EP2618099B1 - Dispositif de vérification et de test pour un appareil de démarrage de corps volant et procédé de vérification et/ou de test de la capacité de fonctionnement d'un appareil de démarrage de corps volant - Google Patents

Dispositif de vérification et de test pour un appareil de démarrage de corps volant et procédé de vérification et/ou de test de la capacité de fonctionnement d'un appareil de démarrage de corps volant Download PDF

Info

Publication number
EP2618099B1
EP2618099B1 EP13000176.1A EP13000176A EP2618099B1 EP 2618099 B1 EP2618099 B1 EP 2618099B1 EP 13000176 A EP13000176 A EP 13000176A EP 2618099 B1 EP2618099 B1 EP 2618099B1
Authority
EP
European Patent Office
Prior art keywords
missile
computer
test
testing
monitoring
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP13000176.1A
Other languages
German (de)
English (en)
Other versions
EP2618099A3 (fr
EP2618099A2 (fr
EP2618099B8 (fr
Inventor
Karl Fischer
Michael Grabmeier
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MBDA Deutschland GmbH
Original Assignee
MBDA Deutschland GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MBDA Deutschland GmbH filed Critical MBDA Deutschland GmbH
Publication of EP2618099A2 publication Critical patent/EP2618099A2/fr
Publication of EP2618099A3 publication Critical patent/EP2618099A3/fr
Application granted granted Critical
Publication of EP2618099B1 publication Critical patent/EP2618099B1/fr
Publication of EP2618099B8 publication Critical patent/EP2618099B8/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A31/00—Testing arrangements
    • 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
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/006—Guided missiles training or simulation devices

Definitions

  • the present invention relates to a test and test device for a missile launch device. It further relates to a unit of a missile launch device and such a test and test device. The invention also relates to a method for testing and / or testing the functionality of a missile launcher.
  • a missile launch device having at least one launch device for at least one missile and a weapon control computer controllable thereon and controllable by a weapons system center on which a missile launch control program is installed and wherein the launch device is provided with at least one electrical connector provided for Data transmission is associated with the weapon control computer and associated with the at least one missile and connectable to this and this communication ports for unidirectional and / or bidirectional data transmission to the missile must be tested at different times for its functionality and tested. For example, a final test must be performed as part of the development integration of the missile launcher. Also in the context of production, a final test must be carried out before delivery of the missile launcher to the customer.
  • missile launchers are generally mobile devices that are controlled by a weapon system center remote from the particular site, and since the weapon system center is typically a continually occupied and always active device, the operation of the weapon system center should not be affected by any test or testing procedures for a missile launcher be affected. In addition, for safety reasons, a test or test of the missile launcher must not be performed with sharp missiles.
  • the object of the present invention is therefore to provide a testing and testing device for a missile launching device, as specified in claim 1, with which the functionality of the missile launching device can be tested at any time at different locations and with which specifically checked individual functions of the missile launcher can be. Furthermore, it is an object of the present invention to provide a corresponding method for testing and / or testing the functionality of a missile launcher.
  • This test and test device simultaneously integrates two simulators, namely on the one hand the missile simulation unit, which simulates the presence of a missile on the missile launch device, and on the other hand, the test and test computer, which simulates at least a part of the functions of the weapons system center.
  • the testing and testing device together with the missile launching device, forms a unit which behaves like a missile launching device connected to a weapon system center and provided with a sharp missile during a testing or testing procedure.
  • test and test computer is connected to a data transmission device for data transmission, which can be connected to the weapon control computer for data transmission wireless or wired.
  • a data transmission device for data transmission which can be connected to the weapon control computer for data transmission wireless or wired.
  • test and test computer with the weapon control computer via a data line for data transmission directly connectable.
  • This embodiment makes it possible to read internal data of the missile launcher and thus to monitor processes that take place within the missile launcher (so-called white-box view), even if these processes via the outer communication interfaces of the missile launcher (so-called black box view) are not visible.
  • test and test computer with a telemetry data interface of the weapon control computer for data transmission is connectable. An insight into the processes taking place inside the missile launch device can also be obtained via this telemetry interface, so that the correctness of internal processes can be verified and, if necessary, findings about possible sources of error can be obtained.
  • the missile simulation unit has a simulation computer that is controllable by the test and test computer, thereby the possibilities to perform a test of the missile launcher are significantly enhanced, as this simulates different variants of missile launches and also, for example, complex missile defects and correct Reaction can be verified.
  • the missile simulation unit has a signal adaptation device, which is connected to the simulation computer for data transmission and which can be connected to the communication ports of the starting device for data transmission. This signal adaptation device ensures that the weapon control computer of the missile launcher device can not determine that the respective launch device is not connected to a missile but only to a missile simulator.
  • the invention is further directed to a missile launch device assembly including at least one launch device for at least one missile and a weapon control computer associated therewith, on which a missile launch control program is installed, and wherein the launch device includes at least one electrical connector which is connected to the weapon control computer for data transmission and which is associated with and connectable to the at least one missile and has communication ports for unidirectional and / or bidirectional data transmission to the missile, and a test and test device according to the present invention.
  • This unit of missile launching device and test and test device integrates the missile launch device with the missile simulation unit and the simulator for the weapons system center provided test and test device to an integrated test stand.
  • the invention is further directed to a method for testing and / or testing the operability of a missile launch device according to claim 6.
  • Preferred embodiments of the invention having additional design details and further advantages are described and explained in more detail below with reference to the accompanying drawings.
  • a missile launch device 1 is shown, which is mounted on a likewise schematically illustrated carrier vehicle 2 and forms a launcher L together with this.
  • the missile launch device 1 is provided with two launch devices 10, 12, each receiving four missiles 10A, 10B, 10C, 10D and 12A, 12B, 12C, 12D.
  • Each of the starting devices 10, 12 has an electrical connection device 100 or 120, which respectively have communication connections 101, 102, 103, 104 or 121, 122, 123, 124 for the respective unidirectional and / or bidirectional data transmission with a respectively assigned missile 10A, 10B, 10C, 10D and 12A, 12B, 12C, 12D, respectively.
  • connection devices 100, 120 are each connected to a weapon control computer 14 of the missile launch device 1 for data transmission.
  • the weapon control computer 14 is provided in addition to a central processing unit 140 with a first missile interface module 141 and a second missile interface module 142, each forming an interface for data transmission between the weapon control computer 14 and the first electrical connection device 100 and the second electrical connection device 120 of the starting device 10 and 12 and associated with these. Furthermore, the weapon control computer 14 is provided with a power supply unit 143 which supplies the first starter 10 and the second starter 12 with electric power.
  • the weapon control computer 14 also has an operating unit 144 for the missile launch device 1, by means of which the missile launch device 1 can be operated directly. Finally, the weapon control computer 14 is still provided with an internal diagnostic unit 145.
  • the central computer unit 140 of the weapon control computer 14 is connected to a navigation and localization unit 15 provided in the missile launch device 1, for example via a serial interface 146 of the weapon control computer 14.
  • the weapon control computer 14 is connected via a data line, for example an Ethernet line, to a portable maintenance aid device 11 of the missile launch device 1.
  • the weapon control computer 14 is also connected via a data line, such as an Ethernet line, to a power supply unit 13 of the missile launcher 1.
  • the weapon control computer 14 is connected via a further data line, for example likewise an Ethernet line, to a hydraulic control device 17, which acts on the launch devices for the missiles and aligns them for launching the missile in a predetermined manner.
  • the hydraulic control device 17 further controls the movements of an antenna mast, on which the receiving antenna 160 and optionally also a voice radio receiving antenna for receiving the sent over the radiotelephone 34 to the radio transceiver 36 signals is formed.
  • the hydraulic control device 17 is connected via an, for example serial, data connection to an antenna control operator panel 18 in a data transmission connection.
  • the central computer unit 140 of the weapon control computer 14 is furthermore connected via a data connection 147, for example via an Ethernet connection or via an internal data bus, to a communication system 16 integrated in the missile launch device 1.
  • An external weapon system center 3 communicates with the weapon control computer 14 via the communication system 16.
  • the communication between the weapon system center 3 and the missile launch device 1 can take place in three different ways, namely either via a radio link 30 designed for data transmission, wired via a data line connection 32 or over a radiotelephone 34, which leads to a radio transceiver 36 in the host vehicle 2 and transmitted via the commands to an operator located on or on the carrier vehicle 2, then these commands manually via the control unit 144 in enters the weapon control computer 14.
  • the communication system 16 is provided with an antenna element 160 and a transceiver unit 162 for receiving the signals transmitted via the wireless communication link 30. Furthermore, the communication system 16 has a communication computer 164, which is connected on the one hand to the transceiver unit 162 and on the other hand via the internal data line 147 to the central processing unit 140 of the weapon control computer 14.
  • the communication computer 164 is provided with at least one encrypted-working board computer 165 and at least one unencrypted board computer 166 and with an encryption / decryption device 167.
  • missile launch device 1 receives commands from a weapons system center 3 and converts these commands into control commands for the launch devices 10, 12 and the missiles attached to them. Furthermore, the missile launch device reports internal state data as well as feedback of the missile to the weapon system center.
  • This operational operation must be conducted reliably and without disruption, so that the corresponding mission is not endangered.
  • a missile launch device especially in peacetime, not only after the manufacture and delivery to the customer, but also in rotation during a later unused stay must be checked.
  • the missile launch device 1 is to be tested to ensure that it is suitable for error-free operational operation.
  • test and test device 4 is provided according to the invention, which is explained below with reference to the other figures.
  • Fig. 2 shows a first variant of the tester 4 connected to the missile launch device 1.
  • the test and test device 4 has a test and test computer 40, a missile simulation unit 42 and a data transmission device 44.
  • the missile simulation unit 42 and the data transmission device 44 are each connected via a data transmission connection 41, 43, for example, in each case a data transmission cable, with the test and test computer 40 for data transmission.
  • the missile simulation unit 42 has a signal adaptation device 46, which is connected to a simulation computer 48 of the missile simulation unit 42 for data transmission.
  • the signal adaptation device 46 is further configured to be connected to the communication ports 101, 102, 103, 104, 121, 122, 123, 124 of the starting device 10, 12 for data transmission.
  • the signals generated in the simulation computer 48 are adjusted such that the weapon control computer 14 of the launch device 1 can not determine that instead of a real missile only one missile simulator is connected.
  • the simulation computer 48 is connectable to the test and test computer 40 and is configured and controlled by the latter.
  • the data transmission device 44 is provided with an encryption / decryption device 440 and a transceiver 442, which are connected to one another and to the test and test computer 40.
  • the transceiver 442 is further connected to an antenna 444, from which a wireless data transmission link 446 to the antenna element 160 of FIG Transmitter-receiver unit 160 of the communication system 16 of the missile starting device 1 is formed.
  • the test and test computer 40 communicates with the central processing unit 140 of the weapon control computer 14 via the communication link 446 and the communication system 16 of the missile launcher 1. At the same time, the test and test computer 40 communicates via the communication link 41 with the missile simulation unit 42 facing the weapon control computer 14 simulates the presence of one or more missiles. In the in Fig. 2 As shown, the missile simulation unit 42 simulates the presence of the four in Fig. 1 shown missiles 12A, 12B, 12C and 12D.
  • Test and test set-up shown can be run through a function sequence representing the operational use, a local start-up of the missile launcher 1, its connection to the simulated by the test and test computer 40 external weapons system headquarters, the remote control of the missile launcher 1 by the simulated Kumarsystemmod and the triggering and Execution of the missile launch sequence of the simulated by the missile simulation unit 42 missile.
  • these tests can verify safety-critical features, such as the detection and handling of Misfire or Hangfire situations.
  • the original, operational function chains and processes as well as self-test functions are activated and run through.
  • test and test computer 40 corresponding error messages via a human-machine interface the operator given note, for example, displayed on a screen.
  • Fig. 3 shows a variant in which, in addition to the encrypted data transmission via the wireless data transmission connection 446, a data line 401 from a breakout box 147 'in the data processing connection 147 connecting the central processing unit 140 of the weapon control computer 14 to the communication computer 164 of the communication system 16 via a monitoring data line 400 leads to a monitoring and data recording device 45 of the test and test computer 40. Via this connection, the data traffic running via the internal data connection 147 of the missile launch device 1 can be monitored and recorded by the test and test computer 40.
  • the data streams 402 running inside the weapon control computer 14 are monitored and recorded via a data line 402 connecting the weapon control computer 14 to the monitoring data line 400.
  • Fig. 4 shows an alternative test and test setup in which the data transmission device 44 of the test and test device 4 is not wirelessly connected to the communication system 16 of the missile launcher 1, but via a data transmission line 448, the encrypted, cable-controlled communication of the test and test computer 40 with the missile launch device 1 allows.
  • the antennas 444 and 160 and the wireless data transmission connection 446 are coupled out, so that the radio link is turned off as a possible source of error.
  • FIG. 5 shows a connection of the data transmission device 44 of the testing and test device 4 via a data transmission line 449, for example, an Ethernet connection to the communication computer 164 of the communication system 16 of the missile launcher 1.
  • a data transmission line 449 for example, an Ethernet connection
  • this data line 449 which may be configured, for example, as an Ethernet connection
  • FIG. 6 An alternative variant to that in Fig. 5 shown test and test setup is in Fig. 6 represented, wherein the data transmission line 449 'not with the encrypted board computer 165, but with the unencrypted working Board computer 166 is connected so that over the data line 449 unencrypted signals between the communication computer 164 and the test and test computer 40 are transmitted.
  • FIG. 7 Another alternative shows Fig. 7
  • a telemetry data link 450 is provided which connects a telemetry data interface 148 of the weapon control computer 14 directly to the test and test computer 40.
  • this telemetry data link 450 internally processed data of the missile launcher 1 can be sent directly and unencrypted to the test and test computer 40, so that the test and test computer 40 not only on the outward data links (wireless data link 446 and the data transmission links to the missile simulation unit 42 ) can perform a black-box test, but by means of the additionally obtained telemetry data in the internal data traffic of the missile launcher 1 can take insight and thus obtains a so-called white-box look at the activities of the missile launcher 1 without the missile launcher special Breakout Boxing such as 147 'in Figure 3 must be installed.
  • a simulator for the external weapon system center formed by the test and test computer 40
  • a missile simulator formed by the missile simulation unit 42
  • an analysis device for the telemetry data is also formed by the test and test computer 40.
  • the external weapon system central simulator formed by the test and test computer 40
  • the missile simulation unit 42 By means of the external weapon system central simulator (formed by the test and test computer 40) and the missile simulation unit 42, the external interfaces of the missile launch device 1 are stimulated.
  • the behavior of The simulated external weapon system center and the missile simulation unit 42 can be configured via the test and test software running on the test and test computer 40, so that the measured actual reaction of the missile launch device 1 against the configured target reaction at the external interfaces can be checked. This corresponds to the so-called black box view.
  • the analysis device for the telemetry data which is also implemented as software on the test and test computer 40, the internal data traffic of the missile launcher 1 to the outside becomes transparent, without the need for special devices, such as the connection of special cables is required.
  • the telemetry data can also be transmitted wirelessly to the test and test computer, for example.
  • the telemetry data analyzer implemented in the software allows external stimulation applied by the test and test computer 40 and the missile simulation unit 42 to the missile launch device 1 to check whether the internal information flow in the missile launch device 1 does not map the external stimulation correctly , This so-called white-box view enables the function check not only based on the external reactions and responses but also by checking the internal processes and in case of error, the determination of the internal causes of failure.
  • the telemetry interface can be designed to be activatable and deactivatable, wherein it is active, for example, when the test and test device 4 is connected to the missile launch device 1 and wherein it is deactivated when the missile launch device in the in Fig. 1 illustrated operational network interacts with the external weapon system center 3 and attached to the missile launch device 1 missiles.
  • the activation of the telemetry interface can be done automatically by the missile start device 1 automatically detects whether the test and test device 4 is connected.

Claims (7)

  1. Dispositif de vérification et de test pour un appareil de démarrage de missile (1), qui comporte au moins un dispositif de démarrage (10 ; 12) pour au moins un missile (10A, 10B, 10C, 10D ; 12A, 12B, 12C, 12D) et un ordinateur de commande d'armes (14), qui est associé au dispositif de démarrage et peut être commandé par une centrale de système d'armes (3) et sur lequel un programme de commande pour le démarrage du missile est installé de manière à pouvoir être exécuté,
    dans lequel le dispositif de démarrage (10 ; 12) comporte au moins un moyen de raccordement électrique (100 ; 120), qui est relié à l'ordinateur de commande d'armes (14) pour la transmission de données et qui est associé à l'au moins un missile (10A, 10B, 10C, 10D ; 12A, 12B, 12C, 12D) et peut être relié à celui-ci et qui comporte des ports de communication (101, 102, 103, 104 ; 121, 122, 123, 124) pour la transmission de données unidirectionnelle et/ou bidirectionnelle vers le missile (10A, 10B, 10C, 10D ; 12A, 12B, 12C, 12D),
    dans lequel le dispositif de vérification et de test comporte :
    - un ordinateur de vérification et de test (40), qui est conçu comme simulateur pour au moins une partie des fonctions de la centrale de système d'armes (3) et qui peut être relié à l'ordinateur de commande d'armes (14) pour la transmission de données ; et
    - au moins une unité de simulation de missile (42) reliée à l'ordinateur de vérification et de test (40) pour l'échange de données, comprenant un ordinateur de simulation (48), qui peut être commandé par l'ordinateur de vérification et de test (40) pour générer des signaux de simulation, et comprenant un moyen d'adaptation de signal (46), qui est relié à l'ordinateur de simulation (48) pour la transmission de données et qui peut être relié aux ports de communication (101, 102, 103, 104 ; 121, 122, 123, 124) du moyen de raccordement électrique (100 ; 120) du dispositif de démarrage (10 ; 12) pour la transmission de données.
  2. Dispositif de vérification et de test selon la revendication 1, caractérisé en ce que
    l'ordinateur de vérification et de test (40) est relié à un moyen de transmission de données (44) pour la transmission de données, qui peut être relié sans fil ou par câble à l'ordinateur de commande d'armes (14) pour la transmission de données.
  3. Dispositif de vérification et de test selon la revendication 1 ou 2, caractérisé en ce que
    l'ordinateur de vérification et de test (40) peut être relié directement à l'ordinateur de commande d'armes (14) par le biais d'une ligne de données pour la transmission de données.
  4. Dispositif de vérification et de test selon l'une des revendications précédentes, caractérisé en ce que l'ordinateur de vérification et de test (40) peut être relié à une interface de données télémétriques (148) de l'ordinateur de commande d'armes (14) pour la transmission de données.
  5. Unité constituée d'un appareil de démarrage de missile, qui comporte au moins un dispositif de démarrage (10 ; 12) pour au moins un missile et un ordinateur de commande d'armes (14), qui est associé au dispositif de démarrage et sur lequel un programme de commande pour le démarrage du missile est installé de manière à pouvoir être exécuté,
    et dans laquelle le dispositif de démarrage (10 ; 12) est pourvu d'au moins un moyen de raccordement électrique (100 ; 120), qui est relié à l'ordinateur de commande d'armes (14) pour la transmission de données et qui est associé à l'au moins un missile (10A, 10B, 10C, 10D ; 12A, 12B, 12C, 12D) et peut être relié à celui-ci et qui comporte des ports de communication (101, 102, 103, 104 ; 121, 122, 123, 124) pour la transmission de données unidirectionnelle et/ou bidirectionnelle vers le missile (10A, 10B, 10C, 10D ; 12A, 12B, 12C, 12D), et d'un dispositif de vérification et de test (4) selon l'une des revendications précédentes.
  6. Procédé de vérification et/ou de test de la capacité de fonctionnement d'un appareil de démarrage de missile, qui comporte au moins un dispositif de démarrage (10 ; 12) pour au moins un missile (10A, 10B, 10C, 10D ; 12A, 12B, 12C, 12D) et un ordinateur de commande d'armes (14), qui est associé au dispositif de démarrage et sur lequel un programme de commande pour le démarrage du missile est installé de manière à pouvoir être exécuté, le dispositif de démarrage (10 ; 12) comportant au moins un moyen de raccordement électrique (100 ; 120), qui est relié à l'ordinateur de commande d'armes (14) pour la transmission de données et qui est associé à l'au moins un missile (10A, 10B, 10C, 10D ; 12A, 12B, 12C, 12D) et peut être relié à celui-ci et comportant des ports de communication (101, 102, 103, 104 ; 121, 122, 123, 124) pour la transmission de données unidirectionnelle et/ou bidirectionnelle vers le missile (10A, 10B, 10C, 10D ; 12A, 12B, 12C, 12D), comprenant un dispositif de vérification et de test (4) selon l'une des revendications 1 à 4, le procédé comportant les étapes suivantes consistant à :
    simuler au moins une partie des fonctions de la centrale de système d'armes (3) au moyen de l'ordinateur de vérification et de test (40) relié à l'ordinateur de commande d'armes (14),
    transformer les fonctions simulées de la centrale de système d'armes (3) en instructions de commande pour le missile (10A, 10B, 10C, 10D ; 12A, 12B, 12C, 12D) au moyen de l'ordinateur de commande d'armes (14) et
    simuler les fonctions du missile (10A, 10B, 10C, 10D ; 12A, 12B, 12C, 12D) au moyen de l'unité de simulation de missile (42), la simulation des fonctions du missile (10A, 10B, 10C, 10D ; 12A, 12B, 12C, 12D) comprenant une génération de signaux de simulation au moyen de l'ordinateur de simulation (48) de l'unité de simulation de missile (42) et une adaptation des signaux de simulation au moyen du moyen d'adaptation de signal (46).
  7. Procédé selon la revendication 6,
    caractérisé en ce que
    le moyen d'adaptation de signal (46) adapte les signaux de simulation générés par l'ordinateur de simulation (48) de l'unité de simulation de missile (42) de telle manière qu'il est impossible de constater au moyen de l'ordinateur de commande d'armes (14) si un missile ou l'unité de simulation de missile (42) est raccordé aux ports de communication (101, 102, 103, 104 ; 121, 122, 123, 124) du dispositif de démarrage (10 ; 12).
EP13000176.1A 2012-01-17 2013-01-14 Dispositif de vérification et de test pour un appareil de démarrage de corps volant et procédé de vérification et/ou de test de la capacité de fonctionnement d'un appareil de démarrage de corps volant Active EP2618099B8 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102012000671.3A DE102012000671B4 (de) 2012-01-17 2012-01-17 Prüf- und Testvorrichtung für ein Flugkörperstartgerät und Verfahren zum Prüfen und/oder Testen der Funktionsfähigkeit eines Flugkörperstartgeräts

Publications (4)

Publication Number Publication Date
EP2618099A2 EP2618099A2 (fr) 2013-07-24
EP2618099A3 EP2618099A3 (fr) 2015-08-12
EP2618099B1 true EP2618099B1 (fr) 2017-06-07
EP2618099B8 EP2618099B8 (fr) 2017-08-09

Family

ID=47603207

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13000176.1A Active EP2618099B8 (fr) 2012-01-17 2013-01-14 Dispositif de vérification et de test pour un appareil de démarrage de corps volant et procédé de vérification et/ou de test de la capacité de fonctionnement d'un appareil de démarrage de corps volant

Country Status (2)

Country Link
EP (1) EP2618099B8 (fr)
DE (1) DE102012000671B4 (fr)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013014570B4 (de) * 2013-09-02 2018-06-14 Mbda Deutschland Gmbh Verfahren zum Einschalten einer Treibstoffpumpe eines fliegenden Flugkörpers
CN104503259A (zh) * 2014-11-27 2015-04-08 北京电子工程总体研究所 发控系统用通用可编程飞行器模拟器系统
DE202015004074U1 (de) 2015-02-27 2016-05-31 Mbda Deutschland Gmbh Flugkörper-Startvorrichtung
DE102015002563B3 (de) * 2015-02-27 2016-02-11 Mbda Deutschland Gmbh Flugkörper-Startvorrichtung
DE102015006799B4 (de) * 2015-05-27 2022-11-17 Mbda Deutschland Gmbh Testeinrichtung für eine Flugkörper-Startvorrichtung
CN105403110A (zh) * 2015-12-15 2016-03-16 平顶山宇恒高科电气自动化有限公司 一种自校正检测精度的发爆器测试仪
DE102016000121A1 (de) 2016-01-08 2017-07-13 Mbda Deutschland Gmbh Multifunktionale Prüfvorrichtung für eine Bewaffnung
US10156426B2 (en) 2016-06-21 2018-12-18 The United States Of America, As Represented By The Secretary Of The Navy Apparatus and methods for parallel testing of devices
DE102016008413A1 (de) 2016-07-13 2018-01-18 Mbda Deutschland Gmbh Multifunktionsbedien- und Anzeigesystem
CN108761155A (zh) * 2018-06-05 2018-11-06 北京电子工程总体研究所 一种可配置动力装置模拟系统
CN112344810B (zh) * 2020-09-11 2022-12-13 中国运载火箭技术研究院 导弹武器测试设备
DE202021104039U1 (de) 2021-07-28 2022-11-03 Spherea Gmbh Prüfgerät für eine Selbstschutzanlage eines Luftfahrzeugs

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0309133A2 (fr) * 1987-09-11 1989-03-29 British Aerospace Public Limited Company Simulateur d'armes numérique
CA2100156C (fr) * 1992-07-13 1998-07-28 Ronald W. Monk Methode et appareil pour l'essai des interfaces d'interconnexion de missile
US5624264A (en) * 1995-09-29 1997-04-29 The United States Of America As Represented By The Secretary Of The Navy Missile launch simulator
US7228261B2 (en) * 2003-08-13 2007-06-05 The Boeing Company Methods and apparatus for testing and diagnosis of weapon control systems
US6941850B1 (en) * 2004-01-09 2005-09-13 Raytheon Company Self-contained airborne smart weapon umbilical control cable
US20060288194A1 (en) * 2005-06-17 2006-12-21 Lewis Innovative Technologies Real-time processor
DE102005058546A1 (de) * 2005-12-08 2007-06-14 Lfk-Lenkflugkörpersysteme Gmbh Waffenstations-Testeinheit und Verfahren zum Testen der Einsatzbereitschaft einer Waffenstation eines Luftfahrzeugs
DE102009040304B4 (de) * 2009-09-05 2012-10-04 Lfk-Lenkflugkörpersysteme Gmbh Vorrichtung zur Steuerung von Funktionstests und/oder Serviceprozeduren für von Luftfahrzeugen absetzbare unbemannte Flugkörper

Also Published As

Publication number Publication date
DE102012000671A1 (de) 2013-07-18
EP2618099A3 (fr) 2015-08-12
EP2618099A2 (fr) 2013-07-24
EP2618099B8 (fr) 2017-08-09
DE102012000671B4 (de) 2014-07-17

Similar Documents

Publication Publication Date Title
EP2618099B1 (fr) Dispositif de vérification et de test pour un appareil de démarrage de corps volant et procédé de vérification et/ou de test de la capacité de fonctionnement d'un appareil de démarrage de corps volant
EP2293008B1 (fr) Dispositif de commande de tests fonctionnels et/ou de procédures de service pour aéronefs sans conducteur pouvant être déposés par des avions
EP3270092B1 (fr) Véhicule d'opération militaire avec système d'affichage et de commande multifonctions
EP1795858B1 (fr) Unité de test de station d'armement et procédé pour tester la disponibilité d'une station d'armement d'un aéronef
EP1923658B1 (fr) Procédé de vérification de la capacité d'interaction entre un aéronef et un corps volant non habité armé pouvant être couplé avec celui-ci
EP2390615B1 (fr) Procédé de demande de données de mesure et/ou d'état à partir d'un enregistreur de données d'un corps volant inhabité armé et dispositif destiné à l'exécution du procédé
DE102012017891B4 (de) Verfahren zum Testen der korrekten Kommunikation zwischen einem Flugkörper und einem Trägerflugzeug und Flugkörpertestvorrichtung
EP2648103A2 (fr) Procédé et dispositif d'intégration de systèmes techniques
EP2160854B1 (fr) Procédé pour générer une séquence de signaux pouvant être lue sur un testeur pour tester un appareil radioélectrique mobile
EP3384411B1 (fr) Dispositif de transmission d'une instruction fonctionnelle entre un véhicule automobile et un dispositif extérieur au véhicule, et dispositif d'interface et système
DE102013224809A1 (de) Verfahren zum Testen eines Steuergeräts für ein Fahrzeug sowie entsprechendes Steuergerät, System und Fahrzeug
EP2672660A1 (fr) Méthode pur influencer le communication de bus d'un bloc de contrôle électronique
DE102016118200A1 (de) Systemanordnung für Sicherheitsüberprüfungen sowie Verfahren
DE102015219837A1 (de) Verfahren zum Bereitstellen einer Software
DE102019211118A1 (de) Verfahren zum Testen eines Kraftfahrzeugs
EP2984495B1 (fr) Environnement de test pouvant être utilisé par plusieurs utilisateurs pour une pluralité d'objets à tester
DE102019111558A1 (de) Verfahren und system zum testen von systemen
DE102014007325B3 (de) Rakete mit mehreren Stufen
DE102004051834B4 (de) Prüfgerät und Prüfverfahren für programmierbare Elektroinstallationen, sowie entsprechendes Computerprogramm und entsprechendes computerlesbares Speichermedium
DE102012104842A1 (de) Verfahren zur Beeinflussung der Buskommunikation eines Steuergeräts
EP3190378B1 (fr) Dispositif d'essai multifonctionnel pour l'armement
DE102010055866A1 (de) Verfahren zum Testen einer Erkennungsvorrichtung und Testvorrichtung
EP2878965A1 (fr) Procédé de vérification d'un appareil de commande pour un véhicule et appareil de commande pour un véhicule doté d'un dispositif de diagnostic
DE102010052177A1 (de) Verfahren zum Prüfen eines Steuergeräts
EP4202585A1 (fr) Structure de test et procédé de test d'un appareil de commande

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIC1 Information provided on ipc code assigned before grant

Ipc: F42B 35/00 20060101AFI20150707BHEP

Ipc: F41G 7/00 20060101ALI20150707BHEP

Ipc: F41A 31/00 20060101ALI20150707BHEP

17P Request for examination filed

Effective date: 20160209

17Q First examination report despatched

Effective date: 20160908

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20170223

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

REG Reference to a national code

Ref country code: DE

Ref legal event code: R108

Ref document number: 502013007409

Country of ref document: DE

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 899569

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170615

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502013007409

Country of ref document: DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R107

Ref document number: 502013007409

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20170607

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170908

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170907

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170907

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 6

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171007

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

26N No opposition filed

Effective date: 20180308

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180114

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20180131

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180131

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180131

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180131

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180114

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 899569

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180114

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180114

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20130114

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170607

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170607

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230124

Year of fee payment: 11

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20230119

Year of fee payment: 11

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230509