Abstract: A method is provided for controlling an aircraft-mounted radar system configured to project radar beams and to receive radar returns relating to the projected radar beams. The method includes providing at least one output to the radar system that causes the radar system to sweep the radar beam horizontally to create a horizontal sweep set. The method further includes providing at least one output to the radar system that causes the radar system to conduct two vertical sweeps during the horizontal sweep set, the two vertical sweeps offset from a center horizontal location by at least one beam width, and wherein each of the two vertical sweeps are on opposite sides of the center horizontal location.

Abstract: A method for forming an embedded passive device module comprises depositing a first amount of an alkali silicate material, co-depositing an amount of embedded passive device material with the amount of alkali silicate material; and thermally processing the amount of alkali silicate material and the amount of embedded passive device material at a temperature sufficient to cure the amount of alkali silicate material and the amount of embedded passive device material and form a substantially moisture free substrate.

Abstract: An antenna system for a weather radar system includes a first transceiver and a second transceiver. The polarization of the first transceiver is orthogonal to the polarization of the second transceiver. The first transceiver and the second transceiver are interlaced to occupy the same volume.

Abstract: A method of protecting an electronics package is discussed along with devices formed by the method. The method involves providing at least one electronic component that requires protecting from tampering and/or reverse engineering. Further, the method includes mixing into a liquid glass material at least one of high durability micro-particles or high-durability nano-particles, to form a coating material. Further still, the method includes depositing the coating material onto the electronic component and curing the coating material deposited.

Abstract: A method of and system for determining the altitude of an aircraft can use a relative altitude estimate using information from an onboard radar. The altitude can be referenced to a runway for landing operations. The radar can produce relative altitude information from the range to the landing point and a precision estimation of the vertical angle to the landing point. The vertical angle estimate can be made with a phase processing antenna/radar system.

Abstract: The present invention is a folded monopole antenna assembly. The folded monopole antenna assembly includes a dielectric substrate, the dielectric substrate being configured for receiving at least one input. The folded monopole antenna assembly further includes a folded monopole antenna. The folded monopole antenna is configured for being connected with the dielectric substrate. Further, the folded monopole antenna includes at least one reactive circuit. The folded monopole antenna is further configured for receiving a signal via a received input included in the at least one received input. The antenna assembly is configured for implementation within an artillery shell and/or a munition.

Abstract: An electronics package includes a substrate and at least one electronic component coupled to the substrate. The electronics package comprises an alkali silicate coating forming a hermetic seal around at least a portion of the at least one electronic component.

Abstract: A method of creating and modifying a flight plan using a cursor control device and a display to represent the flight plan in the context of terrain. The method includes inserting waypoints, including origin and destination waypoints, into a flight plan using a cursor control device to position the waypoints in a display and commanding a flight management system (FMS) to connect the waypoints into a flight plan. The flight plan is drawn in the context of terrain on a display where conflicts between the flight plan and terrain are indicated. Selected elements of the flight plan are selected with a cursor control device and the selected elements are dragged to new positions on the display until terrain conflicts are eliminated, thus generating a modified flight plan. The modified flight plan is reviewed in the context of terrain to determine its acceptability and making further modifications thereof if desired.

Abstract: The laser range finding system includes a light detection and ranging (LIDAR) sensor unit (SU) and a LIDAR processor unit (PU). The LIDAR SU is for transmitting light pulses and receiving resulting input light signals reflected from objects within the field of view of the SU. The LIDAR SU includes a flash LIDAR illuminating laser source for transmitting light pulses. The LIDAR illuminating laser source includes an illuminating laser and zoom optics operatively associated with the laser. A LIDAR receiver receives resulting input light signals reflected from the objects. The LIDAR receiver includes a sensor; and, a flash readout integrated circuit (IC). The flash readout IC measures the transit time of the light pulses. The LIDAR processor unit (PU) is operatively associated with the LIDAR SU and it utilizes flash LIDAR ranging. A power source is operatively coupled to the LIDAR PU.

Abstract: An aircraft radar system includes a radar antenna and a processing device. The processing device receives returns from the radar antenna associated with the scan. The processing device uses the returns from the scan for use in both incursion detection and weather phenomenon detection. A method for using the returns from the scan for both incursion detection and weather phenomenon detection is also disclosed.

Abstract: The present invention is a system which includes an interposer. The interposer may include a mounting plate for mounting the interposer to a fuselage of an aircraft. The interposer may interface with the fuselage to form a seal for maintaining pressure within the aircraft. The system may further include an antenna module. The antenna module may include a ground plane, an aircraft antenna, and a radome. The ground plane may be connected to the aircraft antenna and may be configured for allowing the antenna module to be mounted to the interposer. The radome may be connected to the ground plane to form an enclosure for housing the antenna. The antenna module may be removably connected to the interposer. The system may further include an interconnect for electrically connecting the antenna module to electronics located within the aircraft. The antenna module may be disconnected from the interposer without breaking the seal formed between the interposer and the fuselage.

Abstract: A system for providing crosswind component information to a pilot of an aircraft is disclosed. The system is comprised of a navigation system; datalink system; devices for manual input of data; a crosswind component module consisting of, in part, a processor and database; and an indicating system consisting of, in part, a tactical display unit system of an aircraft. A navigation system may provide flight parameters for measured and intended flight data as inputs. Other data may also be provided from manual input devices and a datalink system as inputs. The processor of the crosswind component module receives the data, retrieves runway direction data, and determines the data of the crosswind components. An indicating system receives the data of the crosswind components and displays this information.

Abstract: A shape memory element (a structure formed from a shape memory alloy) includes an electrically conductive ferromagnetic material. The ferromagnetic material may be magnetostrictive. In some embodiments, the shape memory element is formed from a shape memory alloy core and has a cladding over the core that includes the ferromagnetic material. In other embodiments, the shape memory alloy may be selected to be ferromagnetic.

Abstract: A terrain advisory display including a display, a processing circuit coupled to the display and wherein the display is configured to generate a three-dimensional image.

Abstract: The present invention is a methodology for developing high-assurance microcode. The method may comprise one or more of the following steps: (a) receiving a plurality of requirements detailing intended behavior of microcode (b) creating a model of microcode behavior; (c) generating microcode based on the model; (d) generating test cases based on the model; (e) simulating the behavior of the microcode; (f) translating the model into a verification tool-specific format; and (g) formally verifying the model using a verification tool.

Abstract: The present invention is a targeting system for tracking angle changes from a reference azimuth. The system includes a mount. The mount may be configured for supporting a sighting scope. The system further includes an angle encoder which is integrated within the mount and is configured for tracking angle changes from the reference azimuth. The system further includes an inertial sensor which is communicatively which is also integrated within the mount and is configured for tracking angle changes from the reference azimuth. The system may be configured for selectively relying on angle change tracking provided by either the angle encoder or the inertial sensor.

Abstract: The present invention is an H-bridge power amplifier circuit which includes diodes connected in parallel with MOSFET switch pairs of the circuit, each MOSFET switch pair including a MOSFET switch and a reverse-conduction blocking switch. Further, the circuit includes a snubber inductor which is connected to the switch pairs and the diodes. The circuit further includes a control branch/control sub-circuit having a snubber capacitor and a control MOSFET switch. The circuit is configured for: blocking MOSFET negative current to prevent body diode conduction; inhibiting/preventing turn-off losses of the MOSFETs; and reducing switching losses associated with operation into inductive mistuning.

Abstract: An actuator load path monitoring system for an aircraft having an aircraft structure, a control surface, and, an actuator connected between the aircraft structure and the control surface to support and position the control surface as desired relative to the aircraft structure. The actuator is of a type including a) an upper actuator assembly securely connected to the aircraft structure, including a motor assembly and gear assembly; b) a ball screw assembly operatively connected to the gear assembly; c) a tie-rod assembly positioned within the ball screw assembly; and, d) a lower actuator assembly securely connected to the control surface, wherein actuation of the ball screw provides selected positioning of the control surface. The actuator load path monitoring system includes an upper load sensing assembly positioned in an upper load path between the upper actuator assembly and the aircraft structure.

Abstract: In some embodiments, a method for high-performance terrain rendering may include one or more of the following steps: (a) obtaining elevation data, (b) determining slope of a terrain surface, (c) selecting a shading model to apply to the terrain surface based upon the slope of the terrain surface, (d) determining if a vehicle's heading has changed, and (e) aligning the shading model index based upon current heading.

Abstract: The present invention is a Chip Scale Atomic Clock (CSAC)-enabled Time and Frequency Standard (CTFS) architecture. The CTFS architecture includes a microcontroller, a Time Compensated Crystal Oscillator (TCCO) circuit which is connected to the microcontroller, and a Chip Scale Atomic Clock (CSAC) which is connected to the microcontroller. The microcontroller is configured for selectively causing the CTFS to provide a TCCO circuit-based output frequency when the CTFS has not locked to a predetermined atomic resonance, and is further configured for causing the CTFS to provide a CSAC-based output frequency when the CTFS has locked to a predetermined atomic resonance.