EP0650027A2 - Interface pour le transfert de données entre un avion et un missile - Google Patents

Interface pour le transfert de données entre un avion et un missile Download PDF

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Publication number
EP0650027A2
EP0650027A2 EP94116633A EP94116633A EP0650027A2 EP 0650027 A2 EP0650027 A2 EP 0650027A2 EP 94116633 A EP94116633 A EP 94116633A EP 94116633 A EP94116633 A EP 94116633A EP 0650027 A2 EP0650027 A2 EP 0650027A2
Authority
EP
European Patent Office
Prior art keywords
missile
interface
carrier
connecting cable
carrier aircraft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP94116633A
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German (de)
English (en)
Other versions
EP0650027A3 (fr
EP0650027B1 (fr
Inventor
Uwe Mitzkus
Reiner Eckardt
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Bodenseewerk Geratetechnik GmbH
Original Assignee
Bodenseewerk Geratetechnik GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Bodenseewerk Geratetechnik GmbH filed Critical Bodenseewerk Geratetechnik GmbH
Publication of EP0650027A2 publication Critical patent/EP0650027A2/fr
Publication of EP0650027A3 publication Critical patent/EP0650027A3/fr
Application granted granted Critical
Publication of EP0650027B1 publication Critical patent/EP0650027B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/30—Command link guidance systems
    • F41G7/301—Details
    • F41G7/306—Details for transmitting guidance signals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/007—Preparatory measures taken before the launching of the guided missiles

Definitions

  • the invention relates to an interface arrangement for the data transmission between a carrier aircraft and a missile to be launched by the carrier aircraft and provided with a seeker head, which is connected to a computer of the carrier aircraft via a connecting cable (umbilical) designed with few wires for the transmission of analog signals, which during launch the missile is detachable.
  • target-seeking missiles in particular air-to-air missiles, in which the target seeker head generates analog signals depending on the placement of the target on an optical axis.
  • a seeker is referred to below as an "analog seeker”.
  • an imaging optical system sits on a gyro rotor. As a result, it is decoupled from the angular movements of the missile.
  • the gyro rotor and the optical system are arranged behind a "dome" in the tip of the missile which is transparent to infrared radiation.
  • the gyro rotor is gimbal-mounted in the missile.
  • the optical axis of the imaging optical system forms a small angle with the axis of rotation of the gyro rotor.
  • the imaging optical system generates an image of a field of view in the plane of a modulation disk fixed to the missile. This image makes a circular movement relative to the modulation disc.
  • a missile-fixed, 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 placement of a detected, radiating target on 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, by means of which the gyro rotor is constantly aligned with its rotational axis towards the target.
  • a control signal for guiding the missile is derived at the same time from the signals applied to the precession coil.
  • Such a missile is known for example from GB-B-1 355 327.
  • the missiles are usually arranged in a launch device. Before launching, the missiles must be trained on a target. For this purpose, instruction signals are fed to the missile. For this purpose, the missile's target seeker and the carrier aircraft exchange information. In missiles of the type described above, in which the target seeker works with analog signals, this information is a few analog signals that are transmitted via the aforementioned, for example three-wire connection cable.
  • An interface on the carrier aircraft side is provided for receiving these signals and for connection to the data bus of the carrier aircraft. Such an interface can sit in the 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. In order to perceive the target, a scanning movement is commanded to the target seeker before it is launched, so that it searches a larger field of view for a target.
  • the gyro rotor of the target seeker head can also by a command from a carrier aircraft Radar be aimed at a target recognized by the radar.
  • More modern missiles have an image processing target seeker. Such a search head delivers a large number of digital data. This data can be transmitted to the data bus of the carrier aircraft via a data line and a suitable interface.
  • carrier aircraft that are set up for data exchange with missiles that have image-processing seekers.
  • Other carrier aircraft are set up for data exchange with missiles, the seekers of which work in the manner described with analog signals. If the latter carrier aircraft are to be made suitable for operation with more modern image-processing target seekers, a considerable modification is required, in which new cables have to be laid in the carrier aircraft.
  • the invention is based, with the least possible conversion effort missiles of different types, i.e. to operate with an analog or image-processing target seeker with carrier aircraft which are suitable for missiles of any kind, i.e. may also be set up for missiles that differ from the type of missile used. It should therefore be possible to use both missiles with an analog target seeker and missiles with an image-processing target seeker optionally in one and the same carrier aircraft.
  • the conversion effort should be kept low.
  • an interface arrangement which is characterized by: a carrier-side computer system and a carrier-side data bus connected to the computer system; a connecting cable with a small number of conductors for the transmission of analog signals and for connecting the carrier-side data bus to the target seeker; two interfaces for connecting the carrier-side data bus with the connecting cable; a target seeker that optionally forms either an analog target seeker or an image processing target seeker; a first of the two interfaces for signal transmission between the analog target seeker and the carrier-side data bus via the connecting cable; a second of the two interfaces for signal transmission between the image processing target seeker and the carrier-side data bus via the connecting cable; and a controller connected to the connecting cable for controlling the optional connection of the connecting cable to either the first interface or the second interface depending on whether the missile contains the analog target seeker or the image processing target seeker.
  • the data is transmitted in all cases via one and the same connecting cable. This is possible with appropriate preparation.
  • the connection to the data bus of the carrier aircraft is established via one or the other interface. This advantage is exploited if the missile provides more data, for example a larger field of view, from the image processing. If the missile has little data This data can also be processed from the analog signals of the target seeker, although the possibilities are of course limited accordingly.
  • a first interface can be provided in a missile which is equipped with an image-processing target seeker and is connected to a data bus of the missile.
  • This first interface can convert complete sets of signals from the image-processing seeker into signals that correspond to the analog signals originating from an analog seeker.
  • a second interface can process the complete signal sets of the image-processing target seeker head into signal sets for transmission through the connecting cable to an interface on the carrier aircraft side that is set up to receive these signal sets.
  • a switchover device controlled by the interface of the carrier aircraft can be provided, by means of which the first or the second interface of the missile can be connected depending on the type of interface present on the carrier aircraft side. In this way, a missile equipped with an image-processing seeker head can be used in conjunction with a carrier aircraft, which as such is not set up for processing signals from an image-processing seeker head.
  • the first and the second carrier-side interface can optionally be arranged either in the carrier aircraft or in the starter.
  • the computer system of a carrier aircraft is designated by 10 in FIG. With 12 a missile to be fired from the carrier aircraft is designated. The missile 12 and the carrier aircraft are connected via a wiring 14 provided in the carrier aircraft and detachable connections.
  • Carrier-side signal transmitter 15 are provided in order to transmit identification signals or an identification code to the missile 12, which indicates whether the computer system 10 of the carrier aircraft is suitable for processing analog target storage data or image processing data.
  • missile-side signal transmitters 17 are provided in order to transmit identification signals or an identification code to the computer system 10 of the carrier aircraft and to indicate whether the missile is equipped with an analog target placement data generating or an image processing target seeker.
  • FIG. 2 shows a first exemplary embodiment of the interface arrangement according to the invention in the form of equipment on the carrier aircraft side.
  • the computer system 10 arranged in the carrier aircraft contains a data bus 18 on the carrier aircraft side.
  • a first interface 22 on the carrier aircraft side is connected to the data bus 18 via a data line 20.
  • a second interface 26 on the carrier aircraft side is connected to the data bus 18 via a data line 24.
  • the arrows of the data lines 20 and 24 indicate the data flow direction from and to the data bus 18 used in the exemplary embodiment described here.
  • the first interface 22 is located in a component (SEAM box) 28; the second interface 26 is accordingly arranged in a component (SEAM-E-Box) 30.
  • the first interface 22 is designed in a manner known per se to convert signals or data from the computer system 10 and the data bus 18 of the carrier aircraft into signals which are transmitted on a three-wire, detachable connecting cable 32 to a missile (AIM-9) which has an analog target seeker.
  • the second interface 26 is designed, on the one hand, to convert data from the computer system 10 and the data bus 18 of the carrier aircraft into signals which are transmitted on the three-wire connection cable 32 to a missile 12, for example an FK 2 missile, which is an image-processing seeker having.
  • the second interface 26 can process data emanating from the image processing target seeker of the missile 12 and are transmitted via the three-wire connection cable 32 to the data bus 18 and the computer system 10 of the carrier aircraft.
  • the connecting cable 32 runs from the carrier aircraft via plug connections to a starter 34 attached to the carrier aircraft and from there to a connecting part 36.
  • a section 40 of the three-wire connecting cable 32 runs in the component 28.
  • the section 40 is connected via a connection 42 to a further section 44 of the connecting cable 32.
  • the section 44 of the connecting cable 32 runs in the component 30.
  • a control 51 on the carrier aircraft side is provided in the component 30.
  • a corresponding input 50 is connected to section 44 of connecting cable 32.
  • the controller 51 contains switching means in the form of a changeover switch 46, which is connected to a control output 52 of the controller 51 and is arranged in the section 44 of the connecting cable 32.
  • the changeover switch 46 can be used to separate the connecting cable 32 from the connection 42 and thus the component 28 and to connect it to a three-wire cable section 48 which leads to the second interface 26.
  • FIG. 3 shows a modified exemplary embodiment of the interface arrangement, the construction of which is similar to the first exemplary embodiment shown in FIG.
  • the 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 rather in the starter 34.
  • the mode of operation of the modified embodiment shown in FIG. 3 is essentially the same as that of the interface arrangement shown in FIG. 2.
  • the above-mentioned analog seeker head contains no active signal transmitters 17 in the missile. Accordingly, there is no input 50 at the control 51 on the carrier aircraft side Identification signal of the missile on. The absence of this signal indicates that the missile is equipped with an analog seeker. In this case, the controller 51 actuates the changeover switch 46, which then assumes a position in which the first interface 22 is connected to the connecting cable 32. The interface arrangement then assumes the operating position shown in FIG. 2.
  • FIG. 5 shows a second exemplary embodiment of the interface arrangement on the side of the missile 12, which forms an FK 2 missile with an 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 designated by reference numeral 56.
  • the interface arrangement 56 contains a first missile-side interface 58 and a second missile-side interface 60.
  • the first interface 58 is connected to the data bus 54 via a data line 62.
  • 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 connected to the data bus 54 via a data line 64.
  • 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 the data bus 54.
  • the first interface 58 receives signals from the image processing target seeker and a computer which is installed in the FK 2 missile. From these signals, the first interface 58 generates a restricted signal set which corresponds to the analog signal set of an analog target seeker (AIM-9L-SEAM signal set).
  • AIM-9L-SEAM signal set AIM-9L-SEAM signal set
  • such a signal set contains much less information than the signal set from an image processing target seeker is delivered. Accordingly, part of the information is lost when it is provided by an image processing target seeker and processed by the first interface 58.
  • the restricted signal set so generated is intended for use in conjunction with a carrier aircraft that is designed to operate with missiles with an analog target seeker such as the AIM-9L target seeker.
  • the second interface 60 processes the full information provided by the image-processed target seeker, including the missile status data. These signals are processed and sent so that they can be transmitted via the three-wire connection cable 32.
  • the second interface 60 receives instruction data (pre-launch data) from the carrier aircraft via the connecting cable 32, which are converted into data suitable for the data bus 54 and the missile 12 computer.
  • the output of the first interface 58 is formed by a three-wire cable section 66.
  • the output of the second interface 60 is formed by a three-wire cable section 68.
  • the connecting cable 32 can optionally be laid either on the cable section 66 or on the cable section 68 by means of a missile-side control 74.
  • the controller 74 contains switching means in the form of a changeover switch 70, which is connected to the controller 74 by a control line 76.
  • the connecting cable 32 is guided over a "umbilical" 72 that is detachable during firing.
  • the controller 74 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 generated by the carrier-side signal transmitter 15, see FIG. 1, and indicates whether the carrier aircraft is capable of receiving signals or data to process, which originate from 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 active signal generator 17 After being switched on, the active signal generator 17 generates a signal identifying the missile, which is in digital form and is transmitted via the connecting cable 32 to the interface arrangement on the carrier aircraft side. If the aircraft is only equipped with component 28 and thus only for processing analog signals emanating from an analog target seeker head, through an interface 22 on the carrier aircraft side, the missile identification signal does not produce a reaction.
  • the missile-side controller 74 responds to the absence of the reaction by bringing the changeover switch 70 into a position in which the first missile-side interface 58 is connected to the connecting cable 32. Accordingly, the signals emanating from the image-processing target seeker of the FK 2 missile are converted by the first missile-side interface 58 to the aforementioned restricted signal set, which corresponds to the analog signals that can be processed by the computer system 10 of the carrier aircraft.
  • the connecting cable 32 usually contains three conductors or wires.
  • the missile transmits an analog reference signal via one of the conductors, which represents the revolution of the finder rotor in the form of a sine wave.
  • the other two signals are each transmitted by the computer over the other two lines on the basis of the information received by the radar system of the carrier aircraft.
  • These two signals are sine waves that are 90 ° out of phase and the target coordinates in an orthogonal Show coordinate system. This makes it possible for the radar system of the carrier aircraft to transmit signals about the position of the target to the target seeker head of the missile.
  • Such signals can be used to generate the precession signals which provide the finder rotor with a precession directed towards the target detected by the carrier aircraft's radar system.
  • the target seeker head can transmit signals to the carrier aircraft which indicate the deviation of the optical axis of the finder from its central position or the target placement from the optical axis of the finder.
  • the carrier-aircraft-side controller 51 receives the signal identifying the missile from the missile-side signal transmitter 17 and reacts to it by emitting a response signal.
  • the carrier-plane control 51 forms the carrier-plane signal transmitter 15, which supplies the carrier aircraft with identifying signals to the FK 2 missile.
  • the signal for identifying the carrier aircraft is again in the form of a digitally coded signal and is received by the missile-side controller 74 via line 78. After receiving the response signal, the controller 74 switches the switch 70 into a position via the control line 76 in which the second missile-side interface 60 is connected to the connecting cable 32.
  • the presence of the signal identifying the missile on the carrier-side controller 51 also has the effect that the carrier-plane controller 51 switches the changeover switch 46 to a position in which the second carrier-plane interface 26 is connected to the connecting cable 32.
  • the complete signal sets that are generated by the image-processing target seeker are transmitted through the second missile-side interface 60, the connecting cable 32 and the second carrier-plane-side interface 26 to the data bus 18 and thus to the computer system 10 of the carrier aircraft.
  • the active signal transmitter 17 is not present and there is no signal identifying the missile at the carrier-side control 51.
  • the carrier-side controller 51 switches the switch 46 to a position in which the first carrier-plane interface 22 is connected to the connecting cable 32.
  • the response signal emitted by the carrier-side controller 51 remains off, which causes the missile-side controller 74 to switch the changeover switch 70 into a position in which the first missile-side interface 58 is connected to the connecting cable 32.
  • the operating configuration of this arrangement set in this way corresponds to the conventional analog mode of operation of the carrier aircraft in connection with a missile which is equipped with an analog seeker head.
  • the carrier aircraft can only be provided with means for processing analog signals that originate from an analog target seeker of the missile.
  • the carrier aircraft can be provided with means (SEAM-E) for processing digital information originating from an image-processing target seeker.
  • the missile can either be equipped with an analog target seeker or with a digital, ie image processing target seeker.
  • the combination of an analog target seeker with analog signal processing means in the carrier aircraft forms the conventional system.
  • a digital, ie image processing, seeker head enables only a limited function of the system, since the first interface 58 in the missile converts the complete information that originates from the digital, ie, image processing, seeker head into restricted information that corresponds to the information coming from the analog target searcher .
  • the carrier aircraft then does not transmit an identifying signal to the interface arrangement in the missile. This is also the case if the carrier aircraft is set up to process digital information from an image-processing target seeker, but the missile is only equipped with a conventional analog target seeker. In the event that the missile contains an image-processing target seeker and provides digital image information signals and the carrier aircraft is equipped with means for processing the digital image information, the complete signal set of the image-processing target seeker can be used.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP94116633A 1993-10-23 1994-10-21 Interface pour le transfert de données entre un avion et un missile Expired - Lifetime EP0650027B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4336207 1993-10-23
DE4336207A DE4336207A1 (de) 1993-10-23 1993-10-23 Schnittstellenanordnung für die Datenübertragung zwischen Trägerflugzeug und Flugkörper

Publications (3)

Publication Number Publication Date
EP0650027A2 true EP0650027A2 (fr) 1995-04-26
EP0650027A3 EP0650027A3 (fr) 1995-08-30
EP0650027B1 EP0650027B1 (fr) 1999-07-07

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EP94116633A Expired - Lifetime EP0650027B1 (fr) 1993-10-23 1994-10-21 Interface pour le transfert de données entre un avion et un missile

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US (1) US5541839A (fr)
EP (1) EP0650027B1 (fr)
DE (2) DE4336207A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0806625A2 (fr) * 1996-05-09 1997-11-12 Bodenseewerk Gerätetechnik GmbH Interface pour le transfert de données digital entre un missile et un lance-missile
EP1001242A1 (fr) * 1998-11-13 2000-05-17 The Boeing Company Dispositif d'interface de magasin

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US5992290A (en) * 1997-04-09 1999-11-30 Cubic Defense Systems, Inc. Aircraft interface device and crossover cable kit
US5978770A (en) * 1997-04-24 1999-11-02 Visible Interactive Corporation Assigning and managing patron reservations for distributed services using wireless personal communication devices
US6349898B1 (en) 1999-11-16 2002-02-26 The Boeing Company Method and apparatus providing an interface between an aircraft and a precision-guided missile
US6615116B2 (en) 2001-08-09 2003-09-02 The Boeing Company Method and apparatus for communicating between an aircraft and an associated store
US6755372B2 (en) * 2001-12-18 2004-06-29 The Boeing Company Air launch system interface
US6700800B2 (en) * 2002-06-14 2004-03-02 Intel Corporation Retainer for circuit board assembly and method for using the same
US6763289B2 (en) * 2002-07-19 2004-07-13 The Boeing Company System, bypass apparatus and method of operating a store of a first predetermined type
US6941850B1 (en) * 2004-01-09 2005-09-13 Raytheon Company Self-contained airborne smart weapon umbilical control cable
US7137599B1 (en) 2004-04-26 2006-11-21 Raytheon Company Launcher with dual mode electronics
US7353090B2 (en) * 2004-10-04 2008-04-01 The Boeing Company System, bus monitor assembly and method of monitoring at least one data bus of an aircraft
US7551105B2 (en) * 2005-11-30 2009-06-23 Lockheed Martin Corporation Virtual host isolation and detection of embedded operational flight program (OFP) capabilities
US7868276B2 (en) * 2007-10-24 2011-01-11 Lockheed Martin Corporation Airborne vehicle emulation system and method
US7869385B2 (en) * 2007-10-31 2011-01-11 The Boeing Company Interactivity with a bus interface card
DE102022002703A1 (de) * 2022-07-26 2024-02-01 Diehl Defence Gmbh & Co. Kg Effektordatenverbinder zur Datenverbindung eines Effektors mit einer Verschussplattform

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US3609312A (en) * 1968-03-11 1971-09-28 Robert K Higgins Data conversion and control system
US4660170A (en) * 1985-04-29 1987-04-21 General Dynamics, Pomona Division System for providing reprogramming data to an embedded processor
US5036466A (en) * 1989-10-03 1991-07-30 Grumman Aerospace Corporation Distributed station armament system
US5214584A (en) * 1989-12-26 1993-05-25 Hughes Aircraft Company Bidirectional data interface for a processor embedded in a self-propelled vehicle

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0806625A2 (fr) * 1996-05-09 1997-11-12 Bodenseewerk Gerätetechnik GmbH Interface pour le transfert de données digital entre un missile et un lance-missile
EP0806625A3 (fr) * 1996-05-09 1998-12-02 Bodenseewerk Gerätetechnik GmbH Interface pour le transfert de données digital entre un missile et un lance-missile
US5983771A (en) * 1996-05-09 1999-11-16 Bodenseewerk Geratetechnik Gmbh Interface for digital data transfer between a missile and a launcher
EP1001242A1 (fr) * 1998-11-13 2000-05-17 The Boeing Company Dispositif d'interface de magasin
AU759939B2 (en) * 1998-11-13 2003-05-01 Boeing Company, The Store interface apparatus

Also Published As

Publication number Publication date
EP0650027A3 (fr) 1995-08-30
DE4336207A1 (de) 1995-04-27
US5541839A (en) 1996-07-30
DE59408468D1 (de) 1999-08-12
EP0650027B1 (fr) 1999-07-07

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