Data processing system and method for the integration of a simulation module and an on-board module

Abstract

A data processing system (10) comprises: an on-board module (E-1,.„, E-n) configured to be boarded on a vehicle and to operate on board the vehicle; a simulation module (S-1,..., S- n) configured to simulate the behavior of a component of the vehicle; and an integration unit (16) configured to enable communication between the on-board module and the simulation module. The simulation module is configured to process signals (SS-1, SS-n) having a first format and the on-board module is configured to process signals (SH-1, SH-n) having a second format different from the first format. The integration unit is configured to: receive a first signal processed by the simulation module and having the first format; convert the first format into the second format, generating in response a second signal having the second format; and provide the second signal to the on-board module; and / or receive a third signal processed by the on-board module and having the second format; convert the second format into the first format, generating in response a fourth signal having the first format; and provide the fourth signal to the simulation module.

Description

[0001] "DATA PROCESSING SYSTEM AND METHOD FOR THE INTEGRATION OF A

[0002] SIMULATION MODULE AND AN ON-BOARD MODULE"

[0003] Cross Reference to Related Patent Applications

[0004] This patent appl ication claims the priorities of the Italian patent application no . 102023000022980 filed on October 31 , 2023 , the entire disclosure of which is incorporated herein by reference .

[0005] Technical Field

[0006] The present invention refers to a data processing system and a method for the integration of a simulation (processing) module and an on-board (processing) module . In particular, the invention finds preferred application in the case of a flight training data processing system for pilots .

[0007] Background of the Invention

[0008] In the avionic / aeronautic field, training systems , for example flight training, are increasingly widespread which attempt to simulate the experience of piloting an aircraft as close to reality as possible .

[0009] Data processing systems that simulate the behavior of an aircraft and / or of a component of a vehicle in order to determine their respective des ign and / or the respective maintenance plan are also widespread .

[0010] These data processing systems provide for the mixed use of processing devices of both physical and simulated type .

[0011] Physical devices are hardware units installed or installable on the aircraft ( e . g . , an aircraft radar, the avionics of an aircraft , etc . ) while the simulated devices are computers provided with software that simulates the operation of a respective real device by means of , for example , di f ferential equations or neural networks .

[0012] The physical devices execute on-board software , which is written for the speci fic hardware equipment of the aircraft .

[0013] The simulated devices execute simulated software , which is written for a synthetic system not boarded on the aircraft .

[0014] In other words , the simulation software is a software model configured to be executed on a standard type processor, for example a consumer type such as a laptop or a server . Consequently, the simulation software is written according to the operating logics of the simulation processor .

[0015] Usually, standard type simulation processors operate via logical signals and are conf igured to provide signals according to a standard type format ( shared memory or tcp / ip channels ) .

[0016] On the other hand, on-board software is software written to be executed on a speci fic on-board processor, for example a navigation processor or a processor that controls a speci fic aircraft equipment . In the aeronautical field, onboard processors operate according to particular logics , which are not typical of the consumer world .

[0017] For example , the on-board processors communicate via avionics-type data buses (military or civilian) , which are di f ferent from the buses used in the simulated processing devices .

[0018] Furthermore , the on-board processors may operate via discrete signals mutually coupled via speci fic communication protocols .

[0019] For example , the on-board processors may be configured such that they do not transmit numbers in floating point coding, but as an integer . For example , this allows to increase the robustness of the hardware architectures configured to be boarded and used on board an aircraft during flight of the aircraft , to reduce the risk of corruption of the transmitted signals and to reduce the space necessary for data transmission .

[0020] As a result , simulation software cannot be used directly in on-board hardware equipment , and conversely, on-board software cannot be used directly in a simulation device .

[0021] One approach to overcome this problem is to speci fically modi fy the on-board software so that it can be used in a simulation environment / processor .

[0022] A di f ferent approach involves designing a dedicated simulation software that can be used in a simulation processor and at the same time ref lects the operation of the on-board software .

[0023] However, such approaches require high design time and costs .

[0024] EP 3 599 599 Al describes methods and systems for training how to become familiar with flight management system ( FMS ) . The system comprises a user application programming interface (API ) that receives a request for a training scenario from a user . A flight management engine ( FME ) generates the training scenario that simulates the flight mission of an FMS on-board a designated aircraft . The training scenario is generated using the same algorithms as the EMS . A database configuration module retrieves the data related to performance and conditions that are provided to the EME for training scenario generation . An external API retrieves external third-party data that are provided to the EME for use in generating the training scenario .

[0025] In practice , EP 3 599 599 Al provides for the integration of a training system by ground personnel wherein the training is provided through on-vehicle apparatuses or an always-connected simulation thereof . Accordingly, EP 3 599 599 Al provides for adding training functions to an in- vehicle software , i . e . modi fying vehicle software and hardware to allow ground training .

[0026] However, the system and method of EP 3 599 599 Al have a low versatility .

[0027] US 2011 / 250569 Al and EP 2 755 137 Al describe further examples of data processing methods and systems usable in avionic field . However, the aforementioned disadvantages are not overcome .

[0028] Aim of the present invention is to overcome the disadvantages of the prior art .

[0029] The aim of the present invention is to allow an automatic and bidirectional integration between an on-board software and a simulation software , whether the simulated software is connected to the actual aircraft hardware ( containing the on-board software ) or whether the on-board software is converted to run on a computer system where the simulated software also runs ( therefore without actual aircraft hardware involved) . Summary

[0030] According to the present invention there is therefore provided a data processing system, a method and a computer program, as defined in the appended claims which form an integral part of the present description .

[0031] Brief Description of the Drawings

[0032] To better understand the present invention preferred embodiments thereof will be now described, for merely exemplary and non-limiting purposes , with reference to the appended drawings , wherein :

[0033] Figure 1 shows a block diagram of a system according to the present invention; and

[0034] Figure 2 shows a flow chart of a method according to the present invention .

[0035] Description of Embodiments

[0036] Figure 1 shows a data processing system 10 , usable in the aeronautical field, comprising one or more simulation modules 12 , one or more on-board modules 14 , and an integration unit 16 configured to couple together the simulation modules 12 and the on-board modules .

[0037] According to a preferred embodiment , the system 10 is a flight training system for pilots . However, the system 10 may be a data processing system 10 usable in the aeronautical field and of di f ferent type , for example a generic synthetic simulation system .

[0038] With reference to the embodiment described herein, the simulation modules 12 are software models , also referred to as simulated devices , of components of an aircraft ; and the on-board modules 14 are hardware equipment , also referred to as physical devices, configured to be used on board the aircraft .

[0039] In detail, the system 10 comprises a plurality of physical devices 12 or hardware equipment E-l,...,E-n, and a plurality of simulated devices 14 or software models S-1,...,S- n .

[0040] The integration unit 16 is configured to allow communication between the hardware equipment E-l,..., E-n and the software models S-l,...,S-n.

[0041] The software models S-l,...,S-n are software that simulate the behavior of a component of an aircraft, such as for example an aircraft sensor, a weapon system or an onboard computer.

[0042] The software models S-l,..., S-n are software modules configured to be loaded and executed on data processing architectures, i.e. processors / computers , for simulation, for example standard or consumer type processors such as for example laptops, servers, cloud or distributed processing environments. In other words, the software models S-l,..., S-n are configured to process signals having a format that is not compatible with on-board hardware architectures; in practice, signals that do not comply with the requirements of the avionic field.

[0043] For example, the format of such signals may comprise one or more of the following specific signal features: type of data packing, type of endianess, type of transmission protocol, scaling of the data indicated by the signal, unit of measurement of the data indicated by the signal.

[0044] In the following, a generic software model of the plurality of software models S-l S-n is identified with the reference S-x.

[0045] For example, a software model S-x may be the model of a sensor (e.g., an infrared sensor, radar, etc.) of the aircraft. Or, for example, a software model S-x may be the model of an aircraft on-board computer; for example, a navigation computer or a computer that controls a specific component of the aircraft.

[0046] Each software model S-x is configured to generate a respective signal SS-x. According to one embodiment, the signal SS-x provided by the software model SS-x is of a logical type.

[0047] The hardware equipment E-l,...,E-n is physical devices that can be used on board an aircraft, in particular during flight of the aircraft. For example, the hardware equipment E-l,..., E-n may comprise navigation computers, control computers of a specific aircraft component, or elements of sensor systems.

[0048] The hardware equipment E-l,..., E-n is therefore configured to store and execute on-board software compatible with the on-board hardware architectures; in practice, which comply with the signal transmission requirements used in the avionics field.

[0049] In other words, the hardware equipment E-l,..., E-n is configured to operate according to operating logics other than the operating logics of the simulation processors for which the simulation software models have been designed / written .

[0050] In other words, the hardware equipment E-l,..., E-n is configured to process signals having a respective type of format different from that of the signals processed by the software models S-l,...,S-n.

[0051] For example, the format of such signals may comprise one or more of the following specific signal features: type of data packing, type of endianess, type of transmission protocol, scaling of the data indicated by the signal, unit of measurement of the data indicated by the signal.

[0052] In the following, a generic hardware equipment of the plurality of hardware equipment E-l,..., E-n is identified with the reference E-x.

[0053] Each hardware equipment E-x is configured to each generate one or more signals SH-x according to a respective protocol P-x, e.g. STANAG-3838 or ARINC-429.

[0054] Each hardware equipment E-x comprises a respective hardware interface I-x through which the hardware equipment E-x communicates the signal SH-X.

[0055] For example, the hardware interfaces I-x may be STANAG- 3838 or ARINC-429.

[0056] The interfaces i-l,...,I-n allow hardware equipment E- 1,..., E-n to exchange data packets with each other and thus communicate with each other.

[0057] The hardware equipment E-l,..., E-n can have interfaces i-l,...,I-n different from each other and operate according to protocols P-l,...,P-n different from each other.

[0058] In other words, considering two hardware equipment E- x, E-y of the plurality of hardware equipment E-l,..., E-n different from each other, the protocol P-x used may be different from the protocol P-y. The interface I-x of the hardware equipment E-x may be different from the interface I-y of the hardware equipment

[0059] E-y.

[0060] The integration unit 16 comprises a plurality of modules programmed to enable communication between the software models S-l,..., S-n and the hardware equipment E-l,..., E-n, i.e. to enable the exchange of signals between the software models S-l,..., S-n and the hardware equipment E-l,..., E-n.

[0061] The integration unit 16 can receive the signals SS-

[0062] 1.....55-n from the software models S-l,..., S-n and convert the respective format thereof into the format processable by the hardware equipment E-l,..., E-n.

[0063] The integration unit 16 can receive the signals SH-

[0064] 1.....5H-n from the hardware equipment E-l,..., E-n and convert the respective format thereof into the format processable by the software models S-l,..., S-n.

[0065] According to a preferred embodiment, the integration unit 16 is configured to allow bidirectional communication between the software models S-l,..., S-n and the hardware equipment E-l,..., E-n.

[0066] In detail, the interface unit 16 may comprise: a modular input / output (I / O) interface 20 configured to receive and provide the signals SH-1 , ..., SH-n and S S — 1 , ... , S S — n ; a number n of protocol drivers 22, one for each protocol P-l,...,P-n; and a number n of low-level drivers 24, one for each interface i-l,...,I-n.

[0067] In this embodiment, the interface unit 16 also comprises an HS / SW conversion module 28. The HS / SW conversion module 28 is optional and may be useful for taking into account specific differences between hardware equipment, e.g. different physical format of the signals, in particular signal scaling.

[0068] The modular I / O interface 20 may be configured to drive the set of protocol drivers 22.

[0069] The protocol drivers 22 are configured to make the protocols Pl,...,P-n equivalent / interchangeable with each other .

[0070] The low-level drivers 24 are configured to enable the exchange of signals between the interfaces i-l,...,I-n.

[0071] In practice, the integration unit 16 may comprise: a low-level physical layer (module 24) that is configured to communicate with the specific operating system drivers of the hardware equipment in question; a protocol layer (module 22) , configured to interpret and interface the bus protocol with the hardware interface ; an interchange layer (module 20) configured to link the physical decoded data with the logical decoded data and vice versa; and, optionally, a physical format layer (module 28) that is configured to decode and encode the physical format (e.g. endianess, packing, scaling) .

[0072] Figure 2 shows an embodiment of a method 50, executable by the integration unit 16, for the integration of a software model S-x with hardware equipment E-x, i.e. for the transmission to a generic hardware equipment E-x of a signal SS-x provided by a generic software model S-x.

[0073] In a step SI, the integration unit 16 receives, via the modular I / O interface 20, the provided signal SS-x software model S-x.

[0074] In a step S3, the protocol modules (drivers) 22 transform the protocol of the signal SS-x into a protocol compatible with that of the hardware equipment E-x. In practice, the protocol driver 22-x associated with the protocol P-x forms, starting from the converted value, a data packet according to the protocol P-x of the hardware equipment E-x.

[0075] For example, the modular interface 20 can internally drive all the protocol modules 22 so that all the protocols P-l,...,P-n are equivalent / interchangeable with each other; that is, so that the hardware equipment E-l,..., E-n can communicate with each other. This can ensure high integration efficiency between software models and hardware equipment.

[0076] In a step S5, the integration unit 16 (in particular the respective module 28) transforms the physical format, e.g. endianess, packing, scaling, etc., of the signal SS-x, into a physical format that is compatible (processable) by the hardware equipment E-x.

[0077] In a step S7, the low-level driver 24-x associated with the interface I-x adapts the signal SS-x according to the interface I-x of the hardware equipment I-x.

[0078] In a step S9, the integration unit 16 generates the signal SH-x to be sent to the hardware equipment E-x, based on the transformations of steps S3, S5, S7.

[0079] In practice, in steps S3 to S5, the integration unit 16 converts the format of the signal SS-x, which is processable by the simulation module S-x and not by the hardware equipment E-x, into the format that is processable by the hardware equipment E-x.

[0080] Preferably, steps S3 to S7 are executed in the sequence described above and illustrated in Figure 2.

[0081] By way of non-limiting example, an example of application of the method 50 for use of a software model S- x of a radar sensor of an aircraft by hardware equipment E- x (e.g. an aircraft navigation computer) on board the aircraft is now described.

[0082] For example, the software model S-x may be a model made in a simulation environment, for example for the simulation of dynamic object systems, known per se.

[0083] In the example considered, the signal SS-x provided by the software model S-x may be indicative of an angle. For example, the software model S-x may receive in input a range of scan angles of the radar sensor and in output the angular position of an identified object in the scanned range. For example, the input and output angles may comprise angles in the range ± 10° with respect to the front portion of the aircraft .

[0084] Suppose by way of example that the model S-x provides in output the angular value +5.7° and this value is to be used by the hardware equipment E-x for the operation of the system 10. In practice, the software model S-x is designed to process signals / data packets indicative of values referred to a specific reference system (e.g. positive and negative angles with respect to the front portion of the aircraft ) and having a certain format ( e . g . floating point coding, etc . ) . In addition, the software model may be configured to process signals having a certain endianess .

[0085] In the example considered, the hardware equipment E-x may be configured to process signals / data packets indicative of values referred to a di f ferent reference system, for example angular values measured with respect to the geographic north pole . In addition, the hardware equipment E-x is not configured to process values in floating point coding and has an endianess di f ferent from that used by the software model .

[0086] With reference to the method 50 of Figure 2 , in the example considered, the modular interface 20 receives the signal SS-x provided by the radar sensor model ( step S I ) . The signal SS-x i s a logic signal indicating an angle value .

[0087] The integration unit 16 converts the signal protocol SS-X into the protocol P-x of the hardware equipment E-x ( step S3 ) .

[0088] The integration unit 16 converts the physical format of the value indicated by the signal SS-x ( e . g . measurement unit and reference system) indicated by the signal SS-X into a value processable by the hardware equipment E-x, step S5 . In the example considered, the integration unit 16 converts the value provided by the simulation model in the reference system of the simulation model , into a value in the reference system of the hardware equipment E-x .

[0089] Then, the low-level driver 24-x adapts the signal S-x as a function of the interface I-x .

[0090] The integration unit 16 generates in response the signal SH-x which is indicative of the same information indicated by the signal SS-x ( angular position of the detected obj ect ) , but has a format that allows it to be read and subsequently processed by the hardware equipment E-x .

[0091] The method 50 has been described with reference to the transmission of a signal from a software model to hardware equipment . However, it will be clear to the person skilled in the art that the method 50 can also be used for the conversion of a signal SH-x provided by an hardware equipment E-x into a signal SS-x processable by the software model S- x .

[0092] From the above , the advantages of the present invention emerge .

[0093] The integration unit 16 and the respective integration method allow to automatically convert all the pecul iarities related to the buses , protocols and aircraft side physical formats towards the logical format in a bidirectional way .

[0094] The invention therefore allows an on-board software to interface with a simulated software and vice versa, without impacting its design and to carry out speci fic code development for one of the two types .

[0095] The invention allows an on-board software to be directly interfaced with a simulated software whether the simulated software is connected to the actual aircraft hardware containing the on-board software or whether the on-board software is converted to run on a computer system where the simulated software also runs ( therefore without actual aircraft hardware involved) .

[0096] In practice , the present invention makes it possible to simpli fy the use of simulated devices and physical devices within the same data processing system . This can be particularly advantageous in case the data processing system is a flight training system for a pilot .

[0097] In other words , according to the present invention, the data processing system 10 may be configured to be used on board the vehicle during use of the vehicle itsel f ; that is , the data processing system 10 may be used on board an aircraft during flight of the aircraft . In fact , although the simulation modules S- l , ..., S-n were born ( designed) to be executed on standard type hardware ( i . e . designed not to be executed on board the aircraft ) , the integration unit 16 allows the simulation modules to be used correctly on board the vehicle , without modi fying the on-board modules .

[0098] The present invention can therefore guarantee a high versatility and simplicity of integration of simulation modules , which were born for simulation, on board the aircraft .

[0099] Furthermore , the modules of the integration unit can be designed as modular intermediate layers and configurable through external files that allow the transition from the avionic interfaces , including their speci fic internal formats , to the logic interfaces and non-coded logic signals . This guarantees a high versatility of use thereof according to the invention .

[0100] Finally, it is clear that the invention described and illustrated herein, can be modi fied and varied without departing from the protective scope of the present invention, as defined in the attached claims . For example , the on-board modules may be processing devices configured to be executed on board a vehicle other than an aircraft , for example in the automotive or aeronautical field, wherein the on-board hardware equipment is configured to have operating logics di f ferent from those of the simulation modules .

[0101] For example , the simulation modules and the on-board modules may be software , hardware type or mixed type processing modules , depending on the speci fic platforms used and the design needs .

[0102] For example , the simulation modules may be stored, executed, loaded, or made within the same processor or in distinct processors . For example , the on-board modules may be stored, executed, loaded, or made within the same processor or in distinct processors .

[0103] For example , the data processing system may be a centrali zed or distributed data processing system .

Claims

CLAIMS1. A data processing system (10) comprising: an on-board module (E-l , E-n) configured to be boarded on a vehicle and to operate on board of the vehicle; a simulation module (S-l, S-n) configured to simulate the behavior of a component of the vehicle; and an integration unit (16) configured to enable communication between the on-board module and the simulation module, wherein the simulation module is configured to process signals (SS-1, SS-n) having a first format and the on-board module is configured to process signals (SH-1, SH-n) having a second format different from the first format, the integration unit being configured to: receive (SI) a first signal processed by the simulation module and having the first format; convert (S3 — S7) the first format into the second format, generating in response a second signal having the second format; and provide (S9) the second signal to the on-board module; and / or - receive a third signal processed by the on-board module and having the second format; convert the second format into the first format, generating in response a fourth signal having the first format; and provide the fourth signal to the simulation module.

2. The system according to the previous claim, wherein the vehicle is an aircraft.

3. The system according to claim 1 or 2, wherein the data processing system (10) is configured to be used onboard the vehicle during use of the vehicle, in particularon-board an aircraft during flight of the aircraft.

4. The system according to any one of claims 1-3, wherein the data processing system is a flight training system for a pilot.

5. The system according to any of the preceding claims, wherein the first and the second formats differ from each other in one or more of the following signal features: type of packing, type of endianess, type of transmission protocol, scaling, and unit of measurement.

6. The system according to any of the preceding claims, wherein the integration unit (16) comprises: a low-level physical module (24) configured to communicate with operating system drivers of the on-board module ;- a protocol module (22) configured to convert the transmission protocol of the first format to the transmission protocol of the second format; and- an interchange module (20) configured to link physical decoded data with a logic signal processable by the simulation module and / or to link a logic signal processed by the simulation module with physical decoded data processable by the on-board module.

7. The system according to the preceding claim, wherein the integration unit (16) further comprises a physical format module (28) configured to decode and encode the physical format, e.g., endianess and / or packing.

8. The system according to any one of the preceding claims, wherein the simulation module is a first simulation module of a plurality of simulation software models (12)each configured to generate a respective logic signal (SS- l,...,SS-n) , wherein the on-board module is a first on-board module of a plurality of hardware equipment (14) each configured to generate a respective signal (SH-x) according to a respective protocol (P-x) and to communicate with each other via a respective hardware interface (I-x) .

9. The system according to any of the preceding claims, wherein the on-board module (E-l , E-n) is adapted for being uses on board of the vehicle, in particular on board of an aircraft during flight of the aircraft, and wherein the simulation module (S-l , S-n) is not adapted for being used on board of the vehicle, in particular on board of the aircraft during flight of the aircraft.

10. A method implemented by a data processing system for the integration of simulation software and on-board software, wherein the on-board software (E-l , E-n) is configured to be boarded in a vehicle and to be executed by an on-board vehicle processor, and the simulation software (S-l, ..., S-n) is configured to simulate the behavior of a vehicle component, wherein the simulation software is configured to process signals having a first format and the on-board software is configured to process signals having a second format different from the first format, the method comprising:- receiving a first signal processed by the simulation software and having the first format; converting the first format to the second format, generating in response a second signal having the second format; and providing the secondsignal to the on-board module; and / or- receive a third signal processed by the on-board module and having the second format; convert the second format into the first format, generating in response a fourth signal having the first format; and provide the fourth signal to the simulation module.

11. Method according to any preceding claim, wherein the method is performed on-board the vehicle during use of the vehicle, in particular on-board an aircraft during flight of the aircraft.

12. Method according to claim 10 or 11, where the data processing system is a flight training system for a pilot.

13. Method according to any one of claims 10-12, wherein converting the first signal into the second signal comprises:(a) transforming the protocol associated with the first format into the protocol associated with the second format;(b) transforming the physical format associated with the first format into the physical format associated with the second format; and(c) adapting the signal to be converted according to a hardware interface of the on-board module.

14. Method according to any one of claims 10-13, wherein converting the third signal into the fourth signal comprises:(a) transforming the protocol associated with the second format into the protocol associated with the first format ;(b) transforming the physical format associated with the second format into the physical format associated with the first format; and(c) adapting the signal to be converted according to a hardware interface of the on-board module.

15. Method according to claim 12 or 13, in which steps a) , b) and c) are performed in the sequence a) -b) -c) .

16. A computer programme stored in a data processing system and configured such that, when executed, the data processing system becomes configured to execute the method according to any one of claims 10-15.

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