EP0650027B1 - Interface for data transfer between an airplane and a missile - Google Patents

Description

The invention relates to an interface arrangement for the carrier aircraft or the missile Data transmission between a carrier-side computer system and one with this computer system connected data bus on the one hand and one of the Carrier to be launched missile, with the carrier over a few wires designed for signal transmission, releasable when fired Connection cable (umbilical) is connected according to the preamble of claim 1 or claim 4.

There are homing missiles, especially air-to-air missiles, where the target seeker is dependent on analog signals from placing the target on an optical axis generated. Such a seeker is referred to below as "more analog Target seeker ". This is the case with conventional missiles Art sits an imaging optical system on a gyro rotor. This makes it from the angular movements of the missile decoupled. The gyro rotor and the optical system are behind a "dome" in the Tip of the missile arranged. The gyro rotor is gimbal stored in the missile. The optical axis of the imaging optical system forms a small angle with the circumferential axis of the gyro rotor. The imaging optical system creates an image of a field of view in the plane of a missile fixed Modulation disc. This picture performs a circling Movement relative to the modulation disc. A Missile-proof, infrared-sensitive detector is in the Pivot point of the gyro rotor behind the modulation disc arranged. The detector delivers frequency or amplitude modulated analog signals depending on the storage of a detected, radiant target from the axis of rotation of the gyro rotor.

The target seeker contains means, e.g. in the form of a precession coil surrounding the transversely magnetized gyro rotor, through which the gyro rotor with its orbital axis constantly is aimed at the goal. From the on the precession coil signals are applied to known homing heads at the same time a control signal for guiding the missile derived.

Such a missile is for example from the patent GB-B-1 355 327.

The missiles are usually arranged in a launch device. Before launching, the missiles must be on a target be briefed. For this purpose, induction signals are sent to the missile fed. To do this, swap the destination seeker of the Missile and the carrier aircraft information. At Missiles of the type described above, in which the Target seeker works with analog signals, this is information a few analog signals, which over the above, for example, transfer three-wire connection cables become. To receive these signals and to connect to the Carrier aircraft data bus is a carrier aircraft side Interface provided. Such an interface can Sitting carrier aircraft itself. The interface can also be arranged in the starting device (launcher).

The target seeker has a relatively small current field of view. The target seeker becomes the target perception before the launch commands a scanning movement so that it has a larger field of view searches for a destination. The gyro rotor of the seeker head can also be carried out by a command from a carrier aircraft side Radar to a target recognized by the radar be aligned.

More modern missiles have an image processing target seeker on. Such a seeker head delivers a multitude of digital data. This data can be transmitted over a data line and a suitable interface on the data plane of the carrier aircraft be transmitted.

US 5,036,466 A discloses a weapon system for use with a plurality of different types of missiles. For this purpose, the weapon system contains one A plurality of distributed missile acquisition stations. In a central unit there is one Plurality of different programs stored, with a specific program is assigned to a specific missile acquisition station. Everyone who Station-specific programs are designed so that they can transfer data between control a missile and the associated missile receiving station. The Central unit controls the operation of the weapon system and data transmission between the central unit and the distributed missile acquisition stations as well as the Transmission of the station-specific programs to the distributed missile reception stations. The data transmission between a missile and the associated missile acquisition stations via a single interface.

A data conversion system is known from US Pat. No. 3,609,312 A analog signals from a missile into digital signals for processing by a digital calculator is converted. The data conversion system is for missiles provided which deliver analog or both analog and digital signals. The digital signals are fed directly to the computer and the analog signals converted into digital signals and also processed in the computer.

There are now carrier aircraft that are used for data exchange are set up with missiles, the image-processing seekers exhibit. Other carrier aircraft are for data exchange set up with missiles, their seekers work with analog signals in the manner described. Are the latter carrier aircraft to operate with more modern ones image processing target seekers are made suitable, a significant modification is necessary, in the carrier aircraft new cables have to be laid.

The invention is based, with the least possible task Modification of missiles of various types, i.e. With analog or image processing target seeker with carrier aircraft operate for missiles of any kind, i.e. may also be set up for missiles launched by the type of missile used in each case. It should thus be possible, both missiles with an analog target seeker as well as missiles with image processing target seeker optional to be used in the same carrier aircraft. Here the conversion effort should be kept low.

In the case of an interface arrangement on the carrier aircraft, this task is accomplished solved according to the invention by the features of claim 1.

With a missile-side interface arrangement, this task becomes solved according to the invention by the features of claim 4.

According to the invention, the data is transmitted in one and the same way in all cases Connection cable. This is possible with appropriate preparation. In the Carrier aircraft side interface arrangement is the connection to the data bus of the Carrier aircraft via the first or the second carrier-plane interface manufactured, depending on whether the missile with an analog or a image processing target seeker is equipped. If the missile comes out of the Image processing more data, e.g. a larger field of vision, then it will Take advantage. If the missile has little data from the analog signals of the destination seeker, this data can also be processed, of course the possibilities are limited accordingly.

In the missile-side interface arrangement, the first and the second are Interface provided in the missile. The first interface can be complete Convert signal sets of the image processing target seeker into signals that the correspond to analog signals originating from an analog target seeker. The second interface can the complete signal sets of the image processing Target seeker to signal sets for transmission through the connecting cable to one Carrier-plane-side interface set up for the reception of these signal sets prepare. In this way, one with an image-processing target seeker equipped missiles are used in connection with a carrier aircraft, as such not for processing signals from an image processing Destination seeker is set up.

The switching means can be controlled by the carrier-side or missile-side control are kept in the first switching state without identification signals and at Reception of identification signals can be switched to the second switching state.

Embodiments of the invention are the subject of the dependent claims.

Fig. 1

ist ein Blockdiagramm und zeigt schematisch den Grundaufbau für den Signalaustausch zwischen Trägerflugzeug und Flugkörper.

Fig. 2

ist ein schematisches Blockschaltbild und zeigt ein erstes Ausführungsbeispiel der Schnittstellenanordnung nach der Erfindung, das zwei Schnittstellen direkt im Trägerflugzeug zum wahlweisen Abschuß von Flugkörpern enthält, die entweder mit einem analogen oder einem bildverarbeitenden Zielsuchkopf ausgerüstet sind.

Fig. 3

ist ein schematisches Blockschaltbild und zeigt eine modifizierte Ausführung der Schnittstellenanordnung nach Figur 2, in der die beiden Schnittstellen im Startgerät angebracht sind.

Fig. 4

veranschaulicht die Wirkungsweise der Schnittstellenanordnung nach Figuren 1 und 2.

Fig. 5

ist ein schematisches Blockschaltbild und zeigt die flugkörperseitige Ausrüstung der erfindungsgemäßen Schnittstellenanordnung, die zwei Schnittstellen in einem Flugkörper mit bildverarbeitendem Suchkopf enthält und die je nach Ausrüstung des Trägerflugzeugs über das Verbindungskabel wahlweise entweder die vollständigen Signalsätze des bildverarbeitenden Zielsuchkopfes oder eingeschränkte Signalsätze überträgt, die den von einem analogen Zielsuchkopf gelieferten analogen Signalen entsprechen.

Embodiments of the invention are explained below with reference to the accompanying drawings.

Fig. 1

is a block diagram and shows schematically the basic structure for the signal exchange between carrier aircraft and missile.

Fig. 2

is a schematic block diagram and shows a first embodiment of the interface arrangement according to the invention, which contains two interfaces directly in the carrier aircraft for selective launching of missiles, which are equipped with either an analog or an image-processing seeker.

Fig. 3

is a schematic block diagram and shows a modified embodiment of the interface arrangement according to Figure 2, in which the two interfaces are mounted in the starter.

Fig. 4

illustrates the mode of operation of the interface arrangement according to FIGS. 1 and 2.

Fig. 5

is a schematic block diagram and shows the missile-side equipment of the interface arrangement according to the invention, which contains two interfaces in a missile with an image processing seeker head and which, depending on the equipment of the carrier aircraft, either transmits via the connecting cable either the complete signal sets of the image processing target seeker head or restricted signal sets that are transmitted by one analog target seeker supplied analog signals.

In Figure 1, 10 is the computer system of a carrier aircraft designated. At 12 is one to be fired from the carrier aircraft Called missile. The missile 12 and that Carrier aircraft are provided over a carrier aircraft Wiring 14 and detachable connections connected.

The computer system 10 is an interface arrangement for the exchange of signals with the missile 12 for the purpose of target acquisition assigned. The signal exchange is through the double arrow 16 symbolizes. Carrier-side signal transmitter 15 are provided to 12 identification signals or on the missile transmit an identification code which indicates whether the computer system 10 of the carrier aircraft for processing analog Target storage data or image processing data is suitable. Missile-side signal transmitters 17 are also provided in order to identification signals or to the computer system 10 of the carrier aircraft transmit an identification code and indicate whether the missile with an analog target storage data generating or an image processing Target seeker is equipped.

Figure 2 shows a first embodiment of the interface arrangement according to the invention in the form of a carrier aircraft side Equipment. The one arranged in the carrier aircraft Computer system 10 contains a carrier-side data bus 18. A first is connected to the data bus 18 via a data line 20 Carrier aircraft-side interface 22. Furthermore, with the Data bus 18 a second carrier-side on a data line 24 Interface 26 connected. The arrows of the data lines 20 and 24 show those in the embodiment described here used data flow direction from and to the data bus 18 on. The first interface 22 is located in FIG a component (SEAM box) 28; the second interface is 26 arranged accordingly in a component (SEAM-E-Box) 30.

The first interface 22 is in a manner known per se designed to receive signals or data from the computer system 10 and convert the carrier aircraft data bus 18 into signals, on a three-core, detachable connecting cable 32 too a missile (AIM-9) can be transmitted, the an analog Has a seeker. The second interface 26 is on the one hand designed to transfer data from the computer system 10 and the Data carrier 18 to convert the carrier aircraft into signals based on the three-wire connection cable 32 to a missile 12, for example a FK 2 missile, which has an image processing target seeker. On the other hand the second interface 26 can process data generated by go out the image processing target seeker of the missile 12 and via the three-wire connection cable 32 to the data bus 18 and the computer system 10 of the carrier aircraft become. The connecting cable 32 runs from the carrier aircraft via plug connections to a on the carrier aircraft attached starting device 34 and from this to a connecting part 36.

A section 40 of the three-wire runs in the component 28 Connection cable 32. Section 40 is via a connection 42 with a further section 44 of the connecting cable 32 connected. The section 44 of the connecting cable 32 runs in component 30. A control on the carrier aircraft side 51 is provided in component 30. A corresponding entrance 50 is connected to section 44 of connecting cable 32. The controller 51 contains switching means in the form of a Switch 46, which is connected to a control output 52 of the controller 51 connected and in section 44 of the connecting cable 32 is arranged. Through the switch 46, the connecting cable 32 separated from the connection 42 and thus the component 28 and connected to a three-wire cable section 48 that leads to the second interface 26.

Figure 3 shows a modified embodiment of the Interface arrangement, the construction of which is the first in FIG 2 shown embodiment is similar.

In the modified exemplary embodiment shown in FIG. 3 components 28 and 30 each contain the first Interface 22 and the second interface 26 and are not arranged in the carrier aircraft itself, but in that Starting device 34. The mode of operation of that shown in FIG. 3 modified version is essentially the same as that of the interface arrangement shown in FIG. 2.

The analog seeker mentioned above does not contain any active signal generator 17 in the missile. Accordingly, it applies the input 50 of the carrier 51 control 51 none Identification signal of the missile on. The absence of this signal indicates that the missile has an analog seeker is equipped. In this case, the controller 51 operates the Switch 46, which then assumes a position in which the first interface 22 connected to the connecting cable 32 is. The interface arrangement then takes the one shown in FIG. 2 shown operating position.

The schematic block diagram of Figure 5 shows a second embodiment of the interface arrangement the side of the missile 12 with an FK 2 missile image processing target seeker.

The FK 2 missile 12 delivers and receives signals or Data via a missile-side data bus 54. The interface arrangement of the FK 2 missile is generally with the reference symbol 56 designated. The interface arrangement 56 contains a first missile side interface 58 and one second missile side interface 60. The first interface 58 is connected to data bus 54 via a data line 62 connected. The data line 62 transmits data or signals in both directions, i.e. from the data bus 54 to the first interface 58 as well as from the first interface 58 to the data bus 54. The second interface 60 is via a data line 64 connected to the data bus 54. The data line 64 transmits Data or signals in both directions, i.e. from the data bus 54 to the second interface 60 as well as from the second Interface 60 to data bus 54.

The first interface 58 receives signals from the image processor Target seeker and a computer in the FK 2 missile is installed. The generates from these signals first interface 58 a restricted signal set that the analog signal set of an analog target seeker (AIM-9L-SEAM signal set) corresponds. Such a signal set contains of course, as already stated, much less information than the set of signals from an image processing seeker is delivered. Part of the information goes accordingly lost when viewed from a vision seeker provided and by the first interface 58 is processed. However, the one created is limited Signal set for use in connection with a carrier aircraft determined that for operation with missiles with analog Homing head is set up like the AIM-9L homing head.

In contrast, the second interface 60 processes the full information from the image-processed seeker including data on missile status becomes. These signals are processed and sent that they transmit over the three-wire connection cable 32 can be. Correspondingly, the second receives Interface 60 from the carrier aircraft via the connecting cable 32 instruction data (pre-launch data) which are used for the data bus 54 and the computer of the missile 12 implemented suitable data become.

The output of the first interface 58 is a three-wire Cable section 66 formed. The exit of the second Interface 60 is from a three-wire cable section 68 educated. The connecting cable 32 can be through a missile side Controller 74 either on the cable section 66 or be placed on the cable section 68. The control 74 contains switching means in the form of a switch 70, the connected to the controller 74 by a control line 76 is. The connecting cable 32 is detachable when fired "Umbilical" 72 led. The controller 74 in turn receives an identification signal or an identification code from the carrier aircraft via the connecting cable 32 and a conductor 78. This identification signal is from the carrier-side signal transmitter 15 generated, see Figure 1, and indicates whether the carrier aircraft is able to process signals or data generated by an analog or an image-processing target seeker. The controller 74 responds by either the first interface 58 or the second interface 58 turns on.

The mode of operation of the interface arrangement described above in a missile 12 with an image processing Target seeker head and an active signal generator 17 equipped is shown schematically in Figure 4 and will described below:

After switching on, the active signal generator 17 generates a the missile-identifying signal, which is in digital form is present and via the connecting cable 32 to the carrier aircraft side Interface arrangement is transmitted. If that Aircraft equipped only with component 28 and thus only for Processing analog signals from an analog target seeker go out through an interface on the carrier aircraft side 22 is set up, the missile identification signal does not call Reaction. The missile control 74 reacts to the absence of the reaction by the Switch 70 in a position in which the first missile side Interface 58 with the connecting cable 32 is connected. As a result, those of the image processor Destination seeker of the FK 2 missile outgoing signals through the first missile-side interface 58 to the aforementioned restricted signal set implemented that the analog Corresponds to signals generated by the computer system 10 of the Carrier aircraft can be processed.

The connecting cable 32 usually contains three conductors or veins. In analogue mode, the missile over one of the conductors transmit an analog reference signal that the Orbiting the viewfinder rotor in the form of a sine wave. The other two signals are generated by the computer over the other two lines based on the information transmitted, received by the radar system of the carrier aircraft becomes. These two signals are sine waves that are 90 ° out of phase are and the target coordinates in an orthogonal Show coordinate system. This makes it possible for the radar system of the carrier aircraft signals the location of the Transmits the target to the missile's seeker. Such Signals can be used to generate the precession signals be that the viewfinder rotor with one to that of the radar system the target aircraft detected target directed precession.

In the same way, the destination seeker can send signals to the carrier aircraft transmitted which is the deviation of the optical axis of the seeker from their central position or the target position from the viewfinder optical axis.

If the second or SEAM-E component 30 in the carrier aircraft is present, the carrier-side controller 51 receives the signal identifying the missile from the missile side Signal generator 17 and responds to it by the delivery a response signal. This means that in this case the Carrier plane control 51 the carrier plane side Signal generator 15 forms that identifying the carrier aircraft Delivers signals to the FK 2 missile. These signals show the missile that the carrier aircraft for processing the complete signal sets is set up by the image processor Go out target seeker.

The signal to identify the carrier aircraft is present again in the form of a digitally encoded signal via line 78 from missile control 74 receive. The controller switches after receiving the response signal 74 via the control line 76 to the changeover switch 70 in a Position in which the second missile-side interface 60 is connected to the connecting cable 32. The existence of the the missile-identifying signal on the carrier aircraft side Control 51 also has the effect that the Carrier aircraft control 51 the switch 46 in a Position switches in which the second carrier side Interface 26 is connected to the connecting cable 32. As a result, the complete sets of signals generated by the image processing target seeker are generated by the second missile-side interface 60, the connecting cable 32 and the second interface 26 on the carrier aircraft side on the data bus 18 and thus on the computer system 10 of the Carrier aircraft transferred.

If the missile is equipped with an analog target seeker is, the active signal generator 17 is not present and the control 51 on the carrier aircraft side is not the cause Missile identifying signal. As a result, switches the carrier-side controller 51 the changeover switch 46 in a position in which the first carrier-side interface 22 is connected to the connecting cable 32. As another consequence of this remains that of the carrier aircraft side Controller 51 outputs the response signal, which causes the missile-side controller 74 changes the switch 70 into a Switch position in which the first missile-side interface 58 is connected to the connecting cable 32. The so set operating configuration corresponds to this arrangement the conventional analog mode of operation of the carrier aircraft in connection with a missile that with an analog Seeker head is equipped.

There are actually four possible combinations:

The carrier aircraft can only be processed of analog signals provided by an analog Go out the missile's seeker. The carrier aircraft can with means (SEAM-E) for processing digital information be provided by an image processing seeker going out. The missile can either use an analog Target seeker or with a digital, i.e. image processing Zieuchkopf be equipped. The combination of analog Target seeker head with analog signal processing means in the carrier aircraft forms the conventional system. The combination of analog signal processing means in the carrier aircraft a digital, i.e. image processing target seeker enables only a limited function of the system, since the first interface 58 in the missile the complete information, that of the digital, i.e. image processing target seeker goes out, converted into restricted information, that of the information originating from the analog target seeker corresponds. The carrier aircraft then transmits no identifying one Signal to the interface arrangement in the missile. This is also the case when the carrier aircraft is for processing of digital information from an image processor Target seeker is set up, but the missile only with a conventional analog target seeker. In the event that the missile has an image processing target seeker contains and digital image information signals are available represents and the carrier aircraft with means for processing the digital image information is set up, the complete signal set of the image processing target seeker be used.

Claims (5)

1. Interface arrangement provided on the carrier aircraft side for the data transmission between a computer system (10) provided on the carrier aircraft side and a data bus (18) connected to this computer system (10) on one hand, and to a missile to be fired from the carrier aircraft, which missile is provided with a target seeker head and is connected to the carrier aircraft through a connection cable (32) detachable when firing and provided with few leads for transmitting analog signals, a first interface (22) being provided on the carrier aircraft side, which first interface (22) is designed for signal transmission through the connection cable (32) between an analog target seeker head of a missile and the data bus (18) provided on the carrier aircraft side,
   characterized in that, for optional use of missiles having analog target seeker head or missiles having image processing target seeker heads, there is provided:

   (a) a second interface (26) provided on the carrier aircraft side, which second interface (26) is designed for signal transmission through the connection cable (32) between an image processing target seeker head of a missile and the data bus (18) provided on the carrier aircraft side,

   (b) a control system (51) provided on the carrier aircraft side and connected to the connection cable (32), which control system (51) responds to identification signals from the missile, and

   (c) switching means switchable in dependence on the identification signals by the control system (51) provided on the carrier aircraft side, which switching means, in a first switching state, connects the connection cable (32) to the first interface (22) provided on the carrier aircraft side and, in a second switching state, connects the connection cable (32) to the second interface (26) provided on the carrier aircraft side.
2. Interface arrangement as set forth in claim 1, characterized in that the switching means are kept in the first switching state by the control system (51) provided on the carrier aircraft side when no identification signals are received and are switchable into the second switching state when identification signals are received.
3. Interface arrangement as set forth in claim 1 or 2, characterized in that the carrier aircraft includes a launcher (34) for firing the missile and the first interface (22) provided on the carrier aircraft side and the second interface (26) provided on the carrier aircraft side are arranged in the launcher (34).
4. Interface arrangement provided on the missile side for the data transmission between a computer system (10) provided on the carrier aircraft side and a data bus (18) connected to this computer system (10) on one hand and to a missile to be fired from the carrier aircraft, which missile is provided with an image processing target seeker head and a data bus (54) provided on the missile side and is connected to the carrier aircraft through a connection cable (32) detachable when firing and provided with few leads for transmitting analog signals,
   characterized in that, for optional use of the missile together with a computer system (10) provided on the carrier aircraft side and designed for processing only analog target deviation data from an analog target seeker head or together with a computer system (10) provided on the carrier aircraft side and suitable for processing digital image processing data from an image processing target seeker head, there is provided:

   (a) a first interface (58) provided on the missile side and connected to the data bus (54), which first interface (58) is designed for converting complete data records generated by the image processing target seeker head into analog signals corresponding to the analog signals from an analog target seeker head and for transmitting these signals through the connection cable,

   (b) a second interface (60) provided on the missile side and connected to the data bus (54), which second interface (60) is designed for converting complete data records received from the image processing target seeker head into a format adapted to be transmitted through the connection cable (32),

   (c) a control system (74) provided on the missile side and connected to the connection cable (32), which control system (51) responds to identification signals from the carrier aircraft, and

   (d) switching means switchable in dependence on the identification signals by the control system (74) provided on the missile side, which switching means, in a first switching state, connects the connection cable (32) to the first interface (58) provided on the missile side and, in a second switching state, connects the connection cable (32) to the second interface (60) provided on the missile side.
5. Interface arrangement as set forth in claim 4, characterized in that the switching means are kept in the first switching state by the control system (74) provided on the missile side when no identification signals are received and are switchable into the second switching state when identification signals are received.

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