DE102015002563B3 - Missile launcher - Google Patents

Abstract

A missile launch device for at least one missile (41, 43, 45, 47), comprising at least one missile launcher (2) and at least one weapon computer (3) as a start, test and / or diagnostic computer for missiles to be launched (3A , 3B, 3C, 3D), characterized in that the weapon computer (3) has a weapon computer core (30) and has a modular structure, to which it is provided with at least one exchangeable missile interface module (32, 33) a standardized weapon computer-internal first electrical interface (32A, 33A) and on the other hand an individualized missile start device side second electrical interface (32B, 33B), wherein the electrical computer-internal first electrical interface (32A, 33A) and the missile start device side second electrical interface (32B, 33B) at least electrical supply connections (32A ', 33A', 32B ', 33B') and signal line connections (32A '', 33A '', 32B '', 3 3B '') for signal transmission.

Description

TECHNICAL AREA

The present invention relates to a missile launch device for at least one missile, with at least one missile launcher and at least one weapon computer as start-test and / or diagnostic computer for launching missile according to the preamble of patent claim 1.

BACKGROUND OF THE INVENTION

Aircraft launchers, such as anti-aircraft systems, have a centralized weapons computer that controls the subsystems of the missile launcher, such as the power supply, the hydraulic system, the communication system and the navigation system, and that communicates with a higher level command center. Conventional weapons computers are connected to the missile launcher and thus to the missile (s) in a variety of ways. The necessary interfaces in the weapon computer are designed missile-specific, so that developed and manufactured in conventional missile launchers of the weapons computer specifically for a missile type. This missile-individual embodiment of a weapons computer with the said distribution of the missile-specific signals and functions on several components of the weapon computer prevents easy adaptability of a once constructed weapon computer to different types of missile.

STATE OF THE ART

The DE 10 2011 115 963 B3 shows and describes an unmanned training and test missile having an on-board computer, a navigation computer, a seeker and an image processing computer, which are connected to each other via an internal data bus for data exchange. This missile is designed to be launched from a carrier aircraft.

The DE 10 2011 114 225 B3 shows and describes a missile training session with a training missile having weapon computers with built-in fault memory and connectable to an external service and test device as well as to an external configuration device. Also, this training missile is adapted to be coupled to a carrier aircraft, so that with this training missile the withdrawal of real missiles can be trained from a carrier aircraft.

The DE 10 2009 040 304 A1 shows and describes a device for controlling functional tests and / or service procedures for aircraft-deductible unmanned missiles. This device can be connected by means of an attachable to the weapon station of a carrier aircraft missile simulation device and with an attachable to a missile test and service device. With this one control device, it is therefore possible to test both the weapon station of the carrier aircraft and the missile in a variety of tests and / or service procedures.

The DE 31 27 844 A1 shows and describes a method for dropping ammunition from a fighter aircraft, wherein the aircraft is provided with a weapons computer, to which an aiming point-directed image capture device is connected. By means of the data of this image capture device, the weapon computer can determine values for the throwing distance and throwing direction and control a triggering sensor for the discharge of the ammunition accordingly. This ammunition is a ballistic ammunition deposited by a carrier aircraft.

From the DE 10 2012 000 671 A1 are known a missile launch device and an associated test and test device comprising a missile simulation unit, a simulator of Waffensystemzentrale, running in a test and test computer control software and a data transmission device.

This known testing and testing device consists of two elements, a simulation computer and a signal adaptation device. If several missile simulation units are connected to the missile launch device, the control of a missile simulation unit via a router. The simulation computer is controlled by the test and test computer and communicates with the signal adaptation device. It enables the simulation of different variants of missile launching (normal and exceptional behavior), allowing for the correct response of the missile launcher to complex missile failures. The behavior of the simulation computer is configurable. He simulates only one missile. The signal adaptation device communicates with the simulation computer and interacts with the missile interface of the missile launcher so that the weapon control computer of the missile launcher can not determine whether the respective missile launcher is connected to a missile or only to a missile simulator. The missile simulation unit known from this prior art can simulate only one missile and is therefore connected to the distribution box of the missile launcher; it is also not directly connectable to the weapons computer.

• – ein Flugkörper-Interface-Modul erzeugt Zündimpulse und schaltet Versorgungsspannungen gesteuert durch den Waffenrechenkern, misst Monitorspannungen vom Flugkörper und leitet die Messwerte zum Waffenrechenkern weiter.
• – ein Wechselstrom-Modul schaltet eine Heizung für einen Startkanister, gesteuert durch den Rechenkern;
• – der Waffenrechenkern managt die Milbus-Kommunikation mit dem Startkanister und dem Flugkörper und steuert die Startsequenz;
• – ein Gleichstrom Modul stellt verschiedene Spannungen für das Flugkörper-Interface-Modul bereit, gesteuert durch den Rechenkern.

Conventionally, in missile launch devices known so far, the missile-specific interface signals and functions are distributed over several modules of the weapon computer:

• A missile interface module generates firing pulses and switches supply voltages under the control of the weapon core, measures monitor voltages from the missile, and forwards readings to the weapon core.
• - An AC module switches a heater for a start canister, controlled by the computing core;
• - the weapon computer core manages the Milbus communication with the launch canister and the missile and controls the launch sequence;
• A DC module provides various voltages to the missile interface module, controlled by the computing core.

• – Kommunikation mit Waffenrechenkern 30, gesteuert von Waffenrechenkern 30,
• – Durchführen von Selbsttests,
• – Ein-/Ausschalten und Messen einer Spannung zur Versorgung der Flugkörper-Elektronik an einer Monitorleitung und Weiterleiten des Messwerts zum Waffenrechnerkern,
• – Ein-/Ausschalten und Messen einer Spannung zur Versorgung der Rudermaschinen und Weiterleiten des Messwerts zum Waffenrechnerkern,
• – Ein-/Ausschalten und Messen einer Spannung zur Versorgung der Suchkopf-Elektronik und Weiterleiten des Messwerts zum Waffenrechnerkern,
• – Ein-/Ausschalten und Messen einer Spannung für die Suchkopf-Heizung und Weiterleiten des Messwerts zum Waffenrechnerkern,
• – Durchleiten der MIL-STD-15538-Datenkanäle von/zum Waffenrechenkern, Erzeugen von Impulsen zur Zündung der Thermalbatterien des Flugkörpers,
• – Messen der Spannung der Batterie-Pyro-Leitung und Weiterleiten des Messwerts zum Waffenrechnerkern,
• – Ein-/Ausschalten und Messen einer Spannung zur Schärfung des Raketenmotors und Weiterleiten des Messwerts zum Waffenrechnerkern,
• – Messen einer Spannung an der Interlockleitung und Weiterleiten des Messwerts zum Waffenrechnerkern und
• – Messen des Durchgangs der Energie- und Signal-Kabelstränge und Weiterleiten des Messwerts zum Waffenrechnerkern.

The respective missile interface module performs the following functions:

• - Communication with the weapon computing core 30 , controlled by weapon computing core 30 .
• - performing self-tests,
• - switching on and off and measuring a voltage to supply the missile electronics to a monitor line and forwarding the measured value to the weapon host core,
• - switching on and off and measuring a voltage to supply the steering machines and forwarding the measured value to the weapon processor core,
• - switching on and off and measuring a voltage to supply the seeker electronics and forwarding the measured value to the weapon processor core,
• - turning on / off and measuring a voltage for the seeker head heating and forwarding the measured value to the armament core,
• Passing the MIL-STD-15538 data channels to / from the weapon computer core, generating pulses to ignite the missile's thermal batteries,
• - measuring the voltage of the battery pyro line and forwarding the measured value to the weapon processor core,
• - turning on and off and measuring a voltage to sharpen the rocket motor and passing the reading to the armament core,
• Measuring a voltage on the interlock line and forwarding the measured value to the weapon processor core and
• - Measuring the passage of the power and signal cable strands and forwarding the measured value to the weapon processor core.

Thus, in the conventional missile launcher, the missile interface module only turns on and off signals initiated by the arithmetic core, measures voltages, and generates pulses. The control of the missile-specific AC module the starting canister heater on / off according to the temperature-dependent control by the weapon computing core. This distribution of the missile-specific signals and functions on several modules prevents easy adaptability of the weapon computer of a missile launch device to different types of missile.

PRESENTATION OF THE INVENTION

Object of the present invention is to design a missile launch device of the generic type so that different types of missile can be fired with this missile launch device.

This object is achieved by the missile launch device having the features of patent claim 1.

For this purpose, the invention provides that the weapon computer has a weapon computer core and is modular, to which it is provided with at least one interchangeable missile interface module (FIM), on the one hand a standardized weapon computer-internal first electrical interface and on the other hand an individualized missile start device side second electrical interface wherein the weapon computer-internal first electrical interface and the missile start device-side second electrical interface each comprise at least electrical supply connections and signal line connections for signal transmission and wherein the missile interface module is electrically connectable to the missile launcher on its missile launch device side electrical interface. The missile start device-side second electrical interface may also be an external interface to the weapon computer.

ADVANTAGES

The modular design of the weapon computer of the missile launch device according to the invention with at least one interchangeable missile interface module (FIM) allows the weapon computer by simply replacing the missile interface module against a on the missile launch device side electrical interface to another, for example more modern To quickly and easily convert missile adapted missile interface module so that it can be used with the other missile. The provision of the standardized computer-internal electrical interface and the individualized FEM launch device-side electrical interface make this interchangeability possible in the first place. Thus, it is only necessary to adapt the missile interface module as a replaceable unit to a particular type of missile, for example a modernized, younger generation missile that it requires a redesign of the entire weapons computer.

Further preferred and advantageous design features of the missile launch device according to the invention are the subject matter of subclaims 2 to 6.

Further preferably, the missile interface module on electrical voltage converter means which convert at least one of the weapon computer-internal first electrical interface voltage applied in at least one electrical voltage which is applied to the missile start device side second electrical interface. This makes it possible to provide any required voltage converter means in the FIM and thereby provide required for the missile power supplies predetermined voltage from a provided in the weapon computer power distributor.

In another preferred embodiment, the missile interface module has electrical signal converter means which converts at least one control signal present at the weapon computer-internal first electrical interface into a missile-specific control signal applied to the missile start device-side second electrical interface. In this way it is also possible to convert standard control signals emitted by the weapon computer core into specific control signals required for the missile and thus to control functions of the missile with standard control signals output by the weapon computer.

The missile interface module preferably also has data communication means which convert incoming and / or outgoing data communication streams into and / or outgoing missile-specific data communication streams at the second electrical interface on the missile host device-side. In this way, the FIM can also be used to translate data communication streams between the weapon core and the missile between the standard communication language used by the gun computer and the specific communication language used by the missile in both directions.

It is also advantageous if the weapon computer is provided with at least one interchangeable, mirror-image missile emulation module (FEM), which has, on the one hand, a standardized weapon computer-internal first electrical emulation interface and, on the other hand, an individualized missile launch device-side second electrical emulation interface, wherein the first internal emulation interface and the missile start device-side second electrical emulation interface in each case comprises at least electrical supply connections and signal line connections for signal transmission.

This additional provision of a missile emulation module (FEM) makes it possible, due to the interchangeability and modularity of the missile emulation module, to test a weapon computer and / or a missile launcher for different missiles, with each interchangeable missile emulation module. Module is designed so that it emulates the function of a very specific missile; the FEM is missile specific.

It is advantageous if the missile emulation module at its missile start device side second electrical emulation interface with the missile launcher or with the missile launch device side electrical interface of the missile interface module is electrically connected. The weapon computer thus equipped with at least one FEM can therefore be autonomously tested by means of the FEM or tested together with the missile launcher together with the missile launcher and the connecting cables running between the weapon computer and the missile launcher.

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 schematic block diagram of a missile starting device according to the invention;

2 a test setup for an autonomous test of the weapons computer and

3 a test setup of connected to a missile launcher weapons computer.

PRESENTATION OF PREFERRED EMBODIMENTS

In 1 is a schematic block diagram of a missile launch device according to the invention reproduced. The missile launch device 1 has a missile launcher 2 and a weapons calculator 3 on. The missile launcher 2 is with a missile launching arrangement 4 provided, in the example shown four starting canisters 40 . 42 . 44 . 46 for each one missile 41 . 43 . 45 . 47 having.

The missile launcher 2 further comprises an electrical distribution device 20 on, the input side (weapon computer side) electrical interfaces 22A . 23A having, with input side electrical supply terminals 22A ' . 23A ' , with input signal line connections 22A '' . 23A '' and with input-side data communications ports 22A ''' . 23A ''' is provided.

Output-side interfaces 22B . 23B . 24B . 25B the electrical distribution device 20 have electrical supply connections 22B ' . 23B ' . 24B ' . 25B ' connected to a respective electrical supply port of an associated startup canister 40 . 42 . 44 . 46 the missile launcher 4 are electrically connected. Furthermore, in the output side interfaces 22B . 23B . 24B . 25B Signal line terminals 22B '' . 23B '' . 24B '' . 25B '' and data communication ports 22B ''' . 23B ''' . 24B ''' . 25B ''' provided with the corresponding signal line terminals or data communication terminals of an associated Startkanisters 40 . 42 . 44 . 46 are electrically connected.

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 electrical power supply unit 31 provided by a line 31 ' supplied from the outside with electrical voltage. This external supply voltage may be an AC voltage and / or a DC voltage. To the weapon core 30 is an external control computer 30 ' with a connection cable 30 '' connected, so that the weapons computer 3 by means of the external operating computer 30 ' is controllable.

In the weapons computer 3 are also two interchangeable missile interface modules (FIM) 32 . 33 provided, for example, are mechanically designed as plug-in units and in this way with the weapons computer 3 mechanically interchangeable connectable. Electrically are the missile interface modules 32 . 33 each with a standardized Waffenrechnerinternen first electrical interface 32A . 33A and with a missile start device side second electrical interface 32B . 33B Mistake. The missile launch device side electrical interface 32B . 33B can also be the external electrical controller external to the computer.

The weapon computer internal first electrical interface 32A . 33A of each missile interface module 32 . 33 has electrical supply connections 32A ' . 33A ' on that with the electrical power unit 31 are electrically connected. This connection can be one or more electrical supply voltages (DC and / or AC) for the missile interface module 32 . 33 to be provided. The weapon computer internal first electrical interface 32A . 33A also has signal line connections 32A '' . 33A '' on, each with the weapon core 30 electrically connected to the signal transmission. Control and / or control signals from the weapon processor core can be used via these signal line connections 30 to the respective missile interface module 32 . 33 and also be transmitted in the opposite direction. Finally, the respective weapon computer-internal first electrical interface 32A . 33A still electrical data communication connections 32A ''' . 33A ''' on that over data communication lines with the weapon host core 30 are electrically connected to the data transmission.

The respective weapon computer-internal first electrical interface 32A . 33A is due both to the mechanical arrangement of the corresponding weapon computer-internal contacts for contacting with the associated contacts of the respective missile interface module 32 . 33 as well as in terms of the first electrical interfaces at the corresponding weapon computer-internal 32A . 33A provided voltages, signals and data standardized and the associated interchangeable missile interface modules 32 . 33 are adapted to these standardizations on their WAT computer-internal side.

The respective missile interface module 32 . 33 is at its missile launch device side second electrical interfaces 32B . 33B with electrical supply connections 32B ' . 33B ' provided, via corresponding electrical connection lines of a wiring harness K with the associated electrical connections 22A ' . 23A ' the input-side electrical interfaces 22A . 23A the electrical distribution device 20 of the missile launcher 2 electrically connected or connectable. This is what the missile interface module provides 32 . 33 at its missile launch device side electrical supply port 32B ' . 33B ' at least one electrical voltage (DC and / or AC voltage) in the required amperage available from the missile launcher 2 is needed. The missile interface module 32 . 33 is with electric voltage transformers 32 ' . 33 ' provided to the at least one at the Waffenrechnerinternen first electrical interface 32A . 33A applied voltage to convert into at least one electrical voltage, at the missile start device side second electrical interface 32B . 33B is applied.

Furthermore, the missile start device-side second electrical interface 32B . 33B of each missile interface module 32 . 33 Signal line terminals 32B '' . 33B '' on, via corresponding lines of the wiring harness K with associated input-side signal line terminals 22A '' . 23A '' the electrical distribution device 20 electrically connected or connectable. The missile interface module 32 . 33 is with electrical signal transducers 32 '' . 33 '' provided that the at least one at the Waffenrechnerinternen first electrical interface 32A . 33A applied control signal in at least one of the missile start device side signal line terminals 32B '' . 33B '' convert the applied control signal.

Finally, the missile launch device side second electrical interface 32B . 33B of each missile interface module 32 . 33 Communications ports 32B ''' . 33B ''' on, via corresponding lines of the wiring harness K with associated input side data transmission connections 22A ''' . 23A ''' the electrical distribution device 20 electrically connected or connectable. The missile interface module 32 . 33 is with data converter means 32 ''' . 33 ''' provided, the data or a data stream, or the either at the weapon computer-internal first electrical interface 32A . 33A or at the missile start device side second electrical interface 32B . 33B enter into or enter into another data format, so that these data or this data stream via the respective other electrical interface to the missile launcher 2 or to the Waffenrechnerkern 30 can be delivered in the expected data format there.

The respective missile interface module 32 . 33 thus forms an adaptation hardware, which corresponds to the current needs, that is, according to the to the weapons computer 3 connected missile launcher 2 or in such a missile launcher 2 used missiles 41 . 43 . 45 . 47 , is usable. That's how the weapons calculator works 3 by simply exchanging a missile interface module 32 . 33 to the missile launcher 2 or their missile can be adjusted quickly and easily, without it being a further change of the weapons computer and in particular of its Waffenrechnerkern 30 and the software running on it needs.

• a) waffenrechnerseitig:
• • Gleich- und Wechselspannungsversorgung,
• • Datenbus-Anbindung (Ethernet) zum Waffenrechenkern 30 des Waffenrechners 3,
• • sicherheitskritische diskrete Sperrsignale für Zündkreise (Batterie, Schärfen),
• • Test&Debug-Mittel;
• b) flugkörperstartgeräteseitig:
• • Energie-Schnittstelle(n),
• • Signal-Schnittstelle(n),
• • Stromversorgung für Startkanister-Heizung(en),
• • optionale Kühlung des Flugkörpersuchkopfs,
• • optionale Steuerung des Datenlinksystems zum Flugkörper im Flug.

In the missile starting device according to the invention 1 all missile-specific interface signals and functions in a 'real' missile interaction unit, the Missile Interface Module (FIM) 32 . 33 , encapsulated and implemented. The missile interface module 32 . 33 has the following interfaces:

• a) weapon computer side:
• • DC and AC power supply,
• • Data bus connection (Ethernet) to the weapon computer core 30 of the weapon computer 3 .
• • Safety-critical discrete inhibit signals for ignition circuits (battery, sharpening),
• • test & debug means;
• b) missile launch device side:
• • energy interface (s),
• Signal interface (s),
• Power supply for starting canister heater (s),
• Optional cooling of the missile seeker,
• • optional control of the data link system to the missile in flight.

• • die Wandlung von Eingangsspannungen zu den vom Flugkörper benötigten Spannungen (Wechsel- und Gleichstrom),
• • die Generierung von Zündimpulsen (Batterie, Schärfung) aus der Eingangsgleichspannung bei Verarbeitung der sicherheitskritischen, diskreten Sperrsignale (Enable/Disable, Enable Power to critical relays),
• • die Datenbus-Kommunikation (z. B. Milbus, Bus Control Unit) mit dem Flugkörper beziehungsweise dem Startkanister,
• • die Steuerung der Startkanister-Heizung basierend auf der im Kanister gemessenen Temperatur,
• • die Steuerung der Signale und der Datenbus-Botschaften, die während der Startsequenz zwischen Flugkörper und Waffenrechner gesendet, empfangen und ausgewertet werden (im Gegensatz zu bisherigen Lösungen also nicht im Rechenkern des Waffenrechners, sondern im FIM),
• • die Kommunikation mit dem Rechenkern des Waffenrechners nach Server-Client-Schema, das heißt: das Flugkörper-Interface-Modul sendet keine Botschaft selbständig, sondern nur auf Anforderung durch den Rechenkern; zum Beispiel:
• – Request für Health-Status, BIT-Ergebnisse (Selbsttest-Ergebnisse), Spannungs-Messwerte, Konfiguration, Startergebnis
• – einige Daten sendet der Rechenkern (z. B. Startkommando mit allen Daten, die der Flugkörper zum Start benötigt) zum Flugkörper-Interface-Modul, die das Flugkörper-Interface-Modul dann mit 'Ack' bestätigt;
• • vorzugsweise interagiert ein Flugkörper-Interface-Modul mit vier Flugkörpern beziehungsweise vier Startkanistern.

The Missile Interface Module (FIM) 32 . 33 encapsulates and implements the following missile interface functions:

• The conversion of input voltages to the voltages required by the missile (alternating and direct current),
• The generation of ignition pulses (battery, sharpening) from the input DC voltage when processing the safety-critical, discrete disable signals (enable / disable, enable power to critical relays),
• The data bus communication (eg Milbus, Bus Control Unit) with the missile or the starting canister,
• The control of the starting canister heater based on the temperature measured in the canister,
• The control of the signals and the data bus messages that are sent, received and evaluated during the takeoff sequence between the missile and the weapon computer (in contrast to previous solutions, not in the core of the weapon computer, but in the FIM),
• • the communication with the arithmetic core of the weapon computer according to server-client scheme, that is: the missile interface module sends no message independently, but only on request by the calculation engine; for example:
• - Request for health status, BIT results (self-test results), voltage readings, configuration, startup result
• Some data is sent by the calculation kernel (eg start command with all data the missile needs to start) to the missile interface module, which then confirms the missile interface module with 'Ack';
• • Preferably, a missile interface module interacts with four missiles or four launch canisters.

In 2 shows another use of a missile launch device according to the invention, in which the weapon computer 3 in addition to in conjunction with 1 Replaceable Missile Interface Modules (FIM) 32 . 33 two replaceable and mirror-image missile emulation modules (FEM) 34 . 35 having. The missile emulation modules 34 . 35 are trained to emulate a particular type of missile to the weapons computer 3 with the help of these missile emulation modules 34 . 35 to test or staff at the missile launch device 1 to be able to train.

The missile emulation modules 34 . 35 also have a standardized Waffenrechnerinterne first electrical emulation interface 34A . 35A and an individualized FIM-side second electrical emulation interface 34B . 35B on. The connections of the respective FIM-side second electrical emulation interface 34B . 35B are intended to communicate with the appropriate missile launch side ports of a missile interface module 32 . 33 to be connected.

The FIM-side second electrical interface 34B . 35B of each missile emulation module 34 . 35 has electrical supply connections 34B ' . 35B ' on, with the respective missile starter side electrical supply connections 32B ' . 33B ' an associated missile interface module 32 . 33 are electrically connected. This connection can be from the assigned missile interface module 32 . 33 delivered electrical supply voltages (DC and / or AC) for the missile emulation module 34 . 35 to be provided.

The FIM-side second electrical interface 34B . 35B also has signal line connections 34B '' . 35B '' on, with the respective missile start device side electrical signal line connections 32B '' . 33B '' the assigned missile interface module 32 . 33 are electrically connected. Control and / or control signals from the missile interface module can be used via these signal line connections 32 . 33 to the respective missile emulation module 34 . 35 and also be transmitted in the opposite direction.

Finally, the respective FIM-side second electrical interface 34B . 35B still electrical data communication connections 34B ''' . 35B ''' via the data communication lines with the respective missile start device side electrical data communication ports 32B ''' . 33B ''' the assigned missile interface module 32 . 33 are electrically connected to the data transmission.

That's how the weapons calculator works 3 by simply exchanging a missile interface module 32 . 33 to the missile launcher 2 or their missiles are adjusted quickly and easily, without any further change of the weapons computer 3 and in particular of its weapon core 30 requirement.

The respective missile emulation module 34 . 35 is at its weapon computer's first electrical interfaces 34A . 35A with the missile emulation module 34 . 35 feeding electrical supply connections 34A ' . 35A ' Mistake.

The weapon computer internal first electrical interfaces 34A . 35A of the respective missile emulation module 34 . 35 have signal line connections 34A '' . 35A '' on, over appropriate lines with the weapon computer core 30 electrically connected or connectable.

Finally, the weapon computer-internal first electrical interface 34A . 35A of each missile emulation module 34 . 35 Communications ports 34A ''' . 35A ''' on, over appropriate lines with the weapon computer core 30 electrically connected or connectable.

Each of the missile emulation modules 34 . 35 is thus a missile interface module 32 . 33 assigned. To emulate the individual missiles are the individual connections of the missile start device side electrical interfaces 34B . 35B the missile emulation modules 34 . 35 with the associated ports of the missile launch device side interfaces of the missile interface modules 32 . 33 connected. These compounds, which in the example of the 2 are made directly through corresponding connection lines of a connecting cable V, in the example of 3 by connecting the individual connections of the output-side interfaces of the distributor device 20 of the missile launcher 2 provided so that in the variant of 3 the wiring harness K with in a test of the weapons computer 3 is involved.

The respective missile emulation module 34 . 35 thus forms an adaptation hardware, which according to the current test or training needs like a to the weapons computer 3 connected missile launcher 2 or like those in such a missile launcher 2 used missile 41 . 43 . 45 . 47 , is usable.

• – auf der Seite des Flugkörper-Interface-Moduls:
• – Energie-Schnittstelle,
• – Signal-Schnittstelle,
• – Kanister Heizung,
• – Anschluss für externe Lasten (Kanister Heizung, Suchkopf Heizung)

und

• – applikationsseitig (waffenrechnerinternseitig):
• – Gleichspannungsversorgung,
• – Datenbus-Anbindung (Ethernet) zum Applikationsclient,
• – Test & Debug.

The respective missile emulation module (FEM) 34 . 35 provides the following interfaces:

• - on the side of the missile interface module:
• - energy interface,
• Signal interface,
• - canister heating,
• - Connection for external loads (canister heating, seeker heating)

and

• - Application side (Waffenrechnerinternseitig):
• - DC power supply,
• - Data bus connection (Ethernet) to the application client,
• - Test & Debug.

• – die Vermessung von Zündimpulsen (Batterie, Schärfung), die flugkörperstartgeräteseitig empfangen werden;
• – die Datenbus-Kommunikation (z. B. Milbus, Remote Terminal) mit dem Flugkörperstartgerät;
• – die Simulation der Kanister-Heizung und die Messung der anliegenden Heizungsspannung;
• – die Vermessung von Eingangsspannungen (Suchkopf-Heizung, Flugkörper-Elektronik, Suchkopf-Stromversorgung, Rudermaschinen-Stromversorgung);
• – die Generierung von Monitorspannungen (für Monitor Flugkörper-Elektronik, Monitor Suchkopf, Monitor Pyro-Batterie)
• – das Schalten von Signalen (Monitor Interlock, Monitor Power-Kabel-Durchgang, Monitor Signal-Kabel-Durchgang, FIM Jumper B1, FIM Jumper B2, Hydraulik-Durchgang);
• – die Simulation der flugkörperseitigen Startsequenz;
• – die Kommunikation mit dem Applikationsclient (Waffenrechnerkern) nach Server-Client-Schema : FEM (Server) sendet keine Botschaft selbständig, sondern nur auf Anforderung des Applikationsclients analog zum Server-Client-Schema des FIM und
• – vorzugsweise simuliert ein FEM vier Flugkörper oder Flugkörper-Startkanister.

The respective missile emulation module (FEM) 34 . 35 encapsulates and implements the following missile interface functions:

• - The measurement of ignition pulses (battery, sharpening), the missile start device side are received;
• The data bus communication (eg Milbus, Remote Terminal) with the missile launch device;
• - The simulation of the canister heater and the measurement of the applied heating voltage;
• - the measurement of input voltages (seeker heater, missile electronics, seeker power supply, steering machine power supply);
• - the generation of monitor voltages (for monitor missile electronics, monitor seeker head, monitor pyro-battery)
• - signal switching (Monitor Interlock, Monitor Power Cable Passage, Monitor Signal Cable Passage, FIM Jumper B1, FIM Jumper B2, Hydraulic Passage);
• The simulation of the missile side start sequence;
• - the communication with the application client (weapon computer core) according to server-client scheme: FEM (server) does not send a message independently, but only at the request of the application client analogous to the server-client scheme of the FIM and
• Preferably a FEM simulates four missiles or missile launch canisters.

In a test or training mode, the weapon calculator 3 by means of the external actuation computer 31 ' over the weapon core 30 (Application client) with appropriate test or training commands commanded. The tests of the weapon computer can be done in a single mode or in an automatic mode.

• – jede interne Last eines vom entsprechenden FEM emulierten Flugkörpers ist vom Applikationsclient konfigurierbar und schaltbar und der Schaltzustand jeder internen Last ist vom Applikationsclient abfragbar;
• – jedes Relais ist vom Applikationsclient schaltbar und der Schaltzustand jedes Relais' ist vom Applikationsclient abfragbar;
• – jeder Messwert der Eingangsspannungen am FEM ist vom Applikationsclient abfragbar;
• – jede interne Spannungsquelle ist vom Applikationsclient konfigurierbar und schaltbar und der Schaltzustand jeder internen Spannungsquelle ist vom Applikationsclient abfragbar;
• – der Inhalt der Milbus-Botschaften, die vom FIM zum Flugkörper-Startgerät gesendet werden, ist vom Applikationsclient konfigurierbar;
• – der Inhalt der Milbus-Botschaften, die vom Flugkörper-Startgerät empfangen werden, ist vom Applikationsclient abfragbar.

The operating mode 'Single Mode' has the following properties:

• Each internal load of a missile emulated by the corresponding FEM can be configured and switched by the application client and the switching status of each internal load can be queried by the application client;
• - Each relay can be switched by the application client and the switching state of each relay can be queried by the application client;
• - each measured value of the input voltages at the FEM can be interrogated by the application client;
• - Each internal voltage source can be configured and switched by the application client and the switching state of each internal voltage source can be queried by the application client;
• The content of the Milbus messages sent by the FIM to the missile launcher can be configured by the application client;
• The content of the Milbus messages received by the missile launcher can be interrogated by the application client.

• – der Start einer Startsequenz eines (emulierten) Flugkörpers wird erkannt, wenn die externer Spannung der (emulierten) Suchkopfheizung des Flugkörpers abgeschaltet wird und innerhalb eines vorgegebenen Zeitintervalls (zum Beispiel 100 ms) die externen Spannungen für die Flugkörperelektronik und für die Suchkopfelektronik für einen Flugkörper auf größer als 23 V erkannt werden;
• – für jeden emulierten Flugkörper sind für die Startsequenz folgende Parameter einstellbar bezogen auf den erkannten Beginn einer Startsequenz:
• – die Ein/Ausschalt-Zeitpunkte der Lasten der externen Spannungen;
• – die Einschalt-Zeitpunkte der intern erzeugten Spannungen;
• – die Inhalte der Sende-Milbus-Botschaften und
• – die Höhe der geschalteten Lasten Höhe der internen Spannungen.
• – nach Erkennen der Milbus-Botschaft ”Kommando Zündung” werden nach einer einstellbaren Zeit die intern erzeugten Spannungen für Monitor Pyro-Batterie, Monitor FK-Elektronik und Monitor Suchkopf-Elektronik abgeschaltet sowie die RTU1 (Flugkörper) und RTU28 (Kanister) deaktiviert (-> ”Flugkörper weg”-Erkennung);
• – den Ablauf einer Startsequenz eines Flugkörpers bildet das FEM in einem Launch-History-Vector ab, der das Auftreten jedes Signales (diskret und Milbus) sowie die zugehörigen Signaleigenschaften beinhaltet. Für den Applikationsclient ist der Launch-History-Vector abrufbar;
• – das Verhalten eines simulierten Flugkörpers wird so simuliert wie es die eingestellten Parameter der Startsequenz festlegen und
• – die Signalsequenz (diskret und Milbus) einer laufenden Startsequenz wird vom FEM aufgezeichnet und ist als Liste mit Ereignis/Signaleigenschaften/Zeitstempel vom Applikationsclient abrufbar.

The operating mode 'Automatic mode' has the following properties:

• The start of a starting sequence of an (emulated) missile is detected when the external voltage of the (emulated) search head heater of the missile is switched off and within a predetermined time interval (for example 100 ms) the external voltages for the missile electronics and for the seeker electronics for a missile be detected at greater than 23V;
• - For each emulated missile, the following parameters can be set for the start sequence, based on the detected start of a start sequence:
• The on / off times of the external voltage loads;
• The switch-on times of the internally generated voltages;
• - the contents of the broadcast Milbus messages and
• - the height of the switched loads height of the internal voltages.
• - after detection of the Milbus message "command ignition", the internally generated voltages for monitor pyro battery, monitor FK electronics and monitor seeker electronics are switched off after an adjustable time and the RTU1 (missile) and RTU28 (canister) are deactivated (- >"Missileoff"detection);
• - The sequence of a start sequence of a missile forms the FEM in a Launch History Vector, which includes the occurrence of each signal (discrete and Milbus) and the associated signal properties. For the application client, the Launch History Vector is available;
• The behavior of a simulated missile is simulated as it determines the set parameters of the start sequence and
• - The signal sequence (discrete and Milbus) of a running start sequence is recorded by the FEM and can be called up as a list with event / signal properties / time stamp from the application client.

• – der Applikationsclient kann für alle externen Spannungen obere und untere Schwellwerte einstellen, mit denen die gemessenen Spannungen mit 100 Hz verglichen werden. Das Ergebnis jedes Vergleichs zwischen Schwellwert und Messwert kann der Applikationsclient abrufen;
• – jede Spannungsüberwachungsfunktion ist vom Applikationsclient ein- und ausschaltbar.

In addition, the following monitoring functions are provided:

• - The application client can set upper and lower thresholds for all external voltages, which compare the measured voltages with 100 Hz. The result each comparison between the threshold value and the measured value can be called up by the application client;
• - Each voltage monitoring function can be switched on and off by the application client.

• – der Applikationsclient kann Sollwerte bezüglich externer Spannungen, Zeitabständen und Inhalten der erhaltenen Milbus-Botschaften (Kommando Test, Stellungsdaten, Startdaten 1, Startdaten, Kommando Zündung) definieren, anhand derer die während einer Startsequenz gemessenen Werte verglichen werden, falls der Applikationsclient diese Funktion aktiviert;
• – das Ergebnis dieses Soll/Ist-Vergleiches kann der Applikationsclient abrufen.

During the test, an evaluation of the start sequence is carried out with the following characteristics:

• The application client can define setpoints with respect to external voltages, time intervals and contents of the received Milbus messages (command test, position data, start data 1, start data, command ignition), by means of which the values measured during a start sequence are compared, if the application client activates this function ;
• - The result of this target / actual comparison, the application client can retrieve.

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

Missile launcher

20

distribution facility

22A

electrical interface

22A '

electrical supply connection

22A ''

input side signal line connection

22A '' '

input-side data communication connection

22B

output-side interface

22B '

electrical supply connection

22B ''

Signal line connection

22B '' '

Data communication port

23A

electrical interface

23A '

electrical supply connection

23A ''

input side signal line connection

23A '' '

input-side data communication connection

23B

output-side interface

23B '

electrical supply connection

23B ''

Signal line connection

23W '' '

Data communication port

24B

output-side interface

24B '

electrical supply connection

24B ''

Signal line connection

24B '' '

Data communication port

25B

output-side interface

25B '

electrical supply connection

25B ''

Signal line connection

25B '' '

Data communication port

30

Weapons computer core

31

Power supply unit

31 '

management

32

Missile Interface Module

32 '

Voltage converter means

32 ''

Signal conversion means

32 '' '

Data communications / data conversion means

32A

Weapon computer internal first electrical interface

32A '

electrical supply connection

32A ''

Signal line connection

32B

missile launch device side second electrical interface

32B '

electrical supply connection

32B ''

missile launch device side signal line connection

32B '' '

Communication Port

33

Missile Interface Module

33 '

Voltage converter means

33 ''

Signal conversion means

33 '' '

Data communication means

33A

Weapon computer internal first electrical interface

33A '

electrical supply connection

33A ''

Signal line connection

33B

missile launch device side second electrical interface

33B '

electrical supply connection

33B ''

missile launch device side signal line connection

33B '' '

Communication Port

34

Missile emulation module

34A

first electrical emulation interface

34A '

electrical supply connection

34A ''

Signal line connection

34B

second electrical emulation interface

34B '

electrical supply connection

34B ''

Signal line connection

35

Missile emulation module

35A

first electrical emulation interface

35A '

electrical supply connection

35A ''

Signal line connection

35B

second electrical emulation interface

35B '

electrical supply connection

35B ''

Signal line connection

40

start canister

41

missile

42

start canister

43

missile

44

start canister

45

missile

46

start canister

47

missile

K

harness

V

connection cable

Claims (6)

Missile launch device for at least one missile ( 41 . 43 . 45 . 47 ), with at least one missile launcher ( 2 ) and at least one weapon computer ( 3 ) as a start, test and / or diagnostic computer for missiles to be launched ( 3A . 3B . 3C . 3D ), characterized in that the weapon computer ( 3 ) a weapon core ( 30 ) and has a modular structure, to which end it must be equipped with at least one interchangeable missile interface module ( 32 . 33 ), on the one hand a standardized weapon computer-internal first electrical interface ( 32A . 33A ) and on the other hand an individualized missile launch device side second electrical interface ( 32B . 33B ), wherein the electrical control computer-internal first electrical interface ( 32A . 33A ) and the missile start device side second electrical interface ( 32B . 33B ) in each case at least electrical supply connections ( 32A ' . 33A '; 32B ' . 33B ' ) and signal line connections ( 32A '' . 33A ''; 32B '' . 33B '' ) for signal transmission and wherein the missile interface module ( 32 . 33 ) at its missile start device side second electrical interface ( 32B . 33B ) with the missile launcher ( 2 ) is electrically connected. A missile launching device according to claim 1, characterized in that the missile interface module ( 32 . 33 ) electrical voltage conversion means ( 32 ' . 33 ' ), which has at least one first electrical interface ( 32A . 33A ) convert electrical voltage present in at least one electrical voltage at the missile start device side second electrical interface ( 32B . 33B ) is present. A missile launching device according to any one of the preceding claims, characterized in that the missile interface module ( 32 . 33 ) electrical signal conversion means ( 32 '' . 33 '' ), which comprises at least one first electrical interface ( 32A . 33A ) is present in a signal at the missile start device side second electrical interface ( 32B . 33B ) convert existing missile-specific control signal. A missile launching device according to any one of the preceding claims, characterized in that the missile interface module ( 32 . 33 ) Data communication means ( 32 ''' . 33 ''' ) which are designed to be connected to the first computer-internal electrical interface ( 32A . 33A ) incoming and / or outgoing data communication streams in at the missile start device side second electrical interface ( 32B . 33B ) to convert incoming and / or outgoing missile-specific data communication streams. A missile launching device according to one of the preceding claims, characterized in that the weapon computer ( 3 ) with at least one exchangeable missile emulation module ( 34 . 35 ), on the one hand a standardized weapon computer-internal first electrical emulation interface ( 34A . 35A ) and on the other hand an individualized missile start device-side second electrical emulation interface ( 34B . 35B ), wherein the weapon computer-internal first electrical emulation interface ( 34A . 35A ) and the missile start device side second electrical emulation interface ( 34B . 35B ) in each case at least electrical supply connections ( 34A ' . 35A '; 34B ' . 35B ' ) and signal line connections ( 34A '' . 35A ''; 34B '' . 35B '' ) for signal transmission. A missile launching device according to claim 5, characterized in that the missile emulation module ( 34 . 35 ) at its missile start device side second electrical emulation interface ( 34B . 35B ) with the missile launcher ( 2 ) or with the missile start device side second electrical interface of the missile interface module ( 32 . 33 ) is electrically connected.

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