EP2390615B1 - Method for accessing measurement and/or status data from a data storage unit of an armed unmanned aerial vehicle and device for performing the method - Google Patents
Method for accessing measurement and/or status data from a data storage unit of an armed unmanned aerial vehicle and device for performing the method Download PDFInfo
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- EP2390615B1 EP2390615B1 EP20110004337 EP11004337A EP2390615B1 EP 2390615 B1 EP2390615 B1 EP 2390615B1 EP 20110004337 EP20110004337 EP 20110004337 EP 11004337 A EP11004337 A EP 11004337A EP 2390615 B1 EP2390615 B1 EP 2390615B1
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- Prior art keywords
- missile
- data
- external
- data bus
- state
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/055—Umbilical connecting means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/001—Devices or systems for testing or checking
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
Definitions
- the present invention relates to a method for interrogating measurement and / or state data from a data memory, in particular from a telemetry data memory, a sharp unmanned missile according to the preamble of claim 1. It further relates to an apparatus for performing this method.
- the EP 1 923 659 A2 relates to a method for verifying the ability to interact between an aircraft and an armed, unmanned missile that can be coupled thereto. It reviews the operational interaction between the missile and the aircraft, storing and outputting sporadic non-fatal errors that occur during the review. This known method thus deals only with the detection and output of error messages, but not with a query of measurement and / or state data, ie of specific operating parameters of the missile.
- the DE 10 2004 042 990 B4 discloses a method and apparatus for testing an operational cruise missile in various flight scenarios. There are described different test scenarios (A to D), according to which tests of the functionality of a missile can be performed at different times and with different test equipment requirements. A Concrete query of measurement and / or state data from a data store is not disclosed in this citation.
- the invention thus consists in using the external data bus, which is actually provided only for the operational communication of the missile with the carrier aircraft, via which a mission data exchange between the carrier aircraft and the missile takes place in the armed state of the missile for test purposes, by the test device interrogation commands to send to the central computer, which cause the central computer to send back measurement and / or status data from the present in the operational state telemetry data memory to the tester.
- the central computer of the missile is already provided with a software object, which always collects all relevant internal data of the missile in real time and caches in a volatile telemetry data memory for the telemetry radio transmission.
- a test device is connected to the external data bus not provided and the interrogation commands for outputting the measurement and / or status data are sent by the test device via this external data bus the missile's central computer is sent, which converts it into data accesses into the telemetry data store and then sends the read data back to the tester via this external data bus.
- Fig. 1 is further seen that in the front region of the missile 1, a housing cover 16 is open, so that the interior of the nose of the missile 1 is accessible.
- an IMBUS cable 70 is connected to the internal data bus 3 via a branch at the data bus connection of the seeker head 10.
- the IMBUS cable 70 is connected to a level converter 72 and from there via a digital input / output 74 to an external test computer provided with a monitoring software, which forms a test module 76 for the missile.
Description
Die vorliegende Erfindung betrifft ein Verfahren zur Abfrage von Mess-und/oder Zustandsdaten aus einem Datenspeicher, insbesondere aus einem Telemetriedatenspeicher, eines scharfen unbemannten Flugkörpers gemäß dem Oberbegriff des Patentanspruchs 1. Sie betrifft weiterhin eine Vorrichtung zur Durchführung dieses Verfahrens.The present invention relates to a method for interrogating measurement and / or state data from a data memory, in particular from a telemetry data memory, a sharp unmanned missile according to the preamble of claim 1. It further relates to an apparatus for performing this method.
Bei unbemannten operationellen Flugkörpern ist es bislang aus Sicherheitsgründen nicht möglich gewesen, eine detaillierte Messdatenerfassung für eine Fehlersuche oder für eine Zustandsuntersuchung an einem scharfen, also mit einer Bewaffnung ausgestatteten, Flugkörper durchzuführen. Bislang musste zunächst der Flugkörper inert gemacht werden. Das bedeutet, dass die Bewaffnung sowie pyrotechnische Aktuatoren zunächst aus dem Flugkörper auszubauen waren. Erst danach konnte eine Datenmonitoringvorrichtung für den internen Datenbus des Flugkörpers eingebaut werden, wozu ein externer Computer mit einer geeigneten Software an den internen Datenbus des Flugkörpers angeschlossen wurde. Mittels dieses Aufzeichnungsmoduls konnten dann bei entsprechenden durchgeführten Tests relevante Daten mittels Monitoring des internen Datenverkehrs des Flugkörpers erfasst und verfügbar gemacht werden.In the case of unmanned operational missiles, it has hitherto not been possible for safety reasons to carry out a detailed measurement data collection for troubleshooting or for a status investigation on a sharp, ie equipped with a weapon, missile. So far, the missile had to be made inert first. This means that the armament and pyrotechnic actuators were first to be removed from the missile. Only then could a data monitoring device for the internal data bus of the missile be installed, for which purpose an external computer with suitable software was connected to the internal data bus of the missile. By means of this recording module, relevant data could then be recorded and made available by monitoring the internal data traffic of the missile during corresponding tests.
Diese bekannte Vorgehensweise ist jedoch aus zwei Gründen nachteilig. Zum Einen beträgt der Zeitaufwand für die Umrüstung eines scharfen Flugkörpers in einen inerten Flugkörper und die nach dem Test wieder erforderliche Rückrüstung des inerten Flugkörpers in einen scharfen Flugkörper mehrere Stunden und es ist für den Ausbau der Bewaffnung spezielles Werkzeug erforderlich, das nicht an jedem Lagerort von bewaffneten Flugkörpern zur Verfügung steht, so dass zusätzlich noch ein Transport des scharfen Flugkörpers in eine entsprechende Werkstatt notwendig sein kann. Zum Anderen werden beim Umrüsten des Flugkörpers vom scharfen in den inerten Zustand Änderungen an der Konfiguration des Flugkörpers vorgenommen, wodurch es möglich sein kann, dass bestimmte Fehler, die im scharfen Zustand des Flugkörpers aufgetreten sind, nach der Umrüstung nicht mehr auftreten und somit auch nicht ermittelt werden können.However, this known approach is disadvantageous for two reasons. On the one hand, the time required for the conversion of a sharp missile into an inert missile and the re-arming of the inert missile into a sharp missile, which is required again after the test, are several Hours and it is necessary for the expansion of the armament special tool that is not available at every storage location of armed missiles, so that in addition still a transport of the sharp missile may be necessary in a corresponding workshop. On the other hand, when refitting the missile from the sharp to the inert state, changes are made to the configuration of the missile, which may make it possible that certain errors that occurred in the armed state of the missile after the conversion no longer occur and therefore not can be determined.
Die
Die
Die
Es ist daher die Aufgabe der vorliegenden Erfindung, ein gattungsgemäßes Verfahren anzugeben, mit dem es möglich ist, ohne Umrüstung eines scharfen unbemannten Flugkörpers und ohne Eingriff in den scharfen unbemannten Flugkörper Mess- und/oder Zustandsdaten des scharfen unbemannten Flugkörpers gezielt auslesen zu können.It is therefore an object of the present invention to provide a generic method, with which it is possible to selectively read out measurement and / or state data of the sharp unmanned missile without retooling a sharp unmanned missile and without interference with the sharp unmanned missile.
Diese Aufgabe wird durch das im Patentanspruch 1 angegebene Verfahren gelöst.This object is achieved by the method specified in claim 1.
Dieses erfindungsgemäße Verfahren betrifft die Abfrage von Mess- und/oder Zustandsdaten aus einem Telemetriedatenspeicher eines scharfen unbemannten Flugkörpers, wobei der Flugkörper einen Umbilical-Anschluss aufweist, an dem der Flugkörper über ein Umbilical-Kabel mit einem Trägerflugzeug zum Austausch von operationellen Missionsdaten und/oder Zustandsdaten verbindbar ist, wobei das Umbilical-Kabel eine externe Busleitung aufweist, die Teil eines externen Datenbus ist, über den ein Zentralcomputer des Flugkörpers und ein Computer des Trägerflugzeugs miteinander zum operationellen Datenaustausch kommunizieren können, wobei der Flugkörper im nicht-scharfen Zustand mit einem Testmodul verbindbar ist, das an einen internen Datenbus des Flugkörpers anschließbar ist und das den Datenverkehr des internen Datenbus überwachen kann und das somit Mess- und/oder Zustandsdaten des Flugkörpers abgreifen kann, wobei das Testmodul im scharfen Zustand des Flugkörpers nicht mit dem Flugkörper verbunden ist. Die erfindungsgemäße Lösung der Aufgabe besteht darin, dass im scharfen Zustand des Flugkörpers von einem externen Testgerät, das an den für die operationelle Kommunikation des Flugkörpers mit dem Trägerflugzeug vorgesehenen externen Datenbus angeschlossen wird, Abfragebefehle über den externen Datenbus an den Zentralcomputer des Flugkörpers gesandt werden und dass der Zentralcomputer des Flugkörpers als Antwort auf die Abfragebefehle Mess- und/oder Zustandsdaten aus dem Datenspeicher (beispielsweise dem Telemetriedatenspeicher) über den externen Datenbus an das externe Testgerät sendet.This inventive method relates to the retrieval of measurement and / or state data from a telemetry data memory of a sharp unmanned missile, wherein the missile has a Umbilical connection, at which the missile via a Umbilical cable with a carrier aircraft for the exchange of operational mission data and / or Condition data connectable, wherein the Umbilical cable has an external bus, which is part of an external data bus through which a central computer of the missile and a computer of the carrier aircraft can communicate with each other for operational data exchange, wherein the missile in the non-sharp state with a test module connectable, which is connectable to an internal data bus of the missile and can monitor the traffic of the internal data bus and thus can access measurement and / or condition data of the missile, wherein the test module in the sharp state of the missile not with the Flu Body is connected. The object of the invention is that in the sharp state of the missile from an external test device, which is connected to the provided for the operational communication of the missile with the carrier aircraft external data bus, query commands are sent via the external data bus to the central computer of the missile and that the central computer of the missile in response to the query commands measurement and / or status data from the data memory (for example, the Telemetry data memory) via the external data bus to the external test device.
Die Erfindung besteht also darin, den eigentlich nur für die operationelle Kommunikation des Flugkörpers mit dem Trägerflugzeug vorgesehenen externen Datenbus, über den im Einsatzfall ein Missionsdatenaustausch zwischen dem Trägerflugzeug und dem Flugkörper erfolgt, im scharfen Zustand des Flugkörpers zu Testzwecken dazu zu nutzen, vom Testgerät Abfragebefehle an den Zentralcomputer zu senden, die den Zentralcomputer dazu veranlassen, Mess- und/oder Zustandsdaten aus dem auch im operationellen Zustand vorhandenen Telemetriedatenspeicher an das Testgerät zurückzusenden. Dabei wird die Tatsache genutzt, dass der Zentralcomputer des Flugkörpers bereits mit einem Software-Objekt versehen ist, welches immer alle relevanten internen Daten des Flugkörpers in Realzeit sammelt und in einem flüchtigen Telemetriedatenspeicher für die Telemetriefunkübertragung zwischenspeichert. Anstatt nun mit einem an den internen Datenbus des zunächst inert gemachten Flugkörpers angeschlossenen Testgerät ein Busmonitoring auszuführen wird erfindungsgemäß ein Testgerät an den nicht dafür vorgesehenen externen Datenbus angeschlossen und die Abfragebefehle zur Ausgabe der Mess- und/oder Zustandsdaten werden vom Testgerät über diesen externen Datenbus an den Zentralcomputer des Flugkörpers gesandt, der diese in Datenzugriffe in den Telemetriedatenspeicher umsetzt und dann die gelesenen Daten über diesen externen Datenbus wieder an das Testgerät zurücksenden.The invention thus consists in using the external data bus, which is actually provided only for the operational communication of the missile with the carrier aircraft, via which a mission data exchange between the carrier aircraft and the missile takes place in the armed state of the missile for test purposes, by the test device interrogation commands to send to the central computer, which cause the central computer to send back measurement and / or status data from the present in the operational state telemetry data memory to the tester. In this case, the fact is used that the central computer of the missile is already provided with a software object, which always collects all relevant internal data of the missile in real time and caches in a volatile telemetry data memory for the telemetry radio transmission. Instead of carrying out a bus monitoring with a test device connected to the internal data bus of the initially inertized missile, according to the invention a test device is connected to the external data bus not provided and the interrogation commands for outputting the measurement and / or status data are sent by the test device via this external data bus the missile's central computer is sent, which converts it into data accesses into the telemetry data store and then sends the read data back to the tester via this external data bus.
Der Bediener kann dabei konfigurieren auf welche Daten zugegriffen wird (frei selektierte, baugruppenbezogene oder funktionsbezogene Daten) und mit welchen Updatezyklus die Daten ausgelesen und übertragen werden (einmalig, zyklisch und Rate).The operator can configure which data is accessed (freely selected, module-related or function-related data) and with which update cycle the data is read out and transmitted (once, cyclically and rate).
Dazu wird vorzugsweise zunächst über einen vom Testgerät an den Zentralcomputer des Flugkörpers über den externen Datenbus gesandten Aktivierungsbefehl der schreibende und lesende Zugriff auf den Telemetriedatenspeicher freigeschatet bevor die Befehle zur Datenabfrage des Telemetriedatenspeichers gesandt werden.For this purpose, the write and read access to the telemetry data store is preferably first enabled via a activation command sent to the central computer of the missile via the external data bus before the commands for data query of the telemetry data store are sent.
Vorteilhaft ist bei dieser erfindungsgemäßen Lösung, dass für das erfindungsgemäße Verfahren keine zusätzliche Hardware für den Flugkörper wie z.B. Ausrüstung für Funktelemetrie oder Datenbusmonitoring oder für das externe Test-Equipment erforderlich ist. Es kann somit auf einfache kostengünstige Weise eine detaillierte Messdatenerfassung für die Fehlersuche oder für eine Zustandsuntersuchung am scharfen Flugkörper durchgeführt werden, so dass es nicht mehr erforderlich ist, den Flugkörper von seinem aktuellen Lagerort in eine Werkstatt zu verbringen und zunächst in den inerten Zustand zu versetzen. Die Überprüfung nach dem erfindungsgemäßen Verfahren kann somit auch beispielsweise an einem Flugkörper unmittelbar vor dem Anbringen des Flugkörpers an einem Trägerflugzeug vor einer Mission oder unmittelbar nach Abhängen des Flugkörpers vom Trägerflugzeug nach einem Missionsabbruch durchgeführt werden. Es werden durch das erfindungsgemäße Verfahren somit nicht nur Zeit und Kosten eingespart, sondern auch die Zuverlässigkeit und die Einsatzbereitschaft von unbemannten Flugkörpern wird dadurch deutlich verbessert.It is advantageous in the case of this solution according to the invention that no additional hardware for the missile, such as e.g. Equipment for radio telemetry or data bus monitoring or for the external test equipment is required. It can thus be carried out in a simple cost-effective manner, a detailed data acquisition for debugging or for a state examination on the sharp missile, so that it is no longer necessary to spend the missile from its current storage in a workshop and initially put in the inert state , The check by the method according to the invention can thus also be carried out, for example, on a missile immediately before attaching the missile to a carrier aircraft before a mission or immediately after the missile has been suspended from the carrier aircraft after a mission abort. Thus, not only the time and costs are saved by the inventive method, but also the reliability and operational readiness of unmanned missiles is significantly improved.
Weitere vorteilhafte Ausgestaltungen des erfindungsgemäßen Verfahrens sind in den Unteransprüchen angegeben.Further advantageous embodiments of the method according to the invention are specified in the subclaims.
Schließlich betrifft die Erfindung auch eine Vorrichtung zur Durchführung des erfindungsgemäßen Verfahrens, die insbesondere eine an den Umbilical-Anschluss des Flugkörpers anschließbare Adapterbox aufweist, die mit einem Bediengerät kabelgebunden oder drahtlos verbindbar ist, welches auf diese Weise mit dem Zentralcomputer des Flugkörpers zur Datenkommunikation verbindbar ist.Finally, the invention also relates to a device for carrying out the method according to the invention, which in particular has an adapter box connectable to the umbilical terminal of the missile, which can be wired or wirelessly connected to an operating device, which in this way can be connected to the central computer of the missile for data communication ,
Bevorzugte Ausführungsbeispiele der Erfindung mit zusätzlichen Ausgestaltungsdetails und weiteren Vorteilen sind nachfolgend unter Bezugnahme auf die beigefügten Zeichnungen näher beschrieben und erläutert.Preferred embodiments of the invention with additional design details and other advantages are described and explained in more detail below with reference to the accompanying drawings.
Es zeigt:
- Fig. 1
- den bisherigen Testaufbau zur Mess- und/oder Zustandsdatenabfrage an einem inerten Flugkörper und
- Fig. 2
- den erfindungsgemäßen Testaufbau zur Mess- und/oder Zustandsdatenabfrage an einem scharfen Flugkörper.
- Fig. 1
- the previous test setup for measuring and / or condition data query on an inert missile and
- Fig. 2
- the test structure according to the invention for measuring and / or condition data query on a sharp missile.
In
Der Flugkörper 1 weist einen Zentralcomputer 2 auf, der mit einem flüchtigen Telemetriedatenspeicher 20 versehen ist. Der Zentralcomputer 2 ist an einen internen Datenbus 3 angeschlossen, der in der
Der Flugkörper 1 ist an seiner Oberseite mit einem Umbilical-Anschluss 12 versehen, der über einen externen Datenbus 4 im Einsatzfall mit einem Trägerflugzeug, im gezeigten Testfall jedoch mit einem das Trägerflugzeug simulierenden Steuergerät 5 als Simulationseinrichtung verbunden ist. Das Steuergerät 5 ist über eine Stromversorgungsleitung 52 mit einer Quelle 54 für elektrische Energie verbunden. Der Umbilical-Anschluss 12 des Flugkörpers ist im Inneren des Flugkörpers über eine Datenbus-Leitung 14 mit dem Zentralcomputer 2 verbunden. Die Datenbus-Leitung 14 und entsprechende Datenbus-Leitungen des Umbilical-Kabels 50 bilden gemeinsamen einen externen Datenbus 4, der dem MILBUS-Standard (siehe Mil-Standard 1553, Mil-Standard 1763) entspricht und auch als "MILBUS" bezeichnet wird.The missile 1 is provided on its upper side with a
In
Der Testcomputer ist auf diese Weise in der Lage, den internen Datenverkehr des Flugkörper zwischen dem Zentralcomputer und den Flugkörpersubsystemen (Navigationsystem, Lenksystem, Rudermaschinen, Sensorik, Sicherheitsystem, Triebwerk, Gefechtskopf etc.) zu monitoren und somit auf Mess- und/oder Zustandsdaten des Flugkörpers zuzugreifen, falls der Flugkörper 1 durch das Steuergerät 5 aktiviert wird. Um dies zu ermöglichen, ist es jedoch erforderlich, eine Datenübertragungsverbindung mit dem im Inneren des Flugkörpers 1 verlaufenden internen Datenbus 3 herzustellen, wozu die Klappe 16 geöffnet werden muss. Ein solches Öffnen einer Gehäuseklappe oder Karosserieklappe des Flugkörpers 1 ist jedoch nicht erlaubt, wenn der Flugkörper sich in seinem scharfen Zustand befindet, also mit einer Bewaffnung versehen ist. Der in
Bei dem in
Es ist auf diese Weise möglich, dass vom Bediengerät 56 ein Befehl für eine im Zentralcomputer 2 des Flugkörpers 1' ablaufbare Software zur Aktivierung des Datenzugriffes gesandt wird während der Flugkörper in einer Testsequenz betrieben wird, wie sie zum Beispiel in der
- die Daten werden vom Bediener
am Bediengerät 56 entsprechend seiner Untersuchungsabsicht frei selektiert oder - der Bediener selektiert
am Bediengerät 56 die Daten nach einem bestimmten Kritierum : zum Beispiel baugruppenbezogen oder funktionsbezogen.
- the data are freely selected by the operator on the operating
unit 56 according to his intent to investigate or - The operator selects the data on the operating
unit 56 according to a certain criterion: for example, based on the module or function.
Das Auslesen der Inhalte der selektierten Daten aus dem Telemetriedatenspeicher 20 und die Übertragung mittels des externen Datenbus 4 kann dabei einmalig (asynchron) oder zyklisch (synchron) erfolgen. Im Falle des zyklischen Auslesens und Übertragens ist es vorteilhaft, wenn das Auslesen und das Übertragen mit derselben oder ähnlich großer Frequenz erfolgt wie die Daten in den Telemetriedatenspeicher 20 eingetragen werden.The reading out of the contents of the selected data from the
Von Vorteil ist es zudem, wenn für die Anfrage und den Transfer der Mess-und/oder Zustandsdaten über den externen Datenbus 4 nicht unbenutzte Worte von operationellen Botschaften benutzt werden, sondern wenn für diese Messdatenerfassungszwecke neue Botschaften definiert und benutzt werden, so dass das operationelle Botschafts- und Transferdesign unverändert bleibt. Dadurch können ungewollte und störende Nebeneffekte im operationellen Betrieb vermieden werden.It is also advantageous if not unused words of operational messages are used for the request and the transfer of the measurement and / or status data via the
Vorteilhaft ist es weiterhin, wenn die Adapterbox 5' eine Webserver-Funktionalität (zum Beispiel eine Webserver-Software mit dem Netzwerkprotokoll TCP/IP) beinhaltet und über das Ethernet-Kabel 58 (anstatt des Bediengerätes 56) oder über eine Funkverbindung 59 mit den Internet verbunden ist, wodurch die ermittelten Mess- und/oder Zustandsdaten des Flugköpers für Fernwartungszwecke zugänglich sind und die Fernsteuerung des Flugkörpers (remote control) für Fehlersuche und Zustandsermittlung ermöglicht wird.It is furthermore advantageous if the adapter box 5 'includes a web server functionality (for example a web server software with the network protocol TCP / IP) and via the Ethernet cable 58 (instead of the operating unit 56) or via a
Von besonderem Vorteil ist die Tatsache, dass zur Durchführung des erfindungsgemäßen Verfahrens keine zusätzlich Hardware benötigt wird, da die bereits für scharfe Flugkörper zugelassenen Hardwareausstattungen, nämlich die Adapterbox 5' und das Bediengerät 56 mit der darauf laufenden und für den Betrieb am scharfen Flugkörpers bereits zugelassenen Software verwendet werden.Of particular advantage is the fact that no additional hardware is required to carry out the method according to the invention, since the already approved for sharp missiles hardware equipment, namely the adapter box 5 'and the
Bezugszeichen in den Ansprüchen, der Beschreibung und den Zeichnungen dienen lediglich dem besseren Verständnis der Erfindung und sollen den Schutzumfang nicht einschränken.Reference signs in the claims, the description and the drawings are only for the better understanding of the invention and are not intended to limit the scope.
Es bezeichnen:
- 1
- Flugkörper
- 1'
- Flugkörper
- 2
- Zentralcomputer
- 3
- interner Datenbus
- 4
- externer Datenbus
- 5
- Steuergerät
- 5'
- Adapterbox
- 10
- Suchkopf
- 12
- Umbilical-Anschluss
- 14
- Datenbus-Leitung
- 16
- Gehäusedeckel
- 18
- Bewaffnung
- 20
- Telemetriedatenspeicher
- 50
- Umbilical-Kabel
- 52
- Stromversorgung
- 54
- Stromversorgung
- 56
- externes Bediengerät
- 58
- Ethernet-Kabel
- 59
- Funkverbindung
- 70
- I MBUS-Kabel
- 72
- Pegelwandler
- 74
- digitaler Ein-/Ausgang
- 76
- Testmodul
- 1
- missile
- 1'
- missile
- 2
- central computer
- 3
- internal data bus
- 4
- external data bus
- 5
- control unit
- 5 '
- Adapterbox
- 10
- seeker
- 12
- Umbilical port
- 14
- Data bus line
- 16
- housing cover
- 18
- arming
- 20
- Telemetry data storage
- 50
- Umbilical cable
- 52
- power supply
- 54
- power supply
- 56
- external operating device
- 58
- Ethernet cable
- 59
- radio link
- 70
- I MBUS cable
- 72
- level converter
- 74
- digital input / output
- 76
- test module
Claims (8)
- Method for requesting measurement and/or state data from a data memory (20) in a live unmanned missile (1'),- wherein the missile (1') has an umbilical port (12) at which the missile (1') can be connected by means of an umbilical cable (50) to a carrier aircraft for the purpose of interchanging mission data and/or state data,- wherein the umbilical cable (50) has an external bus line that is part of an external data bus (4) via which a central computer (2) in the missile (1') and a computer in the carrier aircraft can communicate with one another for the purpose of data interchange,- wherein the missile can be connected in the non-live state to a test module (76) that can be connected to an internal data bus (3) in the missile and that can monitor the data traffic of the internal data bus (3) and can therefore tap off measurement and/or state data from the missile,- wherein the test module (76) is not connected to the missile in the live state of the missile (1'),
characterized- in that in the live state of the missile (1') an external tester (5'), which is connected to the external data bus (4) provided for the operational communication of the missile (1') with the carrier aircraft, sends request commands via the external data bus (4) to the central computer (2) of the missile (1'), and- in that the central computer (2) of the missile (1') responds to the request commands by sending measurement and/or state data from the data memory (20) via the external data bus (4) to the external tester (5'). - Method according to Claim 1,
characterized
in that the external tester (5') first of all sends an activation command for read and write access to the data memory (20) via the external data bus (4) to the central computer (2) before the request commands are sent and the data contents are transmitted. - Method according to Claim 1 or 2,
characterized
in that the measurement and/or state data are selected by the user on a user device (56), which communicates with the external tester (5'), freely or on the basis of a prescribed criterion, preferably on the basis of assembly or on the basis of function. - Method according to one of the preceding claims,
characterized
in that the reading of the contents of the selected data from the data memory (20) and the transmission by means of the external data bus (4) take place once synchronously or cyclically synchronously. - Method according to Claim 4,
characterized
in that the cyclic reading and transmission of the selected data take place at the same or a similar frequency as the entry of the data into the data memory (20). - Method according to one of the preceding claims,
characterized
in that the querying and transfer of the measurement and/or state data by the external data bus (4) does not involve the use of unused words from operational messages but rather involves the definition and transmission of new messages, as a result of which the operational message and transfer design remains unaltered. - Method according to one of the preceding claims,
characterized
in that the external tester (5') has a web server functionality and is connected to the Internet, and
in that the ascertained measurement and/or state data from the missile are transmitted via the Internet and are thus accessible for remote maintenance purposes. - Method according to one of the preceding claims,
characterized
in that the external tester (5') has a web server functionality and is connected to the Internet, and
in that the missile (1) is remotely controlled via the Internet for the purpose of error searching and/or state ascertainment.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102010021717 | 2010-05-27 | ||
DE201010024541 DE102010024541B4 (en) | 2010-05-27 | 2010-06-22 | Method for interrogating measurement and / or state data from a data memory of a sharp unmanned missile and device for carrying out the method |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2390615A1 EP2390615A1 (en) | 2011-11-30 |
EP2390615B1 true EP2390615B1 (en) | 2014-03-19 |
Family
ID=44117175
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20110004337 Active EP2390615B1 (en) | 2010-05-27 | 2011-05-26 | Method for accessing measurement and/or status data from a data storage unit of an armed unmanned aerial vehicle and device for performing the method |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP2390615B1 (en) |
DE (1) | DE102010024541B4 (en) |
ES (1) | ES2464521T3 (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102012015363B4 (en) * | 2012-08-06 | 2014-10-23 | Mbda Deutschland Gmbh | Device for detecting errors of an unmanned missile designed to fly on a carrier aircraft and method therefor |
DE102012017891B4 (en) * | 2012-09-11 | 2019-05-02 | Mbda Deutschland Gmbh | A method for testing the correct communication between a missile and a carrier aircraft and a missile test device |
DE102013002717A1 (en) * | 2013-02-16 | 2014-08-21 | Diehl Bgt Defence Gmbh & Co. Kg | Method for operating a stationary missile |
NO343502B1 (en) | 2017-08-23 | 2019-03-25 | Kongsberg Defence & Aerospace As | Method and system for reliably changing operation mode of a weapon |
DE102022002703A1 (en) | 2022-07-26 | 2024-02-01 | Diehl Defence Gmbh & Co. Kg | Effector data connector for data connection of an effector to a firing platform |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4935881A (en) * | 1987-04-14 | 1990-06-19 | Jeffrey Lowenson | Method and apparatus for testing missile systems |
DE10040050A1 (en) * | 2000-08-11 | 2002-02-21 | Mannesmann Vdo Ag | Test module for comparative testing of electronic component, simulation module connects component, simulation interfaces, compares/records component, simulation output signals |
US6941850B1 (en) * | 2004-01-09 | 2005-09-13 | Raytheon Company | Self-contained airborne smart weapon umbilical control cable |
DE102004042990B4 (en) | 2004-09-06 | 2008-11-20 | Michael Grabmeier | Method and device for testing an operational cruise missile in various test scenarios by means of maintenance mode |
DE102006041140B4 (en) | 2006-09-01 | 2009-11-26 | Lfk-Lenkflugkörpersysteme Gmbh | Procedure for checking the functioning of unmanned armed missiles |
DE102006054340A1 (en) * | 2006-11-17 | 2008-05-21 | Lfk-Lenkflugkörpersysteme Gmbh | A method for verifying the ability to interact between an aircraft and an armed unmanned missile coupled thereto |
DE102008054264B4 (en) | 2008-10-31 | 2012-09-13 | Lfk-Lenkflugkörpersysteme Gmbh | Multifunctional service and test facility for unmanned aerial vehicles |
-
2010
- 2010-06-22 DE DE201010024541 patent/DE102010024541B4/en not_active Expired - Fee Related
-
2011
- 2011-05-26 ES ES11004337T patent/ES2464521T3/en active Active
- 2011-05-26 EP EP20110004337 patent/EP2390615B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
EP2390615A1 (en) | 2011-11-30 |
DE102010024541A1 (en) | 2011-12-01 |
ES2464521T3 (en) | 2014-06-03 |
DE102010024541B4 (en) | 2013-11-07 |
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