DE102015006799B4 - Test facility for a missile launcher - Google Patents

Abstract

Test device for a missile launch device, which has a missile launch device (2) equipped with a weapon computer (3) and at least one launch device (4) accommodating at least one missile (41, 43, 45, 47), the test device (5) comprises at least the following components: - a test computer (51) which has a computer core and at least one data memory connected to the computer core and on which test procedure software is stored so that it can be run, - a first interface device (5A) on the weapon computer side for connecting the test computer (5th ) to the missile launcher (2) or to the weapon computer (3) provided in the missile launcher (2) and- at least one missile-side, second interface device (5B) for connection to the at least one missile (41, 43, 45, 47 ) or to the at least one launching device (4); wherein the test device (5) is designed to be functionally switched into a signal and information flow between the missile launch device (2) and the launch device (4) in such a way that electrical connections and signal and data lines between the missile launch device ( 2) and the launching device (4) are guided through the test device (5).

Description

TECHNICAL AREA

The present invention relates to a test device for a missile launcher, which has a missile launcher equipped with a weapon computer and at least one launching device accommodating at least one missile, according to the preamble of patent claim 1. The invention also relates to a missile launcher with an integrated or integratable Test functionality, wherein the missile launch device has a missile launch device equipped with a weapon computer and at least one launching device accommodating at least one missile, according to the preamble of patent claim 3.

BACKGROUND OF THE INVENTION

The correct interaction of a missile launcher with a launcher receiving the missile or missiles is essential for the functioning of a missile launcher formed from these components. It should be noted here that a missile launcher must be able to interact with a plurality of launching devices and thus with a large number of missiles. In peacetime, the missiles are usually stored in the depot — individually or together with the launching device that accommodates them — and are only coupled to the missile launcher in the event of an operation or for shooting campaigns. Although the individual missiles and their launch devices are tested in the depot at specified intervals and at different test depths, these tests do not guarantee that the interaction between a missile launch device and the respective launch device or the respective missile functions reliably. This can have several causes, which lie, for example, in the cable harness connecting the missile launcher with the launcher or in the weapon computer or in the launcher itself. Therefore, the missile launcher and the associated wiring harnesses are also subjected to routine tests at certain time intervals.

But even if both the launcher with the missiles and the missile launcher with the weapon computer have each passed the corresponding isolated functional tests, it is far from guaranteed that the interaction of these devices will also function reliably. In particular, with increasing storage time and increasing environmental influences, tolerances of individual assemblies can shift, which are not noticeable in isolated routine tests, but which can lead to malfunctions when interacting with other assemblies whose tolerances have also changed.

STATE OF THE ART

Missiles are usually treated as a so-called 'certified missile round', i.e. the missile has a predictable reduction in reliability within a defined certification period (typically 10 years with a service life of 30 years). Within this period, the missile is maintenance-free. Periodic testing of a representative sample of missiles is performed during storage to verify reliability targets. After the certification period has expired, the missile is recertified by testing and, if necessary, replacing degraded or defective components in order to keep the missile in a usable condition and to ensure the required reliability and the expected performance.

1. a. Depot-Zuverlässigkeitstest (Stockpile Reliability Test):
   • eine Flugkörper-Stichprobe wird dem Depot entnommen und zum Hersteller transportiert, um dort visuellen Inspektionen und funktionalen Tests unterzogen zu werden.
2. b. Produktdatenbank (Certified Round Data Management Database):
   • diese Datenbank ermöglicht die Nach-Verfolgbarkeit eines jeden Flugkörpers, wodurch die Flugkörper-Historie (verbaute, getauschte, defekte Komponenten, Zertifizierungen, Testdaten etc.) verfügbar wird und Trends erkannt werden können.
3. c. Depot- und Alterungsprogramm (Storage and Aging Program):
   • ausgewählte Flugkörper-Komponenten werden an unterschiedlichen klimatischen Orten gespeichert (heiß, kalt, feucht und nominal in gemäßigter Klimazone) und periodisch geprüft, um Trends auszuprägen und zu analysieren.
4. d. Schießkampagne (Missile Firing Program):
   • Los-Abnahmeschießen während der Produktion werden durchgeführt, um sicherzustellen, dass nur qualitativ hochwertige Flugkörper eingelagert werden. Los-Verifizierungsschiessen während der Nutzungsphase überprüfen Leistungsparameter, detektieren Trends und analysieren Driften von kritischen Parametern bevor Spezifikationsgrenzen überschritten werden.

A typical missile surveillance program consists of the following elements:

1. a. Stockpile Reliability Test:
   • a missile sample is taken from the depot and shipped to the manufacturer for visual inspection and functional testing.
2. b. Product database (Certified Round Data Management Database):
   • this database enables the traceability of each missile, whereby the missile history (installed, exchanged, defective components, certifications, test data, etc.) becomes available and trends can be identified.
3. c. Storage and Aging Program:
   • selected missile components are stored in different climatic locations (hot, cold, humid and nominally temperate) and periodically tested to identify and analyze trends.
4. i.e. Missile Firing Program:
   • Lot acceptance shooting during production is carried out to ensure only high quality missiles are stored. Lot verification shoots during the use phase check performance parameters, detect trends and analyze drifts of critical parameters before specification limits are exceeded.

In addition to theoretical reliability models (flight reliability, on-launcher reliability, long-term storage reliability), this missile monitoring program is the primary source of information intended to ensure that a missile with high reliability can be used by military users at any time.

• - während der Lagerung am Depot (am Heimatstandort)
• - nach Transport (zum Einsatzstandort)
• - vor und während des Einsatzes (am Einsatzstandort)
• - vor Übergabe an den Hersteller bzw. nach Erhalt vom Hersteller (am Heimatstandort oder Herstellerstandort)

erforderlich ist.The logistical user experiences with known missile systems show that in military practice the review of the missile functions

• - during storage at the depot (at the home location)
• - after transport (to the deployment site)
• - before and during the mission (at the mission site)
• - before handover to the manufacturer or after receipt from the manufacturer (at home location or manufacturer location)

is required.

However, the operational capability of a missile or a launching device receiving the missile(s) must not only be considered in isolation, but must also be given in the combination of (any) launching device with (any) missiles and (any) missile launch device. For this purpose, the functionality of missile launch devices has been tested with the missile emulating test devices. In the interaction of one of the aforementioned combinations, however, errors can still occur which, in extreme cases, can result in the loss of a missile.

the DE 10 2012 000 671 B4 US Pat. The missile launcher to be checked or tested is detached from the task force to carry out the check or test and assumes a depot or maintenance status. This checking and testing device is connected to those interfaces of a missile launcher that are provided for the connection to the weapon system center and to the missiles. Both the weapon system center and the missiles are simulated in the test facility.

PRESENTATION OF THE INVENTION

The object of the present invention is therefore to specify a test device for a missile launcher with which it is possible to test the interaction of a missile launcher with a launcher receiving the missiles in the operational state before this combination is released for operational use becomes. Furthermore, it is the object of the present invention to specify a missile launch device with integrated or integrable test functionality, which is equipped or can be equipped with such a test device.

The part of the task related to the test device is solved by the test device with the features of patent claim 1.

• - einen Testcomputer, der einen Rechnerkern sowie zumindest einen mit dem Rechnerkern verbundenen Datenspeicher aufweist und auf dem eine Testprozedur-Software ablaufbar gespeichert ist,
• - eine waffenrechnerseitige, erste Schnittstelleneinrichtung zum Anschluss des Testcomputers an das Flugkörper-Startgerät oder an den im Flugkörper-Startgerät vorgesehenen Waffenrechner und
• - zumindest eine flugkörperseitige, zweite Schnittstelleneinrichtung zum Anschluss an den zumindest einen Flugkörper oder an die zumindest eine Abschusseinrichtung.

For this purpose, in a test device for a missile launcher, which has a missile launcher that is or can be connected to a weapon system control center and is equipped with a weapon computer, and at least one launch device that has at least one missile, the invention provides that the test device comprises at least the following components:

• - a test computer, which has a computer core and at least one data memory connected to the computer core and on which test procedure software is stored so that it can run,
• - A first interface device on the weapon computer side for connecting the test computer to the missile launcher or to the weapon computer provided in the missile launcher and
• - At least one second interface device on the missile side for connection to the at least one missile or to the at least one launch device.

ADVANTAGES

The configuration of this test device with a first interface device on the weapon computer side and a second interface device on the missile side makes it possible to operate this test device between the missile launcher and the launching device, and thereby both the missile launcher with the weapon computer and the launching device provided with the missiles to test and monitor with the at least one missile.

In an advantageous development of this test device, the test procedure software running in the test device is designed in such a way that it can forward control signals, which are received via the first interface device on the weapon computer side, to the second interface device on the missile side, or block them. This makes it possible for the test device to block certain control signals, for example control signals for carrying out irreversible actions, and not to pass them on to the launch device or the missiles located there.

The part of the task related to the missile launcher is solved by a missile launcher having the features of patent claim 3.

This missile launcher according to the invention with integrated or integrable test functionality, wherein the missile launcher has a missile launcher connected or connectable to a weapon system control center and equipped with a weapon computer and at least one launching device having at least one missile, is characterized in that between a test device according to one of the preceding claims is or can be arranged between the weapon computer and the launching device such that the signal and data streams between the weapon computer and the launching device and between the launching device and the weapon computer run through the test device.

This integration of the test device in the unit composed of a missile launcher and at least one launcher equipped with at least one missile not only makes it possible to check these components with the test device, but also allows peripherals, such as connection or connection cables, to be checked in the operational deployment configuration. In addition, this integration of the test facility allows the signal and data traffic between the missile launcher and the launch facility to be recorded and monitored.

Further preferred and advantageous design features of the missile launcher according to the invention are the subject matter of dependent claims 4 to 9.

In this case, the test computer of the test device is preferably connected or can be connected to a monitor line of the missile and is designed in such a way that it can read monitor information from the missile and monitor the missile.

More preferably, the test computer of the test device is connected or can be connected to a data bus of the missile launcher and is designed in such a way that it can send and read data bus messages. This allows the test computer to communicate effectively with the missile launcher.

It is particularly advantageous if the test computer of the test device is designed to send a command to the weapon computer, which starts a test routine implemented in the weapon computer, and that the test computer of the test device is designed to carry out actions and reactions that are carried out by the test routine on the weapon computer side are triggered in the missile or in its launcher, monitored.

With this embodiment of the missile launcher according to the invention, it is possible to run test routines from the test computer of the test facility that are already implemented in the weapon computer, and then the actions and reactions that, triggered by this test routine, take place in the missile or in the launcher , monitor. Although the test routine is triggered by the test computer, the test computer is only an observer during the course of the test routine and does not itself intervene in the test procedure.

In a further advantageous embodiment of the invention, the test procedure software running in the test device is designed in such a way that it stimulates the missile for test purposes and for this purpose sends or forwards control signals to the missile which trigger an action in the missile. In this way, the test device according to the invention can also be used to test a missile or a launcher equipped with the missile in isolation, i.e. without the missile launcher, which is a sensible solution, for example, for routine testing of the missiles in the weapons depot. In this way, the test device has a dual functionality, namely being able to carry out routine tests in the weapons depot and at the same time being able to test the interaction of the missile launch device and the launch device equipped with missiles in an integrated form.

It is also advantageous if the test procedure software running in the test device is designed in such a way that it stimulates the weapon computer for test purposes and for this purpose sends or forwards control signals to the weapon computer which trigger an action in the weapon computer. In this way, on the one hand, it is possible to check the function of the weapon computer and, on the other hand, the already described interaction between the system provided in the missile launcher can be achieved Weapon computers and the missiles contained in the launcher are tested.

Finally, it is also advantageous if the test procedure software running in the test device is designed in such a way that it allows control signals that are provided to trigger reversible actions in the missile to pass from the weapon computer to the launch device and that they control signals that are provided , in order to trigger irreversible actions in the missile, is blocked and not forwarded to the launch facility. This embodiment ensures on the software side that signals which would trigger an irreversible action in the missile are not forwarded to the missile. As a result, this signal flow sub-calculation does not have to be implemented on the hardware side. It is therefore not necessary to use special connection cables for the test operation, but the test can be carried out with the original connection cables intended for operational use.

Preferred exemplary embodiments of the invention with additional design details and further advantages are described and explained in more detail below with reference to the accompanying drawings.

character list

• 1 eine Flugkörper-Startvorrichtung mit integrierter Testeinrichtung;
• 2 eine Testeinrichtung gemäß der Erfindung;
• 3 eine Abwandlung der in 1 dargestellten Flugkörper-Startvorrichtung mit integrierter Testeinrichtung und
• 4 eine erfindungsgemäße Testeinrichtung zum Testen nur einer Abschusseinrichtung.

It shows:

• 1 a missile launcher with integrated test facility;
• 2 a test device according to the invention;
• 3 a modification of the 1 shown missile launcher with integrated test facility and
• 4 a test device according to the invention for testing only one launch device.

ILLUSTRATION OF PREFERRED EMBODIMENTS

1 shows a schematic block diagram of a missile launch device 1 according to the invention with a missile launch device 2, which has a weapon computer 3, a first and a second missile launching device 4, 4' and one between the weapon computer 3 and at least one of the missile launching devices 4, 4' attachable test device 5 according to the invention (Test and Safety Device TSD). The test device 5 can either be provided between the missile launcher 2 and the relevant missile launcher 4, 4', or it can be integrated into the missile launcher 2 in a modular manner. For this purpose, the test device has a first interface device 5A on the weapon computer side and a second interface device 5B on the missile side.

The weapon computer 3 has a weapon computer core 30 which contains the actual computer of the weapon computer 3 . Furthermore, the weapon computer 3 is provided with an AC electric power supply unit 31A for alternating current and a DC electric power supply unit 31B for direct current, each of which is supplied with electric power from the outside via a line (not shown). This external supply voltage can be an AC voltage and/or a DC voltage.

A control unit 30' is integrated into the weapon computer 3 and/or an external control computer can be connected to the weapon computer 3 with a connecting cable, so that the weapon computer 3 can be controlled using the internal control unit 30' or the external control computer.

In the weapon computer 3 there are also two interchangeable missile interface modules (FIM) 32, 33 which are designed, for example, mechanically and electrically as plug-in units and which in this way can be mechanically and electrically interchangeably connected to the weapon computer 3. Electrically, the missile interface modules 32, 33 are each provided with a standardized first electrical interface 32A, 33A inside the weapon computer and are connected to the weapon computer core 30 via this. The missile interface modules 32, 33 each also have a second electrical interface 32B, 33B on the missile launcher side, via which they are connected to an electrical connection panel 20 of the missile launcher 2. A data bus 37 of the weapon computer 3 is connected to a router 38 to which the test device can be connected by means of an external data bus cable 37'.

In addition to the weapon computer, the missile launcher 2 also has an electrical antenna system 21, a communication system 22, a hydraulic missile righting system 24, an energy system 25 and a navigation system 26, which are connected to the weapon computer core 30 via the data bus 37. A communication link with a higher-level weapon system center W and one of these higher-level operations centers Z can be set up via the antennas of the electrical antenna system 21 .

Missile test software is stored in the memory 30" assigned to the computer of the weapon processor core 30 and runs on the computer of the weapon processor core 30 when it is called up.

The two missile launchers 4, 4' are constructed identically, so that only the missile launcher 4 is described below.

In the example shown, the missile launching device 4 has four launch canisters 40, 42, 44, 46 for one missile 41, 43, 45, 47 each. Furthermore, the missile launching device 4 is provided with a distributor device 48 which has a first electrical interface 49 on the launcher side and a second electrical interface 49' on the missile side.

In the operational state, the first electrical interface 49 of the missile launcher 4 on the launcher side is electrically conductively connected or can be connected to the electrical connection panel 20 of the missile launcher 2 via electrical connecting lines of a cable harness K. According to the invention, the test device 5 is installed in an electrically effective manner in the wiring harness K or between the wiring harness K and the launch device-side electrical interface 49 of the missile launch device 4 or the electrical connection panel 20 of the missile launch device 2 or within the missile launch device 2. According to the invention, the electrical connections and the signal and data lines between the missile launcher 2 and the missile launcher 4 are routed through the test device 5 and the test device 5 is thus functionally integrated into the signal and information flow between the missile launcher 2 and the Missile Launcher 4 on.

• - einen TSD-Rechenkern, der einen Testcomputer 51 bildet,
• - eine Milbus-Bus-Steuerungseinheit 52 in folgenden Funktionen: bus control unit (BCU), remote terminal unit (RTU) und bus monitor,
• - Spannungswandler 53,
• - Kurzschlussstecker 54, die im Kabel K' zwischen Flugkörper und TSD flugkörperseitig und ebenso TSD-seitig die Power- und Return-Leitungen folgender Signale kurzschließen: Raketenmotorschärfung, Batteriezündung A und Batteriezündung B,
• - eine Signal-Adaptionselement 55, durch das die Signale, die vom Flugkörper versorgt werden (Monitor-Versorgung) in ihren elektrischen Eigenschaften so transformiert werden, dass sie vom nachstehenden Leistungsmessungselement 56 vermessen (Spannung, Strom, zeitlicher Verlauf) werden können,
• - Leistungsmessungselement 56,
• - Temperatursensor 57, der die die Umgebungstemperatur des Gehäuses 50 ermittelt,
• - Relais 58; alle Signale zwischen der Flugkörper-Abschusseinrichtung 4 und dem Flugkörper-Startgerät 2 sind jeweils durch ein Relais der TSD schaltbar
• - Sicherungen 59; alle Signale zwischen der Flugkörper-Abschusseinrichtung 4 und dem Flugkörper-Startgerät 2 sind jeweils gegen Überlastströme mittels Sicherungen geschützt.

The test device (TSD) 5 has, as in 2 is shown, in addition to a housing 50 (or in another embodiment, a device carrier) the following elements:

• - a TSD computing core, which forms a test computer 51,
• - a Milbus bus control unit 52 with the following functions: bus control unit (BCU), remote terminal unit (RTU) and bus monitor,
• - voltage converter 53,
• - Short-circuit plug 54, which short-circuits the power and return lines of the following signals in the cable K' between missile and TSD on the missile side and also on the TSD side: rocket motor activation, battery ignition A and battery ignition B,
• - a signal adaptation element 55, through which the signals supplied by the missile (monitor supply) are transformed in their electrical properties in such a way that they can be measured by the following power measurement element 56 (voltage, current, time course),
• - power measurement element 56,
• - Temperature sensor 57, which determines the ambient temperature of the housing 50,
• - relay 58; all signals between the missile launcher 4 and the missile launcher 2 can each be switched by a relay of the TSD
• - fuses 59; all signals between the missile launcher 4 and the missile launcher 2 are each protected against overload currents by means of fuses.

• - Der TSD-Rechnerkern 51, auf dem eine TSD-Software als Client läuft, und der mit dem Waffenrechner 3 des Flugkörper-Startgerätes 2, auf dem die Flugkörper-Testsoftware als Server läuft, interagiert. Die TSD-Software überwacht, vermisst, protokolliert und wertet die Interaktionen des Waffenrechners 3 (Rechenkern 30, Flugkörper-Interface-Module 32, 33, AC-Energie-Modul) mit den Startkanistern 40, 42, 44, 46 bzw. den darin aufgenommenen Flugkörpern 41, 43, 45, 47 aus.
• - Die Milbus-Bus-Steuerungseinheit 52 arbeitet als Milbus-Monitor und zeichnet die Milbus-Kommunikation zwischen dem Waffenrechner (BCU) 3 und den Startkanistern 40, 42, 44, 46 bzw. den darin aufgenommenen Flugkörpern 41, 43, 45, 47 auf und stellt die aufgezeichnete Interaktion der TSD-Software zur Auswertung zur Verfügung. Die Milbus-Bus-Steuerungseinheit 52 erkennt startgeräteseitig die Milbus-Botschaft „Kommando Flugkörper-Zündung“ und blockiert flugkörperseitig die Weiterleitung an die Startkanister 40, 42, 44, 46.
• - Kurzschlussstecker 54 sind startgeräteseitig in der TSD vorgesehen, um die Power-Leitungen für die Raketenmotorschärfung, die Batteriezündung A und die Batteriezündung B mit den zugehörigen Return-Leitungen jeweils kurzzuschließen. Kurzschlussstecker sind auch flugkörperseitig in der TSD vorgesehen, um die Power-Leitungen für die Raketenmotorschärfung, die Batteriezündung A und die Batteriezündung B mit den zugehörigen Return-Leitungen jeweils kurzzuschließen.
• - Das Signal-Adaptionselement 55 transformiert alle Signale zwischen dem Waffenrechner 3 und den Flugkörpern in ihren elektrischen Eigenschaften so, dass sie vermessen werden können (Spannung, Strom, zeitlicher Verlauf).
• - Das Leistungsmessungselement 56 vermisst alle Versorgungssignale sowie die Interlockleitung, die der Waffenrechner 3 erzeugt und die zum Flugkörper geliefert werden, bezüglich Spannung, Strom und zeitlichem Verlauf. Vom TSD-Rechenkern werden diese Signale dann ausgewertet. Das Leistungsmessungselement 56 vermisst weiterhin alle Monitorsignale, die der jeweiligen Flugkörper erzeugt und die zum Waffenrechner geliefert werden, bezüglich Spannung, Strom und zeitlichem Verlauf. Diese Signale werden von der TSD vermessen und vom Rechenkern ausgewertet.
• - Der Temperatursensor ermittelt die Umgebungstemperatur des Flugkörper-Startgerätes.
• - Alle Signale zwischen der Abschusseinrichtung 4 und dem Waffenrechner 3 sind jeweils durch ein Relais der TSD schaltbar
• - alle Signale zwischen der Abschusseinrichtung 4 und dem Waffenrechner 3 sind jeweils gegen Übelastströme mittels Sicherungen (Sicherungsautomaten) geschützt.
• - Die TSD-Software läuft auf dem Rechenkern der TSD und interagiert mittels Ethernet-Link mit dem Rechenkern 30 (Flugkörper-Testsoftware) des Waffenrechners 3 in Clientfunktion (fordert von der Flugkörper-Testsoftware Aktionen wie Ein/Ausschalten von Versorgungen oder Senden von Milbus-Botschaften an). Sie steuert die internen Baugruppen der TSD: Milbus-Monitor, Relais, Messaufnehmer und überwacht, vermisst, protokolliert und wertet die Interaktion des Waffenrechners 30 (Rechenkern, FK-Interface- Modul, AC-Energie Modul) mit der Abschusseinrichtung 4 und den in ihr aufgenommenen Flugkörper aus. Sie steuert weiterhin den Testablauf durch Aufträge an die Flugkörper-Testsoftware und an die internen TSD-Baugruppen, wertet Flugkörper-Messdaten aus und generiert ein Testprotokoll, das am Bedienterminal des Waffenrechners 3 angezeigt wird.

the inside 1 The test setup shown requires the following configuration of the TSD 5 test device:

• - The TSD computer core 51, on which TSD software runs as a client, and interacts with the weapon computer 3 of the missile launch device 2, on which the missile test software runs as a server. The TSD software monitors, measures, logs and evaluates the interactions of the weapon computer 3 (computing core 30, missile interface modules 32, 33, AC energy module) with the launch canisters 40, 42, 44, 46 or those contained therein Missiles 41, 43, 45, 47 out.
• - The Milbus bus control unit 52 works as a Milbus monitor and records the Milbus communication between the weapon computer (BCU) 3 and the launch canisters 40, 42, 44, 46 or the missiles 41, 43, 45, 47 accommodated therein and makes the recorded interaction available to the TSD software for evaluation. The Milbus bus control unit 52 recognizes the Milbus message "command missile ignition" on the launch device side and blocks the forwarding to the launch canisters 40, 42, 44, 46 on the missile side.
• - Shorting plugs 54 are provided on the launcher side in the TSD in order to short-circuit the power lines for rocket motor activation, battery ignition A and battery ignition B with the associated return lines. Shorting plugs are also provided on the missile side in the TSD in order to short-circuit the power lines for rocket motor activation, battery ignition A and battery ignition B with the associated return lines.
• - The signal adaptation element 55 transforms all signals between the weapon computer 3 and the missiles in their electrical properties so that they can be measured (voltage, current, time course).
• - The power measurement element 56 measures all supply signals and the interlock line, which generates the weapon computer 3 and which are supplied to the missile, with regard to voltage, current and time profile. These signals are then evaluated by the TSD computing core. The power measurement element 56 also measures all monitor signals that are generated by the respective missile and that are supplied to the weapon computer with regard to voltage, current and time profile. These signals are measured by the TSD and evaluated by the calculation core.
• - The temperature sensor determines the ambient temperature of the missile launcher.
• - All signals between the firing device 4 and the weapon computer 3 can each be switched by a relay of the TSD
• - All signals between the firing device 4 and the weapon computer 3 are each protected against overload currents by means of fuses (circuit breakers).
• - The TSD software runs on the computing core of the TSD and interacts via Ethernet link with the computing core 30 (missile test software) of the weapon computer 3 in client function (requires actions from the missile test software such as switching supplies on/off or sending Milbus messages to). It controls the internal assemblies of the TSD: Milbus monitor, relays, sensors and monitors, measures, logs and evaluates the interaction of the weapon computer 30 (computing core, FK interface module, AC energy module) with the firing device 4 and the ones in it captured missiles. It also controls the test procedure through orders to the missile test software and to the internal TSD assemblies, evaluates missile measurement data and generates a test protocol that is displayed on the control terminal of weapon computer 3.

• - S1 / S4 Energie (für vier Flugkörper):
  • - 4x Versorgung Suchkopfelektronik
  • - 4x Versorgung Lenkelektronik
  • - 4x Impuls Batteriezündung A
  • - 4x Impuls Batteriezündung B
  • - 1x Kontinuitäts-Signal (zeigt an, ob die Kabelverbindung besteht Waffenrechner -Distribution-Box besteht, in der dieses Signal gebrückt ist)
• - S2 / S5 Daten (für vier Flugkörper):
  • - 4x Milbus 1553B Datenbus,
  • - 4x Versorgung Suchkopfheizung,
  • - 4x Versorgung Rudermaschinen,
  • - 4x Impuls Raketenmotorschärfung,
  • - 4x Monitor Versorgung Suchkopfelektronik,
  • - 4x Monitor Versorgung Lenkelektronik,
  • - 4x Monitor Pyro Batterien,
  • - 4x Interlock-Signal,
  • - 1x Kontinuitäts-Signal (wie bei S1/S4).
• - S3 / S6 Heizung (für vier Flugkörper):
  • - 4x Versorgung Kanister Heizung
• - S7: Ethernet-Link zwischen TSD (Client) und Waffenrechner (Server):
  • - Aufträge für das Ein/Ausschalten von Versorgungssignalen (LCCU - MIM)
  • - Requests für Zustandsreports von Signalen
  • - Reports von Signalzuständen
  • - Aufträge für Senden von Milbus-Botschaften
  • - Request von Milbus-Botschaften
  • - Inhalt von empfangenen Milbus-Botschaften
  • - Requests für Anzeigen am Toughpanel des Waffenrechners
  • - Requests für Bedienerkommandos
  • - Bedienerkommandos.
• - S8: Datenschnittstelle (USB, Netzwerk) nach außen
• - S9: Spannungsversorgung der TSD, die vom Flugkörper-Startgerät geliefert wird, sodass keine zusätzliche externe Versorgung erforderlich ist.

The missile test facility 5 has the following interfaces:

• - S1 / S4 energy (for four missiles):
  • - 4x supply of search head electronics
  • - 4x supply steering electronics
  • - 4x pulse battery ignition A
  • - 4x pulse battery ignition B
  • - 1x continuity signal (indicates whether the cable connection exists weapon computer distribution box in which this signal is bridged)
• - S2 / S5 data (for four missiles):
  • - 4x Milbus 1553B data bus,
  • - 4x supply search head heating,
  • - 4x supply rowing machines,
  • - 4x impulse rocket motor arming,
  • - 4x monitor supply search head electronics,
  • - 4x monitor supply steering electronics,
  • - 4x Monitor Pyro batteries,
  • - 4x interlock signal,
  • - 1x continuity signal (like S1/S4).
• - S3 / S6 heater (for four missiles):
  • - 4x supply canister heater
• - S7: Ethernet link between TSD (client) and weapon computer (server):
  • - Orders for switching supply signals on/off (LCCU - MIM)
  • - Requests for status reports of signals
  • - Reports of signal states
  • - Orders for sending Milbus messages
  • - Request from Milbus messages
  • - Content of received Milbus messages
  • - Requests for displays on the weapon calculator tough panel
  • - Requests for operator commands
  • - Operator commands.
• - S8: Data interface (USB, network) to the outside
• - S9: Power supply of the TSD, which is supplied by the missile launcher, so that no additional external supply is required.

The test procedure with the in 1 test setup shown is described below.

The TSD 5 is connected to the weapon computer 3 of the missile launcher 2 by means of the Ethernet interface S7. The TSD is supplied with voltage from the missile launcher 2 via the interface S9 and the missile test menu is selected on the control panel 30'.

A cabling and validity check is then carried out between weapon computer 3 and TSD 5. To do this, the TSD 5 sends the alive request to the computer core 3D of the weapon computer, which responds to this request with its starting device ID. The touchbook checks the boot device ID for acceptance dance. Communication is aborted if the ID is invalid. If the weapon computer 3 registers the alive request, a symbol in the missile test menu indicates that there is a connection to the TSD 5 if the ID of the TSD 5 contained in the alive request is valid. If invalid, the Weapon Calculator 3 terminates interaction with the TSD 5.

• - nach Anwahl einer Testfunktion mittels Menü erfolgt via Bedienpanel 30' die zu bestätigende Anweisung an den Bediener, die TSD über die Schnittstellen S1, S2, S3 an die linken (FK-Interface-Modul 1, MIM1) oder rechten (FK-Interface-Modul 2, MIM2) Kabel der Anschlusstafel 20 anzustecken und mittels der Testkabel über die Schnittstellen S4, S5 und S6 mit entsprechend der Verteilereinrichtung 48 zu verkabeln und beide zu erden.

A wiring check follows between weapon computer 3, the TSD 5 and the 4-pack canister (missile launcher 4):

• - after selection of a test function via the menu, the instruction to be confirmed is given to the operator via the control panel 30', the TSD via the interfaces S1, S2, S3 to the left (FK interface module 1, MIM1) or right (FK interface Module 2, MIM2) cable of the connection panel 20 and using the test cable via the interfaces S4, S5 and S6 to wire it to the distribution device 48 accordingly and to ground both.

• - Anfordern des Status' der Kabelverbindung Verteilereinrichtung 20 via Waffenrechner 3 und Prüfen auf Power Kabel vorhanden und Signal Kabel vorhanden.
• - Anfordern des Status' der Interlock-Leitung (TIVS) via Waffenrechner 3 und Prüfen auf lethaler oder inerten Flugkörper präsent.
• - Falls eine der Bedingungen nicht erfüllt ist, erfolgen die Ausgabe einer Fehlermeldung, die Aufforderung an den Bediener die Kabelverbindung Anschlusstafel 20, TSD 5, Verteilereinrichtung 48, Flugkörper zu prüfen, ggf. erfolgt die Wiederholung dieses Checks oder Testabbruch
• - Prüfen auf Erdung : Bestätigung durch den Bediener, dass das Flugkörper-Startgerät 2, die TSD 5 und die Abschusseinrichtung 4 korrekt geerdet sind
• - Sicherheitschecks: Anfordern der entsprechenden Zustände vom Waffenrechner 3 und Prüfen auf spannungslosen Zustand des Flugkörpers :
  • -- Monitor Pyro-Batterien < 1V
  • -- Monitor Versorgung Suchkopfelektronik < 1V
  • -- Monitor Versorgung Lenkelektronik < 1V
  • -- Monitor Versorgung Suchkopf Gimbal < 1V
  • -- Monitor Versorgung Suchkopf RF < 1V

Falls wenigstens eine dieser Bedingungen nicht erfüllt wird, erfolgen eine entsprechende Fehlermeldung, Testabbruch und das Auftrennen der Signalleitung zwischen dem betreffenden Flugkörper und TSD 5 mittels Relais.

• - Falls ein lethaler oder ein inerter Flugkörper und korrekte Kabelverbindungen erkannt werden, wird ein Datenbus-Kommunikationscheck für jeden Flugkörper/Kanister des 4-Pack Kanisters der Abschussanordnung 4 durchgeführt :
  • -- via Waffenrechner einschalten der Versorgung Suchkopf-Heizung und Request der Milbus-Botschaften Kanister-Temperpatur von der RTU 28 mittels Waffenrechner, falls die RTU 28 nicht mit dem korrekten Statuswort und der definierten Anzahl von Datenworten antwortet, erfolgen eine Fehlermeldung und Testabbruch.
  • -- via Waffenrechner einschalten der Versorgung Lenkelektronik und Request der Milbus-Botschaften Flugkörper-Status, Schärfungs-Status und RTU Status von der RTU1 mittels Waffenrechner, als Antwort wird folgendes erwartet:
    • --- korrekte Statusworte und Datenworte mit der definierten Wortanzahl und Validity Check
    • --- Flugkörper-Status : prelaunch BIT Status = NOGO, Stellungs-Daten preprocessed = unsucessful, Abschuss-Daten processed = unsuccessful, Cas Actuator Voltage Status = unsatisfactory, Major Missile Type, Canister Type = one pack
    • --- Schärfungs-Status : Arm Status = not armed
  • -- falls die RTU1 eine der obigen Bedingungen nicht erfüllt, erfolgt eine Fehlermeldung und Testabbruch.
  • -- ausschalten der beiden Versorgungsspannungen via Waffenrechner.
• - Folgende Tests sind mittels Menü Flugkörper-Test verfügbar:
  • -- Test Kanister-Heizung
  • -- Test Suchkopf-Heizung
  • -- Test Versorgung Suchkopfelektronik
  • -- Test Versorgung Lenkelektronik
  • -- Test Versorgung Rudermaschinen
  • -- Test Stellungs-Daten
  • -- Test Abschuss-Daten
  • -- Test Prelaunch BIT
  • -- Test der reversiblen Launch Phase
  • -- Test Trockenmittel
  • -- Test auf äußere Beschädigung des Kanisters
  • -- Protokollerstellung und Protokollausgabe.

After appropriate confirmation by the operator, the following steps take place:

• - Requesting the status of the cable connection distribution device 20 via weapon computer 3 and checking for power cables and signal cables.
• - Requesting the status of the interlock line (TIVS) via weapon computer 3 and checking for lethal or inert missiles present.
• - If one of the conditions is not met, an error message is output and the operator is requested to check the cable connection between terminal board 20, TSD 5, distributor device 48 and missile. If necessary, this check is repeated or the test is aborted
• - Check for Grounding : Operator confirmation that Missile Launcher 2, TSD 5 and Launcher 4 are properly grounded
• - Safety checks: requesting the appropriate states from weapon computer 3 and checking that the missile is de-energized:
  • -- Monitor pyro batteries < 1V
  • -- Monitor supply of seeker electronics < 1V
  • -- Monitor supply steering electronics < 1V
  • -- Monitor supply seeker gimbal < 1V
  • -- Monitor supply seeker RF < 1V

If at least one of these conditions is not met, a corresponding error message occurs, the test is aborted and the signal line between the missile in question and the TSD 5 is disconnected by means of a relay.

• - If a lethal or an inert missile and correct cable connections are detected, a databus communication check is performed for each missile/canister of the 4-pack canister of launch assembly 4 :
  • -- via the weapon computer switch on the supply of the seeker head heating and request the Milbus messages canister temperature from the RTU 28 using the weapon computer, if the RTU 28 does not respond with the correct status word and the defined number of data words, an error message occurs and the test is aborted.
  • -- via the weapon computer switch on the supply of the guidance electronics and request the Milbus messages missile status, arming status and RTU status from the RTU1 via the weapon computer, the following is expected as an answer:
    • --- correct status words and data words with the defined number of words and validity check
    • --- Missile status: prelaunch BIT status = NOGO, position data preprocessed = unsuccessful, launch data processed = unsuccessful, Cas Actuator Voltage Status = unsatisfactory, Major Missile Type, Canister Type = one pack
    • --- Arm Status : Arm Status = not armed
  • -- if the RTU1 does not meet one of the above conditions, an error message occurs and the test is aborted.
  • -- switch off the two supply voltages via the weapon computer.
• - The following tests are available via the Missile Test menu:
  • -- Test canister heater
  • -- Test seeker heating
  • -- Test supply of seeker electronics
  • -- Test supply of steering electronics
  • -- Test supply rowing machines
  • -- Test position data
  • -- Test kill data
  • -- Test Prelaunch BIT
  • -- Test of the reversible launch phase
  • -- Test desiccant
  • -- Test for external damage to the canister
  • -- Log creation and log output.

The TSD 5 activates and controls the switching on/off of missile supplies and the Milbus traffic via the weapon computer 3 (computing core 30 via FK interface module 32 or 33) as well as the interaction with the operator (computer core 30 via control panel 30' ).

• • die Zündimpulse der irreversiblen Funktionen sind zwischen dem Waffenrechner 3, der TSD 5 und dem jeweiligen Flugkörper unterbrochen und beidseitig durch Massekurzschluss gesichert;
• • die Milbus-Botschaft Kommando Flugkörper-Zündung wird von der TSD 5 erkannt und die Weitergabe an den betreffenden Flugkörper wird von der TSD 5 blockiert.

TSD 5 provides for the following safety devices to prevent the irreversible launch phase of a missile from being triggered:

• • the ignition pulses of the irreversible functions are interrupted between the weapon computer 3, the TSD 5 and the respective missile and protected on both sides by a ground short circuit;
• • The TSD 5 recognizes the Milbus message Command Missile Ignition and the transmission to the relevant missile is blocked by the TSD 5.

3 shows an alternative test setup, in which an external control computer 6 is connected to the connection S8 of the test device 5 (TSD). In this test setup, the operator guidance of the missile test does not take place via the control panel 30' integrated in the weapon computer 3, but by means of the external control computer 6, which is connected to the TSD 5 via Ethernet. As a result, fewer extensions are required in the weapon calculator 3 than in the variant of the 1 . The TSD software has a server function in relation to the external control computer 6 and works in relation to the missile test software of the weapon computer 3 as a client. The missile test software is as in the variant according to 1 Server opposite the TSD software. The test protocol is output on the external control computer 6, which exchanges data with the outside world by means of an interface S10 (eg USB, network). Test objects are the weapon computer 3, the wiring up to the distribution device 48 and the 4-pack canister (missile launching device 4) including the distribution device 48.

4 shows a possible additional use of the test device 5 according to the invention (TSD in the device carrier) in the depot or in the field before a missile launching device 4 is attached to the missile launcher 2. The test device 5 (TSD) contains a voltage converter 53 to convert the supply signals for the To be able to produce missiles/canisters. The interaction between the test device 5 (TSD) working as a server and an external computer 7 working as a client takes place as in the example in FIG 1 , wherein the external computer 7 emulates the weapon computer 3. Optionally, the test device 5 (TSD) can contain a battery 50' in order to be independent of an external energy source for a shorter time.

Reference signs in the claims, the description and the drawings are only intended for a better understanding of the invention and are not intended to limit the scope of protection.

Reference List

1

Flugkörper-Startvorrichtung

2

Flugkörper-Startgerät

3

Waffenrechner

4, 4'

Flugkörper-Abschusseinrichtung

5

Testeinrichtung

5A

erste Schnittstelleneinrichtung

5B

zweite Schnittstelleneinrichtung

6

externer Bediencomputer

7

externer Computer

20

Elektrische Anschlusstafel

21

Antennenanlage

22

Kommunikationsanlage

24

Aufrichtanlage

25

Energieanlage

26

Navigationsanlage

30

Waffenrechnerkern

30'

Bedieneinheit

30"

Speicher

31A

AC-Stromversorgungseinheit für Wechselstrom

31B

DC-Stromversorgungseinheit für Gleichstrom

32, 33

Flugkörper-Interface-Module

32A, 33A

erste elektrische Schnittstelle

32B, 33B

zweite elektrische Schnittstelle

37

Datenbus

37'

Datenbuskabel

38

Router

40, 42, 44, 46

Startkanister

41, 43, 45, 47

Flugkörper

48

Verteilereinrichtung

49

startgeräteseitige elektrische Schnittstelle

49'

flugkörperseitige elektrische Schnittstelle

50

Gehäuse

50'

Batterie

51

Testcomputer

52

Milbus-Bus-Steuerungseinheit

53

Spannungswandler

54

Kurzschlussstecker

55

Signal-Adaptionselement

56

Leistungsmessungselement

57

Temperatursensor

58

Relais

59

Sicherungen

K

Kabelbaum

K'

Kabel

W

Waffensystem-Zentrale

Z

Operationszentrale

Designate it:

1

Missile Launcher

2

missile launcher

3

weapon calculator

4, 4'

missile launcher

5

test facility

5A

first interface device

5B

second interface device

6

external operating computer

7

external computer

20

Electrical connection panel

21

antenna system

22

communication system

24

erecting system

25

power plant

26

navigation system

30

weapons processor core

30'

operating unit

30"

Storage

31A

AC power supply unit for alternating current

31B

DC power supply unit for direct current

32, 33

Missile Interface Modules

32A, 33A

first electrical interface

32B, 33B

second electrical interface

37

data bus

37'

data bus cable

38

routers

40, 42, 44, 46

starting canister

41, 43, 45, 47

missile

48

distribution device

49

Launcher side electrical interface

49'

missile-side electrical interface

50

Housing

50'

battery

51

test computer

52

Milbus bus control unit

53

voltage converter

54

shorting plug

55

signal adaptation element

56

performance measurement element

57

temperature sensor

58

relay

59

fuses

K

wiring harness

K'

Cable

W

Weapons System Center

Z

Operations Center

Claims (9)

Test device for a missile launch device, which has a missile launch device (2) equipped with a weapon computer (3) and at least one launch device (4) accommodating at least one missile (41, 43, 45, 47), the test device (5) includes at least the following components: - a test computer (51), which has a computer core and at least one data memory connected to the computer core and on which test procedure software is stored so that it can run, - A first interface device (5A) on the weapon computer side for connecting the test computer (5) to the missile launcher (2) or to the weapon computer (3) provided in the missile launcher (2) and - at least one second interface device (5B) on the missile side for connection to the at least one missile (41, 43, 45, 47) or to the at least one launch device (4); wherein the test device (5) is designed to be functionally switched into a signal and information flow between the missile launch device (2) and the launch device (4) in such a way that electrical connections and signal and data lines between the missile launch device ( 2) and the launching device (4) are guided through the test device (5). test facility claim 1 , characterized in that the test procedure software running in the test device is designed in such a way that it can forward or block control signals which are received via the first interface device (5A) on the weapon computer side to the second interface device (5B) on the missile side. Missile launcher with integrated or integrable test functionality, wherein the missile launcher (1) has a missile launcher (2) equipped with a weapon computer (3) and at least one launching device accommodating at least one missile (41, 43, 45, 47). (4), characterized in that between the weapon computer (3) and the launching device (4) a test device (5) according to one of the preceding claims in a signal and information flow between the missile launcher (2) and the launching device ( 4) it is or can be arranged that electrical connections and the signal and data streams between the weapon computer (3) and the launching device (4) and between the launching device (4) and the weapon computer (3) are routed through the test device (5). . missile launcher claim 3 , characterized in that the test computer (51) of the test device (5) is connected or can be connected to a monitor line of the missile and is designed in such a way that it can read and monitor monitor information from the missile (41, 43, 45, 47). missile launcher claim 3 or 4 , characterized in that the test computer (51) of the test device (5) is connected or can be connected to a data bus (37) of the missile launcher (2) and is designed such that it can send and read data bus messages. missile launcher claim 3 , 4 or 5 , characterized in that the test computer (51) of the test device (5) is designed to send a command to the weapon computer (3) which starts a test routine implemented in the weapon computer (3), and that the test computer (51) of the test device (5) is designed to monitor actions and reactions that are triggered by the weapon computer-side test routine in the missile (41, 43, 45, 47) or in its launch device (4). missile launcher claim 3 , 4 or 5 , characterized in that the test procedure software running in the test device (5) is designed in such a way that it stimulates the missile (41, 43, 45, 47) for test purposes and for this purpose transmits control signals to the missile (41, 43, 45, 47 ) sends or forwards that trigger an action in the missile (41, 43, 45, 47). Missile launcher according to any one of claims 3 until 7 , characterized in that the test procedure software running in the test device (5) is designed in such a way that it stimulates the weapon computer (3) for test purposes and for this purpose sends or forwards control signals to the weapon computer (3), which in the weapon computer (3) trigger action. Missile launcher according to any one of claims 3 until 8th , characterized in that the test procedure software running in the test device (5) is designed in such a way that it sends control signals, which are intended to trigger reversible actions in the missile (41, 43, 45, 47), from the weapon computer (3). allows the launching device (4) to pass and that it blocks control signals intended to trigger irreversible actions in the missile (41, 43, 45, 47) and does not forward them to the launching device (4).

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