymer matrix component and the nano-filler component to form a mixture, curing the mixture under curing conditions, and laminating the cured mixture with at least one elastic laminated layer.

Abstract: In an example embodiment, an attitude, orbit, and de-orbit control system (AODCS) for a satellite is provided. In an example embodiment, the AODCS system comprises one or more selectively retractable booms. The one or more selectively retractable booms are collectively configured to provide a selectively adjustable drag during de-orbiting of a satellite over a predefined de-orbiting time.

Abstract: A method of making a multi-layer coating on a substrate is provided and involves applying a mirror coating to a substrate then spraying a silicate topcoat onto the mirror coating. Applying the mirror coating can involve applying a reflective material to the substrate to form a reflective layer and applying an oxide layer to the reflective layer to form the mirror coating. The oxide layer can be made of one or more oxide layers, and each of the one or more oxide layers can include aluminum oxide, silicon oxide, or a combination thereof. The multi-layer coating provides increased IR emittance and decreased solar absorptance relative to conventional thermal control coatings.

Abstract: A method of making a thermal control coating is provided. A primer layer can be applied to a substrate to form an exposed surface. The primer layer can include an epoxy binder and a silica filler. The exposed surface can be treated with an oxygen plasma to form a treated surface. A silicate-based thermal control coating can be applied to the treated surface, for example, by spraying, to form a thermal control coating on the substrate. Spacecraft and spacecraft hardware components coated with the thermal control coating, are also provided.

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.