EP1821060A1 - Missile sans occupant et procédé de positionnement d'un missile sans occupant désaccouplable d'un aéronef - Google Patents

Missile sans occupant et procédé de positionnement d'un missile sans occupant désaccouplable d'un aéronef Download PDF

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Publication number
EP1821060A1
EP1821060A1 EP07002169A EP07002169A EP1821060A1 EP 1821060 A1 EP1821060 A1 EP 1821060A1 EP 07002169 A EP07002169 A EP 07002169A EP 07002169 A EP07002169 A EP 07002169A EP 1821060 A1 EP1821060 A1 EP 1821060A1
Authority
EP
European Patent Office
Prior art keywords
missile
signals
aircraft
receiver
navigation
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
EP07002169A
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German (de)
English (en)
Other versions
EP1821060B1 (fr
Inventor
Michael Grabmeier
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.)
MBDA Deutschland GmbH
Original Assignee
LFK Lenkflugkoerpersysteme 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 LFK Lenkflugkoerpersysteme GmbH filed Critical LFK Lenkflugkoerpersysteme GmbH
Publication of EP1821060A1 publication Critical patent/EP1821060A1/fr
Application granted granted Critical
Publication of EP1821060B1 publication Critical patent/EP1821060B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F41G7/007—Preparatory measures taken before the launching of the guided missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/34—Direction control systems for self-propelled missiles based on predetermined target position data
    • F41G7/346—Direction control systems for self-propelled missiles based on predetermined target position data using global navigation satellite systems, e.g. GPS, GALILEO, GLONASS

Definitions

  • the present invention relates to an unmanned missile according to the preamble of patent claim 1 and to a method for determining the position of an unmanned missile detachable from an aircraft according to the preamble of patent claim 8.
  • Unmanned missiles are well known, for example in the military field as Aufteilungsflug stresses or missiles.
  • a problem with such unmanned missiles is to ensure the navigation accuracy of the missile immediately after uncoupling from the aircraft and in the subsequent solo flight.
  • the missile is shielded by the aircraft, so that the reception of positioning signals, for example signals from satellites of a navigation system such as GPS or Galileo, from the receiver provided in the missile by means of the antenna mounted on the missile difficult if not impossible.
  • the receiver in the missile can receive position determination signals by means of the missile-side antenna and determine its own position. The described time delay until receipt of position-determining signals by the missile-side receiver influences the accuracy of the missile's accuracy immediately after uncoupling from the aircraft and the accuracy of the target achievement of the missile.
  • an unmanned missile which is provided with a navigation receiver, said navigation receiver receives before uncoupling of the missile from the aircraft navigation signals via a repeater provided in the aircraft via radio.
  • the invention has the object of reliably improving the navigation accuracy of a generic missile immediately after uncoupling from the aircraft and in the subsequent solo flight. Furthermore, it is an object of the invention to specify a method for determining the position of an unmanned missile which can be decoupled from an aircraft, which enables a more accurate position determination.
  • the receiver of the missile By supplying the missile in the coupled state with appropriate signals for determining the position of the aircraft during the flight, when the missile is still coupled to the aircraft, the receiver of the missile receives signals for determining the position before uncoupling from the aircraft.
  • This signal supply can be done continuously or during the flight, but it can also be performed only immediately before uncoupling the unmanned missile from the aircraft. In this way, at the time of decoupling the missile from the aircraft already a signal reception of the receiver integrated in the missile on the aircraft-side antenna, so that the receiver is already switched to the navigation system at the time of uncoupling and a so-called "lock-on" with the transmitters of the navigation system, for example the satellite.
  • the receiver By switching the receiver at the time of uncoupling on the missile-side antenna this "lock-on" not interrupted, so that the receiver further receives corresponding signals for determining the position after uncoupling via the missile-side antenna without interruption.
  • the resulting position determination signals from the missile-side receiver to the navigation and control device are directed so that they then check the pre-planned flight path of the unmanned missile and possibly take corrective control measures.
  • the missile Since the missile is provided with at least one further antenna, which is also electrically connected to the receiver, it is ensured that are received in both the horizontal flight of the missile, as well as in the subsequent vertical flight of the missile down reliable signals emitted by satellites for position determination.
  • a first antenna is mounted in the tail of the missile, which is optimized for signal reception in vertical downward flight
  • a second antenna is mounted in the area of the top of the missile and is optimized for signal reception in horizontal flight.
  • the missile according to the invention immediately after uncoupling from the aircraft is navigable and thus targeted maneuverable and not wait until the missile has moved out of the receiving shadow of the aircraft and received until the missile-side receiver corresponding signals for the position determination.
  • the maneuverability of the unmanned missile according to the present invention is thus significantly improved.
  • the provision of the two differently oriented antennas in the missile ensures that regardless of the respective attitude of the missile always a reliable reception of the signals emitted by satellites for position determination is possible because both in vertical flight, and in horizontal flight always an antenna up, ie in the direction of the satellites of the navigation system.
  • the electrical signal input of the missile is electrically connected to the receiver for position-determining signals of the missile, wherein the signals supplied by the aircraft to the electrical signal input of the missile are supplied by an aircraft-side antenna.
  • the analog antenna signal is forwarded from the aircraft to the unmanned missile, which then processed accordingly in his receiver.
  • the electrical signal input of the missile may be electrically connected to the navigation and control device of the missile, wherein the signals supplied by the aircraft to the electrical signal input of the missile are position determination signals provided by an aircraft-side receiver.
  • the missile-side receiver is bypassed during the flight and the signals supplied by the aircraft-side receiver are delivered directly into the navigation and control device of the missile.
  • the unmanned missile in which the missile has a device for determining the attitude and wherein the receiver is acted upon in dependence on the attitude of the missile with signals from the first antenna or from one of the other antennas.
  • the receiver is acted upon in dependence on the attitude of the missile with signals from the first antenna or from one of the other antennas.
  • a particularly advantageous embodiment of the missile is achieved in that the receiver is designed as a multiple receiver, so that it signals for determining the position of at least two different Navigation systems, such as GPS signals and Galileo signals, which he receives via the antennas, process and forward to the navigation and control device.
  • This embodiment makes it possible to use data for position determination, which originate from different navigation systems, and thus to achieve a redundancy.
  • the navigation and control device is designed such that it compares the received and processed in the receiver position determination signals of the different navigation systems in a test and comparison device with each other, checked for plausibility and a position determination by evaluating the position determination signals of the different navigation systems performs.
  • the position data originating from the different navigation systems can be mutually checked for plausibility and thus a possibly disturbed navigation system can be detected so that the data originating from this disturbed navigation system can be excluded from further processing.
  • the missile is designed as a gliding missile.
  • the missile may alternatively or additionally have a separate drive.
  • the method according to claim 8 receives the provided in the missile receiver for positioning signals to the decoupling of the missile from the aircraft, the signals for the position determination of at least one aircraft-side antenna and after decoupling the Missile from the aircraft only from at least one missile-side antenna.
  • the receiver of the missile receives after decoupling the missile from the aircraft, the signals for determining the position in vertical flight from a first missile-side antenna and in horizontal flight from a second missile-side antenna.
  • the first missile-side antenna is preferably provided at the rear of the missile and the second missile-side antennas at the top of the missile in horizontal flight of the missile.
  • the decoupling of the missile from the aircraft is only possible when the receiver of the missile has received signals for determining position via the aircraft-side antenna and the navigation and control device of the missile has received from the receiver the assigned position-determining signals.
  • This condition ensures that the intended in the missile receiver at the moment of uncoupling has established a receiving contact with at least one satellite of the corresponding navigation system, which contact does not break during switching of the antennas after decoupling on the missile side antennas, so that the continuity of positioning guaranteed in the decoupling phase of the missile from the aircraft.
  • the configured as a multiple receiver receiver of the missile receives signals from at least two different navigation systems via the antennas and generates therefrom each position determining signals, which are forwarded to the navigation and control device, wherein the navigation and control device, the different position determination signals compared with each other and with a positioning bus of a missile-side navigation system, such as an inertial system, and mutually checked for plausibility and wherein the navigation and control device based on the Position determination signals of the different navigation systems resulting position data performs a position determination.
  • This method provides redundancy since the current position of the missile can be determined based on different navigation systems.
  • the navigation and control device of the missile to the decoupling of the missile from the aircraft can receive position determination signals from an aircraft-side receiver and after decoupling only from a missile-side receiver.
  • the aircraft 1 shows an unmanned missile 1, which is coupled to a schematically illustrated aircraft 2.
  • the aircraft 2 has a bomb pylon 20 on the underside of the fuselage or on the underside of a wing, which is shown partially cut in FIG.
  • the bomb pylon 20 is partially open on its underside and in this area inside the bomb pylon 20 with two releasable holding devices 22, 24, which engage with two corresponding counter-holding devices 12, 13, which protrude from an upper support member 10 of the missile 1, respectively stand and fix the missile 1 on the aircraft 2.
  • an aircraft-side electrical connector 26 is provided, which is mechanically and electrically connected to a mating connector 17 on the upper side of the missile 1, wherein the missile-side mating connector 17 has an electrical signal input 31.
  • the missile 1 is provided with an avionics 30 shown only schematically in the figures, of which in the figures, only a navigation and control device 32 with integrated testing and comparison device 39, one with the navigation and control device 32 electrically connected receiver 34 for position determination signals and antennas 36, 38 electrically connected to the receiver 34 are shown.
  • the missile 1 is at its rear portion with preferably four evenly spaced over the circumference, pivotable and acted upon by the navigation and control device 32 control surfaces 14, 15 is provided. In the upper part of the missile two wings 16 are attached, which give the missile 1 improved sliding properties.
  • the electrical signal input 31 of the missile 1 is connected via a first signal line 33 to the navigation and control device 32.
  • a first missile-side antenna 36 is mounted in the tail of the missile and connected via a second signal line 35 to the missile-side receiver 34.
  • a second missile-side antenna 38 is mounted in the region of the upper side of the missile and connected via a third signal line 37 to the missile-side receiver 34.
  • the aircraft-side connector 26 includes a signal output 23 which is connected via a first aircraft-side signal line 25 to a position signal receiver 27 aviation avionics, which receives signals for determining the position of an aircraft-side antenna 29 via a second aircraft-side signal line.
  • the analog signal of the aircraft-side antenna 29 is passed through the position signal receiver and is applied to the signal output 23.
  • the receiver 34 of the avionics 30 of the missile 1 becomes via the first missile-side data line 33, the connector 16, 26 and the first aircraft-side data line 25 supplied by the aircraft-side antenna 29 with signals for determining position.
  • the navigation and control device 32 is therefore supplied with positioning signals during the flight and can permanently determine the current position of the aircraft 2 and of the missile 1 connected thereto.
  • the receiver 34 of the missile 1 is initialized via the data lines 25, 33 of the avionics of the aircraft, where current position, speed and time data and various others navigation-relevant and communication-relevant data are transmitted to the avionics 30 of the wing. Only when the aforementioned data to the Missile 1 have been transmitted and the receiver 34 of the missile 1 via the aircraft-side antenna 29 receives corresponding signals for position determination and thus has established a connection to one or more satellites of a navigation system, a release for the decoupling mechanism for the unmanned missile 1, so that the missile can be decoupled from the aircraft 2 only after receiving the aforementioned signals and establishing a communication link to at least one satellite of a navigation system.
  • the connector 17, 26 is released and the signal flow from the aircraft 2 to the missile 1 is interrupted.
  • the position determined immediately before the interruption of the signal flow by the navigation and control device 32 of the missile 1 on the basis of the signals supplied by the aircraft for position determination is stored in a memory (not shown) of the navigation and control device 32 and the navigation and control device 32 determined from this stored position immediately after disconnecting the missile 1 from the aircraft 2, the flight route to a predetermined destination.
  • the first missile-side antenna 36 provided in the tail of the missile 1 autonomously receives signals for the position determination. These signals are passed from the first antenna 36 via the second missile-side data line 35 to the missile-side receiver 34 and this passes corresponding position determination signals to the navigation and control device 32 on, so that the missile 1 can perform an autonomous position determination already in this Fallflugphase.
  • the second missile-side antenna 38 provided on the upper side of the missile 1 receives the Signals for position determination and forwards them via the third missile-side signal line 37 to the missile-side receiver 34, which in turn forwards the corresponding position determination signals to the navigation and control device 32. In this way, autonomous position determination can also be carried out in the horizontal flight phase of the missile 1.
  • a peculiarity of the missile-side receiver 34 is that the receiver 34 can be configured as a multiple receiver, for example as a multi-frequency receiver and either alternately or simultaneously receive signals from satellites of different navigation systems, for example GPS and Galileo. These different signals are then provided by the receiver 34 to the navigation and control device 32, which then processes them in parallel or alternately and then compares the resulting position data. Such a comparison is used for a plausibility check, by means of which it can be detected whether one of the navigation systems is disturbed or the data supplied by it is falsified.
  • the navigation and control device 32 can carry out a more precise determination of the own position of the missile 1, as a result of the signals of the several navigation systems with signals from a single navigation system would be possible.
  • the device according to the invention may also assume other than the above-described embodiments.
  • the device may in particular have features that represent a combination of the respective individual features of the claims.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Position Fixing By Use Of Radio Waves (AREA)
EP07002169.6A 2006-02-16 2007-02-01 Missile sans occupant et procédé de positionnement d'un missile sans occupant désaccouplable d'un aéronef Active EP1821060B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006007142.5A DE102006007142B4 (de) 2006-02-16 2006-02-16 Verfahren zur Positionsbestimmung eines von einem Luftfahrzeug abkoppelbaren unbemannten Flugkörpers

Publications (2)

Publication Number Publication Date
EP1821060A1 true EP1821060A1 (fr) 2007-08-22
EP1821060B1 EP1821060B1 (fr) 2017-03-29

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EP07002169.6A Active EP1821060B1 (fr) 2006-02-16 2007-02-01 Missile sans occupant et procédé de positionnement d'un missile sans occupant désaccouplable d'un aéronef

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Country Link
US (1) US7960675B2 (fr)
EP (1) EP1821060B1 (fr)
DE (1) DE102006007142B4 (fr)

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EP2133648A1 (fr) * 2008-04-10 2009-12-16 LFK-Lenkflugkörpersysteme GmbH Missile sans equipage et procédé de conduite de vol
EP2080981A3 (fr) * 2007-11-24 2011-03-02 LFK-Lenkflugkörpersysteme GmbH Missile sans équipage

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US7845263B1 (en) * 2008-01-18 2010-12-07 Frank Miller Bomb release mechanism for radio-controlled airplane
FR2928063B1 (fr) * 2008-02-26 2011-02-18 Airbus France Dispositif pour la transmission point-a point de donnees, sans fil et a haut debit, entre un vehicule en stationnement et une infrastructure fixe
DE102008034618B4 (de) * 2008-07-25 2015-05-13 Mbda Deutschland Gmbh Verfahren zum Abkoppeln eines unbemannten Flugkörpers von einem Trägerluftfahrzeug
US9188657B2 (en) * 2013-12-03 2015-11-17 The Boeing Company Systems and methods of transmitter location detection
NO340726B1 (en) 2015-08-12 2017-06-06 Kongsberg Defence & Aerospace As Method and system for planning and launching a plurality of missiles to be included in the same mission

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Cited By (3)

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EP2080981A3 (fr) * 2007-11-24 2011-03-02 LFK-Lenkflugkörpersysteme GmbH Missile sans équipage
DE102007056661B4 (de) * 2007-11-24 2015-04-02 Mbda Deutschland Gmbh Verfahren zur Datenkommunikation und unbemannter Flugkörper
EP2133648A1 (fr) * 2008-04-10 2009-12-16 LFK-Lenkflugkörpersysteme GmbH Missile sans equipage et procédé de conduite de vol

Also Published As

Publication number Publication date
EP1821060B1 (fr) 2017-03-29
DE102006007142A1 (de) 2007-08-30
DE102006007142B4 (de) 2014-12-18
US20080035785A1 (en) 2008-02-14
US7960675B2 (en) 2011-06-14

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