EP2581699A2 - Corps volant de test et de formation sans conducteur - Google Patents

Corps volant de test et de formation sans conducteur Download PDF

Info

Publication number: EP2581699A2
Authority: EP; European Patent Office
Prior art keywords: missile; training; test; data; navigation
Prior art date: 2011-10-13
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

EP12007013.1A

Other languages

German (de)

English (en)

Other versions

EP2581699B8 (fr

EP2581699A3 (fr

EP2581699B1 (fr

Inventor

Michael Grabmeier

Oliver Menn

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

MBDA Deutschland 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.)

2011-10-13

Filing date

2012-10-10

Publication date

2013-04-17

2012-10-10 Application filed by MBDA Deutschland GmbH filed Critical MBDA Deutschland GmbH

2012-10-10 Priority to PL12007013T priority Critical patent/PL2581699T3/pl

2013-04-17 Publication of EP2581699A2 publication Critical patent/EP2581699A2/fr

2015-08-12 Publication of EP2581699A3 publication Critical patent/EP2581699A3/fr

2018-02-28 Application granted granted Critical

2018-02-28 Publication of EP2581699B1 publication Critical patent/EP2581699B1/fr

2018-04-18 Publication of EP2581699B8 publication Critical patent/EP2581699B8/fr

Status Active legal-status Critical Current

2032-10-10 Anticipated expiration legal-status Critical

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Classifications

- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/08—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles for carrying measuring instruments; Arrangements for mounting sensitive cargo within a projectile; Arrangements for acoustic sensitive cargo within a projectile
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/006—Guided missiles training or simulation devices
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
- F42B12/365—Projectiles transmitting information to a remote location using optical or electronic means

Definitions

the present invention relates to an unmanned training and test missile according to the preamble of claim 1.
Such training and test missiles are used to train and handle the handling in the case of the missile staff and use procedures. It further relates to a method for checking the mission plan data stored in a mission data memory of such a training and test missile.
a mission plan certain coordinates of the planned route as well as terrain data of the area to be overfly and certain landmarks are included, with which the missile during the mission flight compares the sensor information taken by him via sensors to navigate in this way to the destination. It is therefore equally important for mission planners to have a way to train their work of drawing up a mission plan and selecting and defining navigation points.
From the DE 10 2009 040 304 A1 is a device for controlling functional tests and / or service procedures for aircraft deductible unmanned missiles known by means of which also a simulation of errors outside the missile is possible. Even with this device, no realistic mission plan training can be performed.
a method for optimizing the image-based automatic navigation of an unmanned missile is known in which a navigation data-containing mission plan based on satellite or aerial photography is created by means of a mission planning computer, the navigation data containing information about selected topological structures.
the mission plan is loaded into a mission computer of the unmanned missile and with the attached to a carrier aircraft missile, the flight route is flown off by means of the carrier aircraft, the navigation of the unmanned missile uses navigation data of the carrier aircraft.
image analysis in the unmanned missile is performed by analyzing images of the preceding route generated by an unmanned aerial imaging device on topological structures present therein, and the information thus obtained on the analyzed topological structures, together with the image data, the attitude data, and the Position data stored in a memory device.
a three-dimensional reference model is created for those topological structures which have been recognized in the image analysis. Based on the three-dimensional reference model of this topological structure then takes the calculation of a two-dimensional view of a topological structure to a given point on the flight route, taking into account the attitude of the missile at this point.
the two-dimensional view of the topological structure is then compared with the topological structure recognized in the image analysis at that point of the flight route, and the goodness of fit is determined. Subsequently, the reference model is modified if the match quality is below a predetermined value.
a missile training unit with a training missile forming unmanned missile and connectable to the missile configuration device for the training missile known, the training missile has at least one fault memory.
the configuration device is designed in such a way that simulated error data and / or simulated error images are stored in the error memory are playable.
the object of the present invention is therefore to provide a generic unmanned training and test missile, with which it is possible to validate mission plans and to train the staff setting up the mission plan, and to provide a corresponding method.
the first object is achieved by the unmanned training and test missile having the features of claim 1.
a generic unmanned training and test missile in which at least one device for detecting and storing occurring during a training or test flight of the missile equipped carrier aircraft navigation events is provided, data from the navigation computer of the unmanned training and test missile using pass the flight path determined in the mission data memory to the carrier aircraft so that its control navigates during a training or test flight with the navigation data determined by the training and test missile.
the mission planner receives feedback to verify his own work and to check how well his definition of navigation points he has given in the mission plan was suitable for the automatic navigation of the unmanned aerial vehicle.
An advantageous development is characterized in that the device for detecting and storing is designed such that it acquires and stores data relating to the image acquired by the seeker and its matching with the landmark image data stored in the mission data memory.
This development makes it possible in a particularly reliable manner to verify the detection of landmark image data given in the mission plan by the seeker head of the missile.
the image processing computer is connected to graphics processing means arranged to associate lines and / or points extracted by the image processing computer from an image taken by the seeker with a first color and to arrange lines and / or points parallel thereto from the image processing computer and stored in the mission data memory reference landmark assigned a second color, and that the image processing computer is configured so that the image detected by the seeker image or moving image with lines and / or points in the two colors is stored in a memory of an image recording device ,
This color coding of the target data and the actual data during a training flight facilitates the later evaluation, since deviations of the detected by the image capture devices of the missile during the training landmarks are clearly visible from the predetermined in the mission plan landmarks, so that the quality of assignment by the image processing computer is immediately recognizable.
an event storage device is further provided, which is adapted to capture and store command data, which are commanded during the training or test flight from the carrier aircraft to the missile.
the event storage device is configured to acquire and store flight condition data of the missile during the training or test flight.
a further advantageous embodiment of the training and test missile according to the invention is characterized in that a telemetry data storage device is provided, which is designed such that it records telemetry data transmitted on a missile-internal data bus.
This telemetry data recording enables a fine evaluation of a mission simulated in a training flight with the command and / or flight condition data preferably registered in addition to the event logging in the event storage device.
This method according to the invention for checking the mission plan data stored in a mission data memory of an unmanned training and test missile according to one of the preceding claims in a training or test flight of a carrier aircraft equipped with the unmanned training and test missile is characterized in that the control of the carrier aircraft with the Navigational data determined by the training missile navigates that a recording of the navigation events takes place and that the recorded navigation events are subsequently evaluated and from this conclusions about the quality of the mission plan are made.
Fig. 1 the hardware architecture of a training and test missile 1 according to the invention is shown schematically.
the dashed line symbolically represents the unmanned training missile 1, which is also referred to as CATM (captive air training missile).
CATM consumer air training missile
This training and test missile 1 is provided on its upper side with an umbilical plug 10 for electrical connection to a carrier aircraft.
the training and test missile 1 has a test and load (TLP) device 11 with a TLP connector 12, to which in the application example shown a configuration device 2 for the training and test missile 1 is connected for data exchange.
TLP test and load
the training and test missile 1 is equipped with a central weapon computer 14 (Central Weapon Computer CWC) and with a power supply unit PS1.
the power supply unit 16 is supplied via the umbilical plug 10 and / or the TLP plug 12 with electrical energy from the outside and in turn supplies the central weapon computer 14 with electrical energy.
the central weapon computer 14 is connected to both the umbilical connector 10 and the TLP connector 12 by data lines.
the Fig. 1 is shown symbolically and that is connectable to the TLP connector 12 as an alternative to the configuration device 2, performs tests or operating operations for exercise purposes, the missile is then, as if simulated error data are stored in the error configuration memory 142, respond as if the simulated errors were actually present, so that the operator team can train their skills in detecting and resolving simulated errors.
the configuration device 2 may also be provided in the service and test device 3.
the training and test missile 1 further comprises a navigation computer 13 (NAVC), which is provided with a GPS receiver 130, to which a GPS antenna 131 is connected.
the navigation computer 13 is further connected to a radar altimeter 132.
a battery 133 is provided for the power supply of the GPS receiver 130 in the navigation computer 13.
the battery 133 is in electrical communication both with the navigation computer and with the test and programming unit 11.
the navigation computer 13 is further connected via corresponding connecting lines directly with the test and programming unit 11 and the umbilical plug 10 in electrical connection.
the navigation computer 13 is connected to a data bus 15 (IMBUS). To this data bus 15 and the central weapon computer 14 is connected.
IMBUS data bus 15
a seeker head 16 is provided in the nose of the training and test missile 1 and has a seeker head sensor 160, which is designed, for example, as a stabilized infrared camera, and an inertial measurement unit 161. Also, the seeker 16 is connected to the central data bus 15. Furthermore, an image processing computer 17, which is connected via an image data bus connection 170 to the seeker head 16 for data transmission, is connected to the central data bus 15. The image processing computer 17 is provided or connected to a graphics processing device 171, which in turn is connected to a converter device 172 for transferring an image signal, for example an RGB signal. The converting means 172 converts the image signal obtained from the graphic processing means 171 into an image signal of a storable signal format (for example, CVBS) supplied to an image recording device 173 such as a flash VTR.
a storable signal format for example, CVBS
the training and test missile 1 is further provided with a device 18 for sharpening and firing of an active charge, both with the central Data bus 15 and is connected to the Umbilical connector 10 for data exchange.
the device 18 for sharpening and firing (SIU: Safety and Ignition Unit) is used in a sharp missile to activate a not present in the present training and test missile 1 thermal battery through which the training missile after uncoupling from the carrier aircraft during the mission with electric Energy is supplied.
this thermal battery is not present and in an operational missile device 18 for sharpening and ignition with the thermal battery connecting electrical cable 180 is in the training and test of the invention 1 by a flight to a valve for controlling the coolant reservoir 162nd for the seeker 16 extending cable replaced, as in the German patent application 10 2010 017 974.4 is described.
the training and test missile 1 is still provided with a fuel tank 19 in its central portion.
the error memory 141 assigned to the central weapon computer 14 is preferably configured as a flash memory, so that the stored data is retained even when the power supply is switched off. In this error memory 141 actually occurring errors or defects of the missile are stored in order to perform a quick and effective repair can.
simulated error data are recorded by means of the configuration device 2, for example data about a defective module, about a time of the occurring defect and about a type of error image, so that a missile defect in the flying flight can be simulated for training purposes.
a flash memory event data store 143 as an event logger, which stores during the execution of the test timestamp occurring events that are based on an interaction between carrier aircraft and missile.
This event recording is carried out, for example, from switching on the training missile to the simulated departure of the training missile or switching off the training missile.
it contains periodic missile flight state data (eg position, speed, Euler angle) stored.
the data stored in this event memory for example, with a service and testing device as in the DE 10 2008 054 264 A1 is revealed, read out and evaluated in relation to the mission plan. In this way, additional information about the actions performed by the responsible operating personnel on board the carrier aircraft during training can be obtained and the performance of the operating personnel can be checked and evaluated.
the missile's march and attack phase is simulated by the carrier aircraft with the coupled missile flying off the flight path determined by the missile's navigation systems using the mission plan data.
the number of lines and / or points of the reference landmark used for navigation as well as the counter values of the image-guided navigation data sets provided absolutely by the image processing computer 17 and quality criteria of the image processing performed are also stored.
a record of the seeker video including the aforementioned fades in different colors is recorded by the VCR 173, for example, a flash VTR.
This video data can be evaluated after a successful training flight, in which case geographic and / or geometric errors, for example of reference landmarks, can also be identified.
a data recording device 150 such as a flash data recorder, built with which the transmitted over the weapon system data bus 15 telemetry data is recorded.
the data recording device 150 is connected to the data bus 15 via a telemetry module 151 (TM-MK4) and thus effectively connected to the data recording device 150 for data transmission from data available on the data bus 15.
T-MK4 telemetry module 151
a transmitter 250 is provided, which is connected for data transmission to the telemetry module 251, which in turn is connected to the data bus 15.
the transmitter 250 is connected to a transmitting antenna 250 'for signal transmission.
a radar transponder 252 is connected to the telemetry module 251, which in turn is connected to a second transmitting antenna 252 'for signal transmission.
a flight test termination system (FTTS) 254 is provided, which is connected on the one hand to the signal transmission to the telemetry module 251 and which on the other hand is operatively connected to the signal transmission to a third antenna 254 '.
An FTTS battery 256 provides the Flight Test Termination System 254 and the telemetry module 251 with electrical energy released from the carrier aircraft.
a video transmitter 273 is provided, which is connected to the converter device 172 for image signal transmission and which is likewise connected to a fourth antenna 273 'for image signal transmission, in order to transmit the video signal.
the in Fig. 3 illustrated training and test missiles 1 is preferably equipped with the required for a free flight components of an operational missile to autonomously fly the mission plan after decoupling from the carrier aircraft can (TOM telemetry operational missile), in particular the rudder control (FCU fin control unit) and the rudder actuators (FD fin drive) available in FIG. 3 symbolically shown as a unit and denoted by the reference numeral 20.
TOM telemetry operational missile in particular the rudder control (FCU fin control unit) and the rudder actuators (FD fin drive) available in FIG. 3 symbolically shown as a unit and denoted by the reference numeral 20.
the third embodiment of the training and test missile it is also possible to perform the last part of a mission plan, the approach to the target and the flight to the target, and to transmit the data obtained by telemetry to a ground station where they will then be available for evaluation and validation of the mission plan.
This final mission, the flight to the finish is understandably unworkable, when the missile remains coupled to the carrier aircraft and the carrier aircraft with the navigation data of the missile flies off the mission plan, as described in connection with the examples of Fig. 1 and 2 has been described.
the image recording device for the image data output from the video transmitter 273 and the recording device for the data bus telemetry data output from the transmitter 250 are in the variant of FIG Fig. 3 provided in the ground station.
the in the Figure 3 shown variant of the training and test missile is used in sharp practice shooting on military shoots that require special safety devices in the missile.
this variant allows the maintenance crew to practice the installation of safety devices in operational production missiles.

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Engineering & Computer Science (AREA)
Chemical & Material Sciences (AREA)
Combustion & Propulsion (AREA)
General Engineering & Computer Science (AREA)
Aviation & Aerospace Engineering (AREA)
Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

EP12007013.1A 2011-10-13 2012-10-10 Corps volant de test et de formation sans conducteur Active EP2581699B8 (fr)

Priority Applications (1)

Application Number	Priority Date	Filing Date	Title
PL12007013T PL2581699T3 (pl)	2011-10-13	2012-10-10	Zdalnie kierowana rakieta treningowo-testowa

Applications Claiming Priority (1)

Application Number	Priority Date	Filing Date	Title
DE102011115963A DE102011115963B3 (de)	2011-10-13	2011-10-13	Unbemannter Trainings- und Testflugkörper

Publications (4)

Publication Number	Publication Date
EP2581699A2 true EP2581699A2 (fr)	2013-04-17
EP2581699A3 EP2581699A3 (fr)	2015-08-12
EP2581699B1 EP2581699B1 (fr)	2018-02-28
EP2581699B8 EP2581699B8 (fr)	2018-04-18

Family

ID=46967586

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP12007013.1A Active EP2581699B8 (fr)	2011-10-13	2012-10-10	Corps volant de test et de formation sans conducteur

Country Status (4)

Country	Link
EP (1)	EP2581699B8 (fr)
DE (1)	DE102011115963B3 (fr)
ES (1)	ES2671227T3 (fr)
PL (1)	PL2581699T3 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE102015002587B4 (de)	2015-02-27	2021-09-09	Mbda Deutschland Gmbh	Stationäres Testgerät für Flugkörper
DE102015002563B3 (de) *	2015-02-27	2016-02-11	Mbda Deutschland Gmbh	Flugkörper-Startvorrichtung
DE202015004074U1 (de) *	2015-02-27	2016-05-31	Mbda Deutschland Gmbh	Flugkörper-Startvorrichtung

Citations (6)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE102007018187A1 (de)	2007-04-18	2008-10-30	Lfk-Lenkflugkörpersysteme Gmbh	Verfahren zur Optimierung der bildgestützten automatischen Navigation eines unbemannten Flugkörpers
DE102008054264A1 (de)	2008-10-31	2010-05-12	Lfk-Lenkflugkörpersysteme Gmbh	Multifunktionale Service- und Testeinrichtung für unbenannte Flugkörper
DE102009040304A1 (de)	2009-09-05	2011-05-12	Lfk-Lenkflugkörpersysteme Gmbh	Vorrichtung zur Steuerung von Funktionstests und/oder Serviceprozeduren für von Luftfahrzeugen absetzbare unbemannte Flugkörper
DE102009022007B4 (de)	2009-05-19	2011-09-22	Lfk-Lenkflugkörpersysteme Gmbh	Unbemannter Flugkörper
DE102010017974A1 (de)	2010-04-23	2011-10-27	Lfk-Lenkflugkörpersysteme Gmbh	Verfahren zum Simulieren einer Mission eines unbemannten bewaffneten Flugkörpers
DE102011114225B3 (de)	2011-09-23	2012-06-14	Lfk-Lenkflugkörpersysteme Gmbh	Flugkörper-Trainingseinheit

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE102010018186B4 (de) *	2010-04-26	2013-11-14	Mbda Deutschland Gmbh	Verfahren zur Fehlererfassung eines im Tragflug an einem Trägerflugzeug angekoppelten, unbemannten Flugkörpers sowie unbemannter Flugkörper

2011
- 2011-10-13 DE DE102011115963A patent/DE102011115963B3/de active Active
2012
- 2012-10-10 PL PL12007013T patent/PL2581699T3/pl unknown
- 2012-10-10 ES ES12007013.1T patent/ES2671227T3/es active Active
- 2012-10-10 EP EP12007013.1A patent/EP2581699B8/fr active Active

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE102007018187A1 (de)	2007-04-18	2008-10-30	Lfk-Lenkflugkörpersysteme Gmbh	Verfahren zur Optimierung der bildgestützten automatischen Navigation eines unbemannten Flugkörpers
DE102008054264A1 (de)	2008-10-31	2010-05-12	Lfk-Lenkflugkörpersysteme Gmbh	Multifunktionale Service- und Testeinrichtung für unbenannte Flugkörper
DE102009022007B4 (de)	2009-05-19	2011-09-22	Lfk-Lenkflugkörpersysteme Gmbh	Unbemannter Flugkörper
DE102009040304A1 (de)	2009-09-05	2011-05-12	Lfk-Lenkflugkörpersysteme Gmbh	Vorrichtung zur Steuerung von Funktionstests und/oder Serviceprozeduren für von Luftfahrzeugen absetzbare unbemannte Flugkörper
DE102010017974A1 (de)	2010-04-23	2011-10-27	Lfk-Lenkflugkörpersysteme Gmbh	Verfahren zum Simulieren einer Mission eines unbemannten bewaffneten Flugkörpers
DE102011114225B3 (de)	2011-09-23	2012-06-14	Lfk-Lenkflugkörpersysteme Gmbh	Flugkörper-Trainingseinheit

Also Published As

Publication number	Publication date
ES2671227T3 (es)	2018-06-05
PL2581699T3 (pl)	2018-08-31
EP2581699B8 (fr)	2018-04-18
EP2581699A3 (fr)	2015-08-12
EP2581699B1 (fr)	2018-02-28
DE102011115963B3 (de)	2012-10-25

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