METHODS AND SYSTEMS FOR REQUESTING AND RECOVERING DATA FROM AN AIRCRAFT, DURING THE FLIGHT OF THE SA

专利摘要:
methods and systems for requesting and retrieving data from an aircraft, during its flight the present invention relates to methods and systems for requesting and retrieving data from aircraft during their flight, data that can be used to perform an additional monitoring of aircraft subsystems to detect an abnormal condition and / or to identify one or more sources that are causing the abnormal condition; in one embodiment, data for one or more relevant parameters can be requested from the ground, · measured on board the aircraft, and stored in a data file, which is then transmitted back to the teams in Earth; aircraft data in real time from one or more relevant parameters can then be analyzed to identify one or more sources that are causing the abnormal condition.
公开号:BR112014018976B1
申请号:R112014018976-5
申请日:2013-01-31
公开日:2020-12-15
发明作者:Jim Gallagher；Keith Conzachi；Noëlle Britt；William Kerekesh；Robert J Geary；Robert O'Dell
申请人:Gulfstream Aerospace Corporation；
IPC主号:

专利说明:

BACKGROUND OF THE INVENTION
[0001] The present invention patent refers to aircraft in general, and, more particularly, to methods and systems for requesting and retrieving data from an aircraft during its flight. DESCRIPTION OF THE STATE OF THE TECHNIQUE
[0002] When an aircraft is in flight, it is difficult to detect when its subsystems or components begin to operate abnormally, and / or correctly diagnose the specific source that is causing an abnormal operation situation in a particular subsystem or component. Although these abnormal operating conditions may persist after the aircraft lands, in many cases, this does not occur, which can make the task of correctly diagnosing the specific source that caused or continues to cause the abnormal conditions of that subsystem even more difficult. or particular component.
[0003] There is, therefore, a great need for methods and systems to monitor the health of an aircraft and the various components and subsystems that integrate it. It would be desirable for such methods and systems to be able to automatically detect abnormal conditions that indicate when one or more subsystems or components of an aircraft are experiencing operating / performance problems. It would also be desirable that such methods and systems could identify the specific source (s) within those subsystems or components that are causing the operating / performance problems, so that corrective actions could be taken with respect to such identified subsystems or components, before a serious error or failure has occurred. It would also be desirable for such methods and systems to be automatically implemented, without the need for intervention by the crew. And it would also be desirable that the aforementioned methods and systems would allow ground crews to request, collect, retrieve and communicate aircraft data during their flight. Other features of the present invention will become evident from the detailed description presented below and the attached claims, taken in conjunction with the drawings accompanying this report. SUMMARY OF THE INVENTION
[0004] In one embodiment, a method is provided by which relevant parameters can be determined that are measured on board an aircraft. A parameter request message is generated, which includes a parameter file that specifies the relevant parameters to be measured on the aircraft. The parameter request message is communicated to the aircraft via satellite communication links, and the data for each relevant parameter is measured and recorded in a data file, which is then transmitted from the aircraft to another computer that is connected to the ground-based computer for further analysis.
[0005] In another embodiment, a system is provided. The system includes an aircraft, a satellite that is communicatively coupled to the aircraft and a gateway through satellite communication links, a ground support network comprising a ground-based computer, and another computer, coupled to the computer based on land, which is configured to generate a parameter request message. The parameter request message includes a parameter file that specifies the relevant parameters to be measured on the aircraft. The parameter request message can be communicated to the gateway for transmission and to the aircraft via satellite communication links. The aircraft comprises an on-board computer and a transceiver. The on-board computer is configured to measure data for each relevant parameter in the parameter file and to record the measured data in a data file. The transceiver is configured to transmit the data file to the satellite, for sending to the other computer. BRIEF DESCRIPTION OF THE DRAWINGS
[0006] Various embodiments of the present invention will be described below in conjunction with the accompanying drawings, in which similar numbers indicate similar elements:
[0007] FIG. 1 illustrates an integrated system for monitoring the health and course trend of an aircraft and the various subsystems of that aircraft, in accordance with some of the embodiments of the present invention.
[0008] FIG. 2A is a perspective view of an aircraft that can be used in accordance with some of the exemplary embodiments of the present invention.
[0009] FIG. 2B is a block diagram of an Aircraft Health and Trend Course Monitoring (AHTM) system, in accordance with an exemplary embodiment of the present invention.
[0010] FIG. 2C is a block diagram of some of the various subsystems of an aircraft, in accordance with an exemplary embodiment of the present invention.
[0011] FIG. 3 is a block diagram of parts of a ground support network, according to an embodiment of the present invention.
[0012] FIG. 4 is a flow chart of a method for requesting and retrieving data from an aircraft from various subsystems of said aircraft during its flight, in accordance with an embodiment of the present invention.
[0013] FIG. 5A is a flow chart of a method for requesting and retrieving data from an aircraft from various subsystems of said aircraft during its flight, in accordance with another embodiment of the present invention.
[0014] And FIG. 5B is a block diagram showing some of the processing and communication steps of different messages, according to an exemplary implementation of the method of FIG. 5A. DETAILED DESCRIPTION OF THE INVENTION
[0015] The words "example" and "exemplificative" used in this report mean "to serve as an example, a model or an illustration". The following detailed description is merely exemplary in nature, and is not intended to limit the invention or the application and use thereof. Any embodiment described herein as "exemplary" should not necessarily be interpreted as the preferred or most advantageous embodiment over other embodiments. All embodiments described in this report are exemplary embodiments, provided to allow those skilled in the art to reproduce or use the present invention, and not to limit the scope of the invention, which is defined by the appended claims. Furthermore, there is no intention that the present invention is linked to any explicit or implicit theory already known in the art.
[0016] FIG. 1 illustrates an integrated system (100) for monitoring the health and course trend of an aircraft (110) and the various subsystems of said aircraft, in accordance with some of the embodiments of the present invention. As used herein, the term "health monitoring" refers to the process of collecting and evaluating relevant parameters and / or corresponding measured data, to determine the status, condition or numerical output value of a component and / or subsystem, in any given period of time. As used herein, the term "trend monitoring" refers to the process of collecting and evaluating relevant parameters and / or corresponding measured data to determine the state, condition or numerical value of a component's output and / or subsystem, in any given period of time, in order to predict, estimate or propose the said state, condition or numerical value of output of a component and / or subsystem, at a future time.
[0017] The system (100) includes an aircraft (110), a satellite (112) communicatively coupled to the aircraft (110) and to a gateway (114) via satellite communication links (111) and (113) , a ground support network (116) that includes at least one ground-based computer (117) [FIG. 1 illustrates an example of implementation with eleven computers (117-1) to (117-11)], and another computer (122) that is coupled to the ground support network (116) through a server (118). The computer (122) can be arranged, for example, in the aircraft monitoring center or of an operator or aircraft manufacturer.
[0018] During the flight, the aircraft (110) can transmit information via a satellite communication link (111). For example, in one embodiment, the data transmitted by the aircraft during the flight comprises a message from a crew alert system (CAS), generated by the aircraft's on-board computer (not shown in FIG. 1). To better explain, many modern aircraft use CZJS messages (messages from the Crew Alert System - CAS) to provide the crew with information about faults or defects in the aircraft systems. CAS messages are announced to the crew based on triggers and logic embedded in the avionics suite (set of aircraft electronic systems). The logic typically contains inputs from all aircraft information systems and subsystems. A CAS message is triggered when the combination of inputs meets the criteria of the built-in logic. These inputs could be boolean or binary inputs, or floating point parameters. As soon as the logic is satisfied, the avionics set displays a message to the crew, in red (indicating Warning / Alarm), or in amber (orange / yellow) (indicating Care / Attention), or in cyan (blue) / green) (indicating Consultation / Council). Many CAS messages display information about faults or defects to the crew. In these cases, when a fault or defect information is displayed, it is assumed that the system is experiencing an abnormal situation, and that corrective action must be taken to successfully extinguish the CAS message. The system records (records) all parameters of the CAS messages at a given time. The CAS message parameter value is 0 (zero) until the CAS message becomes active. Once active, the parameter value of the CAS message changes, ranging from 0 (zero) to an integer between 1 (one) and 63 (sixty-three), depending on the failure. As CAS messages are recorded (recorded), the system detects when the value of the parameters changes from 0 (zero) to a value other than 0 (zero).
[0019] The CAS message includes raw data. The CAS message automatically indicates that the data measured for a relevant parameter or variable of an aircraft subsystem is outside one or more limits, and that an abnormal condition has been detected. some described embodiments, when a CAS message is generated on board the aircraft (110), the data for the relevant parameters associated with that particular CAS message are automatically measured and stored in a file that is transmitted to the ground support network ( 116). The aircraft's engineering and maintenance teams can determine, based on experience, a number of different parameters that are the common triggers for each particular CAS message. Thus, for each particular CAS message, relevant parameters and their respective limits can be pre-defined (for example, upper and / or lower limits for each relevant parameter).
[0020] The aircraft's on-board computer is configured to open a communication path that includes a first satellite communication link (111) between the aircraft (110) and the satellite (112), and a second satellite communication link (113) between the satellite (112) and the ground-based gateway (114). Thus, the satellite (112) is communicatively coupled to the aircraft (110) and the gateway (114) through the satellite communication links (111) and (113), respectively, and to all servers between the aircraft (110 ) and the entrance door (114). The aircraft's on-board computer (110) can communicate the CAS file message to the satellite (112) via the first satellite communication link (111). The satellite (112) can then communicate the CAS message file to the gateway (114) via the second satellite communication link (113), and the gateway (114) can communicate the CAS message file to the ground support network (116) via a communication link (115).
[0021] The ground support network (116) can be operated by a party or entity other than the party or entity that operates the aircraft. The ground support network (116) includes several health management algorithms that are used to process the data and data files received from the aircraft (110). As soon as the aircraft data (110) is processed using the appropriate health management algorithms, the ground support network (116) can generate web pages that are provided to the server (118). The web pages can include the processed data generated from the raw data communicated by the aircraft (110), the aircraft data files (110), information derived from the processed data or data files, etc. The web pages may also include information that identifies elements of the aircraft, such as the subsystems (or their components) that need to be inspected.
[0022] According to the described embodiments, the ground support network (116) includes at least one ground-based computer (117) [eleven computers (117-1) have been illustrated ... (117-11 ) in the exemplary embodiment of FIG. 1] . In a non-limiting example, the ground-based computer (117) of the ground support network (116) is configured to process the raw data from the CAS message file that was transmitted from the aircraft (110), to generate data processed. For example, when the file corresponding to the CAS message is received and loaded on one of the ground-based computers (117) of the ground support network (116), the ground-based computer (117) can load and execute a module (380 ) (see FIG. 3) of an appropriate Aircraft Health and Trend Monitoring (AHTM) Monitoring and Aircraft Trend (AHTM) program, which corresponds to the particular CAS message indicated in the file. When the ground-based computer (117) performs a Health and Trend Monitoring Algorithm (HTMA) Algorithm, the measured data for each of the parameters that are included in the file can be analyzed to determine which parameters are at an abnormal level (that is, outside their upper and / or lower limits), and thus constitute the parameters most likely to be causing that particular CAS message to be generated. For example, in some embodiments, each parameter can be compared to one or more limits, and all parameters that are determined to be outside their respective limits can then be identified as being the potential cause of generating the CAS message. When the data measured for any parameter is determined to be abnormal, the HTMA program can signal the abnormality, and parameters that are outside their respective limits can then be stored as processed data, in a processed data file. In some embodiments, the processed data may also indicate one or more particular subsystems (or their components) with which each of the relevant parameters is associated. In this way, those particular subsystems (or their components) can be easily identified for further inspection, to determine whether such subsystems are functioning correctly, or whether corrective measures should be taken.
[0023] The ground support network (116) is connected to the server (118) through a communication link (125). The server (118) serves as a portal to the ground support network (116), and provides web pages from the ground support network (116) to the computer (122) as soon as they can be displayed. Among other information, the land-based computer (117) can communicate the processed data [which was generated from the "raw" or unprocessed data received from the aircraft (110)] to the server (118) through the referred pages web.
[0024] The computer (122) is connected to the ground support network (116) through a communication link (119) with the server (118). The computer (122) allows communication with the ground support network (116), for example, from a network operator and / or another computer system, and can be implemented using any suitable methods and devices. In this way, the information generated on the ground support network (116) can be viewed by the teams or by the operator on the computer (122). The computer (122) can include one or more network interfaces to communicate with other systems or components, one or more terminal interfaces to communicate with technicians, and one or more connection interfaces to connect to the ground support network (116).
[0025] According to the described embodiments, the server (118) communicates the processed data to another computer (122).
[0026] Although not illustrated in FIG. 1, the computer (122) includes a processor that can perform the processing both automatically and in response to an operator's input, to generate a parameter request message. In some situations, processing can be performed based on, or in response to, processed data that was generated based on the data received from the aircraft (110) during the flight.
[0027] The parameter request message includes a parameter file that specifies the relevant parameters that have been selected to be measured and recorded on the aircraft (110), to provide additional parametric data. In some embodiments, the parameter file also includes a duration value for each relevant parameter. Each duration value specifies how long the parametric data for that particular relevant parameter is to be measured and recorded.
[0028] According to a non-limiting embodiment, the relevant parameters can be selected automatically by the software or manually by a human operator.
[0029] In a phoneme of realization, the relevant parameters are determined based on the analysis of the data processed automatically by the software, or manually by a human operator, who analyze the processed data. Each of the relevant parameters can correspond to additional aircraft parametric data (110) that is needed to identify one or more sources that are causing an abnormal condition (for example, that caused the CAS message to be generated). In some implementations, each relevant parameter can influence or affect the data to be measured by the aircraft.
[0030] For example, in some embodiments, the relevant parameters can be determined using computer executable software to automatically analyze the processed data, in order to automatically determine the relevant parameters that should be measured on the aircraft to provide the additional data . On the other hand, in other embodiments, the relevant parameters can be determined by an operator on any observation or information basis. For example, in one embodiment, the operator can, for example, view the processed data through a computer interface, and can manually identify and select the relevant parameters on the computer (122), based on the processed data.
[0031] Regardless of how the parameter request message is generated, the computer (122) communicates the parameter request message to the server (118), which communicates the parameter request message to the shore support network (116). The ground support network (116) then communicates the parameter request message to the gateway (114), which communicates the parameter request message to the satellite (112) via the second communication link via satellite (113). The satellite (112) then communicates the parameter request message to the aircraft (110) via the first satellite communication link (111).
[0032] As will be described in more detail below, the aircraft (110) includes at least one on-board computer and a transceiver, and a wireless communication network interface to communicate information via the satellite communication link (111). After receiving the parameter request message, the on-board computer is configured to extract the parameter file from the parameter request message on the aircraft's on-board computer (110), to: determine the relevant parameters, and, optionally, the duration values (time periods) corresponding to each of the relevant parameters in the parameter file; measure parametric data for each relevant parameter, for the corresponding time period (duration value); and write the measured parametric data to a data file. In some embodiments, the measured parametric data for each of the relevant parameters comprises a flow of measured parametric data for that particular relevant parameter, which is measured over a specific period of time (duration value).
[0033] The transceiver is configured to transmit the data file to the satellite (112), through the first satellite communication link (111), for sending it to the ground support network (116) and to the other computer (122).
[0034] In one embodiment, after receiving the data file, the satellite (112) transmits said data file, via the second communication link (113), to the gateway (114), and the gateway (114) transmits the data file to the ground support network (116). The ground support network (116) can then communicate the data file to the server (118), which can communicate the data file to the computer (122), for display on a computer interface.
[0035] FIG. 2A is a perspective view of an aircraft 110 that can be used in accordance with some of the described embodiments. According to a non-limiting embodiment, the aircraft (110) includes a fuselage (205), two main wings (201-1) and (201-2), a vertical stabilizer (212), an elevator (209) that includes two horizontal stabilizers (213-1) and (213-2) in a "T" tail configuration, and two jet engines (211-1) and (211-2). For flight control, each of the two main wings (201-1) / (201-2) has an aileron (202-1) / (202-2) ("ailerons" being the moving parts provided for in the trailing edges of the wings, which allow the aircraft to tilt sideways in relation to its longitudinal axis), an aileron compensator (206-1) 7 (206-2), a spoiler (204-1) / (204-2) ("spoilers" means moving parts positioned on the wings, which have the function of reducing the lift of the aircraft), and a flap (203-1) / (203-2) (understood as "flaps" the flaps or articulated surfaces provided on the trailing edges of the wings, which have the function of increasing the lift and drag of the aircraft); the vertical stabilizer (212) includes a rudder (207), and each of the horizontal stabilizers (213-1) / (213-2) includes an elevator compensator (208-1) 7 (208-2). Although not shown in FIG.2A, the aircraft (110) also includes an on-board computer, aircraft instruments and various control systems and subsystems, which will now be described with reference to FIG. 2B.
[0036] FIG. 2B is a block diagram of an Aircraft Health and Trend Monitoring (AHTM) Monitoring System (200), according to an exemplary embodiment. Part of the system (200) is implemented inside the aircraft (110), for data acquisition. These data may include data measured for one or more relevant variables, data measured for relevant parameters associated with one or more relevant variables, messages from the Crew Alert System (CAS), and data measured for the relevant parameters associated with one or more of the CAS messages. These data can be communicated from the aircraft (110) to the ground support network (116), and used to monitor the health of one or more elements of the aircraft (110), for example, subsystems (230) or components of such subsystems (230), and / or to monitor the behavioral trend exhibited by one or more elements of the aircraft (110). As shown, the system (200) includes several subsystems (230) of the aircraft (110). »
[0037] Said part of the system (200) implemented inside the aircraft (110) includes an on-board computer (210), several subsystems (230), the instrumentation (250) of the aircraft, exit devices (260) from the cabin , for example, display units (262) (such as control display units, multi-function monitors, etc.), audio elements (264) (such as speakers, etc.) and various input devices (270) , such as a keyboard, which includes a controlled cursor device, and one or more touch screens, devices (270) which can be implemented as part of the display units.
[0038] The instrumentation (250) of the aircraft may include, for example, an airspeed information system, elements of a Global Positioning System (GPS), which provides information on the aircraft's position and speed, elements of an Inertial Reference System (IRS), proximity sensors, switches, relays, video cameras, etc. In general, the IRS system is an autonomous navigation system that includes inertial detectors, such as accelerometers and rotation sensors (for example, gyroscopes) to automatically and continuously calculate the position, orientation, direction and speed (speed of the movement) of the aircraft, without the need for external references, as soon as it is initialized.
[0039] The on-board computer (210) includes a data bus (215), a processor (220), a system memory (223), satellite communication transceivers and wireless network interfaces (271).
[0040] The data bus (215) serves for the transmission of programs, data, states and other information or signals between the various elements illustrated in FIG. 2B. The data bus (215) is used to carry the information communicated between the processor (220), the system memory (223), the various subsystems (230), the aircraft instrumentation (250), the cabin exit devices (260), input devices (270), and satellite communication transceivers and wireless network interfaces (271). The data bus (215) can be implemented using any suitable physical or logical means to connect the on-board computer (210) to at least the above mentioned internal and external elements. This includes, but is not limited to, direct hard-wired connections (built-in or physically connected to a system or network), fiber optics and infrared and wireless bus technologies.
[0041] The processor (220) performs the calculation and control functions of the computer system (210), and can comprise any type of processor (220) or multiple processors (220), individual integrated circuits, such as a microprocessor, or any suitable number of integrated circuit devices and / or circuit boards that work cooperatively to carry out the functions of a processing unit.
[0042] It should be understood that the system memory (223) can include a single type of memory element, or it can be composed of several different types of memory components. The system memory (223) can include a non-volatile memory (224), such as a ROM memory, a flash memory, etc., a volatile memory (225), such as a RAM memory, or a combination of both. RAM (225) can be any type of suitable random access memory, including the various types of random access memory (DRAM), such as SDRAM, and the various types of static RAM (SRAM). RAM (225) includes an operating system (226) and programs for generating parameter files (228). RAM memory (225) stores executable code for one or more programs for generating parameter files (228). The parameter file generation programs (228), stored in the system memory (223), can be loaded and executed on the processor (220) to implement a parameter file generation module (222) on the processor (220). As will be explained below, the processor (220) runs the parameter file generation programs (228) to generate parameter files that include the measured parametric data used on the ground support network (116) and / or the computer (122 ), to monitor the health and the course trend for one or more subsystems of the aircraft (or its components).
[0043] Furthermore, it is important to note that, in some embodiments, the system memory (223) and the processor (220) can be distributed through several different on-board computers, which collectively comprise the computer system of board (210).
[0044] The satellite communication transceivers and the wireless communication network interfaces (271) are functionally and communicatively coupled to a satellite antenna (272) that can be external to the on-board computer (210). The satellite antenna (272) can be used to communicate information to the satellite (112) via the satellite communication links (111) and (113). The gateway (114) of the satellite can be connected to other networks, including the Internet, so that information can be exchanged with remote computers.
[0045] FIG. 2C is a block diagram of the various subsystems (230) of an aircraft (110), according to an exemplary embodiment.
[0046] In an exemplary non-limiting embodiment, the diverse subsystem (s) (230) - (231) to (246) - include: impulse reverser subsystem (s) (231); brake control subsystem (s) (232); flight control subsystem (s) (233); direction control subsystem (s) (234); subsystem (if aircraft sensor (235);} control sub-system (s) of the entrance door of an auxiliary power unit (APU) (236); cabin environment control subsystem (s) (237); subsystem ( s) landing gear control (238); propulsion subsystem (s) (239); fuel control subsystem (s) (240); lubrication subsystem (s) (241); monitoring subsystem (s) ground proximity (242); aircraft actuator subsystem (s) (243); fuselage subsystem (s) (244); avionics subsystem (s) (245); and software subsystem (s) (246) .
[0047] The subsystem (s) (231) to (246) illustrated in FIG. 2B are exemplary only, and, in other embodiments, other subsystem (s) may be included, such as, for example: aerial data subsystem (s); automatic flight subsystem (s); engine / powertrain / ignition subsystem (s); electric energy subsystem (s); communications subsystem (s); fire protection subsystem (s); hydraulic power subsystem (s); rain and ice protection subsystem (s); navigation subsystem (s); oxygen subsystem (s); pneumatic subsystem (s); information subsystem (s); exhaust subsystem (s); etc.
[0048] Although not illustrated in FIG. 2C, experts in the field will understand that each of the various subsystems can include one or more components. In addition, each of the various subsystems may include one or more sensors to facilitate the measurement and generation of data related to the operation of each of the aircraft subsystems (110) (and / or a component of that subsystem), to assist in the making a diagnosis and monitoring the health of one or more subsystems. Each sensor can generate data that is used to generate information that can be included in the parameter files generated by the data file generation unit (222) of FIG. 2B.
[0049] In general, a "sensor" is a device that measures a physical quantity and converts it into a signal that can be read by an observer or an instrument. In general, sensors can be used to detect light, movement, temperature, magnetic fields, gravitational forces, humidity, vibration, pressure, electric fields, current, voltage, sound, and other physical aspects of an environment. Examples of non-limiting sensors may include acoustic sensors (for example, sound, microphone, seismograph, accelerometer, etc.); vibration sensors; vehicle sensors (e.g., airspeed indicator, altimeter, altitude indicator, gyroscope, inertial reference unit, magnetic compass, navigation instrument sensor, speed sensor, accelerator position sensor, variable reluctance sensor, viscometer, wheel speed sensor, yaw sensor, etc.); chemical sensors / detectors; electric current sensors; electrical power sensors; magnetic sensors; radio frequency sensors; environmental sensors; fluid flow sensors; position, angle, displacement, distance and speed sensors; acceleration sensors (eg accelerometer, tilt sensor, position sensor, rotary encoder, linear / rotary variable differential transformer, tachometer, etc.); optical sensors; light sensors; image sensors (for example, charge-coupled devices, infrared sensors, LEDs, fiber optic sensors, photodiode sensors, photo transistor sensors, photoelectric sensors, etc.); pressure sensors or gauges; tension meters; torque sensors; energy sensors; piezoelectric sensors; density sensors; level sensors; thermal sensors; temperature sensors (for example, heat flow sensors, thermometers, temperature meters, resistance-based sensors, thermistors, thermocouples, etc.); proximity / presence sensors; etc.
[0050] FIG. 3 is a block diagram of parts of a ground support network (GSN) (116), according to an exemplary embodiment. As illustrated in FIG. 3, the ground support network (116) includes a processor (390), a memory (392) and communication interfaces (393) which are coupled to 1 different and different wired communication links. Although not illustrated, in some embodiments, the ground support network (116) can include multiple servers / processors. Such a server / processor can be used for processing incoming satellite communications, and for generating messages. output to be communicated to the aircraft, via satellite communications.
[0051] The memory (392) can be implemented using any of the memory technologies presented here. The memory (392) stores a plurality of modules (380) of the Aircraft Health and Trend Monitoring (AHTM) Monitoring Program and Aircraft Trend (AHTM), modules that can be loaded and executed in a processor ( 390). Each of the modules (380) of the AHTM program is programmed with instructions executable by computer, for the implementation of a Health and Trend Monitoring Algorithm (HTMA) Monitoring Algorithm. The memory (392) can store several different modules (380) of the AHTM program, which can be used to implement the different and different HTMA algorithms by means of computer executable instructions.
[0052] The memory (392) can also store files of CAS messages (310) received from the aircraft (110), processed data (320) generated from the files of CAS messages after being processed by the processor (390), files of parameters (340) provided from the computer (122), and data files (370) received from the aircraft (110).
[0053] When CAS message files (310) and / or data files (370) are received on the ground support network (116) from the aircraft (110), CAS message files (310) and / or the data files (370) can be loaded into the processor (390) together with a corresponding module (380) of the AHTM program, which corresponds to that particular type of CAS message file (310) and / or data file (370 ). When the processor (390) executes the computer executable code of a module (380) of the AHTM program with respect to the measured data included in said CAS message file (310) and / or in said data file (370), an instantiation of the processor (390) of the AHTM program is implemented in the processor (390) (understood by "instantiation", in terms of programming, the process by which an instance of a variable is created).
[0054] Each parameter file (340) can include one or more relevant parameters that are selected and identified based on the CAS messages file (310). Each of the data files (370) can include measured data corresponding to the relevant parameters specified in the parameter file (340). The relevant parameters included in one of the data files (370), as well as the limits (for example, upper and / or lower limits) for each of the relevant parameters, are configured and can be predefined. As will be explained below, the measured data for each of the relevant parameters included in one of the data files (370) can be associated with the particular subsystem or component of the aircraft (110), and can be used on the ground support network ( 116) of the computer (122) to help analyze the performance or operational characteristics of that particular subsystem or component, and / or to isolate the specific cause (s) of an abnormality. For example, the modules (380) of the AHTM program, and their corresponding HTMA algorithms, can examine the measured data for the relevant parameters (RP) to determine which particular subsystems of the aircraft (or their particular components) are the most likely causes of the abnormality that generated the CAS message. In this way, that particular subsystem (s) (or its components) can be easily identified for further inspection, to determine if it (s) is working correctly or if corrective actions are being taken. must be taken.
[0055] FIG. 4 is a flow chart of a method for requesting and retrieving data (400) from the various subsystems of the aircraft during the flight, according to an exemplary embodiment.
[0056] The block (401) is optional and, therefore, is illustrated in dashed lines. In step (401), in an exemplary non-limiting embodiment, the data received from an aircraft in flight is processed, and the processed data is supplied to a computer interface of a land-based computer. Before step (402), the relevant parameters to be measured can be determined and / or specified on the ground-based computer or on another computer (either automatically or via a human operator). In one embodiment, these additional relevant parameters that will be measured can be determined and / or specified on the ground-based computer or on another computer, based on, or taking into account the processed data.
[0057] In step (402), a parameter request message is transmitted to the aircraft via a satellite communication link. The parameter request message includes a parameter file that specifies relevant additional parameters to be measured and, optionally, specifies the time period (the duration) over which each additional relevant parameter is to be measured.
[0058] In step (403), the aircraft data for each relevant parameter is measured for a certain period of time and recorded in a data file that is transmitted, from the aircraft (110), back to the computer based on land, where it can be directed to a computer (122). Once the data file is received on the computer (122), it can be processed manually or automatically by the software, to determine whether the measured data is within one or more limits, or whether it is tending to deviate from a normal value. . In some embodiments, an abnormal condition is detected when the measured data is determined to be outside one or more limits. Information comprising each of the particular relevant parameters whose measured data has been determined to be outside the particular limit associated with that particular parameter, can then be analyzed to determine which source (s) is causing the data to depart. measured from one or more limits.
[0059] An exemplary embodiment of the method (400) will be described below with reference to FIGs. 5A and 5B. Note that, in the said non-limiting embodiment shown in FIGs. 5A and 5B, steps (505) to (520) are optional and are illustrated to show how the trigger event (or trigger) for determining relevant parameters and generating a parameter file can be configured by receiving a CAS message on the ground support network (116). It should be noted that the trigger event for step (525) is not limited to this specific example, and other ways of carrying out the trigger events for steps (525) to (540) can be predicted. In this regard, note that a wide variety of trigger events could trigger steps (525), (530) and (540) which will be described below, and that the receipt of a CAS message [or data processed from of a CAS message on the computer (122) before step (525)] is just a specific, non-limiting example. A CAS message does not necessarily have to be the triggering event (or trigger) to execute the data request. In some embodiments, a trigger event may not even be necessary. Data can be requested from the aircraft by anyone at any time during the flight, with or without the announcement of a CAS message. For example, an operator at the computer (122) can decide at random about determining the relevant parameters and generating a parameter file for transmission to the aircraft.
[0060] FIG. 5A is a flow chart of a method for requesting and retrieving data from an aircraft from various subsystems of said aircraft during flight, in accordance with an embodiment of the present invention. FIG. 5B is a flow diagram of the method (500) of FIG. 5A, which shows some of the processing and communication steps of the various messages, according to an exemplary embodiment. FIG. 5B will be described in conjunction with FIG. 5A, and the method (500) of FIGs. 5A and 5B will be described with reference to FIG. 1 to 3, to explain how method (500) can be applied in the context of an exemplary non-limiting embodiment.
[0061] As mentioned above, steps (505), (510), (515) and (520) are optional and, therefore, are illustrated in dashed lines. In a particular non-limiting example, it is assumed that before the method (500) starts, the aircraft (110) is in flight, and an aircraft computer (210) of the aircraft (110) is in a state of monitoring, monitoring and waiting to receive a message from the crew alert system (CAS). The CAS message triggers an announcement to the aircraft's flight crew and automatically indicates that a relevant parameter or a relevant variable is outside its limit (s). For example, in some embodiments, certain logical bits indicating faults can be processed logically (for example, through AND / OR logic) in the aircraft's avionics software, to define when a CAS message is announced in the aircraft cabin . These bits, in general, indicate an abnormal condition. A CAS message necessarily indicates that a measured parameter or variable is outside one or more limits (for example, values are above or below expectations), and therefore an abnormal condition has been detected (for example, detects / identifies / observes an abnormality in that subsystem).
[0062] In step (505), the aircraft's on-board computer (210) (113) generates data intended for transmission to the ground support network (116). In one embodiment, this data can be a file of CAS messages. When the CAS message file is generated, the raw data for each of a set of parameters that are associated with that particular CAS message, is measured and recorded in a CAS message file corresponding to that CAS message. Each particular parameter can have a parameter name associated with it, for easy identification. The data for each parameter is raw (or "raw") data. With respect to any CAS message, a data stream can be measured for the parameter (s) during a specific period of time based on the initial trigger event (which caused the CAS message to be generated). The CAS message file is typically a small file that includes some relevant parameters measured over a relatively short period of time.
[0063] After generating the CAS message file, in step (510), the aircraft (110) performs operations to open a first satellite communication link (111) between the aircraft (110) and the satellite (112) and a second satellite communication link (113) between the satellite (112) and a land-based gateway (114). Once configured, the aircraft (110) then transmits the CAS message to the satellite (112) via the satellite communication link (112). The satellite (112) then transmits the CAS file message to the gateway (114) via the other satellite communication link (113). In an exemplary embodiment, the gateway (114) can be a gateway to an "Iridium" satellite. The gateway (114) forwards the CAS message file to the ground support network (116). The gateway (114) can then communicate the CAS message file to a ground-based computer on the ground support network (116). The ground support network (116) is typically implemented on a third party website.
[0064] In some embodiments, CAS messages may have different priorities. In some modalities, only CAS messages with high priority, and their corresponding CAS message files, are immediately sent to the ground support network (116) (that is, immediately after the generation of the CAS message file), through the satellite communication link (111), during the aircraft's flight, before it lands. As used herein, the term "high priority" refers to a CAS message that has a higher priority than other CAS messages. In some embodiments, the system administrator can select which private CAS messages are to be designated as high priority CAS messages. In other words, the list of high priority CAS messages can be configured, for example, by an operator, such as, for example, an operator of the ground support network (116) or another computer (122), by a aircraft manufacturer, or by any other entity. The lowest priority CAS messages, and their corresponding CAS message files, can be transmitted to the ground support network (116) when the aircraft lands, via, for example, a wireless link or a link of cellular communication.
[0065] In step (515), a land-based computer on the ground support network (116) processes the raw data that was transmitted with the aircraft's CAS message file (110) (while it was in flight), to generate the processed data from the CAS message file. For example, the shore support network (116) can receive the raw data, decompress the raw data from one format to another format that is readable and usable, and then process the data for possible use on the computer (122) . As an example of processing that can be performed, the ground support network (116) can determine whether the measured data for the parameters are within one or more limit values. The limits can be, for example: state limits (for example, binary 0 or binary 1); time limits (less than or greater than a certain period of time); data information limits (for example, less than or greater than a given data value); parameter value limits; etc. Note that although data from the CAS message file can be processed on the ground support network (116) [step (515)], in other embodiments, the data from the CAS message file can be processed in other computers, including a computer on board the aircraft, before the transmission of the CAS message file. In this embodiment, the CAS message file can include the processed data, and the shore support network (116) simply relays the processed data to the server (118).
[0066] In step (520), the processed data is communicated to the computer (122), which is coupled to the ground-based computer (117). In one embodiment, the processed data is communicated from the ground-based computer (117) of the ground support network (116) to a server (118), which serves as a portal to the ground support network ( 116). The server (118) then communicates the processed data to the computer (122) for display on a user interface.
[0067] In some modalities, in step (520), the ground support network (116) can process the measured data for the parameters that were included in the CAS message file, to determine / identify / isolate one or more cause ( s) basic of the abnormality or abnormal condition that may have caused the generation of the CAS message. To accomplish this, in one embodiment, each of the parameters can be analyzed to determine which parameters measured values that are outside their corresponding limits (that is, they are not within their expected values). When the data measured for the particular parameter is outside one or more limits (for example, above or below one or more limits), that parameter is recorded together with the indication of the subsystem to which that parameter refers (for example, in an identification file). In addition, in some embodiments, a list of elements can be generated, indicating the elements that need to be inspected for possible corrective actions to resolve the abnormality. For example, in one embodiment, teams can inspect the elements that are included in the inspection file to determine what corrective actions (if any) need to be taken to resolve the abnormality and restore the elements that are the cause (or the cause) of the abnormality (in relation to normal or expected operating conditions), before the abnormality becomes significant. In some embodiments, the information can be displayed on a monitor.
[0068] However, in some cases, the raw data provided in the CAS message file and / or the data processed from the CAS message file, may not be adequate, so it would be desirable to obtain other information that could adequately assess the source or situation that caused the generation of the CAS message. For example, in many cases, the data measured for the CAS message file parameters is not suitable for determining the source [e.g., the subsystem (s) or components of the same (s) that caused it ( aram) the generation of the CAS message]. For this reason, it would be desirable to provide a mechanism that would allow the request for data measurement for other relevant parameters. This can help ground teams determine (more precisely) which elements need to be inspected for potential corrective actions to resolve the abnormality, before that abnormality becomes significant.
[0069] Thus, according to some of the embodiments, when receiving the processed data from the CAS message file on the computer (122), it can be determined or not (either automatically by software or manually by an operator human) whether additional data or information is needed from the aircraft (110) to properly assess the situation that caused the generation of the CAS message. In some embodiments, by analyzing the raw data and / or the data processed from the CAS message file, additional relevant relevant parameters can be determined.
[0070] Thus, in step (525), the relevant additional parameters that must be measured or generated in the aircraft are determined.
[0071] For example, in one embodiment, the relevant additional parameters can be determined either automatically, via software, or manually by a human operator, based on the raw data and / or the data processed from the file. CAS messages. In other words, raw data and / or processed data can be analyzed to determine what additional parametric data is needed from the aircraft (110) to identify one or more sources that are causing an abnormal condition that caused the generation of the CAS message file, and the relevant relevant parameters can then be determined. The analysis for this determination can be done automatically by software that runs on the computer (122), or it can be done by an operator who is displaying the raw data and / or the data processed by the computer (122). In other words, the parameter file will not always be generated each time it is received on the computer (122). On the contrary, the parameter file will only be generated when it is determined (either automatically by computer software or manually by an operator), based on the raw data and / or the processed data, what additional aircraft data or information is necessary to properly assess the cause or origin of the CAS message file. For example, when it is determined that additional data or information is required from the aircraft (110), the relevant parameters corresponding to that additional data or information can be selected or identified (automatically or manually) in step (525).
[0072] In step (530), a parameter request message can be generated, which includes a parameter file that specifies the relevant parameters that must be measured and recorded on the aircraft to provide additional parametric data and, optionally, a duration value for each relevant parameter. Each relevant parameter can influence or affect the data to be measured. Each duration value specifies how long the parametric data for a particular relevant parameter should be measured and recorded.
[0073] In some embodiments, the parameter file can be automatically generated by a computer program (software) that runs on the computer (122). In another embodiment, an operator on the computer (122) manually generates the parameter file, selecting the relevant parameters that are to be included in the parameter file. As will be explained below, the data for each of these relevant parameters will be measured on the aircraft and sent back to land from the aircraft.
[0074] In one embodiment, the parameter request message is a relatively small message, just like a text message. The number of relevant parameters specified in the parameter file can be relatively large. For example, in one embodiment, the parameter file can specify up to 50 (fifty) different relevant parameters whose data must be measured and recorded on the aircraft (110). In addition, the parameter file can also specify how long the data for each of the relevant parameters must be measured on the aircraft.
[0075] In step (540), the parameter request message can be transmitted to the aircraft (110). In one embodiment, the computer (122) communicates the parameter request message to the server (118), which communicates it to a ground-based computer on the ground support network (116); the ground support network (116) then communicates the parameter request message to the gateway (114), which communicates the parameter request message to the satellite (112), via a communication link by satellite (113). The satellite (112) then communicates the parameter request message to the aircraft (110) via another satellite communication link (111).
[0076] According to some embodiments, the parameter request message can be automatically transmitted whenever it is generated. According to other embodiments, the decision as to whether or not to transmit the parameter request message can be made by an operator or team ♦ on the computer (122). When an operator at the computer (122) decides that the parameter request message must be communicated back to the aircraft (110) to obtain additional data, the operator sends, via the computer's computer interface (122), a command to communicate the parameter request message to the server (118).
[0077] In step (550), a computer (210) on board the aircraft (110) receives the parameter request message, extracts the parameter file from the parameter request message and then determines the relevant parameters requested specified in the * parameter file (and optionally, the corresponding duration values during which each of the relevant parameters requested must be measured and recorded).
[0078] In step (560), a computer (210) on board the aircraft (110) generates a data file. In one embodiment, the data file can be generated by measuring parametric data for relevant parameters (which are, for example, received via a data bus from several sensors or other on-board computers), by a corresponding time value and then by recording the measured parametric data in the data file on the on-board computer. In some embodiments, data can be measured over a period of time that is specified in the parameter file for that particular relevant parameter. In one embodiment, the parametric data measured for each of the relevant parameters comprises a data stream for that particular relevant parameter, which is measured by a corresponding particular duration value.
[0079] In one embodiment, the computer (210) on board the aircraft (110) creates or generates the data file by automatically recording the measured data for each of the relevant parameters (specified in the parameter file) in a data file. The measured data can be supplied to the on-board computer, for example, from several sensors or other on-board computers along a bus. In general, the data for each of the relevant parameters can be measured for relatively long periods of time compared to the period of time during which other data is measured, for example, when generating the CAS message files. For example, in one embodiment, the data for each relevant parameter can be recorded for a period of time between 5 (five) and 120 (one hundred and twenty) seconds. The size of the data file can be relatively large compared to the size of the parameter file. For example, in one embodiment, the data file can be between 25 KB and 250 KB in size.
[0080] In step (570), the aircraft (110) transmits the data file to the computer (122). In the form of particular realization shown in FIG. 5B, the aircraft (110) communicates the data file to the satellite (112) via the first satellite communication link (113), the satellite (112) communicates the data file to the gateway (114) via the second satellite communication link (111), and the gateway (114) communicates the data file to the ground support network (116). The ground support network (116) communicates the data file to the server (118) and the server (118) communicates the data file to another computer (122) for display on a computer interface. »
[0081] As soon as the data file is received on the computer (122), in step (580), the data file can be processed manually or automatically by the software. In some embodiments, it can be determined whether the data measured for each relevant parameter is within one or more limits, or is tending to deviate from a normal value. In some embodiments, an abnormal condition is detected when the data measured for a relevant parameter is determined to be outside one or more limits. Information comprising each of the particular relevant parameters that were determined to have their data measured outside the specific limit associated with that particular relevant parameter, can then be analyzed to determine which source (s) is causing the measured data fall outside one or more limits.
[0082] Thus, the method (500) can be used to detect / identify / observe an abnormality in an aircraft subsystem (or its components), and to isolate / identify the basic cause (s) that is causing the abnormality - for example, identifying the source (s) that is causing the abnormal condition.
[0083] The flow chart illustrated in FIG. 5A is a simple example, and has been simplified for the sake of clarity. In some embodiments, additional blocks / tasks / steps can be implemented, even if they have not been 'illustrated for the sake of clarity. Such additional blocks / tasks / steps can occur before or after, in parallel and / or simultaneously with any of the blocks / tasks / steps that have been illustrated in FIG. 5A. Note also that some of the blocks / tasks / steps illustrated in FIG. 5A can be optional, and need not be included in all of the embodiments described here. In some embodiments, although not illustrated, the presence or absence of certain conditions may need to be confirmed before the execution of a block / task / step, or before the completion of a block / task / step. In other words, a block / task / step can include one or more conditions that must be met before proceeding from a block / task / step to the next block / task / step of FIG. 5A. For example, in some cases, a timer, a counter, or a combination of both, can run and needs to be satisfied before proceeding to the next block / task / step in the flowchart. Thus, any block / task / step can be conditioned to other blocks / tasks / steps that were not illustrated in FIG. 5A.
[0084] Note also that there is no implicit order or temporal relationship in the flowcharts illustrated in FIGs. 5A and 5B, unless an order or temporal relation is expressly stated or implied from the context of the language that describes the various blocks / tasks / steps of the flowchart. The order of the blocks / tasks / steps may vary, unless expressly indicated otherwise, implicitly or explicitly, in other parts of the text.
[0085] In addition, in some embodiments, FIG. 5A may include feedback loops or additional feedforward loops, which are not illustrated for the sake of clarity ("feedback loops" by return messages, and "feedforward loops" by pre-fed messages). The absence of a feedback loop or a feedforward loop between two points in the flowchart does not necessarily mean that such feedback or feedforward loops are not present between the two points. Likewise, some feedback or feedforward loops are optional in some embodiments. Although FIG. 5A has been illustrated as including a single iteration, this does not necessarily imply that the flowchart is not performed for a number of iterations, either continuously, or until one or more conditions occur.
[0086] Examples of Relevant Parameters Associated with Some Aircraft Systems and Subsystems
[0087] The systems and methods described above can be designed to acquire the relevant parameters to be used to analyze the various aircraft subsystems (or their components) also described above. Some specific non-limiting examples of relevant parameters will now be described for that context .
[0088] Examples of relevant parameters may include date and time, hydraulic pressures, valve positions, temperatures, quantities, rates, flap positions, altitude, speed, altitude rate, acceleration, position information (latitude and longitude), temperature airflow, total fuel, ice detection, landing gear position, aircraft weight, wheel sensor landing gear weight, status parameters, availability or status (status) of a given communication, main battery and spare battery charge, temperature, voltage, current, main transformer / rectifier unit voltage and spare transformer / rectifier unit voltage, load, frequency, external supply voltage, load, frequency and auxiliary unit voltage 'Power iar (APU), load, frequency and voltage of the transformer / rectifier unit, load, frequency and voltage of the integrated generating unit, load factors, voltage, in APU door dicators, APU door actuators, APU speeds, fuel flow, valve position, voltages, APU door position, turbine gas temperature, vibrations, compressor speed (Nl), turbine speed (N2), valve positions, oil pressures, temperatures, fuel flow, temperature and compression rates, initial movement of the right and left ailerons, initial movement of the compensators of the right and left ailerons, position difference between the right ailerons and left, position difference between the right and left aileron compensators, pilot input in relation to the actual movement of the left and right ailerons, pilot input in relation to the actual movement of the left and right ailerons compensators, rolling angles, movement rudder initial, rudder flap initial movement, position difference between rudder pedal position and actual rudder position, position difference between entry that of the pilot and the actual movement of the rudder flap, difference in position between the pilot's entry in relation to the actual movement of the aileron, difference in position between the pilot's entry in relation to the actual movement of the rudder, incidence angles, rudder pedal, forces, rudder compensator position, servo drum positions, compensator positions, landing gear information parameters, flap positions, time between the moment the flaps move to a position and the moment where the tabs reach that position, position difference between the position of the right flap and the position of the left flap, position of the flap lever, position of the spoiler, position of the speed brake lever, position of the horizontal stabilizer, position of the reverser and the time it takes for the reverser to store and distribute, engine data, fuel flow, reverser positions, flight control surface position, servo-clutch states, pilot forces and copilot servo-drum positions, compensator positions, landing gear position and other information parameters, flight control computer status information, elevator and / or elevator compensator movement, initial movement of the elevator, initial elevator compensator movement, position difference between the pilot input and the actual elevator movement, position difference between the pilot entrance and the actual elevator compensator movement, step angles, temperature difference between the temperature when the anti-freeze system was turned off and the temperature when the anti-freeze system was turned on, engine torque and current (wing) or pressure (hood) depending on the temperature, anti-freeze temperature of the wing, motor currents, ice detection status, hood anti-ice pressures, wing, difference between aerial data collection probes, including the angle of attack for all probes, skid angle for all probes, total static pressure l for all probes, impact pressure, CAS message data on angle of attack (AOA) error comparison, Enhanced Vision System (EVS) sensor temperatures, valid image parameters, information from temperature sensors, elapsed time for the camera and EVS system processor, etc.
[0089] Conclusion
[0090] The methods and systems now innovated provide a mechanism to request an aircraft to measure additional parametric data from the systems on board the aircraft, and to send such measured parametric data to a ground support network and to computers ground-based systems to assist in monitoring the aircraft's health and course trend. The methods and systems described here can be used to request the measurement of relevant parameter data for various components and subsystems of the aircraft in real time, without the intervention of the crew. When communicating the relevant parameter data of the aircraft to the ground systems, a more detailed analysis of the data acquired from the aircraft can be performed, guiding the taking of corrective actions. The methods and systems described here can detect the performance degradation of the various components and subsystems of an aircraft, and can identify the specific source of a potential failure in certain components and subsystems of the aircraft. The methods and systems described here can substantially reduce the time required to identify and diagnose problems and to perform troubleshooting tasks and routine maintenance services. Eventual problems with the aircraft can be identified by ground crews as soon as they occur, facilitating the development and implementation of fast and efficient return services when the aircraft lands. The precise source causing the technical problems on the aircraft can be identified substantially more quickly, and the time spent on performing aircraft maintenance tasks can be significantly reduced. In addition, potential problems in a particular subsystem can be identified before the subsystem actually fails.
[0091] Experts in the field will understand that the various blocks / tasks / logical steps, modules, circuits and steps of algorithms illustrated and described in relation to the embodiments disclosed here, can be implemented as electronic equipment (hardware), software computer (software), or a combination of both. Some embodiments and implementations have been described here in terms of functional and / or logical components and blocks (or modules) and the various processing steps. However, it should be noted that these components and blocks (or modules) can be made by any number of hardware, software and / or firmware components configured to perform specified tasks. To clearly illustrate this possibility of exchanging hardware and software, several components, blocks, modules, circuits and steps have been described here generally in terms of their functionality. This functionality can be implemented as hardware or software, depending on the particular application and design restrictions imposed by the global system. Those skilled in the art will be able to implement the functionality described herein in different ways> for each particular application, but such different embodiments should not be construed as departing from the scope of the present invention. For example, an embodiment of a system or component may employ several components of integrated circuits, for example, memory elements, digital signal processing elements, logic elements, look-up tables, or the like, which can perform a variety of functions under the control of one or more microprocessors or other control devices. In addition, experts in the field will understand that the forms of Achievement described here are merely exemplary, without any restrictive or limiting characteristics.
[0092] The various logic blocks, modules and circuits described in connection with the embodiments disclosed herein can be implemented or executed as being a general purpose processor, a digital signal processor (DSP), an application specific integrated circuit (ASIC ), a field programmable gate arrangement (FPGA), or any other programmable logic device, discrete gate or logic transistor, or hardware components, or any combination of them, to perform the functions described herein. A general purpose processor can be a microprocessor, but alternatively, the processor can be any conventional processor, controller, microcontroller or state machine. A processor can also be implemented as a combination of computing devices, for example, a combination of a digital signal processor (DSP) and a microprocessor, one or more microprocessors together with a digital signal processor (DSP) core, or any other type of configuration. The word "exemplary" is used exclusively here to mean "to serve as an example, an instance or an illustration." Any embodiment described herein as "exemplary" is not necessarily to be interpreted as preferred or advantageous over other embodiments.
[0093] The steps of a process or algorithm described in relation to the embodiments described here can be configured directly in hardware, in a software module executed by a processor, or in a combination of the two. A software module can reside in RAM memory, flash memory, ROM memory, EPROM, EEPROM, registry, hard disk, removable disk, CD-ROM, or any other storage medium known in the art. Any exemplary storage medium is coupled to the processor in such a way that the processor can read the information from said storage medium, and can write information to it. Alternatively, the storage medium can be integrated with the processor. The processor and storage medium can reside in an ASIC.
[0094] In this document, related terms, such as "first" and "second", and the like, can be used only to distinguish an entity or action from another entity or action, without necessarily requiring or implying any real relationship or order between those entities or actions. Numerical ordinal terms, such as "first", "second", "third", etc., simply denote different terms from a plurality of them, and do not imply any order or sequence, unless specifically defined by the language of the claims. The sequence of the text, in any of the claims, does not imply that the steps of the process must be performed in a temporal or logical order according to that sequence, unless specifically defined by the language of the claims. The steps of the process can be exchanged with each other, in any order, without departing from the scope of the invention, provided that such change does not contradict the language of the claim and does not present itself logically meaningless.
[0095] Furthermore, depending on the context, words like "connected" or "coupled", used to describe a relationship between the different elements, do not imply that a direct physical connection must be made between these elements. For example, two elements can be connected to each other physically, electronically, logically, or in any other way, through one or more additional elements.
[0096] Although at least one exemplary embodiment has been presented in the previous detailed description, it should be noted that there are a large number of variations. It should also be understood that the exemplary embodiment, or the exemplary embodiments presented above are examples only, and are not intended to limit the scope of the invention in terms of its application or its configuration in any way. On the contrary, the detailed description presented above will provide those skilled in the art with a roadmap of the most convenient way to carry out the exemplary embodiment, or the exemplary embodiments. It should also be understood that several modifications can be made to the function and arrangement of the elements, without departing from the scope of the invention as defined in the attached claims and their legal equivalents.

权利要求:
Claims (15)
[0001]
1. Method for requesting and retrieving data from an aircraft, during its flight, characterized by the following steps: communication, between an aircraft (110) and a land-based computer (117) through a communication link by satellite (111), a message file from the crew alert system (CAS) comprising raw data, where the message file CAS automatically indicates that the parametric data measured from an aircraft subsystem is outside one or more limits, and that an abnormal condition has been detected; processing the raw data in the CAS message file to generate processed data; determining, based on the processed data, the relevant parameters that must be measured and recorded on the aircraft (110) to provide additional parametric data, each of the relevant parameters corresponding to the additional parametric data that is required from the aircraft to identify one or more sources that are causing the abnormal condition and that caused the generation of the CAS message file; receipt, on an aircraft computer (210, 220) of the aircraft, of a parameter request message, which includes a parameter file (340) that specifies the relevant parameters, extracting the parameter file (340), and determining the parameters relevant parameters from the parameter file; and measurement of parametric data for each relevant parameter in the parameter file, with the measured parametric data for each of the relevant parameters comprising: a data flow for that particular relevant parameter.
[0002]
2. Method, according to claim 1, characterized by the fact that it also comprises the following stage: communication, to an input port (114), of a parameter request message, which includes the parameter file (340) which specifies the relevant parameters to be measured and recorded on the aircraft (110).
[0003]
3. Method according to claim 2, characterized by the fact that the communication step, for an input port (114), of a parameter request message, which includes the parameter file that specifies the relevant parameters that they must be measured and recorded on the aircraft (110), including: the generation of a parameter request message, which includes a parameter file that specifies the relevant parameters to be measured and recorded on the aircraft; communicating the parameter request message to a gateway (114) for transmission to the aircraft via a satellite communication link (111) / (113).
[0004]
4. Method, according to claim 3, characterized by the fact that it also comprises the following steps: opening, on the on-board computer (210, 220), of a communication shortcut that includes a first satellite communication link (111 ) between the aircraft (110) and the satellite (112), and a second satellite communication link (113) between the satellite (112) and the gateway (114); and communication of the aircraft's CAS message file (110) through the first satellite communication link (111) to the satellite (112), while the aircraft (110) is in flight.
[0005]
5. Method, according to claim 4, characterized by the fact that it also comprises the following steps: communication, from the satellite (112), of the CAS message file through the second satellite communication link (113) to the gateway (114), and communication, from the gateway (114), of the CAS message archive to a ground support network (116), which includes the ground-based computer (117).
[0006]
6. Method, according to claim 4, characterized by the fact that it also comprises the following steps: communication of the parameter request message to a server (118); communication of the parameter request message from the server (118) to the ground support network (116); communication of the parameter request message from the ground support network (116) to the entrance door (114); communication of the input parameter request message (114) via the second satellite communication link (113) to the satellite (112); and communication of the parameters request message to the aircraft (110), through the first satellite communication link (111).
[0007]
7. Method, according to claim 1, characterized by the fact that it also comprises the following steps: recording of the parametric data measured in a data file; and communication of the aircraft data file (110) to the satellite (112) for delivery to the land-based computer (117).
[0008]
8. Method, according to claim 7, characterized by the fact that the transmission of the data file from the aircraft (110) to the satellite (112) for delivery to the ground-based computer (117), comprises: the communication of the file data from the aircraft (110) to the satellite (112) via the first satellite communication link (111); and further comprising: communication of the satellite data file (112) via the second satellite communication link (113) to the gateway (114); communicating the data file from the gateway (114) to the ground support network (116); communicating the ground support network data file (116) to a server (118); and communicating the data file from the server (118) to another computer (122) for display on a computer interface.
[0009]
9. Method according to claim 1, characterized by the fact that the determination step comprises: the determination, based on the processed data, of the relevant parameters that must be measured and recorded on the aircraft (110) to provide additional parametric data , and a duration value for each relevant parameter, with each of the relevant parameters corresponding to the additional aircraft parametric data that is required by the aircraft to identify one or more sources that are causing the abnormal condition and that caused the file to be generated CAS messages, while each duration value specifies how long the parametric data of a particular relevant parameter should be measured and recorded; where the receiving step comprises: receiving, on an on-board computer (210, 220) of the aircraft (110), a parameter request message that includes a parameter file that specifies the relevant parameters, extracting the parameters, and determining the relevant parameters and the corresponding duration values for each of the relevant parameters from the parameter file; and where the measurement step comprises: the measurement of the parametric data for each relevant parameter in the parameter file for a corresponding duration value, and the measured parametric data for each of the relevant parameters comprises: a data flow for that parameter particular relevant, which is measured to a corresponding corresponding duration value.
[0010]
10. System (100) for requesting and retrieving data from an aircraft, during its flight, characterized by: an entrance door (114); an aircraft (110) comprising a transceiver, a plurality of subsystems (230) and an on-board computer (210, 220) configured to generate a message file from the crew alert system (CAS) comprising raw data, the CAS message file automatically indicates that the parametric data measured from an aircraft subsystem (110) is outside one or more limits, and that an abnormal condition has been detected; a satellite (112) that is communicatively coupled to the aircraft (110) and to the gateway (114) via satellite communication links (111, 113); a ground support network (116) comprising a land-based computer (117) configured to process the raw data in the CAS message file, to generate processed data; and a computer, coupled to the ground-based computer (117), configured to: determine, based on the processed data, the relevant parameters that must be measured and recorded on the aircraft to provide additional parametric data, and a duration value for each parameter relevant, each of the relevant parameters corresponding to the additional parametric data that is required from the aircraft (110) to identify one or more sources that are causing the abnormal condition and that caused the generation of the CAS message file, while each value of duration specifies how long the parametric data for that particular relevant parameter is to be measured and recorded; and generate a parameter request message that includes a parameter file that specifies the relevant parameters to be measured and recorded on the aircraft; and communicating the parameter request message to the gateway (114) for transmission to the aircraft (110) via the satellite communication links (111, 113); the on-board computer (210, 220) is further configured to: after receiving the parameter request message, extract the parameter file from the parameter request message; determine the relevant parameters and the corresponding duration values for each of the relevant parameters from the parameter file; measure the parametric data for each relevant parameter in the parameter file for a corresponding duration value, the measured parametric data for each of the relevant parameters comprising: a data flow for that particular relevant parameter, which is measured to a value of particular corresponding duration; and record the parametric data measured in a data file; and the transceiver is further configured to transmit the data file to the satellite (112) for delivery to the other computer.
[0011]
11. The system according to claim 10, characterized by the fact that the on-board computer is configured to open a communication shortcut, which includes a first satellite communication link between the aircraft and the satellite, and a second satellite communication between the satellite and a land-based gateway, and to communicate the aircraft's message file (CAS) via the first satellite communication link to the satellite while the aircraft is in flight.
[0012]
12. System (100) according to claim 11, characterized by the fact that the satellite (112) is configured to communicate the CAS message file via the second satellite communication link (113) to the gateway ( 114), and the gateway (114) is configured to communicate the CAS message file to a ground support network (116) that includes the ground-based computer (117).
[0013]
13. System (100), according to claim 11, characterized by the fact that the parameter request message is communicated to the aircraft (110) through satellite communication links (111, 113), through the communication of the message parameter request from server (118), communication of parameter request message from server (118) to ground support network (116), communication of parameter request message from ground support network (116) 116) for the gateway (114), the communication of the parameter request message from the gateway (114) through the second satellite communication link (113) to the satellite (112); and communicating the parameter request message to the aircraft (110) via the first satellite communication link (111).
[0014]
14. System (100), according to claim 11, characterized by the fact that the transceiver is still configured to communicate the data file via the first satellite communication link (111) to the satellite (112), in which the satellite (112) is configured to communicate the data file via the second satellite communication link (113) to the input port (114), where the input port (114) is configured to communicate the data file for the ground support network (116), where the ground support network (116) is configured to communicate the data file to a server (118), and where the server (118) is configured to communicate the data file to the other computer for display on a computer interface.
[0015]
15.Computer (122) used in the method and system for requesting and retrieving data from an aircraft, during its flight, characterized by comprising: a processor that is configured to perform the processing of the following steps: determine, in response to processed data generated based on raw data from a message file from the crew alert system (CAS) transmitted from an aircraft (110) during the flight, the relevant parameters that must be measured and recorded on the aircraft (110) to provide additional parametric data that is required from the aircraft to identify one or more sources that are causing an abnormal condition, and a duration value for each relevant parameter, each of the relevant parameters corresponding to the additional parametric data that is required from the aircraft to identify one or more sources that are causing the abnormal condition and that caused the generation of the CAS message file, in whereas each duration value specifies how long the parametric data for a particular relevant parameter should be measured and recorded; and generate a parameter request message comprising a parameter file that specifies the relevant parameters that must be measured on an aircraft and recorded in a data file, as well as the duration value for each relevant parameter, and communicate the request message parameters for transmission to the aircraft (110) through satellite communication links (111, 113), in which the relevant parameters are preferably determined and selected based on the analysis of the processed data, and each of the relevant parameters influences or affects the data that must be measured by the aircraft.

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同族专利:

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公开号 | 公开日

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CA2863079A1|2013-08-08|

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BR112014018976A2|2017-09-26|

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EP2810156A4|2015-11-04|

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US8798817B2|2014-08-05|

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WO2013116447A1|2013-08-08|

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US20130197725A1|2013-08-01|

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US9725186B2|2017-08-08|

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US20140309820A1|2014-10-16|

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CN104508624A|2015-04-08|

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EP2810156A1|2014-12-10|

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CN104508624B|2017-06-30|

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CA2863079C|2020-01-14|

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EP2810156B1|2017-09-27|

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2020-09-24| B09A| Decision: intention to grant|

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2020-12-15| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 31/01/2013, OBSERVADAS AS CONDICOES LEGAIS. |

优先权:

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申请号 | 申请日 | 专利标题

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US13/362,931|2012-01-31|

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