Abstract: A vehicle burglar alarm system includes a global position system installed in a vehicle for receiving a satellite signal, and an on-vehicle main unit installed in the vehicle and electrically connected with the global position system, the on-vehicle main unit having a first flag, the first flag having a first status without satellite signal and a second status with satellite signal for indicating satellite receiving status of the global position system, the on-vehicle main unit being to output a relocation signal immediately after changing of the first flag from the first status without satellite signal to the second status with satellite signal during burglar alarming mode.

Abstract: A reconfigurable digital processing system for space includes the utilization of field programmable gate arrays utilizing a hardware centric approach to reconfigure software processors in a space vehicle through the reprogramming of multiple FPGAs such that one obtains a power/performance characteristic for signal processing tasks that cannot be achieved simply through the use of off-the-shelf processors. In one embodiment, for damaged or otherwise inoperable signal processors located on a spacecraft, the remaining processors which are undamaged can be reconfigured through changing the machine language and binary to the field programmable gate arrays to change the core processor while at the same time maintaining undamaged components so that the signal processing functions can be restored utilizing a RAM-based FPGA as a signal processor.

Abstract: A field unit for warning of a danger of collision between an aircraft and an obstacle, in particular a topographical ground obstacle or an obstacle formed by a mast, building or aerial cable structure, comprises a multi-part tubular mast having devices for fixing a solar panel and a radar antenna; an elongate radar antenna in an environment-protective casing, which, with an electronics unit, forms a radar system for synthesized radar detection of an aircraft in a radar coverage area; a central processing unit for identifying on the basis of information from the radar system an aircraft which is in a zone of the radar coverage area and which on the basis of radar information such as direction, distance and/or speed computes a collision danger area; and a high-intensity light system and radio transmitter system that can be activated by the central processing unit upon detection of an aircraft in a collision danger area.

Abstract: A method, system, and computer program product for using airport information based on the flying environment are provided. When a helicopter is determined to be approaching a runway, ground proximity warning envelopes are automatically reduced to prevent unwanted, or nuisance, terrain alerts. On the other hand, when a helicopter is flown near a runway without intent to land or when a helicopter is taking off, ground proximity warning envelopes may remain unchanged. As a result, nuisance alerts are reduced when a helicopter is approaching a runway for landing and ground proximity warnings may remain in effect to maximize protection when a helicopter is flying near a runway without an intent to land or is taking off from a runway.

Abstract: A system, method, and computer program product are provided for monitoring for high energy landing approaches and advising a flight crew of an aircraft. Specific aircraft energy is predicted at a touchdown zone of a runway. The predicted specific energy is compared with predetermined threshold specific energy. An alert is generated when the predicted specific energy is at least the predetermined threshold specific energy. The present invention improves flight crew awareness of an impending problem with a landing approach, such as a high energy approach, provides an advisory when probability of an unsuccessful approach is significant, and allows a margin from stable approach criteria while avoiding increased aural and visual clutter in the flight deck.

Abstract: Methods and systems for performing auto-recovery for an aircraft. An example system includes position and information systems, an automatic flight control system, a database, and a processor. The database includes terrain data, airport data, obstacle data, and protected airspace data. The processor determines if one of a caution alert or a warning alert exists based on data stored in the database and information received from the position and information systems. Auto-recovery instructions are generated and sent to the automatic flight control system if no positive flight control input has been performed at time of expiration of a waiting period. Auto-recovery instructions are generated based on an analysis of two or more auto-recovery routes. The system does not perform auto-recovery if components of the system fail to meet a predefined validity or integrity level.

Abstract: A graphical display of a vertical speed indicator showing “fly-to” and “no-fly” commands on the periphery of a vertical speed indicator during TCAS traffic or resolution advisory conditions.

Abstract: The present invention provides for detecting device information including information about a device. First ID information is obtained which is specific to the device via a digital interface after second ID information is assigned to the device, wherein the first ID information includes the device information, and the second ID information is used for communicating with the device. The first ID information and the second ID information are stored in a memory. The device information is detected from the first ID information. A new second ID information is checked using the first ID information, if the new second ID information is assigned to the device.

Abstract: Methods and systems are disclosed for preventing aircraft collisions with forward looking terrain avoidance (FLTA) functionality based on a terrain avoidance profile used to evaluate potential terrain threats based on the projected flight path of an aircraft in flight, and a clear terrain profile to determine whether the terrain threat has been cleared. If the terrain avoidance profile conflicts with terrain, a collision threat may exist whereby the pilot is notified and a terrain avoidance maneuver is executed. During the terrain avoidance maneuver the clear terrain profile extends in a direction substantially parallel with the horizon at or near the present altitude of the aircraft to check whether it is safe to return to the previous flight path angle or otherwise end the terrain-avoiding maneuver. When the clear terrain profile no longer conflicts with the terrain threat, a terrain clear indicator is then issued to the pilot.

Abstract: There is disclosed a system and method wherein precise geographical location information such as Global Positioning System coordinate data is utilized as a principal criterion for implementing other wireless transmitted instructions and communications advising aircraft of nearby restricted areas, the proximity of a hazardous condition, or virtually any other situation which is relevant to the intended recipient because of their location. The system and method further can involve intervention and control of a vehicle, such as an aircraft or automobile, which comes into a predetermined location or area, or under other circumstances. The system and method use transmitting units and receiving units, both of which can receive geographical positioning information and which may sound or otherwise output an appropriate advisory, warning or other communication selected based on their positions, heading, and/or speed.

Abstract: A remote control signal, such as a signal from a GPS satellite or from an escort aircraft, is received at a servant aircraft. If the remote control signal is valid and is a landing remote control signal, the processor causes the landing of the servant aircraft. The processor may cause a crash landing or a landing at an airport.

Abstract: A system and a method for providing a continuous, semi-continuous and/or repetitive aural signal to an aircraft pilot indicative of a difference between a set value and an actual value for one or more flight characteristics of the aircraft.

Abstract: A flight guidance system providing perspective flight guidance symbology using positioning and terrain information provides increased pilot situational awareness of the pilot's aircraft. The guidance system uses a positioning system and a detailed mapping system to provide a perspective display for use in an aircraft. A precision pathway flight guidance (PFG) symbology set is thereby displayed on a pilot display. The PFG symbology set includes broken line symbols representing an open tunnel and providing flow field data, a half-bracket symbol to indicate that the aircraft is no longer in the open tunnel represented by the broken line symbols and a quickened flight path vector (QFPV) symbol to provide the pilot with predictive flight path information. A flight director system and tunnel generator component provide for updating the displayed PDFG symbology set based upon current aircraft conditions (e.g., aircraft position) and stored flight path information.

Abstract: The present invention relates to a system and to an arrangement for evaluating in a defined space or area a delimited area (7) in which there is a degree of urgency greater than the degree of urgency in respect of the remainder of said space (1), wherein there is disposed within said space or area (1) a plurality of sensors which can evaluate the current or ongoing degree of urgency on the basis of one or more criteria. Selected sensors (2, 3, 4) shall be connected to computer equipment (50) which includes storage elements (52, 53, 54) adapted for storing current criteria-related values in a chosen time order, and wherein a calculating circuit (51) included in or connected to said computer equipment (50) is adapted for evaluation of a calculated degree of urgency on the basis of time-dependent changes in the evaluated current values, and determining and establishing the local orientation or geographic location of the delimited area through the medium of the calculating circuit.

Abstract: A method and system is utilized to produce an output corresponding to a safety level, particularly in relation to an activity on a moving body. The method involving producing an output corresponding to the ability to perform an operation within a safe limit on a moving vessel. The method comprising the steps of acquiring real time data from instrumentation on the vessel indicative of first and second elements of vessel motion relevant to the safety of the operation. Processing the data relating to each element of motion. Scaling the data relating to each element to a common scale to provide first and second values relating to the respective elements of vessel motion. Determining which value is of greatest significance and providing a output indicative of the greatest value.

Abstract: This invention control system having: means (12) for detecting an irregularity in aircraft handling during flight; means (18) for causing temporarily a rigid body excitation in at least a portion of the aircraft; means (20) for monitoring an actual response to the excitation; means (22) for comparing the actual response and a target response to the rigid body excitation; and means (14) responsive to an output from the comparison means for determining the need for a modification of the current flight plan and for generating a corresponding control output. The invention also provides a corresponding method for controlling an aircraft.

Abstract: A passenger aircraft with a security alarm system includes an aircraft fuselage divided into a cockpit and a passenger cabin. One or more portable transmitter units carried by cabin crew members or other authorized personnel are adapted for discrete activation which sends a coded signal in the form of a radio frequency data burst to a receiver unit located at an intermediate location in the passenger cabin. The receiver unit activates and alarm unit through hard wiring past the bulkhead wall. The alarm unit includes one or more audio or visual alarm devices that alert the cockpit crew to an emergency situation in the cabin. The system includes a mute function that automatically mutes various alarms in the cockpit to prevent distraction of the cockpit crew. During the mute on condition, the alarm assembly stores any received signals until the mute on condition is ended.

Abstract: An avionics system and method is employed for alerting pilots of low premature descent during final landing approach. The method involves determining Final Approach Flight Safety Altitudes for a plurality of runways, identifying which runway an aircraft is likely to land on, and alerting the pilot if the aircraft altitude is lower than the final approach flight safety altitude. The method takes into account terrain information, airport and runway information, and aircraft reference data to make its determination. Particular embodiments reference the Final Approach Fix, one or more step down fix values, the Minimum Descent Altitude and the Missed Approach Point in calculating the Final Approach Flight Safety Altitudes. The system and method have particular utility with a Terrain Awareness and Warning System (“TAWS”) and display in an aircraft.

Abstract: A method and apparatus for capturing and processing images from a portion of a system in order to detect a warning condition for providing warnings to users or operators of the system. One or more image capture devices capable of capturing an image, for example, a continuous video, monitor at least a portion of the system. An image processing assembly processes the image captured by the image capture devices in real time for determining if the warning condition exists. Upon determining that the warning condition exists the image processing assembly causes a warning device to provide a warning to the user. The captured image may then be displayed to the user or operator if desired.

Abstract: The present invention provides an aircraft navigational system including a graphical user interface that is capable of displaying navigational information in a split-screen format. The split-screen format includes displaying multiple graphical user panels, each depicting different traffic information. For example, one of the panels displays a plurality of air traffic symbols corresponding to airborne obstacles and another of the panels simultaneously displays ground traffic symbols representing ground obstacles. The obstacles can include other aircraft in the air and on runways as the pilot's aircraft approaches for a landing. The navigational system also is capable of switching between a single graphical user panel and multiple panels in response to a triggering event, such as a change in the course of the aircraft.

Abstract: An aircraft surveillance system that includes an uninterruptible aircraft information broadcasting system (such as an ADS-B system) for transmitting flight information from an aircraft, and one or more ground stations for receiving the broadcast flight information. The flight information preferably includes the aircraft's aircraft ID, current three-dimensional position, and intended path. Optional components according to the invention include a system and method for validating messages received from the aircraft, and an alternative system and method for determining the aircraft's position if a primary navigation aid, such as GPS, is not available. In one embodiment of the invention, the system includes a transmitter and an uninterruptible power supply that are disposed within a secure housing within the aircraft. This serves to prevent passengers and crew members from disabling the system.

Abstract: The device (1) for aiding piloting comprises means (2) for determining a speed vector of the aircraft, means of depiction (4) for presenting on a display screen (6) a first characteristic sign illustrating the speed vector of the aircraft, and auxiliary means (7) for determining at least one longitudinal margin of maneuver of the aircraft, which is expressed as a load factor and which relates to one of the two maneuvers of pitch-up and of pitch-down of the aircraft. The means of depiction (4) moreover present, on the display screen (6), at least one second characteristic sign which is associated with said first characteristic sign and which illustrates the longitudinal margin of maneuver.

Abstract: A system and method for advanced warning of severe weather for general aviation aircraft is presented. An aircraft includes an onboard weather tracker which monitors atmospheric condition changes. The weather tracker uses data from an onboard barometric altimeter and a GPS device to calculate air pressure changes in order to identify when the aircraft is flying into a low-pressure zone. The weather tracker uses the air pressure's rate of change and the aircraft's speed to determine the criticality of a situation and appropriately notifies a pilot. The weather tracker provides the pilot with local airport information and alternative flight pattern information per the pilot's request.

Abstract: A method for transmitting environmental conditions information, which includes receiving at least some environmental conditions information, scaling the received information such that a scaled environmental conditions value is determined for a particular vehicle, receiving an environmental conditions threshold value, comparing the scaled value to the received threshold value, determining whether the scaled value is greater than the received threshold value, and transmitting, if the scaled value is greater than the received threshold value, at least some of the information.

Abstract: A signal is received from an off limits facility and it is determined from the signal whether an aircraft is within a distance of the off limits facility. The course and/or flight of the aircraft is changed if the aircraft is within the distance of the off limits facility. A signal is received from an airport and it is determined from the signal whether an aircraft will be allowed to take off from the airport. The aircraft is prevented from taking off if the signal from the airport indicates that the aircraft should be prevented from taking off. A signal is received from a satellite and it is determined from the signal whether an aircraft is within a distance of an off limits facility. The course and/or flight of the aircraft if the aircraft is changed if the aircraft is within the distance of the off limits facility.

Abstract: An apparatus, method and computer program product for alerting rotary wing aircraft of potentially hazardous proximity to terrain also reduces nuisance warnings and provides a terrain display consistent with the unique performance capabilities of such aircraft.

Abstract: A system for reducing nuisance alerts and warnings in a terrain awareness and warning system for an aircraft, including determining if the aircraft is within a predetermined geometric volume surrounding an airport. If the aircraft is within the geometric volume, then determining the aircraft's current projected flight path for a selected distance or time and comparing it with at least one approach volume extending from a runway at the airport towards an outer boundary of the geometric volume. If the aircraft's current projected flight path is such that the aircraft is expected to be within the approach volume and stay within the approach volume to the runway, then inhibiting selected alerts and warnings associated with non-threatening terrain.

Abstract: In an aircraft flight instrument display system having a display screen for displaying flight information, an airspeed indicator is displayed in a vertical tape format, and has a low speed range indicator with a low speed range identified on the airspeed indicator by highlighting the low speed range, and has at least a settable indicator within the low speed range indicating a critical airspeed. The low speed range indicator and the critical airspeed indicator are both set with only manual inputs.

Abstract: The present invention is an aircraft having a memory loaded with geolocation data corresponding to restricted airspace boundaries and an autonomous means for rerouting the aircraft outside of the restricted airspace boundaries as the aircraft approaches to within a predetermined distance of the restricted airspace.

Abstract: A preventive method for preventing suicidal hijack by means of aircraft-carried global position electronic map is disclosed. The data such as the identity of the pilot on the aircraft, the real-time data of the aircraft-carried global position device, the electronic maps of the flight courses, data for automatically entering aerodromes, data for ground piloting, data of the fixed or movable targets on the ground or water requested to be protected, and the pre-fixed electronic maps of the flight-prohibition targets within the whole airspace, are collected and processed by computers, so as to determine whether the aircraft is in a legal or illegal manipulation condition, and thereby automatically protect the flight security and public security. By means of high-techs, this invention enhances the ability of aircrafts for preventing suicidal hijacks. Thus incidents such as Sep. 11 suicidal hijack can be prevented.

Abstract: Process and system for transmitting information on an aircraft.

Abstract: A ground proximity warning system, method and computer program product are provided that controllably alter the base width of the alert envelope in order to accommodate uncertainties associated with the current position of the aircraft. In one embodiment, the ground proximity warning system, method and computer program product controllably alter the base width of the alert envelope depending upon an error value, i.e., an uncertainty, associated with the current position of the aircraft. Since the error value associated with the current position of the aircraft is largely dependent upon the type of navigation equipment onboard the aircraft, the ground proximity warning system, method and computer program product of another embodiment controllably alter the base width of the alert envelope depending upon the type of navigation equipment that provides the current position of the aircraft.

Abstract: A system for graphically displaying on a cockpit display an indication of closure (i.e. a “closure indictor”) with a selected target aircraft. In a preferred embodiment of the invention, the system only displays a closure indicator if: (1) the selected target aircraft is within a predetermined monitoring zone; and (2) the track of the selected target aircraft is within a pre-determined variation angle of the track of the Own Ship aircraft. If the rate of closure between the selected target aircraft and the Own Ship aircraft is within a predetermined range of values, the closure indicator includes a closing/receding indicia (such as an upwardly or downwardly directed arrow) that indicates whether the Own Ship aircraft is closing in on or receding from the selected target aircraft. The system preferably removes the closure indicator from display when the Own Ship aircraft or the selected target aircraft ceases to be airborne.

Abstract: A method and system is provided for performing automated air refueling of uninhabited airborne vehicles (UAVs). The method and system includes any combination of a positioning system component, an air collision avoidance system (ACAS) component, a voice processing component, an image processing component, a flight controller, a wireless data link connecting the UAV with the tanker, and refueling components. The ACAS component receives position information of other aircraft, such as UAVs and tankers, over the wireless data link, and generates navigation instructions based on the received position information, and sends the generated navigation instructions to the flight controller. The refueling components include sensors that determine the status of the refueling components. Refueling of the UAV is based on the determined status.

Abstract: Flight plan information is provided in the form of a series of waypoints having attributes which preferably include, among others, latitude, longitude, altitude constraint, and waypoint identifier. A flight path, defined by this information is modeled, and the flight plan model is checked against terrain information to locate any instances in which a potentially unsafe flight altitude exists. In flight, the flight path model is updated using aircraft position so that the path from the aircraft position to the next waypoint is reflected in the model. In the event that a potentially unsafe flight altitude is detected, an alert may be issued to the flight crew. The crew may then amend the flight plan or take other appropriate action.

Abstract: A remote control signal, such as a signal from a GPS satellite or from an escort aircraft, is received at a servant aircraft. If the remote control signal is valid and is a landing remote control signal, the processor causes the landing of the servant aircraft. The processor may cause a crash landing or a landing at an airport.

Abstract: The invention relates to remote control of an unmanned aerial vehicle, UAV, (100) from a control station (110) by means of a wireless command link (115). The UAV (100) may be controlled in an autonomous mode wherein it flies according to a primary route (R1, R1′) defined by a first set of predefined waypoints (WP1-WP8, IP). The UAV (100) may also be controlled in a manual mode wherein it flies according to an alternative primary route (R1′) defined in real-time by control commands received via the wireless command link (115). Flight control parameters are monitored in both modes, and in case a major alarm condition occurs, the UAV (100) is controlled to follow an emergency route (R2′) defined by a second set of predefined waypoints (HP1-HP7, TP1-TP9, IP). Particularly, a major alarm condition is activated if an engine failure is detected.

Abstract: A signal is received from an off limits facility and it is determined from the signal whether an aircraft is within a distance of the off limits facility. The course and/or flight of the aircraft is changed if the aircraft is within the distance of the off limits facility. A signal is received from an airport and it is determined from the signal whether an aircraft will be allowed to take off from the airport. The aircraft is prevented from taking off if the signal from the airport indicates that the aircraft should be prevented from taking off. A signal is received from a satellite and it is determined from the signal whether an aircraft is within a distance of an off limits facility. The course and/or flight of the aircraft if the aircraft is changed if the aircraft is within the distance of the off limits facility.

Abstract: Methods and system for recording data from an aircraft and alerting with a wireless network are disclosed. The methods contain receiving signals containing data from a plurality of aircraft, determining normal thresholds for the data, monitoring and analyzing the data, and generating an alert signal if the data is beyond the thresholds with a ground based computer terminal in real time. The system includes a ground computer and other mechanisms for implementing the disclosed method.

Abstract: A terrain warning system includes an indicator to inform a pilot of a proposed degree of flight parameters for safely clearing terrain. An aural message may identify a vertical speed that may be used to safely traverse terrain to the pilot. A visual indicator on a display informs the pilot of a vertical speed or climb angle to traverse terrain. The display may be a vertical speed indicator also capable of displaying traffic advisories.

Abstract: An airborne collision avoidance system includes a receiver stage constructed and arranged to detect (a) at a first radio frequency, first interrogation signals, and first collision resolution advisory (RA) signals transmitted from other nearby aircraft, and (b) at a second radio frequency, first acquisition signals including position information with respect to the nearby aircraft, and first reply signals from the nearby aircraft. A transmitter stage is constructed to produce (a) at the first radio frequency, second interrogation signals and second collision RA signals, and (b) at the second radio frequency, second acquisition signals including position information with respect to the given aircraft, and second reply signals from the given aircraft in response to the first interrogation signals. Tracking and collision avoidance information derived by a system processor from the detected first acquisition and first RA signals is shown on a cockpit display.

Abstract: The ground proximity warning system and method provide a number of alerts based upon a substantially reduced list of input parameters relative to a conventional ground proximity warning system and method. The ground proximity warning system and method generally constructs alert envelopes and generates alerts if the upcoming terrain or other obstacles pierce the alert envelopes. The ground proximity warning system and method can also generate alerts if the aircraft has an excessive descent rate at a relatively low altitude and if the aircraft descends immediately following takeoff in a similar fashion to Mode 1 and Mode 3 alerts. Further, the ground proximity warning system and method can provide altitude call outs at predefined altitudes above a target runway and can provide alerts if the aircraft appears to be landing short of a runway.

Abstract: A reconfigurable digital processing system for space includes the utilization of field programmable gate arrays utilizing a hardware centric approach to reconfigure software processors in a space vehicle through the reprogramming of multiple FPGAs such that one obtains a power/performance characteristic for signal processing tasks that cannot be achieved simply through the use of off-the-shelf processors. In one embodiment, for damaged or otherwise inoperable signal processors located on a spacecraft, the remaining processors which are undamaged can be reconfigured through changing the machine language and binary to the field programmable gate arrays to change the core processor while at the same time maintaining undamaged components so that the signal processing functions can be restored utilizing a RAM-based FPGA as a signal processor.

Abstract: A system having replaceable subsystems is operable in a certified configuration after installation of a replacement subsystem. The system includes several subsystems each installed at an interface. For each subsystem, the interface includes memory having a description of the operating environment for that subsystem. The memory stores modules each having a signature, for example, a cyclic redundancy code (CRC). After installation of a replacement subsystem, a processor in the subsystem checks a list of signatures. Each signature corresponds to a module that is certified for use by an application program of the subsystem. If a listed signature corresponds to a module that is available in the memory, is desirable to be used, and the subsystem is not presently configured to use such a module, the subsystem reads the module, integrates the data of the module into an operating configuration, and operates thereafter in accordance with the updated operating configuration.

Abstract: Process and device for detecting the failure of a pressure sensor of an air data system of an aircraft.

Abstract: Flight plan information is provided in the form of a series of waypoints having attributes which preferably include, among others, latitude, longitude, altitude constraint, and waypoint identifier. A flight path, defined by this information is modeled, and the flight plan model is checked against terrain information to locate any instances in which a potentially unsafe flight altitude exists. In flight, the flight path model is updated using aircraft position so that the path from the aircraft position to the next waypoint is reflected in the model. In the event that a potentially unsafe flight altitude is detected, an alert may be issued to the flight crew. The crew may then amend the flight plan or take other appropriate action.

Abstract: A spatial data search method, system and apparatus for identifying particular data of significance around a reference vector through the spatial data. The method involves determining a reference vector within a spatial region for which spatial data exists, loading a portion of the spatial data including the data around the reference vector into a memory buffer, and searching the spatial data in a prioritized order. The method, system and apparatus have particular utility in searching geographic data for a terrain awareness and warning system (“TAWS”) and display in an aircraft. Embodiments of the present invention provide advantages over existing sequential and radial search methods, significantly reducing the processing and calculations required and providing faster alerts to pilots.

Abstract: A method and system is provided for performing automated air refueling of uninhabited airborne vehicles (UAVs). The method and system includes any combination of a positioning system component, an air collision avoidance system (ACAS) component, a voice processing component, an image processing component, a flight controller, a wireless data link connecting the UAV with the tanker, and refueling components. The ACAS component receives position information of other aircraft, such as UAVs and tankers, over the wireless data link, and generates navigation instructions based on the received position information, and sends the generated navigation instructions to the flight controller. The refueling components include sensors that determine the status of the refueling components. Refueling of the UAV is based on the determined status.

Abstract: A remote control signal, such as a signal from a GPS satellite, is received at a servant aircraft. If the remote control signal is valid, a processor on the servant aircraft prevents or inhibits anyone on the servant aircraft from controlling the flight or course of the servant aircraft. The remote control signal controls the flight and/or course of the servant aircraft. The remote control signal may come from an escort aircraft.

Abstract: A system for reducing nuisance alerts and warnings in a terrain awareness and warning system for an aircraft, including determining if the aircraft is within a predetermined geometric volume surrounding an airport. If the aircraft is within the geometric volume, then determining the aircraft's current projected flight path for a selected distance or time and comparing it with at least one approach volume extending from a runway at the airport towards an outer boundary of the geometric volume. If the aircraft's current projected flight path is such that the aircraft is expected to be within the approach volume and stay within the approach volume to the runway, then inhibiting selected alerts and warnings associated with non-threatening terrain.