| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 340963000 | Flight alarm | 75 |
| 20080278351 | Primary flight display (PFD) including weather information and terrain awareness - The present invention provides a method and system for displaying critical navigational data on a primary flight display to a pilot of an aircraft. The method includes providing an image representative of weather information on a primary fight display and superimposing an image representative of a terrain warning indicator over at least part of the image representative of weather information. | 11-13-2008 |
| 20080284619 | Aircraft Doors - An alarm system for an aircraft door comprising; a sensor ( | 11-20-2008 |
| 20090015438 | PROCESS AND SYSTEM FOR MANAGING AN INTERRUPTION OF A BROADCAST OF A SONOROUS MESSAGE IN AN AIRCRAFT - The invention relates to a method for managing an interruption of emission, in an aircraft, of an acoustic message comprising an information item about a state of part of the said aircraft and/or about its environment, characterized in that, the acoustic message being structured into one or more successive acoustic fragments each representative of the said information item, the said method comprises the steps:
| 01-15-2009 |
| 20090189786 | Method and device for modifying the sound volume of an audio alarm signal onboard an aircraft - A method for modifying a current sound-volume value assigned by an on-board system to an acoustic alert signal emitted on board an aircraft is provided. The method includes furnishing, on board the aircraft, the on-board system with at least one information item defining a modification of the current sound-volume value to a new sound-volume value in accordance with a predetermined rule. | 07-30-2009 |
| 20090212977 | DEVICE FOR ERROR DETECTION OF ADJUSTABLE FLAPS - With a device for error detection of adjustable flaps on aircraft wings, it is proposed that each flap is provided with a tube as a transmission element arranged in the wing span. The tube is connected fixedly at one end with the flap and is rotatably held. On the free end of the tube, a measuring arm is fixedly arranged on the tube and a sensor fixed to the flap structure is arranged. When an error occurs, the flap twists, whereby a distance change between the sensor and measuring arm occurs. The signals of the sensor are transmitted for error localization of each flap to an evaluation device, which switches off the drive via a control device with occurring errors. | 08-27-2009 |
| 20090261989 | GAS TURBINE ENGINE ROTOR LOCK PREVENTION SYSTEM AND METHOD - A system and method of at least reducing the likelihood of a rotor lock in an aircraft gas turbine engine is provided. A determination is made that each propulsion gas turbine engine on an aircraft has experienced a flameout. The rotational speed of each propulsion gas turbine engine is compared to a predetermined threshold rotational speed and, if the rotational speed of each propulsion gas turbine engine is below the predetermined threshold rotational speed, a warning is supplied to a flight crew. | 10-22-2009 |
| 20090273487 | APPARATUS FOR INTERCONNECTING A PILOT STATION TO AT LEAST ONE OTHER AIRCRAFT ZONE, COCKPIT AND AIRCRAFT EQUIPPED WITH SUCH AN APPARATUS - An interconnecting apparatus for interconnecting a pilot station of an aircraft to at least one aircraft zone includes a device for communicating between the pilot station and the aircraft zone. The aircraft zone includes a device permitting a person present in the aircraft zone to identify themselves and a display device indicating a functional status of the aircraft. The pilot station includes a display device indicating a location of each person being identified in the aircraft zone. | 11-05-2009 |
| 20090273488 | Method and system for alerting aircrew to unsafe vibration levels - An onboard system for a rotary wing aircraft detects a limit cycle oscillation in the tail mast and provides a timely indication of the limit cycle oscillation to an aircrew before serious damage to the airframe is likely to occur. | 11-05-2009 |
| 20090322567 | Flight restriction zone detection and avoidance - A method, system and computer program product to detect and indicating TFR zone violations, potential TFR zone violations or TFR zones in vicinity of an aircraft and indicating measures to avoid or exit a TFR zone are provided. TFR zone information and an aircraft's position information are received. The aircraft's position information is processed to determine the aircraft's current heading. A TFR zone violation is determined based on the aircraft's current position. A potential TFR violation is determined based on whether the aircraft's current heading intersects a TFR zone. The presence of a TFR zone in the vicinity of the aircraft is determined based on the aircraft's current position and heading. Indicators of a TFR violation, potential TFR violation, no TFR violation or TFR zones in the vicinity are provided. If a TFR violation, or possible TFR violation or TFR zone in the vicinity are found, measures are indicated to exit the TFR zone or change the aircraft's current heading to avoid the TFR zone. | 12-31-2009 |
| 20100007527 | DEVICE AND METHOD FOR DETECTING THE DIGITAL ORIGIN OF AN ANALOGUE SIGNAL - The present invention relates to an alarm management system intended to be carried onboard an aircraft. More precisely, the invention is aimed at improving the certainty level relating to the integrity of the announcements of faults or information intended for the pilot and based on voice syntheses. For this purpose, the present invention proposes a device and a method for detecting the digital origin of an analog signal providing a validity signal (VAL) enabling the voice announcements made to the pilot to be rendered secure. | 01-14-2010 |
| 20100019938 | SYSTEMS AND METHODS FOR RE-TRIGGERING OF A RADAR WEATHER DISPLAY - After deactivation of the presentation of weather information on a radar weather display, systems and methods re-trigger when weather conditions change so that the crew is advised of the changed weather conditions. An exemplary embodiment monitors at least one condition of the weather and in response to the monitored weather condition meeting a re-triggering criteria, presents an advisory to a crew member of the aircraft indicating at least presence of the weather. | 01-28-2010 |
| 20100045486 | METHOD AND DEVICE FOR AUDIBLE WARNING WHEN AN AIRCRAFT AUTOPILOT IS DEACTIVATED - The invention relates to a method for producing an audible warning when an aircraft autopilot ( | 02-25-2010 |
| 20100052948 | DETERMINING AND PROVIDING VEHICLE CONDITIONS AND CAPABILITIES - A transponder module for vehicles. The module has a substantially universal vehicle sensor input interface capable of receiving sensor input from different types of vehicle sensors and from different types of vehicles. One or more processors and memory, in real time, receive vehicle sensor input data via the input interface. Based on a vehicle type stored in the memory, the processor(s) use the sensor input data to determine conditions of subsystems the vehicle. Based on the determined conditions, the processor(s) determine performance capabilities of the vehicle. The transponder module outputs information as to the stored vehicle type, determined conditions, and vehicle performance capabilities. | 03-04-2010 |
| 20100066565 | System for Scheduling Tasks to Control the Execution of Warning Procedures on an Aircraft - The invention relates to onboard failure warning management systems on aircraft, or flight warning systems (FWS). Traditionally, the logic of these systems refers to procedures to be executed by the crew in response to warnings. Modifications, however minor, to the procedures involve a new development that can be installed on the airplane computer only as part of a costly maintenance procedure, given notably the need to carry out exhaustive tests on the application. The invention introduces the concept of tasks defined by a set of variables, notably the warning and the procedure in which the task is executed, its category, its priority level and its status. Thus, the computer programs can be organized in modules that call the tasks to be executed, the parameters of said tasks being defined in a configuration table that can be updated as the procedures change during simple operation maintenance procedures. | 03-18-2010 |
| 20100073199 | Method for Monitoring the Flight of an Aircraft - A method for monitoring the flight of an aircraft consisting in triggering a warning representative of hazardous meteorological conditions liable to face the aircraft while the navigation screen is displaying the terrain-following information. | 03-25-2010 |
| 20100309025 | Method of Presenting Anti-Collision Information in a Head-up Display for Aircraft - The invention relates to a method for managing an anti-collision system for aircraft, said system comprising means of detecting collision with a threat and at least one head-up viewing device. The symbol system comprises two display modes dedicated to collision detection which are: on the one hand an “action” mode: a potential collision is detected by the system, the symbol system comprises at least one symbol representative of the limits of the disengagement path of the aircraft to avoid the collision and enabling the pilot to engage his avoidance maneuver, and on the other hand a “control” mode: this mode is displayed when the avoidance maneuver is engaged and the collision avoided, the symbol system comprises at least the symbol representative of the limits of the disengagement path of the aircraft and a plan view representing the air space around the aircraft and including at least one representation of the threat. | 12-09-2010 |
| 20100315265 | AUTOMATED TURBULENCE DISPLAY SYSTEM - A method identifies turbulence information from turbulence data generated by a set of remote aircraft based on a request to form identified turbulence information. The turbulence information is identified in response to the request received at an aircraft to view the turbulence information. The identified turbulence information is displayed on a display device in the aircraft. | 12-16-2010 |
| 20110006919 | NEAR END-OF-LIFE INDICATION FOR LIGHT EMITTING DIODE (LED) AIRCRAFT NAVIGATION LIGHT - A system and method for determining when a LED-based position light is nearing its end of life by providing to maintenance personnel visible indication that end of life is approaching. An example system includes a controller, a main LED light, an indicator LED light, a first elapsed time counter, a second elapsed time counter, and an oscillator. The first elapsed time counter recognizes when a first time threshold is exceeded, causing the indicator LED light to flash and triggering the second elapsed time counter to start counting. The second elapsed time counter recognizes when a second time threshold is exceeded, disabling both the indicator LED light and the main LED lights, thereby notifying maintenance personnel that the main LED lights have reached their end of life. | 01-13-2011 |
| 20110018739 | METHOD AND DEVICE FOR DETECTING ABSENCES OF MANUAL AND AUTOMATIC PILOTING OF AN AIRCRAFT - According to the invention, as a function of the altitude, the vertical speed and the heading of the aircraft, as well as of the deviation of the actual trajectory of the aircraft with respect to the automatic trajectory, a time interval (T) is determined, during which it is tolerable for said aircraft to be able to fly without any control command, both on the part of the stick ( | 01-27-2011 |
| 20110063136 | METHOD AND DEVICE FOR CENTRALIZED MANAGEMENT OF WARNINGS IN AN AIRCRAFT COMPRISING SEVERAL WARNING PRESENTATION INTERFACES - The invention in particular has as an object a method and a device for centralized management of warnings in an aircraft comprising a centralized system for management of warnings ( | 03-17-2011 |
| 20110063137 | INSTALLATION FOR DETECTING AND DISPLAYING THE FAILURES OF THE FUNCTIONAL SYSTEMS OF AN AIRCRAFT - An installation for detecting and displaying the failures of the functional systems of an aircraft is described. The installation can include both a general alarm system ( | 03-17-2011 |
| 20110095912 | JET ENGINE PROTECTION SYSTEM - A modern jet engine inlet protection system that protects against large birds and operates autonomously, that is dormant in routine aircraft operations, that automatically actuates its protective device(s) only at the immediate point of need, then returning it (them) to a non-interfering position, including a RADAR system and a LIDAR system which detect birds entering the intended flight path of the aircraft, and fast computer-implemented computational algorithms that track and identify those from the detected set that are (1) projected to enter a zone which would lead to ingestion by the engine, and (2) of a size large enough that they would seriously damage the engine if ingested; that includes defensive mechanisms housed in the engine nacelle cowling or center hub, or in the fuselage structure that are instantaneously actuated shortly before arriving at the point of impact to shield, deflect, reduce the size of the approaching bird to an acceptable mass, or destroy it, and, that after the ingestion threat has passed, the devices are stowed/retracted or safely jettisoned. | 04-28-2011 |
| 20110115649 | INTELLIGENT CREW ALERTING SYSTEM AND METHOD FOR AIRCRAFT AND OTHER VEHICLE APPLICATIONS - A method of managing alerts associated with the operation of an aircraft is provided. The method maintains an alert model database that correlates root causes to alerts associated with onboard aircraft subsystems. During operation of the aircraft, the method receives first alert data indicative of at least one alert of a first onboard aircraft subsystem, and traverses the alert model database to determine a root cause of the first alert data. The root cause (or some indicia thereof) can then be displayed on a display element. | 05-19-2011 |
| 20110148665 | Method And A Device For Detecting Lack Of Reaction From The Crew Of An Aircraft To An Alarm Related To A Path - A method and a device for detecting lack of reaction of the crew of an aircraft to an alarm related to a path. | 06-23-2011 |
| 20110175754 | Dynamic dashboard display - This invention relates to an electronic instrument panel for vehicles consisting of information display that provides on-demand imaging where instruments are not in static, fixed position, but rather change in location, dimension, information presented based on conditions and environment the vehicle is in, and based on user or factory preferences and settings. The display can change colors, be self dimming and offer wide array of telemetry, entertainment, vehicle data, climate control, instrumentation, and powertrain information. The instrument panel will be online through wireless connectivity and provide the occupants real-time on-demand information about the vehicle and its surroundings through electronic display and human voice. | 07-21-2011 |
| 20110205089 | AIRCRAFT POWER FAILURE SIMULATION APPARATUS AND METHOD - Disclosed is a flight management means verification apparatus ( | 08-25-2011 |
| 20110267206 | SYSTEMS AND METHODS FOR PROVIDING A SWATH-BASED DISPLAY OF TERRAIN HEIGHT INFORMATION - The present invention provides a system and a method. The method includes receiving data representing a position of a host aircraft, and based on the position of the host aircraft, receiving data extracted from a database representing an elevation of at least one of a terrain and an obstacle surrounding the host aircraft. The method further includes displaying, on a display, information including the position of the host aircraft and the extracted data, and identifying a subset of the displayed information as relevant for situational awareness. Further, the method includes displaying, on the display, an indicia of a maximum elevation within the subset of the displayed information. | 11-03-2011 |
| 20110273314 | METHOD FOR PROVIDING A PILOT WARNING SIGNAL FOR A PILOT OF AN AIRCRAFT, COMPUTER PROGRAM PRODUCT AND WARNING DEVICE - The present invention provides a method and a device for providing a pilot warning signal for a pilot of an aircraft. | 11-10-2011 |
| 20120044093 | COMBINED TIME-OF-FLIGHT AND IMAGE SENSOR SYSTEMS - An object detection system of a vehicle includes a time-of-flight (TOF) sensor that receives a reflected object detection signal at a second time based on an object detection signal transmitted at a first time. An image sensor generates an image signal including an image of a detected object. The image sensor is distinct from and adjacent to the TOF sensor. A TOF control module generates distance data based on the first time and the second time and determines whether at least a portion of a detected object is within a predetermined distance of the vehicle. An image control module generates image data based on the image signal. A detection control module correlates the distance data with the image data to generate a warning indicator when at least a portion of the detected object is within the predetermined distance of the vehicle. | 02-23-2012 |
| 20120068862 | Systems and Methods for Early Detection of Aircraft Approach to Volcanic Plume - Onboard systems and methods for early detection that an aircraft is approaching a volcanic (ash) plume or a gas plume having a concentration of a volcanic gas which would be toxic to humans. The detection method generally comprises the steps of measuring the concentration of one or more volcanic gases in air circulating in a space inside an aircraft and generating an alarm when one or more measured volcanic gas concentrations exceed a respective user-specified threshold or when a pattern of volcanic gas concentration is recognized with a user-specified confidence level. These systems are configured so that the alarm indicates the proximity of dangerous levels of either a volcanic gas or of volcanic ash. In particular, the detection system utilizes the air circulating through an aircraft cabin or cockpit to enable use of low-cost, carry-on electronic devices. | 03-22-2012 |
| 20120068863 | Systems and Methods for Remote Detection of Volcanic Plumes Using Satellite Signals - Systems and methods for remote detection of volcanic plumes using satellite signals. The invention solves the problem of remotely detecting volcanic plumes, including those embedded in clouds, by providing a system that can be installed onboard a mobile platform, such as an aircraft, a satellite, a weather balloon, a ship or a buoy. The volcanic plume detection system tracks RF signals (such as GPS signals from satellites) arriving at the mobile platform, and issues an alert or warning when characteristics of the RF signals indicate the likely presence of a volcanic plume in the monitored space. More specifically, the system in accordance with one embodiment utilizes the refractive properties of hydrogen sulfide (H | 03-22-2012 |
| 20120075122 | ALERT GENERATION AND RELATED AIRCRAFT OPERATING METHODS - A method of generating aircraft flight deck alerts is provided. An onboard alerting subsystem determines that an alert needs to be generated, and an onboard monitoring subsystem obtains a fatigue level of a flight crew member. An alert is generated with nominal audiovisual characteristics when the fatigue level is indicative of a non-fatigued physiological condition of the flight crew member, and with enhanced audiovisual characteristics when the fatigue level is indicative of a fatigued physiological condition. In addition, an automated flight crew training exercise can be launched when the flight crew member is fatigued, in an attempt to engage the flight crew member and alleviate fatigue. | 03-29-2012 |
| 20120075123 | DYNAMIC TASK AND ADAPTIVE AVIONICS DISPLAY MANAGER - A system and method are provided for intelligently managing the avionics display, information, and controls to more evenly distribute pilot task loads and/or automatically configure/reconfigure displays during flights. | 03-29-2012 |
| 20120146816 | Automatic Method And Device For Aiding The Piloting Of An Airplane - The device ( | 06-14-2012 |
| 20120242509 | CONTROL DISPLAY SYSTEM, METHOD, AND PROGRAM - The degree of urgency of a displayed object is promptly recognized in a control display system. The control display system has: an information acquisition unit that acquires a target serving as an object of monitoring and attribute information of the target; a control condition storage unit that stores the attribute information of the target and a viewpoint control condition serving as information about a display mode of the target, the attribute information and the condition being associated with each other in advance; a viewpoint control unit that detects attribute information matching the attribute information of the target acquired by the information acquisition unit from the control condition storage unit and that extracts the viewpoint control condition associated with the detected attribute information; and a display unit that displays a result obtained by carrying out viewpoint control of the target on the basis of the viewpoint control condition extracted by the viewpoint control unit. | 09-27-2012 |
| 20120306667 | DIGITAL AUDIO WARNING SYSTEM - A digital audio warning system (DAWS) that can monitor all relative aircraft systems and provide audio for any warning that requires immediate action. Current aircraft systems only monitor their individual system. The DAWS can monitor all relative aircraft systems. The DAWS may not replace the conventional warning signals, but can be a second level of warning to the flight crew. These warnings are relative to “red flag” type warnings and are not meant to replace warnings such as traffic collision avoidance system (TCAS) or enhanced ground proximity warning system (EGPWS) warnings. | 12-06-2012 |
| 20120319872 | SYSTEMS AND METHODS FOR IMPROVING PREDICTED PATH DISPLAY OUTPUT - Systems and methods for alerting a flight crew when the vertical situation display may be providing incomplete information due to the presence of a non-computed trajectory segment in the flight plan. A processing device in signal communication with a flight management system, a position measuring system, and a velocity measuring system receives a flight plan from the flight management system and determines if the flight plan includes any non-computed trajectory segments. If at least one of time or distance to the beginning of a next non-computed trajectory segment is less than a threshold value, the processing device generates an alert that information displayed on a vertical situation display may be incomplete. An output device outputs the generated alert. | 12-20-2012 |
| 20130176148 | VEHICLE CONDITION MONITORING AND REPORTING - Systems and methods for aircraft cabin noise analysis are disclosed. In one embodiment, a computer based system to monitor vehicle conditions comprises a trigger table stored in a tangible computer readable memory which stores at least one set of logic conditions which may trigger directive to analyze if alert conditions exist. The system further comprises a trigger processor to receive one or more data streams comprising vehicle condition data for a monitored vehicle and transmit the directive to analyze alert logic to an alert evaluation queue when the vehicle condition data satisfies the at least one set of logic conditions in the trigger table, and an alert evaluation processor to execute a stand-alone program to analyze vehicle data and generate an alert when the vehicle condition data satisfies the at least one set of alert conditions. In some embodiments, the system may be implemented in a computing system or as logic instructions recorded on a computer readable medium. | 07-11-2013 |
| 20140049407 | Illuminated Sidestick Controller, Such As An Illuminated Sidestick Controller for Use In Aircraft - A system and method for illuminating one or more sidestick controllers within a cockpit of an aircraft is described. In some embodiments, the system includes a sidestick controller having lighting components that display lighting behaviors representing the movement and/or control of an aircraft. In some embodiments, the system illuminates various different lighting components on a sidestick controller based on information received from aircraft control systems, cockpit lighting systems, and other systems associated with an aircraft. | 02-20-2014 |
| 20140313061 | FIRE DETECTION SYSTEM - A fire detection system for an aircraft, freight transportation vehicle or freight storage facility comprises one or more RFID tags associated with one or more items of freight being transported or stored. The RFID tag is configured to detect a condition indicative of a fire in or in the vicinity the item of freight, for example a temperature rise or generation of smoke. One or more RFID readers are arranged to read the RFID tags. The RFID reader is connected to or forms part of a control system, the RFID reader or the control determining whether the RFID tag has detected a fire. | 10-23-2014 |
| 20150029045 | METHOD AND SYSTEM FOR DYNAMICALLY DETERMINING AND DISPLAYING NAVIGATION INFORMATION - A method and system for dynamically evaluating a quantity of context sensitive information used by an operator of an airborne mobile platform in performing an operational procedure involving said mobile platform, and determining, in real time, a sub-quantity of context sensitive information that pertains to only that sub-quantity of information required by said operator to execute said operational procedure. The sub-quantity of information is then displayed on a display in real time for the operator. The method and system significantly eases the cognitive workload of the operator by enabling the operator to focus on and digest only that sub-quantity of information that is pertinent to performing the operational procedure with the specific type of mobile platform being operated. In one embodiment the sub-quantity of information pertains to minima information for performing an aircraft landing approach operation. | 01-29-2015 |
| 20160016671 | PROCESSING OF AIRCRAFT ALARM AND MAINTENANCE MESSAGES - A computer implemented method for managing alarm and maintenance messages of an aircraft, comprises collecting information relating to the alarm, aircraft status and maintenance messages; transmitting the information collected to an electronic device of EFB or electronic flight bag type, the electronic device being able to correlate the alarm messages with the maintenance messages and to associate the descriptions of the alarms with links and electronic maintenance documents. Developments describe notably the extracting of data from images or audio streams; listening to the communications on an avionics bus between the centralized maintenance system CMS and the printing service Printer and/or ground equipment of AGARS or VHF type; and the establishing of links with the electronic documentation and the use of an electronic flight bag EFB. | 01-21-2016 |
| 20160075446 | METHOD AND SYSTEM FOR TRIGGERING AN EMERGENCY MEASURE - A method for triggering a first emergency measure associated with an aircraft emergency comprising the steps of determining a risk level for an aircraft emergency and triggering the first emergency measure if the risk level exceeds a first threshold for the first emergency measure is described and claimed. The risk level is determined by evaluating a plurality of flight parameters and/or aircraft parameters using a predefined logic. The first threshold is adjusted according to a position of the aircraft over ground. Furthermore, a system for use onboard an aircraft for triggering a first emergency measure and an aircraft comprising such a system are disclosed. | 03-17-2016 |
| 20160083107 | ALERT MANAGEMENT METHOD - An alert management method implemented by a flight management system for triggering alerts during flight of an aircraft, using a look-up table associating, with each alert, at least one flight parameter and establishing, for each alert and the associated flight parameter, a correspondence between the value of the associated parameter and a plurality of predefined ordered priority levels. The method comprises when an alert is triggered: loading a value of the associated flight parameter, as a function of the state of the aircraft in real time, determining the priority level of the current alert out of the plurality, the priority level being determined by the value and from the look-up table; at regular time intervals and for each active alert, reiterating the preceding steps to determine, for each active alert, an associated priority level that is a function of the state of the aircraft in real time. | 03-24-2016 |
| 20160130013 | RISK ASSESSMENT FRAMEWORK - Methods, systems, and apparatus, including computer programs encoded on a computer storage medium, for receiving data related to a first flight risk factor and a second flight risk factor where the first and second risk factors include one of: a proficiency risk factor, an equipment risk factor, an environmental risk factor, or a performance risk factor. Applying a first weighting to the first flight risk factor to generate a first weighted flight risk factor, and applying a second weighting to the second flight risk factor to generate a second weighted flight risk factor. Assessing a flight risk level for a flight based on the first weighted flight risk factor and the second weighted flight risk factor. Providing data indicating the assessed flight risk level for the flight for display to a user. | 05-12-2016 |
| 20190144129 | CREW ALERTING SYSTEMS AND METHODS FOR MOBILE PLATFORMS | 05-16-2019 |
| 340965000 | Tactile | 1 |
| 20110018740 | TACTILE PILOT ALERTING SYSTEM AND METHOD - A method of alerting an occupant of a seat assembly of the occurrence of a triggering event comprising the steps of monitoring for the occurrence of the triggering event, vibrating the seat assembly and/or probing the seat assembly. | 01-27-2011 |
| 340966000 | Stall | 4 |
| 20110285550 | AIRFOIL PERFORMANCE MONITOR - There is described a method for generating a parameter for airfoil performance monitoring, the method comprising: receiving at least a first signal indicative of a first airflow parameter measured at one of an aft position and a side-facing position of a sensor mast mounted to an airfoil and at least a second signal indicative of a second airflow parameter measured at a fore position of the sensor mast; generating a turbulence intensity ratio for each one of the first airflow parameter and the second airflow parameter; and combining the turbulence intensity ratio of the first airflow parameter and the turbulence intensity ratio of the second airflow parameter to generate a combined turbulence intensity ratio for airfoil performance monitoring. | 11-24-2011 |
| 20130335243 | Stall Management System - A method and system for indicating a potential stall condition for an aircraft during flight. An alert lift coefficient is identified for the aircraft. The alert lift coefficient is adjusted in response to a number of changes in a current state of the aircraft. A set of thresholds is identified for use in generating an alert indicating that the aircraft has reached the potential stall condition using the alert lift coefficient. | 12-19-2013 |
| 20140253348 | WARNING SYSTEM FOR AIRCRAFT, AND AIRCRAFT - To provide a warning system that can issue a stall warning taking a flight environment into account. The warning system according to the present invention is a warning system for an aircraft, for issuing a warning in the case where there is a possibility of the aircraft stalling, and includes a selecting section for selecting one of two or more calculation criteria based on an icing state of the aircraft, a calculating section for calculating a stall angle based on the selected calculation criterion, and a warning section for comparing the calculated stall angle with a current angle of attack of the aircraft and issuing a stall warning if the current angle of attack exceeds the stall angle. | 09-11-2014 |
| 20150084792 | ANGLE OF ATTACK DISPLAY - An aircraft safety system includes a Stall/Spin Warning & Recovery Computer, an angle of attack sensor, a side slip sensor and an angle of attack display. The Stall/Spin Warning and Recovery Computer detects whether the aircraft is in a safe condition or an unsafe condition. The angle of attack display includes a first configuration that displays information indicative of safe aircraft condition when the orientation detector detects a safe condition and a second configuration that displays information indicative of unsafe aircraft condition when the computer detects an unsafe condition. The display may transition from the first configuration to the second configuration when the orientation detector detects an unsafe condition and then to a third configuration, which may include visual control-input instructions that enable recovery to a safe condition. | 03-26-2015 |
| 340967000 | Attitude (including yaw, angle of attack, roll, pitch, glide slope) | 6 |
| 20100033350 | STANDBY INSTRUMENT FOR AN AIRCRAFT INSTRUMENT PANEL DETECTING OVERLOAD, PARTICULARLY DURING THE LANDING PHASE - The present invention relates to a standby instrument fitted to the instrument panel of an aircraft detecting overloads. The standby instrument includes a processor to calculate and display flight information based on data provided by associated sensors integrated into a standby system. It additionally includes a module for detecting overload of the aircraft on the basis of the data provided to display the flight information. The invention applies to the detection of overloads during a heavy landing. More generally, it applies to the detection and indication of overloads of an aircraft in various types of environment. | 02-11-2010 |
| 20140218216 | AIRCRAFT SYSTEMS AND METHODS FOR ATTITUDE RECOVERY - A vehicle system is provided. The system includes a processor configured to receive data representative of a current attitude and a desired attitude and to generate display signals associated with the current attitude and the desired attitude. The system further includes a display device configured to receive the display signals and operable to selectively render an image including roll angle alert symbology. The roll angle alert symbology includes a first curved arrow. | 08-07-2014 |
| 20140232568 | Aircraft Monitoring System - A method and apparatus for monitoring an aircraft. A pilot control input signal is received. A response of a control surface system controlled by a flight control model is identified using the pilot control input signal. An alert is generated when the control surface system reaches a threshold with respect to the control surface system becoming saturated. | 08-21-2014 |
| 20150022380 | SYSTEM AND METHOD FOR PROVIDING MODEL-BASED ALERTING OF SPATIAL DISORIENTATION TO A PILOT - A system and method monitor aircraft state parameters, for example, aircraft movement and flight parameters, applies those inputs to a spatial disorientation model, and makes a prediction of when pilot may become spatially disoriented. Once the system predicts a potentially disoriented pilot, the sensitivity for alerting the pilot to conditions exceeding a threshold can be increased and allow for an earlier alert to mitigate the possibility of an incorrect control input. | 01-22-2015 |
| 20150054663 | Aircraft Monitoring System - A method and apparatus for monitoring an aircraft. A pilot control input signal is received. A response of a control surface system controlled by a flight control model is identified using the pilot control input signal. An alert is generated when the control surface system reaches a threshold with respect to the control surface system becoming saturated. | 02-26-2015 |
| 20150123821 | TAILSTRIKE WARNING SYSTEM - An aircraft tailstrike warning method includes identifying a first value representing an aircraft angle of attack, identifying a second value representing a maximum aircraft angle of attack, identifying a difference between the first value and the second value, and providing a tailstrike warning when the difference between the first value and the second value is less than a threshold amount. | 05-07-2015 |
| 340968000 | Wind shear | 2 |
| 20090002196 | SYSTEMS AND METHODS FOR AIRCRAFT WINDSHEAR DETECTION - The present invention allows quick detection of actual hazardous windshears while ignoring the effects of normal turbulence. A system according to one aspect of the present invention comprises a signal processor configured to determine a presence of hazardous windshear based on: (a) whether a measured windshear is beyond a first predetermined threshold, and (b) whether a measured turbulence level is beyond a second predetermined threshold. | 01-01-2009 |
| 20090184846 | METHOD AND DEVICE FOR FILTERING ALARMS - The invention relates to a method, a device and an item of equipment for filtering alarms originating from a windshear detection system embedded in an aircraft being able to emit an alarm. The aircraft has at least one sensor allowing the acquisition of a flight parameter. The device according to the invention includes: means ( | 07-23-2009 |
| 340969000 | Speed | 5 |
| 20100194599 | FLAPS OVERSPEED ADVISORY SYSTEM - A flap advisory system provides an advisory to a pilot informing that a speed of the aircraft should be attended to because of a current or desired flap setting. More specifically, the flap advisory system compares a measured airspeed of the aircraft either directly to a flap placard speed or to a marginal speed range set below the flap placard speed for a given flap setting. If the measured airspeed is determined to be excessive then the system provides an advisory indicating the airspeed is too fast. Further, the system may provide an advisory when a movement of a flap handle is detected such that continued movement of the flap handle would place the flaps in a setting that is inappropriate for the measured airspeed. | 08-05-2010 |
| 20140266807 | SYSTEM AND METHOD FOR GRAPHICALLY DISPLAYING AIRSPACE SPEED DATA - A system and method are provided for graphically displaying airspace data including speed restrictions on an aircraft display. The system comprises an avionics display system coupled to a processor that is configured to retrieve airspace data from a database, display the aircraft data on the display, and display a visual representation of the airspace. Then the processor may alter the format of the visual representation of the airspace to a second visual representation, if the airspace data meets predetermined criteria. | 09-18-2014 |
| 20140368359 | FLIGHT DECK DISPLAY SYSTEMS AND METHODS FOR VISUALLY INDICATING LOW SPEED CHANGE CONDITIONS DURING TAKEOFF AND LANDING - Embodiments of a flight deck display system deployed onboard an aircraft are provided, as are embodiments of a method carried-out by a flight deck display system. In one embodiment, the flight deck display system includes a cockpit display device and a controller. The controller is configured to: (i) establish the speed trend of the aircraft over a predetermined time period; (ii) generate a primary flight display on the cockpit display device including a speed trend vector graphic representative of the established speed trend; and (iii) alter the appearance of the speed trend vector graphic in a first predetermined manner if a low speed change condition is detected during at least one of aircraft takeoff and landing. | 12-18-2014 |
| 20150029046 | METHODS AND SYSTEMS FOR DISPLAYING BACKUP AIRSPEED OF AN AIRCRAFT - The disclosed embodiments relate to an aircraft that includes system for selecting an airspeed reference that is displayed within a cockpit of an aircraft. The system includes a processor and a display located in the cockpit. The processor is configured to determine whether primary airspeed is valid or invalid, and, to select a backup airspeed as the airspeed reference that is output to the display when it is determined that the primary airspeed is invalid. The display is configured to display the backup airspeed as the airspeed reference. The backup airspeed is generated based on Global Position System (GPS) information that is received by the aircraft. | 01-29-2015 |
| 20150084793 | SYSTEM AND METHOD FOR DISPLAYING AIRPORT FEATURES ON A DYNAMIC AIRPORT MOVING MAP DISPLAY - A method and apparatus is provided for enhancing situational awareness onboard an aircraft during an aircraft ground maneuver such as when taxiing on a runway or taxiway. A three-dimensional view including airport features is rendered in a first airport region that extends a first predetermined distance (D | 03-26-2015 |
| 340970000 | Altitude | 11 |
| 20090109064 | Simplified self-powered attitude survival indicator - This simplified self powered aircraft attitude survival indicator is easily and readily transportable from one aircraft to another and provides a simple indicator which gives a visual indication of aircraft attitude and alarms when the aircraft is in a dangerous attitude. The aircraft attitude indicator includes a housing containing a power source, multiple attitude sensors, and at least one piezoelectric alarm, and a front panel display with an arrangement of light emitting elements (electric bulbs or LEDs) providing visual attitude indicators. | 04-30-2009 |
| 20090189787 | SYSTEM AND METHOD FOR GENERATING AN ALTIMETER MIS-SET ALERT ON A PRIMARY FLIGHT DISPLAY - A primary flight display system is provided for deployment on an aircraft including a barometric altimeter and a secondary altitude-determining device. The barometric altimeter provides a first estimated altitude corresponding to a reference pressure setting, and the secondary altitude-determining device provides a second estimated altitude. The primary flight display system includes a primary flight display (PFD), and a controller coupled to the PFD. The controller is configured to generate: (i) an altitude graphic on the PFD indicative of the first estimated altitude, and (ii) a visual alert on the PFD when the difference between the first estimated altitude and the second estimated altitude exceeds a predetermined error threshold. | 07-30-2009 |
| 20100090867 | Method and System for Meteorological Monitoring Aboard an Aircraft - A method and system for meteorological monitoring aboard an aircraft. | 04-15-2010 |
| 20100141481 | Multi-stage label - An aspect of the present invention provides a method for providing information to an air traffic controller. The method comprises the steps of: displaying, on a video display, a symbol representative of a position of an aircraft and a first stage of a multi-stage label comprising information relating to the aircraft ( | 06-10-2010 |
| 20110187562 | Method And Device For Preventing An Anti-Collision System On Board An Airplane From Emitting Alarms, During An Altitude Capture Maneuver - According to the invention, the device ( | 08-04-2011 |
| 20110199237 | METHODS AND SYSTEMS FOR DEPICTING A DATA DRIVEN MINIMUM SAFE ALTITUDE - A method for providing a minimum safe altitude indication on an aircraft display is described. The method includes utilizing current aircraft heading and position data to generate a location and orientation for an own-ship depiction with respect to an aircraft display, utilizing the current position data, along with terrain data, to generate minimum safe altitude data for an area surrounding the aircraft, and displaying on the aircraft display, about the location for own-ship depiction, the minimum safe altitudes surrounding the aircraft. | 08-18-2011 |
| 20110273315 | SYSTEMS AND METHODS FOR ADJUSTING LANDING GEAR ALERT ENVELOPE FOR OFFSHORE PLATFORMS AND BUILDING-TOP LANDINGS - Systems and methods for improving landing gear alerting on a rotary wing aircraft. An example system includes a user interface device that allows a user to set a bug altitude value and a radio altimeter that produces an altitude value, both of which are in communication with a processor. The processor receives a bug altitude setting, generates a landing gear alert altitude value based on the received bug altitude setting and a predefined additive, receives a radio altitude value for the rotary-wing aircraft, and generates a landing gear alert if the radio altitude value is less than the landing gear alert altitude value and the landing gear is not in a landing position. An output device in signal communication with the processor, outputs the generated landing gear alert. | 11-10-2011 |
| 20120001773 | AVIONICS DEVICE, SYSTEMS AND METHODS OF DISPLAY - The present general inventive concept relates to methods and systems to select and display information on an avionics display screen. The systems and methods allow for the selection and display of information using knobs to highlight and select the desired information for display, eliminating the need for a cursor function. The systems and methods also provide for multiple pages and/or multiple windows or “tiles” within these pages and/or windows simultaneously on a single screen of a display, with each window, page, and/or tile being fully controlled independently when selected. The present general inventive concept also relates to systems and methods to provide multiple cues on an electronic display system altitude tape to a pilot in advance and impending approach to a predefined altitude. The present general inventive concept also relates to systems and methods to employ variable resolution topographical data based on display range for an avionics navigation display. | 01-05-2012 |
| 20120056760 | Method And Device For Automatically Determining An Erroneous Height Value Of A Radioaltimeter Mounted On An Aircraft - Method and device for automatically determining an erroneous height value of a radio altimeter mounted on an aircraft. The device ( | 03-08-2012 |
| 20130106623 | SYSTEMS AND METHODS FOR ADJUSTING SINK RATE ALERT ENVELOPE FOR SPECIAL LANDING ZONES | 05-02-2013 |
| 20140354455 | SYSTEM AND METHOD FOR INCREASING SITUATIONAL AWARENESS BY DISPLAYING ALTITUDE FILTER LIMIT LINES ON A VERTICAL SITUATION DISPLAY - A system and method are provided for increasing vertical situational awareness when the display of intruder aircraft on a vertical situation display (VSD) is restricted to a specific region of the VSD as determined by an altitude filter. The method comprises displaying a first altitude filter limit line on the VSD. | 12-04-2014 |
