Abstract: An avionic system for a rotorcraft includes a data source and an enhanced ground proximity warning system. The data source has terrain data and obstacle data stored therein. The enhanced ground proximity warning system can be selectively switched, by a pilot, to operate in either a normal mode or a desensitized mode. The enhanced ground proximity warning system receives flight data, retrieves terrain data and obstacle data from the data source, evaluates the retrieved terrain data and the obstacle data to determine variations in elevations of terrain and obstacles in predetermined area that is a predetermined distance ahead of the current position and along the flight path, and based at least in part on the determined variations, selectively generate a prompt that suggests that the pilot switch the ground proximity warning system to the desensitized mode.

Abstract: A runway overrun prediction system for an aircraft includes a doppler wind measurement system and a runway overrun awareness and alerting system (ROAAS). The doppler wind measurement system is disposed at least partially within the aircraft. The doppler wind measurement system is configured to continuously measure a doppler signature of a wind field over an estimated touchdown zone on a runway ahead of the aircraft and supply wind data representative of the doppler signature. The ROAAS is disposed within the aircraft and is configured to determine a ROAAS model distance (RMD) for the aircraft. The ROAAS is in operable communication with the doppler wind measurement system and is coupled to receive the wind data therefrom. The ROAAS is further configured, upon receipt of the wind data, to adjust the RMD for the aircraft based on the wind data.

Abstract: An avionic system for a rotorcraft includes a data source and an enhanced ground proximity warning system. The data source has terrain data and obstacle data stored therein. The enhanced ground proximity warning system can be selectively switched, by a pilot, to operate in either a normal mode or a desensitized mode. The enhanced ground proximity warning system receives flight data, retrieves terrain data and obstacle data from the data source, evaluates the retrieved terrain data and the obstacle data to determine variations in elevations of terrain and obstacles in predetermined area that is a predetermined distance ahead of the current position and along the flight path, and based at least in part on the determined variations, selectively generate a prompt that suggests that the pilot switch the ground proximity warning system to the desensitized mode.

Abstract: A system and method are provided for controlling operations of an enhanced ground proximity warning system (EGPWS) disposed within an aircraft that is configured to selectively operate in both a helicopter mode and a fixed-wing mode. A processor processes one or more aircraft flight parameters to determine when the aircraft is operating in the helicopter mode and when the aircraft is operating in the fixed-wing mode. The EGPWS is commanded, via the processor, to operate as a helicopter EGPWS when the aircraft is operating in the helicopter mode, and is commanded, via the processor, to operate as a fixed-wing EGPWS when the aircraft is operating in the fixed-wing mode.

Abstract: Methods and apparatus are provided for generating a runway landing alert for an aircraft. The method comprises establishing an altitude parameter and a safety envelope for a designated target runway of the aircraft. A track of the aircraft is monitored with reference to a centerline of the target runway. Any deviation by the aircraft from the centerline of the target runway is detected and determined if it is within a margin of error. If the deviation is within the margin of error, an altitude parameter is increased. If the aircraft is determined to still be maneuvering with respect to the centerline of the target runway, the altitude parameter is decreased. Otherwise, an alert is generated if the aircraft is outside of the safety envelope.

Abstract: A system and method are provided for controlling operations of an enhanced ground proximity warning system (EGPWS) disposed within an aircraft that is configured to selectively operate in both a helicopter mode and a fixed-wing mode. A processor processes one or more aircraft flight parameters to determine when the aircraft is operating in the helicopter mode and when the aircraft is operating in the fixed-wing mode. The EGPWS is commanded, via the processor, to operate as a helicopter EGPWS when the aircraft is operating in the helicopter mode, and is commanded, via the processor, to operate as a fixed-wing EGPWS when the aircraft is operating in the fixed-wing mode.

Abstract: Methods and apparatus are provided for generating a runway landing alert for an aircraft. The method comprises establishing an altitude parameter and a safety envelope for a designated target runway of the aircraft. A track of the aircraft is monitored with reference to a centerline of the target runway. Any deviation by the aircraft from the centerline of the target runway is detected and determined if it is within a margin of error. If the deviation is within the margin of error, an altitude parameter is increased. If the aircraft is determined to still be maneuvering with respect to the centerline of the target runway, the altitude parameter is decreased. Otherwise, an alert is generated if the aircraft is outside of the safety envelope.

Abstract: Methods and apparatus are provided for generating a runway landing alert for an aircraft. The method comprises establishing a Runway Awareness Advisory System (RAAS) envelope for the designated target runway of the aircraft. A track of the aircraft is monitored with reference to a centerline of the target runway. Any deviation by the aircraft from the centerline of the target runway is detected and determined if it is within a margin of error. If the deviation is within the margin of error, an altitude parameter of the RAAS envelope is increased. If the aircraft is determined to still be maneuvering with respect to the centerline of the target runway, the altitude parameter of the RAAS envelope is decreased. Otherwise, an alert is generated if the aircraft is outside of the RAAS envelope.

Abstract: Provided is a surface processing apparatus and a surface processing method for a SiC substrate using anodization. The surface processing apparatus for the SiC substrate includes a surface processing pad and a power supply device. The surface processing pad includes a grinding wheel layer. The grinding wheel layer is disposed facing a workpiece surface of the SiC substrate. The power supply device passes a pulsed current having a period greater than 0.01 seconds and less than or equal to 20 seconds for anodizing the workpiece surface to be processed by the grinding wheel layer through the SiC substrate as an anode in the presence of an electrolyte.

Abstract: A system and method of shifting a premature descent protection envelope for an aircraft has been developed. First, a premature descent protection envelope (PDP) is determined including a first boundary at a first distance from the runway. Next, a nominal approach path is determined for approaching the runway and an approach path angle. Also, a flight path angle of the aircraft is determined. The first boundary is shifted in an upward direction from the runway in response to the aircraft being below the nominal approach path, and the flight path angle being greater than the nominal approach path angle.

Abstract: Alerting systems and methods for an enhanced approach monitor are provided. The system is configured to: determine a missed approach altitude (MAA), an intended configuration, and target approach speed, each being related to the intended approach procedure and aircraft specific data. At a decision point defined as a co-occurrence of (a) the RT distance is substantially equal to or less than a distance threshold, and (b) the RT altitude is substantially equal to the MAA, the system identifies go-around scenarios, such as when (i) the RT speed exceeds the target approach speed, or (ii) the RT configuration is not equal to the intended configuration, or (iii) an RT approach path angle exceeds the target angle. The system issues a go-around alert based on whether the aircraft can perform a go-around operation, as determined based on aircraft performance data and terrain data.

Abstract: Systems and methods to provide alerts when a rotorcraft is in a low airspeed condition. During takeoff or go-around, an aural alert is provided to the pilot before the aircraft slows to less than the effective translational lift speed. The aural, visual, and/or tactile alert gets the pilot's attention to manage the aircraft's airspeed before it is too late in this critical flight phase.

Abstract: Methods and apparatus are provided for generating a runway landing alert for an aircraft. The method comprises establishing a Runway Awareness Advisory System (RAAS) envelope for the designated target runway of the aircraft. A track of the aircraft is monitored with reference to a centerline of the target runway. Any deviation by the aircraft from the centerline of the target runway is detected and determined if it is within a margin of error. If the deviation is within the margin of error, an altitude parameter of the RAAS envelope is increased. If the aircraft is determined to still be maneuvering with respect to the centerline of the target runway, the altitude parameter of the RAAS envelope is decreased. Otherwise, an alert is generated if the aircraft is outside of the RAAS envelope.

Abstract: Methods and apparatus are provided for generating a runway landing alert for an aircraft. The method comprises establishing a Runway Awareness Advisory System (RAAS) envelope for the designated target runway of the aircraft. A track of the aircraft is monitored with reference to a centerline of the target runway. Any deviation by the aircraft from the centerline of the target runway is detected and determined if it is within a margin of error. If the deviation is within the margin of error, an altitude parameter of the RAAS envelope is increased. If the aircraft is determined to still be maneuvering with respect to the centerline of the target runway, the altitude parameter of the RAAS envelope is decreased. Otherwise, an alert is generated if the aircraft is outside of the RAAS envelope.

Abstract: A system and method of shifting a premature descent protection envelope for an aircraft has been developed. First, a premature descent protection envelope (PDP) is determined including a first boundary at a first distance from the runway. Next, a nominal approach path is determined for approaching the runway and an approach path angle. Also, a flight path angle of the aircraft is determined. The first boundary is shifted in an upward direction from the runway in response to the aircraft being below the nominal approach path, and the flight path angle being greater than the nominal approach path angle.

Abstract: Alerting systems and methods for an enhanced approach monitor are provided. The system is configured to: determine a missed approach altitude (MAA), an intended configuration, and target approach speed, each being related to the intended approach procedure and aircraft specific data. At a decision point defined as a co-occurrence of (a) the RT distance is substantially equal to or less than a distance threshold, and (b) the RT altitude is substantially equal to the MAA, the system identifies go-around scenarios, such as when (i) the RT speed exceeds the target approach speed, or (ii) the RT configuration is not equal to the intended configuration, or (iii) an RT approach path angle exceeds the target angle. The system issues a go-around alert based on whether the aircraft can perform a go-around operation, as determined based on aircraft performance data and terrain data.

Abstract: Systems and methods are disclosed for detecting security threats during vehicle operations. For instance, retrieving a route plan for a route of a vehicle from a database of the vehicle; identifying either a portion of the route or a portion of the route plan as a security threat based on an analysis of the route plan; and in response to identifying the portion of the route or the portion of the route plan as the security threat, transmitting an alert of the security threat.

Abstract: A system and method are provided for modifying the position or shape of a premature descent protection envelope with regard to a runway when an aircraft making an approach to the runway is below the nominal approach path and has a flight path angle greater than the nominal approach path angle.

Abstract: Systems and methods are disclosed for detecting data corruption in vehicle data systems. Systems and methods of detecting data corruption or tampering in vehicle data systems may include steps for receiving first electronic navigational plan data, the first electronic navigational plan data comprising a plurality of waypoints, and storing the first electronic navigational plan data in a data store. Systems and methods may further comprise receiving second electronic navigational plan data from a vehicle management system, the second electronic navigational plan data comprising a second plurality of waypoints, and, upon determining a discrepancy between the first plurality of waypoints and the second plurality of waypoints, generating an alert indicating possible data corruption in the second electronic navigational plan.

Abstract: Methods and apparatus are provided for generating a runway landing alert for an aircraft. The method comprises establishing a Runway Awareness Advisory System (RAAS) envelope for the designated target runway of the aircraft. A track of the aircraft is monitored with reference to a centerline of the target runway. Any deviation by the aircraft from the centerline of the target runway is detected and determined if it is within a margin of error. If the deviation is within the margin of error, an altitude parameter of the RAAS envelope is increased. If the aircraft is determined to still be maneuvering with respect to the centerline of the target runway, the altitude parameter of the RAAS envelope is decreased. Otherwise, an alert is generated if the aircraft is outside of the RAAS envelope.