DE102015006799A1 - Test device for a missile launch device - Google Patents

Abstract

A test device for a missile launch device comprising a missile launcher (2) equipped with a weapon computer (3) and at least one launcher (4) receiving 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 a test procedure software can be stored,
- A weapon computer-side, first interface device (5A) for connecting the test computer (5) to the missile launcher (2) or to the in the missile launcher (2) provided weapons computer (3) 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).

Description

TECHNICAL AREA

The present invention relates to a test device for a missile launcher having a missile launcher equipped with a gun computer and at least one launcher receiving at least one missile according to the preamble of claim 1. The invention further relates to a missile launcher having integrated or integratable Test functionality, wherein the missile launch device has a equipped with a weapon computer missile launch device and at least one at least one missile receiving launch device, according to the preamble of claim 3.

BACKGROUND OF THE INVENTION

Correct interaction of a missile launcher with a launcher or missile (s) is essential to the functioning of a missile launcher formed from these components. It should be noted that a missile launcher must be able to interact with a plurality of launcher and thus with a variety of missiles. In peacetime, the missiles are usually stored individually or together with the launching device receiving them in the depot and coupled with the missile launcher only in case of action or for shooting campaigns. Although the individual missiles and their launcher are tested in the depot at predetermined intervals and with different test depths, but is not guaranteed by these tests that the interaction between a missile launcher and the respective launcher or the respective missile works reliably. This can have several causes, for example, in the harness connecting the missile launcher with the launcher or in the weapons computer or in the launcher itself. Therefore, at certain time intervals, the missile launcher and associated harnesses are also routinely tested.

But even if both the launcher with the missiles and the missile launcher with the weapons computer have each withstand appropriate isolated function tests, it is far from guaranteed that the interaction of these devices works reliably. In particular, with increasing storage time and increasing environmental influences, tolerances of individual assemblies may shift, which may not stand out in isolated routine tests, which can lead to malfunction in interaction with other assemblies whose tolerances have also changed.

STATE OF THE ART

Typically, missiles are treated as a certified missile round, that is, the missile has a predictable reduction in reliability within a defined certification period (typically 10 years at 30 years of service life). Within this period, the missile is maintenance free. During storage, a periodic inspection of a representative sample of missiles is performed, which verifies the reliability requirements. Upon completion of the certification period, the missile is recertified by testing and, if necessary, replacing degraded or defective components to maintain the missile in a usable condition and to ensure the required reliability and expected performance.

• 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.
• 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.
• 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.
• 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:

• a. Stockpile Reliability Test: a missile sample is taken from the depot and transported to the manufacturer for visual inspection and functional testing.
• b. Certified Round Data Management Database: This database provides traceability of each missile, making missile history (built-in, swapped, broken components, certifications, test data, etc.) available and trends can be recognized.
• c. Storage and Aging Program: Selected missile components are stored in different climatic locations (hot, cold, humid and nominal in temperate climates) and periodically tested to chart and analyze trends.
• d. Shooting Campaign (Missile Firing Program): Lot picking during production is performed to ensure that only high quality missiles are stored. Lot verification firing during the usage phase checks performance parameters, detects trends, and analyzes drift of critical parameters before exceeding specification limits.

This missile surveillance program is the primary source of information in addition to theoretical reliability models (flight reliability, on-launcher reliability, long-term storage reliability) To ensure that a missile with high reliability is always used by military users.

• – 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 verification of missile functions

• - during storage at the depot (at the home location)
• - after transport (to the site of use)
• - before and during use (at the site of use)
• - before handover to the manufacturer or after receipt by the manufacturer (at the home location or manufacturer's location)

is required.

However, the operational capability of a missile or launcher or missile (s) is not only to be considered isolated, but must also be in the combination of any (optional) launcher and missile launcher (s). For this purpose, the functionality of missile launchers has been tested with the missile emulating test equipment. 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.

PRESENTATION OF THE INVENTION

It is therefore an object of the present invention to provide a test device for a missile launch device, with which it is also possible to test the interaction of a missile launch device with a launch device receiving the missiles, before this combination is released for operational use. It is another object of the present invention to provide a missile launch device with integrated or integrable test functionality that is equipped with such a test device or can be equipped.

The directed to the test device part of the object is achieved by the test device with the features of 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, according to the invention, in a test device for a missile launch device which has a missile launch device equipped with a weapon computer and at least one launch device receiving at least one missile, 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 a test procedure software is stored so that it can be run,
• - A weapon computer-side, first interface device for connecting the test computer to the missile launcher or to the provided in the missile launcher weapon computer and
• - At least one missile side, second interface device for connection to the at least one missile or to the at least one launching device.

ADVANTAGES

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

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

The directed to the missile launch device part of the object is achieved by a missile launch device with the features of claim 3.

This missile launch device according to the invention with integrated or integrable test functionality, wherein the missile launch device comprises a missile launcher equipped with a weapon computer and at least one launcher receiving at least one missile, is characterized in that between the weapon computer and the launcher a test device is arranged according to one of the preceding claims such that the signal and data streams between the weapon computer and the launching device and between the launching device and the weapons computer run through the test device.

This integration of the test device in the assembled unit from a missile launcher and at least one provided with at least one missile launcher not only makes it possible to check with the test device these components, but also allows the review of peripherals, such as connection or connection cables in operational deployment configuration. In addition, this integration of the test equipment can record and monitor the signal and data traffic between the missile launcher and the launcher.

Further preferred and advantageous design features of the missile launch device according to the invention are the subject matter of the subclaims 4 to 9.

Preferably, the test computer of the test device is connected to a monitor line of the missile or connected and designed so that he can read monitor information of the missile and monitor the missile.

More preferably, the test computer of the test device is connected or connectable to a data bus of the missile launcher and configured to 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 perform actions and reactions that are performed by the tester side test routine in the missile or in the launcher are triggered monitored.

With this embodiment of the missile launch device according to the invention, it is possible to run from the test computer of the test device from test routines that are already implemented in the weapons computer, and then the actions and reactions that occur, triggered by this test routine, in the missile or in the launching device to monitor. Although the test routine is triggered by the test computer, the test computer is merely an observer during the course of the test routine and does not intervene in the test procedure itself.

In a further advantageous embodiment of the invention, the test procedure software running in the test device is designed such 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 isolate a missile or a launching device equipped with the missile, ie test it without the missile launch device, which is a sensible solution, for example for the routine tests of the missiles in the weapon depot. The test device receives in this way a double functionality, namely to be able to perform routine tests in the weapons depot and at the same time to be able to test the interaction of missile launch device and provided with missiles launcher in an integrated form.

It is also advantageous if the test procedure software running in the test device is designed such that it stimulates the weapon computer for test purposes and sends or forwards control signals to the weapon computer triggering an action in the weapon computer. In this way, on the one hand a review of the function of the weapons computer is possible and on the other hand, the already described interaction between the measures provided in the missile launcher weapon computer and the missile contained in the launcher can be tested.

Finally, it is also of advantage if the test procedure software running in the test device is designed such that it transmits control signals, which are provided to trigger reversible actions in the missile, to the launching device from the weapons computer and that they provide control signals which are provided in order to trigger irreversible actions in the missile, blocked and not forwarded to the launcher. This embodiment ensures on the software side that signals that would trigger an irreversible action in the missile are not forwarded to the missile. As a result, this signal flow split 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, intended for operational use connection cables.

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

BRIEF DESCRIPTION OF THE DRAWINGS

It shows:

1 a missile launch device with integrated test device;

2 a test device according to the invention;

3 a modification of the in 1 shown missile launch device with integrated test device and

4 a test device according to the invention for testing only one launch device.

PRESENTATION OF PREFERRED EMBODIMENTS

1 shows a schematic block diagram of a missile starting device according to the invention 1 with a missile launcher 2 holding a weapons calculator 3 comprising first and second missile launcher means 4 . 4 ' and one between the weapons computer 3 and at least one of the missile launchers 4 . 4 ' attachable test device according to the invention 5 (Test and Safety Device TSD). The test facility 5 can either be between the missile launcher 2 and the missile launcher in question 4 . 4 ' be provided or it may be modular in the missile launcher 2 be integrable. For this purpose, the test device has a first, weapon computer-side interface device 5A and a second, missile-side interface device 5B on.

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

In the weapons computer 3 is a control unit 30 ' integrated and / or an external operating computer is connected to the weapon computer with a connection cable 3 connectable, so that the weapons computer 3 by means of the internal control unit 30 ' or the external operator computer is controllable.

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

The missile launcher 2 has except the weapon computer nor an electrical antenna system 21 , a communication system 22 , a hydraulic missile erecting system 24 , an energy plant 25 and a navigation system 26 on that over the data bus 37 with the weapon core 30 are connected. About the antennas of the electrical antenna system 21 a communication connection with a higher-level weapon system center W and one of these higher-level operation center Z can be set up.

On the computer of the weapon computer core 30 associated memories 30 '' is a missile test software stored on retrieval on the computer of the armor core 30 expires.

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

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

In the operative state, the first, electrical device-side electrical equipment interface 49 the missile launcher 4 with the electrical connection board 20 of the missile launcher 2 electrically conductively connected or connectable via electrical connection lines of a cable harness K. According to the invention in the wiring harness K or between the wiring harness K and the start device side electrical interface 49 the missile launcher 4 or the electrical connection board 20 of the missile launcher 2 or within the missile launcher 2 the test facility 5 installed electrically effective. The electrical connections and the signal and data lines between the missile launcher 2 and the missile launcher 4 are there by the test facility 5 led and the test facility 5 is thus functional in the signal and information flow between the missile launcher 2 and the missile launcher 4 switched 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 facility (TSD) 5 points as in 2 is shown next to a housing 50 (or in another embodiment a device carrier) the following elements:

• - a TSD arithmetic engine, which is a test computer 51 forms,
• A Milbus bus control unit 52 in the following functions: bus control unit (BCU), remote terminal unit (RTU) and bus monitor,
• - Voltage transformer 53 .
• - short circuit plug 54 which in the cable K 'between the missile and the TSD on the missile side and also on the TSD side short-circuit the power and return lines of the following signals: rocket motor sharpening, battery ignition A and battery ignition B,
• - a signal adaptation element 55 by which the signals supplied by the missile (monitor supply) are transformed in their electrical properties to be from the following power measurement element 56 can be measured (voltage, current, time course),
• - Power measurement element 56 .
• - Temperature sensor 57 , which determines the ambient temperature of the housing 50 determined,
• - Relays 58 ; all signals between the missile launcher 4 and the missile launcher 2 are each switchable 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 in 1 The test setup shown requires the following configuration of the test facility TSD 5 :

• - The TSD core 51 on which a TSD software runs as a client, and the one with the weapons computer 3 of the missile launcher 2 on which the missile test software runs as a server interacts. The TSD software monitors, measures, logs and evaluates the interaction of the weapon computer 3 (Calculation engine 30 , Missile interface modules 32 . 33 , AC energy module) with the start canisters 40 . 42 . 44 . 46 or the missiles received therein 41 . 43 . 45 . 47 out.
• - The Milbus bus control unit 52 works as a Milbus monitor and records the Milbus communication between the weapons computer (BCU) 3 and the launch canisters 40 . 42 . 44 . 46 or the missiles received therein 41 . 43 . 45 . 47 and provides the recorded interaction of the TSD software for evaluation. The Milbus bus control unit 52 recognizes the Milbus message "command missile ignition" on the start device side and blocks forwarding to the launch canister on the missile side 40 . 42 . 44 . 46 ,
• - short circuit plug 54 are provided in the TSD on the start of the unit to short-circuit the rocket motor sharpening power lines, the battery ignition A and the battery ignition B with the associated return lines. Shorting plugs are also provided on the missile side in the TSD to short-circuit the power lines for the rocket motor sharpening, the battery ignition A and the 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 misses all supply signals as well as the interlock line that the gun computer 3 generated and delivered to the missile, in terms of voltage, current and time course. These signals are then evaluated by the TSD calculation kernel. The power measurement element 56 continues to measure all monitor signals generated by the particular missile and delivered to the weapons computer in terms of voltage, current, and time history. These signals are measured by the TSD and evaluated by the calculation kernel.
• - The temperature sensor determines the ambient temperature of the missile launcher.
• - All signals between the launching device 4 and the weapons calculator 3 are each switchable by a relay of the TSD
• - all signals between the launching device 4 and the weapons calculator 3 are each protected against over-load currents by means of fuses (automatic circuit breakers).
• - The TSD software runs on the computing kernel of the TSD and interacts with the calculation kernel via Ethernet link 30 (Missile test software) of the weapons computer 3 in client function (requests actions such as power on / off supplies or sending Milbus messages from the missile test software). 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 (Calculator, FK interface module, AC energy module) with the launching device 4 and the missile recorded in it. It also manages the test sequence by issuing orders to the missile test software and internal TSD assemblies, evaluating missile metrics, and generating a test log that is stored on the console's operator terminal 3 is shown.

• – S1/S4 Energie (für vier Flugkörper): – 4× Versorgung Suchkopfelektronik – 4× Versorgung Lenkelektronik – 4× Impuls Batteriezündung A – 4× Impuls Batteriezündung B – 1× Kontinuitäts-Signal (zeigt an, ob die Kabelverbindung besteht Waffenrechner-Distribution-Box besteht, in der dieses Signal gebrückt ist)
• – S2/S5 Daten (für vier Flugkörper): – 4× Milbus 1553B Datenbus, – 4× Versorgung Suchkopfheizung, – 4× Versorgung Rudermaschinen, – 4× Impuls Raketenmotorschärfung, – 4× Monitor Versorgung Suchkopfelektronik, – 4× Monitor Versorgung Lenkelektronik, – 4× Monitor Pyro Batterien, – 4× Interlock-Signal, – 1× Kontinuitäts-Signal (wie bei S1/S4).
• – S3/S6 Heizung (für vier Flugkörper): – 4× 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 device 5 has the following interfaces:

• - S1 / S4 energy (for four missiles): - 4 × supply search head electronics - 4 × supply steering electronics - 4 × pulse battery ignition A - 4 × pulse battery ignition B - 1 × continuity signal (indicates whether the cable connection consists of weapons computer distribution Box in which this signal is bridged)
• - S2 / S5 data (for four missiles): - 4 × Milbus 1553B data bus, - 4 × supply seeker heater, - 4 × power steering systems, - 4 × impulse rocket engine sharpening, - 4 × monitor supply seeker electronics, - 4 × monitor supply steering electronics, - 4 × monitor pyro batteries, - 4 × interlock signal, - 1 × continuity signal (as with S1 / S4).
• - S3 / S6 heater (for four missiles): - 4 × supply canister heating
• - S7: Ethernet link between TSD (client) and weapon computer (server): - jobs for switching on / off supply signals (LCCU - MIM) - requests for status reports of signals - reports of signal states - jobs for sending Milbus messages - Milbus Message Request - Contents of Milbus Messages Received - Requests for Gun Computer Toughpanel Requests - Requests for Operator Commands - Operator Commands.
• - S8: Data interface (USB, network) to the outside
• - S9: power supply to the TSD supplied by the missile launcher so that no additional external power is required.

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

The Ethernet interface S7 becomes the TSD 5 with the weapons computer 3 of the missile launcher 2 connected. From the missile launcher 2 the TSD is supplied with voltage via interface S9 and at the control panel 30 ' the menu missile test is selected.

It will then be a cabling and validity check between weapons computer 3 and TSD 5 carried out. To do this, send the TSD 5 the alive request to the computer core 3D of the weapon computer, which answers this request with its boot device ID. The touchbook checks the boot device ID for acceptance. Invalid ID causes the termination of the communication. Join the weapons calculator 3 The Alive Request is displayed in the Missile Test menu by an icon that indicates the connection to the TSD 5 if the ID of the TSD exists 5 that is contained in the alive request is valid. If invalid, the weapons calculator terminates 3 the 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.

This is followed by a cabling check between the weapons computer 3 , the TSD 5 and the 4-pack canister (missile launcher 4 ):

• - after selecting a test function via menu via the control panel 30 ' the instruction to be confirmed to the operator, 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 be connected and by means of the test cable via the interfaces S4, S5 and S6 with according to the distribution device 48 to wire and 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 < 1 V – Monitor Versorgung Suchkopfelektronik < 1 V – Monitor Versorgung Lenkelektronik < 1 V – Monitor Versorgung Suchkopf Gimbal < 1 V – 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. Hierbei aktiviert und kontrolliert die TSD 5 das Ein/Ausschalten von Flugkörper-Versorgungen sowie den Milbus-Verkehr über den Waffenrechner 3 (Rechenkern 30 via FK-Interface-Modul 32 beziehungsweise 33) sowie die Interaktion mit dem Bediener (Rechnerkern 30 via Bedienpanel 30').

After confirmation by the operator, the steps are:

• - Request the status of the cable connection distribution device 20 via weapon computer 3 and checking for power cable available and signal cable available.
• - Request the status of the interlock line (TIVS) via the weapons computer 3 and testing for lethal or inert missiles present.
• - If one of the conditions is not fulfilled, the output of an error message, the request to the operator, the cable connection terminal board 20 , TSD 5 , Distribution device 48 To check missiles, if necessary, the repetition of this check or test abort
• - Check for grounding: confirmation by the operator that the missile launcher 2 , the TSD 5 and the launcher 4 are properly grounded
• - Security Checks: Request the appropriate conditions from the weapons computer 3 and checking for de - energized condition of the missile: - monitor pyro batteries <1 V monitor supply seeker electronics <1 V monitor supply steering electronics <1 V monitor supply search head gimbal <1 V monitor supply search head RF <1V If at least one of these conditions is not met, a corresponding error message, test abort and disconnecting the signal line between the missile concerned and TSD 5 by means of relay.
• If a lethal or inert missile and correct cable connections are detected, a data bus communication check will be made for each missile / canister of the 4-pack canister of the launching assembly 4 carried out: - via the weapon computer turn on the supply search head heating and request of the Milbus messages canister temperature of the RTU 28 using the weapon calculator, if the RTU 28 not with the correct status word and the defined Number of data words responds, an error message and test abort. - via the weapon computer turn on the supply steering electronics and request of the Milbus messages missile status, sharpening status and RTU status of the RTU1 by means of weapons computer, in response the following is expected: - correct status words and data words with the defined word count and Validity Check - Missile Status: prelaunch BIT Status = NOGO, Position Data preprocessed = unsucessful, Launch Data processed = unsuccessful, Cas Actuator Voltage Status = unsatisfactory, Major Missile Type, Canister Type = one pack - Arm Status: Arm Status = not armed - if If the RTU1 does not fulfill one of the above conditions, an error message and test abort will occur. - Switch off the two supply voltages via weapons computer.
• - The following tests are available by menu missile test: - test canister heater - test seeker heater - test supply search head electronics - test supply steering electronics - test supply steering machines - test position data - test launch data test Prelaunch BIT test of reversible launch phase - test desiccant - test for external damage to the canister - log creation and log output. This activates and controls the TSD 5 turning on / off missile supplies and Milbus traffic through the weapons calculator 3 (Calculation engine 30 via FK interface module 32 respectively 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.

The following safety devices against the triggering of the missile's irreversible launch phase are in the TSD 5 intended:

• • the ignition pulses of the irreversible functions are between the weapon computer 3 , the TSD 5 and the respective missile interrupted and secured on both sides by ground short circuit;
• • the Milbus Embassy command missile ignition is provided by the TSD 5 detected and the passing to the missile concerned is from the TSD 5 blocked.

3 shows an alternative test setup, in which to the terminal S8 of the test device 5 (TSD) an external HMI 6 connected. In this test setup, the operator guidance of the missile test is not performed via the weapon computer 3 integrated control panel 30 ' but by means of the external operating computer 6 that with the TSD 5 connected by Ethernet. As a result, there are fewer extensions in the weapons calculator 3 required as in the variant of 1 , The TSD software is opposite the external HMI 6 in server function and works against 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 compared to the TSD software. The output of the test protocol takes place on the external operating computer 6 which exchanges data with the outside world via an interface S10 (eg USB, network). Candidates are the weapon calculator 3 , the wiring to the distribution device 48 and the 4-pack canister (missile launcher 4 ) including the distributor device 48 ,

4 shows a possible additional use of the test device according to the invention 5 (TSD in the equipment carrier) in the depot or in the field before the installation of a missile launcher 4 to the missile launcher 2 , The test facility 5 (TSD) contains a voltage transformer 53 to generate the supply signals for the missile / canister. The interaction between the test device operating as a server 5 (TSD) and an external computer acting as a client 7 takes place as in the example of 1 where the external computer 7 the weapons calculator 3 emulated. Optionally, the test device 5 (TSD) a battery 50 ' to be independent of an external source of energy for a shorter time.

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

LIST OF REFERENCE NUMBERS

1

Missile launcher

2

Missile launcher

3

weapons computer

4, 4 '

Missile launcher

5

test equipment

5A

first interface device

5B

second interface device

6

external control computer

7

external computer

20

Electrical connection board

21

antenna system

22

communications system

24

Aufrichtanlage

25

power plant

26

navigation system

30

Weapons computer core

30 '

operating unit

30 ''

Storage

31A

AC power supply unit for AC

31B

DC power supply unit for DC

32, 33

Missile interface modules

32A, 33A

first electrical interface

32B, 33B

second electrical interface

37

bus

37 '

databus

38

router

40, 42, 44, 46

start canister

41, 43, 45, 47

missile

48

distribution facility

49

Start device-side electrical interface

49 '

missile-side electrical interface

50

casing

50 '

battery

51

test computer

52

Milbus bus control unit

53

DC converter

54

Shorting plug

55

Signal adaptation element

56

Performance measurement element

57

temperature sensor

58

relay

59

fuses

K

harness

K '

electric wire

W

Weapons system center

Z

operations center

Claims (9)

Test device for a missile launch device, which is equipped with a weapon computer ( 3 ) equipped missile launcher ( 2 ) and at least one at least one missile ( 41 . 43 . 45 . 47 ) receiving launcher ( 4 ), 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 a test procedure software is stored so that it can be run, - a first computer interface-side interface device ( 5A ) for connecting the test computer ( 5 ) to the missile launcher ( 2 ) or to the in the missile launcher ( 2 ) ( 3 ) 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 launch device ( 4 ). Test device according to Claim 1, characterized in that the test procedure software running in the test device is designed in such a way that it receives control signals which are transmitted via the weapon computer-side first interface device ( 5A ), to the missile side, second interface device ( 5B ) can forward or block. A missile launch device with integrated or integrable test functionality, wherein the missile launch device ( 1 ) with a weapons computer ( 3 ) equipped missile launcher ( 2 ) and at least one at least one missile ( 41 . 43 . 45 . 47 ) receiving launcher ( 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 is or can be arranged such that the signal and data streams between the weapon computer ( 3 ) and the launching device ( 4 ) and between the launcher ( 4 ) and the weapon computer ( 3 ) through the test facility ( 5 ) to run. A missile launching device according to claim 3, characterized in that the test computer ( 51 ) of the test device ( 5 ) is connected or connectable to a monitor line of the missile and is configured to provide monitor information of the missile ( 41 . 43 . 45 . 47 ) can read and monitor. A missile launching device according to claim 3 or 4, characterized in that the test computer ( 51 ) of the test device ( 5 ) to a data bus ( 37 ) of the missile launch device ( 2 ) is connectable or connectable and configured to send and read data bus messages. A missile launching device according to claim 3, 4 or 5, characterized in that the test computer ( 51 ) of the test device ( 5 ) is configured to issue a command to the weapons computer ( 3 ), the one in the weapons computer ( 3 ) is started, and that the test computer ( 51 ) of the test device ( 5 ) is configured to perform actions and reactions performed by the weapon computer-side test routine in the missile ( 41 . 43 . 45 . 47 ) or in its launcher ( 4 ) to be monitored. Missile launcher according to claim 3, 4 or 5, characterized in that the (in the test device 5 ) running test procedure software is such that it the missile ( 41 . 43 . 45 . 47 ) and stimulated for testing purposes Control signals to the missile ( 41 . 43 . 45 . 47 ) transmits or forwards in the missile ( 41 . 43 . 45 . 47 ) trigger an action. A missile launching device according to any one of claims 3 to 7, characterized in that in the test device ( 5 ) running test procedure software is such that it the weapon computer ( 3 ) for test purposes and to control signals to the weapons computer ( 3 ) sends or forwards, which in the weapon computer ( 3 ) trigger an action. Missile launcher according to any one of claims 3 to 8, characterized in that the (in the test device 5 ) running test procedure software is such that it provides control signals that are provided to the missile ( 41 . 43 . 45 . 47 ) trigger reversible actions, from the weapons computer ( 3 ) to the launcher ( 4 ) and that they have control signals which are provided to be in the missile ( 41 . 43 . 45 . 47 ) to trigger irreversible actions, blocked and not to the launcher ( 4 ).

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