EP2080981A2 - Missile sans équipage - Google Patents

Missile sans équipage Download PDF

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Publication number
EP2080981A2
EP2080981A2 EP08019799A EP08019799A EP2080981A2 EP 2080981 A2 EP2080981 A2 EP 2080981A2 EP 08019799 A EP08019799 A EP 08019799A EP 08019799 A EP08019799 A EP 08019799A EP 2080981 A2 EP2080981 A2 EP 2080981A2
Authority
EP
European Patent Office
Prior art keywords
missile
mission
satellite communication
satellite
data
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
EP08019799A
Other languages
German (de)
English (en)
Other versions
EP2080981B1 (fr
EP2080981A3 (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
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Application filed by LFK Lenkflugkoerpersysteme GmbH filed Critical LFK Lenkflugkoerpersysteme GmbH
Publication of EP2080981A2 publication Critical patent/EP2080981A2/fr
Publication of EP2080981A3 publication Critical patent/EP2080981A3/fr
Application granted granted Critical
Publication of EP2080981B1 publication Critical patent/EP2080981B1/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
    • F41G7/34—Direction control systems for self-propelled missiles based on predetermined target position data

Definitions

  • the present invention relates to an unmanned missile according to the preamble of claim 1. It further relates to a method for data communication between an unmanned missile flying a given mission and a mission control station. In addition, the invention relates to a method for mission planning for an unmanned missile.
  • a problem with the use of unmanned missiles is that for controlling the unmanned missile a line of sight connection to the missile must exist. Routes that go beyond the horizon with respect to the mission control station for the unmanned missile are therefore difficult.
  • an unmanned missile with a predefined flight route and a predefined target as a mission plan, which is stored in a mission data memory of the unmanned missile and whose data are then available to an autonomous control system of the unmanned missile so that it can travel along the stored, in the mission plan set predetermined distance to the specified destination flies.
  • the invention is based on the object or the technical problem of designing an unmanned missile in such a way that it is also able to communicate with a mission control station when it is flying outside the line of sight to the mission control station.
  • Another object is to provide a method of data communication between an unmanned missile flying a given mission and a mission control station, which is also feasible out of sight line communication between the unmanned missile and the mission control station.
  • This unmanned missile which is, for example, a cruise missile, includes a payload-receiving fuselage, control surfaces movably attached to the fuselage by control drives, a missile propulsion device, and an on-board computer including a mission data memory and a control computer. which acts on the control surface drives with control signals.
  • This missile according to the invention is characterized by a satellite communication device, which is electrically connected to the on-board computer for data exchange, and by at least one satellite communication antenna as a transmitting and / or receiving antenna for the satellite communication device.
  • a communication link can be established during the entire flight of the missile to a corresponding communication satellite, which in turn is in communication with the mission control station.
  • a data exchange between the mission control station and the unmanned missile via the satellite or via several satellites of a satellite network can also take place when the unmanned missile for the mission control station has disappeared behind the horizon.
  • the missile is provided with buoyancy-producing wings on the fuselage. This increases the range of the missile.
  • the at least one satellite communication antenna is arranged in the forward direction of the missile in the direction of flight. It can alternatively or additionally also be arranged in the rear of the missile in the direction of flight.
  • the arrangement in the front region of the missile can be made in a particularly favorable manner in the climb of the missile, a communication link to a satellite.
  • the communication link to the satellite can be made particularly reliable in the descent of the missile.
  • a plurality of satellite communication antennas distributed over the circumference of the missile, preferably uniformly, are provided which form a group of satellite communication antennas.
  • the group of satellite communication antennas has four satellite communication antennas which are circumferentially spaced by 90 ° from each other.
  • the respective satellite communication antenna is arranged in the region of the outer skin of the missile and can be pivoted from a seated on the outer skin or recessed under the outer skin rest position in a working position in which the pivot axis in a plane perpendicular to the missile longitudinal axis, then the aerodynamic properties of the unmanned Missile impacted by the additionally provided satellite communication antenna only slightly.
  • the satellite communication antenna may remain in its rest position during the largest time of the cruise and is only swung into its working position for the period of satellite communication in which it gives the missile a greater aerodynamic drag.
  • the on-board computer of the missile preferably has an antenna control device for the satellite communication antennas, by means of which the individual satellite communication antennas can be controlled and by means of which the swivel angle of the satellite communication antennas can be controlled.
  • an antenna control device for the satellite communication antennas by means of which the individual satellite communication antennas can be controlled and by means of which the swivel angle of the satellite communication antennas can be controlled.
  • a satellite communication device electrically connected to an onboard computer of the missile builds a radio link with the satellite independently at a given time or upon reaching a predetermined flight path point or event-controlled Mission control station via a satellite.
  • bidirectional data transmission takes place between the satellite communication device of the missile and the mission control station via the communications satellites.
  • the missile prior to commencement of the establishment of the radio connection, the missile is brought by a control device of the missile in an attitude in which at least one of the satellite communication antennas of the missile can be aligned with the satellite, and then this satellite communication antenna is aligned with the satellite, wherein the missile during the duration the existence of the radio link preferably remains in this attitude.
  • This further development of the method makes it possible, for example, to put the missile in a vertical climb before the start of the construction of the radio link by means of a so-called pop-up maneuver in which one or more of the satellite communication antennas located in the front region of the missile are reliably aligned with the satellite and so a stable communication link to the satellite can be established.
  • the attitude in which the missile is brought for the duration of the radio link preferably a steep climb or a steep descent. This steep climb or steep descent is advantageously a vertical climb or a vertical dive.
  • the missile is not only placed in an appropriate attitude prior to the start of the construction of the radio link, but also from the previous flight path and selects a flight path, the alignment of a line of sight connection between at least one of the satellite communication antennas and a satellite allows.
  • the missile makes a terrain tracking low-level flight for camouflage purposes, it may be necessary and advisable to choose a flight path of greater altitude over ground for the duration of the satellite communications link to allow line-of-sight connection between the missile and a communications satellite.
  • only the antenna is used for the communication between the missile and the mission control station, which is in radio shadow of the missile with respect to potential interference signal sources. This is implemented in particular when the radio missile detects radio interference signals or when the risk of the impact of radio interference signals on the missile is to be expected.
  • the time at which the radio link is established is specified in a mission plan stored in a mission data memory of the missile's on-board computer.
  • the location where the radio connection is established may also be specified in the mission plan. In this way, it is possible to determine, even before the start of the missile, where or when the missile reports by setting up the communication link at the mission control station.
  • This point in time at which the radio connection is set up or the place where the radio connection is established preferably lies before the time or place at which an originally initiated mission can still be terminated or mission data, such as, for example, destinations to be found, can still be changed effectively.
  • the radio link between the missile and the mission control station during a mission can also be set up several times.
  • the method according to the invention is also advantageously suitable for the mission control station transmitting new or changed mission data to the missile during the existence of the radio link, for storing this new or changed mission data in the mission data memory of the missile and for continuing the mission from the on-board computer of the missile using this new or modified mission data.
  • the mission control station transmitting new or changed mission data to the missile during the existence of the radio link, for storing this new or changed mission data in the mission data memory of the missile and for continuing the mission from the on-board computer of the missile using this new or modified mission data.
  • TAN transaction number
  • the satellite communication device of the missile transmits state information of the missile to the mission control station during the existence of the radio link. This gives the flight line in the mission control station the ability to determine if the missile is functioning properly and if the missile is on the predetermined route.
  • the satellite communication device of the missile transmits image data of a camera provided in the missile, preferably as live video, to the mission control station during the existence of the radio link, preferably in the event of an overburden or approach to a destination.
  • image data of a camera provided in the missile preferably as live video
  • the mission control station can also influence the trajectory of the missile by activating control devices of the unmanned missile if the transmitted images make such a change in route appear necessary.
  • target coordinates and flight path data are set and stored in a mission data store the missile stored, with additional distance ranges are set, in which data communication between the missile and a mission control station is carried out.
  • flight positions of the missile are defined, which the missile occupies on the route sections of the planned data communication, so that there is a line of sight connection between the missile and at least one communications satellite.
  • a change in the distance required for the period of data communication during mission planning can also be entered into the mission data memory of the missile.
  • time slots can also be defined during mission planning, at which time the data communication between the missile and the mission control station takes place.
  • Fig. 1 shows an unmanned missile 1 in a schematic representation.
  • the missile 1 comprises a payload-receiving fuselage 10, wings 12 mounted on the fuselage 10, two drive devices provided laterally on the fuselage 10, of which only the left-hand drive device 14 is shown, and control surfaces 16 which can be moved in a known manner by means of control-surface drives (not shown) attached to the hull 10.
  • the missile 1 is further provided with an avionics 2, which is also shown only schematically and is located inside the hull 10.
  • the avionics 2 contains an on-board computer 20 which, in addition to effective connections to conventional navigation devices, also has a mission data memory 22 and a control computer 24.
  • the control computer 24 is supplied by the mission data memory 22 with data of a predetermined flight path and further receives navigation data from conventionally provided navigation devices, such as a satellite navigation system and / or an inertial navigation system. Based on these data, the control computer 24 generates control signals, which are sent to the control surface drives, whereupon they adjust the control surfaces 16 for controlling the missile 1.
  • a satellite communication device 26 is provided in the avionics 2, which is electrically connected to the on-board computer 20 for data exchange.
  • a first group 30 of satellite communication antennas 32, 34, 36, 38 is provided on the outer circumference of the fuselage 1 of the missile 1.
  • the satellite communication antennas 32, 34, 36 and the invisible satellite communication antenna 38 provided on the right side of the missile 1 are circumferentially spaced from each other by 90 ° with respect to the fuselage 10, so that a first satellite communication antenna 32 is provided on top of the fuselage 10, a second satellite communication antenna 34 on the underside of the fuselage and a respective satellite communication antenna 36, 38 on the left and right side of the fuselage.
  • the individual satellite communication antennas 32, 34, 36, 38 are each pivotable away from the fuselage 10 into a working position about a pivot axis 31, 33, 35, 37 located toward the front of the missile 1.
  • Fig. 1 By way of example, the upper front satellite communication antenna 32 pivoted to a working position is shown.
  • the upper front satellite communication antenna 32 is at a swivel angle pivoted so far away from the fuselage 10 of the missile 1 that it establishes a line-of-sight connection to an in-orbit communications satellite 4 for the purpose of data transmission, where the line-of-sight 3 is at right angles to the antenna surface or coincides with its focal axis at a concave antenna surface.
  • rear satellite communication antennas 42, 44, 46, 48 are provided in the rear area 1 "of the fuselage 10, forming a second, rear group 40 of satellite communication antennas, the pivot axes 41, 43, 45, 47 of these rear satellite communication antennas 42, 44, 46, 48 are located on the side facing the tail of the missile 1 side of the respective satellite communication antenna, so that the individual antennas by means of a respective actuator, of which only the actuator 49 of the lower antenna 44 is shown here, from the fuselage by a pivot angle are pivotable away.
  • the satellite communication antennas 32, 34, 36, 38; 42, 44, 46, 48 are in Fig. 1 shown so that they rest in their non-pivoted rest position on the outer skin of the fuselage 10 of the missile 1.
  • this is only a schematic representation.
  • the satellite communication antennas will be in their rest position either in a respective associated recess of the fuselage 10 or under the outer skin of the Hull 10 may be arranged and swing together with a corresponding, associated hull flap to the outside in the working position.
  • pivot axes 31, 33, 35, 37; 41, 43, 45, 47 are aligned so that the respective axis lies in a plane perpendicular to the missile longitudinal axis X.
  • the on-board computer 20 is provided with an antenna control device 28, are passed from the corresponding control commands to the respective satellite communication antenna associated actuator 39, 49.
  • Fig. 2 schematically shows the flight path 100 of an unmanned missile on the way from a (not shown) starting place to one of several targets 102, 104, 106, 108.
  • a mission planning method is performed, in which the coordinates of the targets 102 , 104, 106, 108 as well as the route data of the flight path 100.
  • These specified data are stored in the mission data memory of the missile prior to the launch of the missile.
  • geographic terrain data of a corridor 110 is stored on both sides of the flight path 100 as well as the environment 112 of the targets 102, 104, 106, 108. With this given data and the on-board navigation means, the missile is able to navigate autonomously on its flight path between the starting point and the destination.
  • route areas are also defined in which data communication takes place between the flying missile and the mission control station. Upon reaching these path ranges, the missile will assume an attitude already established in mission planning that will enable it to establish a line of sight connection to a communications satellite, thus providing data communication between the missile and the mission control station can take place over the communications satellites.
  • the beginning of such a route range is already defined as checkpoint 114 during mission planning and stored in the mission data memory. This checkpoint 114 should be in front of a target decision point 116 at which the cruise path 101 from the start location to the destination flight paths or target trajectories 103, 105, 107, 109 separates to the respective targets 102, 104, 106, 108.
  • a target approach point 113, 115, 117, 119 can still be defined on the respective target trajectory 103, 105, 107, 109, to which the missile once again establishes data communication with the mission control station and transmits images of the target approach to the mission control station, be taken by a camera 18 in the bow of the missile 1.
  • the missile Shortly before reaching the control point 114 or one of the target approaching points 113, 115, 117, 119, the missile is brought by its control device in an attitude in which at least one of the satellite communication antennas 32, 34, 36, 38; 42, 44, 46, 48 can be aligned on the communication satellites 4.
  • it may be necessary, for example, to control the missile from a terrain low-altitude flight into a higher trajectory over ground, in which there is a line-of-sight connection to the communications satellite 4.
  • the missile 1 may also be placed in a steep climb or in a steep descent to obtain a line of sight connection from at least one of the satellite communication antennas to the communications satellite.
  • Satellite communication antennas 32, 34, 36, 38 used in the front of the fuselage 10
  • at least one of the satellite communication antennas 42, 44, 46, 48 of the rear portion of the fuselage 10 is used.
  • the communication link is established via the communications satellites 4 to the mission control station;
  • the satellite communication device 26 of the missile 1 is thus the calling part in setting up the communication link.
  • the data exchange takes place between the on-board computer 20 of the missile 1 and the mission control station, which is preferably carried out bidirectionally. If necessary, the image data transmission from the missile 1 to the mission control station takes place in the approach to the destination until it reaches the destination.
  • the missile 1 If the data transmission begun after reaching the control point 114 has ended during cruise flight, then the missile 1 returns to the originally planned flight path, for example, an off-road low-altitude flight, and continues its cruising flight.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Radio Relay Systems (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP08019799.9A 2007-11-24 2008-11-13 Missile sans équipage Active EP2080981B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE200710056661 DE102007056661B4 (de) 2007-11-24 2007-11-24 Verfahren zur Datenkommunikation und unbemannter Flugkörper

Publications (3)

Publication Number Publication Date
EP2080981A2 true EP2080981A2 (fr) 2009-07-22
EP2080981A3 EP2080981A3 (fr) 2011-03-02
EP2080981B1 EP2080981B1 (fr) 2016-10-12

Family

ID=40585726

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08019799.9A Active EP2080981B1 (fr) 2007-11-24 2008-11-13 Missile sans équipage

Country Status (3)

Country Link
EP (1) EP2080981B1 (fr)
DE (1) DE102007056661B4 (fr)
ES (1) ES2610510T3 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2133648A1 (fr) * 2008-04-10 2009-12-16 LFK-Lenkflugkörpersysteme GmbH Missile sans equipage et procédé de conduite de vol
DE102010008807A1 (de) 2010-02-22 2011-08-25 Engelskirchen, Jürgen, Dipl.-Ing., 22395 Verfahren zur selbsttätigen Bahnsteuerung eines steuerbaren Objektes

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5186414A (en) 1992-04-20 1993-02-16 The United States Of America As Represented By The Secretary Of The Navy Hybrid data link

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19543321B4 (de) * 1995-11-21 2006-11-16 Diehl Stiftung & Co.Kg Verfahren und Einrichtung zum drahtlosen Austausch von Informationen zwischen Stationen
US6056237A (en) * 1997-06-25 2000-05-02 Woodland; Richard L. K. Sonotube compatible unmanned aerial vehicle and system
US5855339A (en) * 1997-07-07 1999-01-05 Raytheon Company System and method for simultaneously guiding multiple missiles
US6118066A (en) * 1997-09-25 2000-09-12 The United States Of America As Represented By The Secretary Of The Navy Autonomous undersea platform
DE19906970C2 (de) * 1999-02-19 2003-03-27 Rheinmetall W & M Gmbh Aufklärungssonde
DE60213843D1 (de) * 2001-11-09 2006-09-21 Ems Technologies Inc Strahlformer für eine mehrkeulenempfangsantenne
DE102006007142B4 (de) * 2006-02-16 2014-12-18 Mbda Deutschland Gmbh Verfahren zur Positionsbestimmung eines von einem Luftfahrzeug abkoppelbaren unbemannten Flugkörpers

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5186414A (en) 1992-04-20 1993-02-16 The United States Of America As Represented By The Secretary Of The Navy Hybrid data link

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2133648A1 (fr) * 2008-04-10 2009-12-16 LFK-Lenkflugkörpersysteme GmbH Missile sans equipage et procédé de conduite de vol
DE102010008807A1 (de) 2010-02-22 2011-08-25 Engelskirchen, Jürgen, Dipl.-Ing., 22395 Verfahren zur selbsttätigen Bahnsteuerung eines steuerbaren Objektes

Also Published As

Publication number Publication date
EP2080981B1 (fr) 2016-10-12
DE102007056661A1 (de) 2009-06-04
EP2080981A3 (fr) 2011-03-02
ES2610510T3 (es) 2017-04-27
DE102007056661B4 (de) 2015-04-02

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