Abstract: A sonar array system comprises a plurality of sonar arrays and a sonar signal processor. Each sonar array is configured to receive transmit electronic signals and transmit corresponding sonar beams in a forward direction and a downward direction. Each sonar array includes a plurality of groups of sonar transducer elements, with each group including at least a first sonar transducer element and a second sonar transducer element. The sonar signal processor is configured to communicate a plurality of transmit electronic signals to the sonar arrays. The transmit electronic signals include a first transmit electronic signal including a periodic waveform having a first phase and a second transmit electronic signal including a periodic waveform having a second phase. A distribution of power between the sonar beams transmitted in the forward direction and in the downward direction varies according to a difference in the first phase and the second phase.

Abstract: A sonar display comprises a processing element and a display. The processing element is configured to receive a first sonar electronic signal from a first sonar transducer, receive a second sonar electronic signal from a second sonar transducer, generate data for a first underwater image stream from the first sonar electronic signal and a second underwater image stream from the second sonar electronic signal. The display is configured to show at least one of the first underwater image stream having a first view derived from reflections of a first sonar beam, the second underwater image stream having a second view derived from reflections of a second sonar beam, and an indication of a position of the first sonar beam relative to the second sonar beam.

Abstract: Autoland systems and processes for landing an aircraft without pilot intervention are described. In implementations, the autoland system includes a memory operable to store one or more modules and at least one processor coupled to the memory. The processor is operable to execute the one or more modules to identify a plurality of potential destinations for an aircraft; calculate a merit for each potential destination identified; select a destination based upon the merit; and create a route from a current position of the aircraft to an approach fix associated with the destination that accounts for the terrain characteristic(s) and/or obstacle characteristic(s).

Abstract: An apparatus is disclosed for determining validity of a measured in-blood percentage of oxygenated hemoglobin. The apparatus has multiple pulse oximetry channels having at least three light sources of at least three distinct wavelengths, which are detected and converted to digital signals. The light sources are selectively activated, and two or more estimated in-blood percentages of oxygenated hemoglobin are calculated. It is determined whether a signal quality associated with the calculated in-blood percentages exceeds a predetermined accuracy threshold, and an associated validity indication is provided.

Abstract: Autoland systems and processes for landing an aircraft without pilot intervention are described. In implementations, the autoland system includes a memory operable to store one or more modules and at least one processor coupled to the memory. The processor is operable to execute the one or more modules to identify a plurality of potential destinations for an aircraft. The processor can also calculate a merit for each potential destination identified, select a destination based upon the merit; receive terrain data and/or obstacle data, the including terrain characteristic(s) and/or obstacle characteristic(s); and create a route from a current position of the aircraft to an approach fix associated with the destination, the route accounting for the terrain characteristic(s) and/or obstacle characteristic(s). The processor can also cause the aircraft to traverse the route, and cause the aircraft to land at the destination without requiring pilot intervention.

Abstract: A wrist-wearable electronic device comprising first and second light emitting elements, a sensor, and a processor. The processor is configured to transmit a first command to the first light emitting element in response to the wrist-wearable device reaching a forward position relative to a user based on data received from the sensor and transmit a second command to the second light emitting element in response to the wrist-wearable device reaching a rearward position relative to the user based on the data from the sensor.

Abstract: An automated avionics system for determining a modified descent path of an aircraft includes a memory operable to store a database of flight information related to a flight plan and a processor operably coupled with the memory. The processor is operable to receive an indication to initiate descent of the aircraft associated with a position of the aircraft, receive information related to the flight plan from the database, and based on the information received, perform modifications to the path of descent. The processor is further operable to, based on a comparison of an original position of descent and the indicated position, determine a modified position of descent for the aircraft and calculate a modified path of descent, the modified path of descent complying with the of altitude constraint(s) of the flight plan.

Abstract: A removable camera lens attachment has at least two optical elements, wherein the at least two optical elements are aligned to share an optical axis with a prime lens of the camera. The lens attachment has at least two curved surfaces. The at least two optical elements have a first surface that is conditioned to reflect a first portion of the incident light away from the image plane as reflected stray light and a second surface that is conditioned to reflect a second portion of the reflected stray light back toward the image plane to form a ghost image on an image plane of the prime lens. The lens attachment alters the effective focal length of the prime lens by no more than 15%.

Abstract: A flight deck system for an aircraft includes a processor, a graphical interface for displaying flight-related information in the form of selectable items, a control interface for receiving a selection of the selectable items, and a non-transitory computer-readable storage medium for storing electronic representations of charts. The selectable items correspond to the electronic representations of charts, and the electronic representations of charts describe minima and associated conditional criteria for operating the aircraft (e.g., proximate to an airport). The processor is configured to arrange the selectable items, receive a selection of the selectable items, identify a corresponding one of the electronic representations of charts, receive a condition associated with the aircraft, compare the condition to the conditional criteria for operating the aircraft to identify an applicable one of the plurality of minima, and display the applicable one of the plurality of minima on the graphical interface.

Abstract: Disclosed are dual-light-source, high dimming-ratio avionics displays with digital light processing projector technology for rendering a visual display from generated light. The dual light sources are directed towards a beam splitter adapted to pass a substantial portion of the light from the first light source and to reflect a minority portion of the light from the second light source. An image is rendered at a substantially transparent, selectively reflective substrate adapted to reflect light of a range of visible wavelengths toward a viewer of the displays.

Abstract: A flight deck system for an aircraft includes a display device for providing a graphical interface for displaying flight-related information including a plurality of windows to an operator. The display device is configured for displaying the plurality of windows within a plurality of regions. The plurality of regions can each have a predefined shape and orientation on the display screen according to a regular grid layout. A touch interface is coordinated with the display device for receiving touch information from the operator and allowing the operator to interact with the graphical interface. A processor is communicatively coupled with the touch interface device and operatively coupled with the display device. The processor can be configured to dynamically recreate a selected window of flight-related information within one or more of the plurality of regions corresponding to an operator-selected icon. In such embodiments, the operator can operate the graphical interface through direct touch.

Abstract: Autoland systems and processes for landing an aircraft without pilot intervention are described. In implementations, the autoland system includes a memory operable to store one or more modules and at least one processor coupled to the memory. The processor is operable to execute the one or more modules to identify a plurality of potential destinations for an aircraft; calculate a merit for each potential destination identified; select a destination based upon the merit; and create a route from a current position of the aircraft to an approach fix associated with the destination that accounts for the terrain characteristic(s) and/or obstacle characteristic(s).

Abstract: Autoland systems and processes for landing an aircraft without pilot intervention are described. In implementations, the autoland system includes a memory operable to store one or more modules and at least one processor coupled to the memory. The processor is operable to execute the one or more modules to identify a plurality of potential destinations for an aircraft. The processor can also calculate a merit for each potential destination identified, select a destination based upon the merit; receive terrain data and/or obstacle data, the including terrain characteristic(s) and/or obstacle characteristic(s); and create a route from a current position of the aircraft to an approach fix associated with the destination, the route accounting for the terrain characteristic(s) and/or obstacle characteristic(s). The processor can also cause the aircraft to traverse the route, and cause the aircraft to land at the destination without requiring pilot intervention.

Abstract: A method of producing a rifle scope and a rifle scope including a conical objective bell, a main tube, and a connector. The objective bell is made of composite materials and increasing in diameter as the bell extends distally from its proximal to its distal end, with the proximal end being adjacent to the distal end of the main tube. The main tube, also constructed of composite materials, is a hollow cylinder. The connector is positioned about the distal end of the main tube with an exterior surface that conforms and is adhered to the interior surface of the proximal end of the objective bell and the interior surface of the distal end of the main tube, thereby joining together the objective bell and the main tube.

Abstract: A resonator paradigm, where the resonator structure is made up of a very large number of small, coupled Coriolis sensitive units arranged in a periodic 1D or 2D (and, possibly, in the future, 3D) structure to create a Coriolis-sensitive fabric that supports a large number of Coriolis-coupled supermodes. Such a fabric can be shaped into arbitrary waveguides that propagate either pulses of excitation that are Coriolis-coupled, thus enabling an acoustic version of a FOG-type gyroscope (where a pulse of excitation travels along a passive waveguide and it's phase/time delay is measured), or support multiple stationary Coriolis-coupled vibration modes analogous to optical laser modes in an RLG where counter-propagating modes of oscillation are maintained at constant amplitude via a continuous addition of energy.

Abstract: To isolate an active portion of a gyroscope resonator from mounting stresses propagating through a resonator attachment center, the resonator includes a stress isolation feature that includes alternating concentric symmetric regions of high and low stiffness. The resonator may be separated into a large number of thin, compliant spring elements and larger stiff mass elements, the aggregate areas of which optimized for an aggregate resonator spring constant (by selecting a width and a length of the spring elements), an aggregate mass (by selecting a size of the mass elements), a thermoelastic loss maximum (by selecting a width of the spring elements) and an operating frequency (by selecting a ratio of the aggregate spring to the aggregate mass).