EP2618099A2 - 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 PDFInfo
- Publication number
- EP2618099A2 EP2618099A2 EP13000176.1A EP13000176A EP2618099A2 EP 2618099 A2 EP2618099 A2 EP 2618099A2 EP 13000176 A EP13000176 A EP 13000176A EP 2618099 A2 EP2618099 A2 EP 2618099A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- test
- missile
- computer
- testing
- data transmission
- 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.)
- Granted
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 217
- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000004891 communication Methods 0.000 claims abstract description 53
- 238000004088 simulation Methods 0.000 claims abstract description 40
- 230000005540 biological transmission Effects 0.000 claims description 56
- 230000006978 adaptation Effects 0.000 claims description 7
- 230000002457 bidirectional effect Effects 0.000 claims description 7
- 238000007689 inspection Methods 0.000 abstract description 4
- 230000008569 process Effects 0.000 description 8
- 238000012545 processing Methods 0.000 description 6
- 239000007858 starting material Substances 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 3
- 230000000875 corresponding effect Effects 0.000 description 3
- 238000012544 monitoring process Methods 0.000 description 3
- 230000004044 response Effects 0.000 description 3
- 230000004913 activation Effects 0.000 description 2
- 235000000332 black box Nutrition 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000013100 final test Methods 0.000 description 2
- 230000004807 localization Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000000638 stimulation Effects 0.000 description 2
- 238000012956 testing procedure Methods 0.000 description 2
- 238000005094 computer simulation Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
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 testing and testing 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 termination device associated with 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 controlled by a weapon system center remotely located from the respective site, and since the weapon system center is typically a constantly occupied and always active device, the operation of the weapon system center should not be affected by any testing 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 test and test device for a missile launch device, as indicated in the preamble of patent claim 1, with which the functionality of the missile launch device can be tested at any time at different locations and with which also individual functions of the Missile launcher device can be tested. 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.
- the test and test device has a test and test computer and at least one missile simulation unit.
- the test and test computer is designed as a simulator for at least part of the functions of the weapons system headquarters and it is connectable to the weapon control computer for data transmission.
- the missile simulation unit is on the one hand connected to the test and test computer for data exchange and on the other hand it is with the Communication terminals of the electrical connection device of the starting device connectable.
- 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 which can be controlled by the test and test computer, the possibilities for carrying out a test of the missile starting device are thereby significantly increased since this simulates different variants of missile starting processes and, for example, complex missile defects and verifies their correct reaction can.
- 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 having 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 Starting device is provided with at least one electrical connection device which is connected to the data transmission with the weapon control computer and which is assigned to the at least one missile and connectable to this and has communication ports for unidirectional and / or bidirectional data transmission to the missile.
- the testing and / or testing of the functionality of the missile launcher takes place with a test and test device according to the present invention, wherein for performing the method at least a part of the functions of the weapon system center is simulated by the test and test computer and simulates functions of the missile from the missile simulation unit become.
- This method according to the invention makes it possible to carry out tests and inspections of missile launch devices in a quick and simple manner, without them having to be provided with a sharp missile and without them having to be connected to a weapon system central.
- 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 via 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 simulated external strengsystemzentrafe and the missile simulation unit 42 is configurable via the running on the test and test computer 40 testing and test software, so that the measured actual response of the missile launcher 1 can be tested against the configured target response to the external interfaces. 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 is 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.
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 true EP2618099A2 (fr) | 2013-07-24 |
EP2618099A3 EP2618099A3 (fr) | 2015-08-12 |
EP2618099B1 EP2618099B1 (fr) | 2017-06-07 |
EP2618099B8 EP2618099B8 (fr) | 2017-08-09 |
Family
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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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)
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EP (1) | EP2618099B8 (fr) |
DE (1) | DE102012000671B4 (fr) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
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 |
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 |
CN112344810A (zh) * | 2020-09-11 | 2021-02-09 | 中国运载火箭技术研究院 | 导弹武器测试设备 |
CN112749480A (zh) * | 2020-12-21 | 2021-05-04 | 北京航天飞腾装备技术有限责任公司 | 一种使用炸弹模拟器与载机联试的方法 |
Families Citing this family (8)
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 |
DE102015002563B3 (de) * | 2015-02-27 | 2016-02-11 | Mbda Deutschland Gmbh | Flugkörper-Startvorrichtung |
DE202015004074U1 (de) * | 2015-02-27 | 2016-05-31 | 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 |
DE102016008413A1 (de) | 2016-07-13 | 2018-01-18 | Mbda Deutschland Gmbh | Multifunktionsbedien- und Anzeigesystem |
DE202021104039U1 (de) | 2021-07-28 | 2022-11-03 | Spherea Gmbh | Prüfgerät für eine Selbstschutzanlage eines Luftfahrzeugs |
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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 |
-
2012
- 2012-01-17 DE DE102012000671.3A patent/DE102012000671B4/de active Active
-
2013
- 2013-01-14 EP EP13000176.1A patent/EP2618099B8/fr active Active
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
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 |
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 |
CN112344810A (zh) * | 2020-09-11 | 2021-02-09 | 中国运载火箭技术研究院 | 导弹武器测试设备 |
CN112749480A (zh) * | 2020-12-21 | 2021-05-04 | 北京航天飞腾装备技术有限责任公司 | 一种使用炸弹模拟器与载机联试的方法 |
CN112749480B (zh) * | 2020-12-21 | 2024-04-30 | 北京航天飞腾装备技术有限责任公司 | 一种使用炸弹模拟器与载机联试的方法 |
Also Published As
Publication number | Publication date |
---|---|
DE102012000671B4 (de) | 2014-07-17 |
EP2618099A3 (fr) | 2015-08-12 |
DE102012000671A1 (de) | 2013-07-18 |
EP2618099B8 (fr) | 2017-08-09 |
EP2618099B1 (fr) | 2017-06-07 |
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