KR20160076230A - Computing apparatus and method for processing flight critical information - Google Patents

Abstract

Disclosed is a computing apparatus for processing flight information. The computing apparatus for processing flight information comprises: a mandatory flight input/output module to receive and convert mandatory flight information sensed by at least one first sensor which senses the mandatory flight information; a graphic processor module to process a display of the mandatory flight information from the mandatory flight input/output module; and a display unit to display the mandatory flight information. The mandatory flight input/output module exists separately from an optional flight input/output module for inputting and outputting optional flight information, excludes other modules from processing for security of the mandatory flight information, and directly transmits the mandatory flight information to the graphic processor module.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a computing device and a method for processing essential information for flight,

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a data processing method in a mission computer, and more particularly, to a data processing method for increasing flight safety of an aviation electronic part.

The aircraft receives flight information from various sensors or other equipment during flight and is piloted by the pilot. Flight-related information is typically handled by the aircraft's mission computer, which may add to the processing load on the mission computer when it is processed and displayed to the pilot in the mission computer.

1 is a block diagram for explaining a process of processing conventional flight information.

Referring to FIG. 1, flight related information is sensed by a sensor 110, and information sensed by a sensor 110 may be input / output to an input / output module 120 (IOM (Input Output Module)). The IOM can include electronic boards. The IOM 120 performs all signal processing alone. That is, it processes ARINC-429 and discrete / analog signals. The IOM plays a role of data synchronization and data format matching in order to enable seamless information exchange between the CPU and the sensor 110. Here, the various sensors 110 used in the aircraft may include Global Positioning System (GPS), Inertial Navigation System (INS), Forward Looking Infra-Red (FLIR), and the like.

The IOM 120 receives the money flow related information through a system processor module 130 (SPM) and a graphic processor module 140 (GPM (Graphic Processor Module) Display System).

In this case, the system processor module 130 (SPM) processes the operations required for flight and converts the data received from the sensor 110 to be easily used by a software developer. The graphics processor module 140 (GPM) is a processor module that takes charge of graphics to be displayed in the MFDS 150. The OFP in the graphics processor module 140 is an operational flight program, which means software (including an operating system) mounted on actual hardware. Traditionally, one software module resides in the GPM 140.

Accordingly, since all the flight related information (including the flight essential information and the non-flight essential information) has to be displayed as one process in the MFDS 150 via the IOM 120, the SPM 130, and the GPM 140, It has to be processed, the flight essential information that requires more secure processing is missing, or security processing can not be performed. In other words, when multiplexing and separation design of flight essential information is not used, failure to provide MEP (Mission Equipment Package) functions could not provide the flight essential information related to the engine and the aircraft system, and serious situation occurred, And the flight crew can not be guaranteed safe flight. In other words, since centralized integration and control are centered on the mission computer, there is a problem that the reliability of the MEP system is degraded and the survivability and flight safety are hindered.

SUMMARY OF THE INVENTION It is an object of the present invention to solve the above-described problems and to provide a safety scheme and an automatic flight control system, And to provide a computing device and method for flight essential information processing for improving flight information.

According to another aspect of the present invention, there is provided a computing device for processing flight information, comprising: a flight essential input / output module for receiving and converting the flight essential information sensed by at least one first sensor that senses flight essential information; Output module, and a display unit for displaying the flight essential information, wherein the flight essential input / output module includes a non-flight essential input / output module for inputting and outputting non-essential flight information, And may transmit the flight essential information to the graphic processor module immediately after eliminating processing in another module for securing the flight essential information.

The essential flight input / output module may perform data synchronization and data format matching of the flight essential input / output module to enable information processing in the graphic processor module.

The graphics processor module may execute a plurality of flight operating software for separately processing the flight essential information and the flight non-essential information.

The flight essential information may include AFCS (Automatic Flight Control System) information, AHRS (Attitude and Heading Reference Sensors) information, engine related information, and fuel related information.

The flight essential information may be transmitted to the flight essential input / output module through an ARINC (Aeronautical Radio Incorporated) interface.

A plurality of the computing devices receiving sensing data from different first and second sensors providing the same result compare the sensing data with each other and determine to display through the display if they are the same, And to display the data obtained from the third sensor providing the same result to the instrument.

According to another aspect of the present invention, there is provided a method for processing a flight information in a computing device, comprising: receiving a flight essential information sensed by at least one first sensor that senses flight essential information, Output module, and the display unit displays the flight essential information, wherein the flight essential input / output module is configured to receive the flight non-essential information from the flight essential input / output module Output module and can transmit the flight essential information to the graphic processor module immediately after eliminating processing in another module for securing the flight essential information.

The essential flight input / output module may perform data synchronization and data format matching of the flight essential input / output module to enable information processing in the graphic processor module.

The graphics processor module may execute a plurality of flight operating software for separately processing the flight essential information and the flight non-essential information.

The flight essential information may include AFCS (Automatic Flight Control System) information, AHRS (Attitude and Heading Reference Sensors) information, engine related information, and fuel related information.

(AFCS, FADEC, VOR / ILS, R-ALT) flight essential information processing through the application of the secured scheme of the mission computer according to the computing device and method for the flight essential information processing of the present invention. The stability and the reliability of the apparatus can be improved.

1 is a block diagram illustrating a process for processing conventional flight information,
2 is a block diagram schematically illustrating a computing device for flight essential information processing according to an embodiment of the present invention;
FIG. 3 is a detailed block diagram of a computing device for flight essential information processing according to an exemplary embodiment of the present invention; FIG.
4 is a diagram showing an actual structure of a mission computer,
5 is a block diagram for explaining a computing device for flight essential information processing according to another embodiment of the present invention;
6 is a block diagram illustrating cross-checking logic of a plurality of mission computer software.

While the invention is susceptible to various modifications and alternative forms, specific embodiments thereof are shown by way of example in the drawings and will herein be described in detail.

It should be understood, however, that the invention is not intended to be limited to the particular embodiments, but includes all modifications, equivalents, and alternatives falling within the spirit and scope of the invention.

The terms first, second, etc. may be used to describe various components, but the components should not be limited by the terms. The terms are used only for the purpose of distinguishing one component from another. For example, without departing from the scope of the present invention, the first component may be referred to as a second component, and similarly, the second component may also be referred to as a first component. And / or < / RTI > includes any combination of a plurality of related listed items or any of a plurality of related listed items.

It is to be understood that when an element is referred to as being "connected" or "connected" to another element, it may be directly connected or connected to the other element, . On the other hand, when an element is referred to as being "directly connected" or "directly connected" to another element, it should be understood that there are no other elements in between.

The terminology used in this application is used only to describe a specific embodiment and is not intended to limit the invention. The singular expressions include plural expressions unless the context clearly dictates otherwise. In the present application, the terms "comprises" or "having" and the like are used to specify that there is a feature, a number, a step, an operation, an element, a component or a combination thereof described in the specification, But do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, or combinations thereof.

Unless defined otherwise, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. Terms such as those defined in commonly used dictionaries should be interpreted as having a meaning consistent with the meaning in the context of the relevant art and are to be interpreted in an ideal or overly formal sense unless explicitly defined in the present application Do not.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In order to facilitate the understanding of the present invention, the same reference numerals are used for the same constituent elements in the drawings and redundant explanations for the same constituent elements are omitted.

2 is a block diagram schematically illustrating a computing device for flight essential information processing according to an embodiment of the present invention. 2, a computing device according to an embodiment of the present invention includes an IOM 220, a Secured IOM 225, a SPM 230, a GPM 240, and an MFDS (250).

Referring to FIG. 2, the aircraft includes various kinds of sensors 210 and 215, and the information sensed through the sensors 210 and 215 is classified into flight essential information and non-flight essential information through a standard communication interface, And transferred to the IOM 220 and Secured IOM 225 of the computer.

Here, the essential information sensor 215 is a sensor for sensing flight essential information, and the non-essential information sensor 210 is a sensor for sensing non-essential information other than flight essential information. It is possible to set whether or not the flight is essential information by the user, and to set it so as to be changeable.

Flight essential information is information that must be recognized, controlled, executed, or maintained essential for flight control and maintenance of an aircraft, and may be used to identify aircraft that cause fatal damage to aircraft or crew, And may refer to flight and flight related information.

The flight essential information can be largely divided into AFCS (Automatic Flight Control System) information, vehicle information, and engine information.

The AFCS information includes Airspeed information, Vertical Speed information, Attitude (Pitch, Roll) information, Altitude (Baro, STD) information, Radar Altitude information, Heading (Magnetic, True) information, AFCS Preset Values information, AFCS Mode & Navigation Data (VOR / ILS, RALT) information may be included.

Vehicle information includes Engine Oil Temp information, Engine Oil Pressure information, MGB Temp & Pressure information, Hydraulic Pressure information, Fuel Pressure information, Transmission Cautions information, Hydraulic Cautions information, ADC Parameters information, Fuel Flow & Fuel Temp. Information, NR Value information, and Failure Messages information.

Engine information includes Engine N1, N2 information, Engine TOT information, TRQ 1, TRQ 2, TRQ 1 + 2 information, OAT information, Engine Auxiliary Data information, System Message information, OEI Selected Power Level information, and Engine Caution information (IDLE, GOV, FADEC, CHIP, BLEED, etc.).

The IOM 220 and the SPM 230 perform the same processing as described in FIG. 1 with respect to the flight non-essential information.

However, the Secured IOM 225 is an input / output module for separating only the flight essential information from the non-flight essential information from the essential information sensor 215. Secured IOM 225 is installed separately from IOM 220 for inputting / outputting non-essential information, and can support AHRS, ADC, and APM functions through an ARINC communication interface. Secured IOM 225 may also perform data synchronization and data format matching functions to enable information exchange between the CPU and the sensor sany. The flight essential information that has passed through Secured IOM 225 may be transmitted through SPM 230 And is provided to the OFP 2 244 of the GPM 240.

The GPM 240 may include a plurality of OFPs 242, 244. The OFP 1 242 is an operating program for receiving and processing the non-flight essential information from the SPM 230. The OFP 2 244 is an operating program for receiving and processing the flight essential information directly from the Secured IOM 225, to be. That is, the GPM 240 may include a plurality of OFPs 242 and 244 through a software structure change, thereby increasing the stability.

The OFP 2 244 may consider coming via the SPM 230, but it operates a separate data processing OFP in the relatively less loaded GPM 240 considering the processing power of the limited SPM 230. The contents of flight essential information (including AFCS, vehicle, and engine information), which are essential information for the flight of the pilot, are input to the mission computer via the ARINC method, which is a more reliable communication method, And then the GPM 240 processes it immediately. This is called the patially secured method. This is different from a fully secured approach where flight essential information is 100% separate and can be more efficient. In the fully secured method, the flight essential information also has to be processed through the separate SPM and the OFP included in the separately provided GPM, which may be inefficient because additional SPM and GPM are required.

The MFDS 250 displays the flight essential information and non-flight essential information processed to be displayed via the OFP 1 242 and the OFP 2 244.

3 is a detailed block diagram of a computing device for flight essential information processing according to an embodiment of the present invention. 3, the computing device for flight essential information processing according to an exemplary embodiment of the present invention includes an input / output module 302 (IOM), a flight required input / output module 304 (FIOM), a power supply module (PSM) VME 64 backplane motherboard 310, system processor module 320, graphics processor module 330, electronic map processor module 340, and video input and output module 350.

Referring to FIG. 3, the aviation electronic part of the aircraft processes information received from various sensors used in the aircraft and displays it on a screen MFDS that the pilot finally sees. For example, the pilot displays four information on the front four screens .

In order to process and display information, a total of two mission computers may be installed on the aircraft. It is the responsibility of the grappling process to process the information of the sensor and process it on the pilot's screen. However, it is possible to fly with only one unit, but two mission computers can be operated at the same time have.

The input / output module 302 can receive the non-flight essential information from a sensor (not shown) and transmit it to the system processor module 320 via the bus of the motherboard 310.

The flight essential input / output module 304 receives the flight essential information and transmits it to the graphic processor module 330 via the bus of the motherboard 310.

The power supply module 306 supplies power to each module.

The system processor module 320 includes a 1553 PMC and a graphical PMC (2 channels) and is capable of processing non-essential information received from the input / output module 302 via the graphical PMC.

The graphics processor module 330 may include two graphics PMCs (two channels) and may include graphics for each of the flight essential information received from the flight essential information input / output module 304 and the non-flight essential information from the system processor module 320 Processing can be performed.

The electronic map processor module 340 may include a graphic PMC (2 channels) and a large capacity memory (2 channels), and may process electronic map related information (GPS / INS related information).

The video input / output module 350 performs an input / output interface function of video data.

4 is a diagram showing an actual structure of a mission computer.

Referring to FIG. 4, a VME 64 backplane motherboard may be provided in a case including a plurality of VME slots on the outermost periphery.

One can have PSM, SPM, digital multimeter (DMM) and GPM for power supply on the VME 64 backplane motherboard. IOM, FIOM, and VIOM can also be provided as input / output modules.

5 is a block diagram illustrating a computing device for flight essential information processing according to another embodiment of the present invention.

Referring to FIG. 5, the flight non-essential information may be graphically generated along a line indicated by a solid line and displayed in an MFDS (not shown).

The flight essential information can be displayed on the MFDS along a line marked with a dotted line.

According to another embodiment of the present invention, the secured essential information is received through the ARINC 429 interface or the like in the Secured IOM 520, and the Secured IOM 520 converts the essential information into the VME essential information memory space of the GPM 530 , The corresponding information is stored in the memory space. The stored information is graphically processed and graphically generated by the OFP that processes the flight essential information.

However, the information inputted to the SPM 510 through the MIL-STD-1553 interface is further processed by the middleware 515 of the SPM 510 to determine whether it is the flight essential information or the non-flight essential information. If it is determined to be the flight essential information, the middleware 515 provides the essential information memory space of the GPM 530, the information is stored in the essential information memory space, and graphics processing is performed in the OFP for essential information processing do. The information is provided to the VME non-essential information memory space of the GPM 530 through the OFP for non-essential information processing of the SPM 510. [ Then, it can be graphically generated through OFP for non-essential information processing.

That is, since 100% complete separation processing may be difficult from the inputting of the sensing information, the SPM 510 can perform processing for filtering the flight essential information once more.

In addition, the higher priority information (for example, AFCS information) of the flight essential information is solved by partially secured through the Secured IOM 520, and lower priority information (for example, engine, fuel and aircraft system Information) can be solved by applying an independent dedicated instrument.

Therefore, the MFD PFD (Multifunctional Display Primary Flight Display) can be considered as the essential CSCI separation and AFCS system display information (Primary Display). The AFCS system information may include AFCS Status, Airspeed, Attitude (Pitch, Roll), Altitude, Heading, DA / DH, Course, and Baro Correction information.

6 is a block diagram illustrating cross-checking logic of a plurality of mission computer software.

Referring to FIG. 6, a plurality of mission computers 610 and 620 include two OFPs together with AHRS (Attitude and Heading Reference Sensors) 602 and 604, i.e., flight essential information Respectively. At this time, a sensor (not shown) having the same role as the sensor for sensing such information can be installed on a total of three aircraft. The mission computers 610 and 620 at the time of flight compare the information of the sensors 1 and 2 with each other through the Ethernet, and the mission computers 610 and 620 receive and compare the information of the sensors 1 and 2 . At this time, the comparison result can be determined to display immediately if there is no problem, and if different, information obtained from the sensor 3 can be displayed on a separate instrument called ISI (Integrated Stand-alone Instrument). At this time, a warning message may be displayed in the MFDS.

It will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the spirit or scope of the inventions as defined by the following claims It will be understood that various modifications and changes may be made thereto without departing from the spirit and scope of the invention.

Claims (10)

A computing device for processing flight information,
A flight essential input / output module for receiving and converting the flight essential information sensed through at least one first sensor sensing flight essential information;
A graphic processor module for processing the display of the flight essential information from the flight essential input / output module; And
And a display unit for displaying the flight essential information,
The essential flight input / output module exists separately from the non-flight essential input / output module for inputting and outputting the flight non-essential information. In order to secure the flight essential information, the required flight information is directly transmitted to the graphic processor module And transmits the generated information to the computing device. The method according to claim 1,
Wherein the flight essential input / output module performs data synchronization and data format matching of the flight essential input / output module to enable information processing in the graphic processor module. The method according to claim 1,
Wherein the graphics processor module executes a plurality of flight management software for separately processing the flight essential information and the flight non-essential information. The method according to claim 1,
Wherein the flight essential information includes AFCS (Automatic Flight Control System) information, Attitude and Heading Reference Sensors (AHRS) information, engine related information, and fuel related information. The method according to claim 1,
Wherein the flight essential information is transmitted to the flight essential input / output module through an ARINC (Aeronautical Radio Incorporated) interface. The method according to claim 1,
A plurality of the computing devices receiving sensing data from different first and second sensors providing the same result compare the sensing data with each other and determine to display through the display if they are the same, And to display data obtained from a third sensor that provides the same result to the instrument. A method of processing flight information in a computing device,
Receiving and converting the flight essential information sensed by at least one first sensor that senses flight essential information by the flight essential input / output module;
Processing the display of the flight essential information from the flight essential input / output module; And
Wherein the display unit displays the flight essential information,
The essential flight input / output module exists separately from the non-flight essential input / output module for inputting and outputting the flight non-essential information, And transmitting the information to the computing device. 8. The method of claim 7,
Wherein the flight essential input / output module performs data synchronization and data format matching of the flight essential input / output module to enable information processing in the graphic processor module. 8. The method of claim 7,
Wherein the graphics processor module executes a plurality of flight management software for separately processing the flight essential information and the flight non-essential information. 8. The method of claim 7,
Wherein the flight essential information includes AFCS (Automatic Flight Control System) information, Attitude and Heading Reference Sensors (AHRS) information, engine related information, and fuel related information.

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