EP4662454A1 - Procédé pour faire fonctionner un missile sur une plate-forme de lancement - Google Patents

Procédé pour faire fonctionner un missile sur une plate-forme de lancement

Info

Publication number
EP4662454A1
EP4662454A1 EP24703321.0A EP24703321A EP4662454A1 EP 4662454 A1 EP4662454 A1 EP 4662454A1 EP 24703321 A EP24703321 A EP 24703321A EP 4662454 A1 EP4662454 A1 EP 4662454A1
Authority
EP
European Patent Office
Prior art keywords
missile
launch
launch platform
seeker
platform
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.)
Pending
Application number
EP24703321.0A
Other languages
German (de)
English (en)
Inventor
Lorenz Schmitt
Thomas Kuhn
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.)
Diehl Defence GmbH and Co KG
Original Assignee
Diehl Defence GmbH and Co KG
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 Diehl Defence GmbH and Co KG filed Critical Diehl Defence GmbH and Co KG
Publication of EP4662454A1 publication Critical patent/EP4662454A1/fr
Pending legal-status Critical Current

Links

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
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2273—Homing guidance systems characterised by the type of waves
    • F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves

Definitions

  • the invention relates to a method for operating a missile on a launch platform.
  • the missile uses its seeker head to determine its orientation relative to the launch platform using a direction indicator on the launch platform that is recognizable to the seeker head.
  • the invention is based on the idea that the information on the orientation of the launch platform is not sufficient to reliably know the orientation of the missile. Even knowing the nominal orientation of the missile relative to its launch platform is not sufficient to know its precise position. In order to ensure that a missile is ready for use from a moving launch platform in the long term, the missile should be mounted in a way that protects it well against shocks and vibrations and yet ensures that it can be easily released during launch. Both of these factors speak in favor of a rather loose mechanical connection of the missile to the launch platform. This means that the nominal position and the actual position of the missile can differ considerably. The position information initialized with nominal data may be too imprecise to always ensure that the missile functions correctly.
  • a missile with a seeker head can be considered, whose task is to provide highly accurate measurements of the line of sight to a target. Before or during During launch, this capability can be used to measure the missile's orientation relative to the launch platform very precisely before or during launch. This data can be used for attitude initialization. A direction error can be avoided and the target can be approached reliably.
  • the missile can be mounted on or in the launch platform, whereby no distinction is made between on and in below.
  • the orientation of the missile in the launch platform can be described as its position in the launch platform.
  • a distinction can be made between orientation and position, whereby the orientation can be defined using three independent axes of rotation and the position using three independent directions of translation.
  • the missile can have a rocket engine and means for directional control, such as steering wings, transverse thrust nozzles, steering nozzles or the like.
  • it can be a guided missile or a guided missile, i.e. a missile with the ability to actively steer itself during flight, e.g. to align itself with a target.
  • It can contain an active body to attack a target.
  • the seeker head contains an optics and a detector that are transparent or sensitive to incoming radiation, whereby the radiation can cover the wavelength range from radar radiation to infrared radiation to the visible wavelength range or a part thereof.
  • signal processing is available to determine the direction of incoming radiation from the data from the detector.
  • the direction indicator can be any element that is recognizable for the seeker head. Recognizability exists when the direction indicator can be recognized as such by the seeker head or its signal processing, for example as a feature in an image provided by the seeker head detector. Recognizability exists in particular when the direction of the direction indicator can be determined by the seeker head, for example in relation to a previously known direction of the seeker head, such as the missile axis, or for example preferably relative to the missile's alignment.
  • the direction indicator can be an optical element, whereby the terms optics and direction indicator are not restricted to the visible wavelength range in their function. The optics are, for example, infrared optics or radar optics, so that radiation emitted by the direction indicator or optical element can also be outside the visible wavelength range.
  • the direction indicator can actively or passively emit radiation in a wavelength range in which the seeker head is sensitive.
  • the beam width and beam direction of the direction indicator are expediently selected so that the Radiation is visible to the seeker over all expected uncertainties of the missile orientation and preferably also over all expected uncertainties of the missile position relative to the launch platform.
  • the direction sensor is attached to the launch platform in a rigid manner and, in particular, with a small alignment tolerance. This means that the nominal and actual alignment of the direction sensor match up well.
  • the nominal alignment of the direction sensor is known to the missile.
  • the alignment of the direction sensor can be determined by the direction of a beam that the direction sensor emits. Since the beam propagates in a straight line, the signal from the direction sensor reaches the seeker head without directional error and can be measured there with high precision. The resulting information about the alignment of the missile relative to the launch platform has a much smaller error than the nominal values of the inaccurate mechanical connection.
  • the seeker head of the missile can determine an orientation of the direction sensor relative to a known direction of the missile, such as its longitudinal axis or a reference direction of the seeker head.
  • the seeker head can measure radiation incident from the direction sensor and use this to precisely determine the position of the missile on the launch device.
  • the optics of the seeker head sharply image the radiation emanating from the direction sensor or optical element on its detector.
  • the orientation of the direction sensor is in a known dependency on an orientation of the launch platform, the orientation of the missile relative to the launch platform can be determined from the orientation of the direction sensor to the orientation of the launch platform and the orientation of the direction sensor relative to the reference direction of the missile.
  • the loose and therefore inaccurate mechanical coupling of the missile to the launch platform can thus be replaced by an accurate electromagnetic coupling, so that the orientation of the missile can be determined precisely.
  • the field of view may be limited, so that the field of view must first be roughly aligned with the direction indicator.
  • This rough direction can either already be stored in the missile software or transmitted from the launch platform to the missile.
  • a search procedure can also swivel the optics of the seeker head until the beam of the direction indicator is in the field of view.
  • the beam of the direction indicator can be referred to as the reference beam.
  • the radiation of the direction indicator is advantageously selected so that it differs from background radiation and other sources of interference. This can be achieved by sufficiently high radiation output, but also by an imaged pattern and/or a clearly recognizable change in intensity over time, for example in the form of amplitude modulation.
  • the method can be seen as part of a method for transferring a flight path, a sequence of waypoints or a target from a launch platform to a missile arranged on it and having a seeker head. Since it is useful to know the orientation of the missile on the launch platform immediately before launch, the method can also be seen as a method for launching a missile with a seeker head from a launch platform.
  • the invention is also directed to a launch system comprising a missile with a seeker head and a launch platform for launching the missile.
  • the launch platform contains a direction sensor according to the invention and that the missile is designed to determine its own orientation, in particular relative to the launch platform, with its seeker head using the direction sensor.
  • the direction sensor can radiate actively or passively, i.e. radiate itself or, for example, reflect or transmit radiation from another source, with the beam direction being expediently set relative to a reference direction of the launch platform.
  • the optics of the missile's seeker head are usually set up for infinite focusing.
  • a sharp image of an object on the seeker head's detector is achieved when the radiation emanating from the object falls parallel into the optics.
  • the seeker head can determine the direction of the direction indicator most accurately when its signal is sharply imaged onto the detector, an advantageous embodiment of the invention proposes that the direction indicator is a parallel radiator, i.e. an element that emits electromagnetic radiation with a parallel beam path.
  • the seeker head can determine the angle of incidence of its radiation and from this its alignment relative to the launch platform.
  • the beam cross-section of the parallel radiator can be large or small.
  • the direction indicator contains a laser, in particular an infrared laser, so that the beam cross-section is as small as a laser.
  • the direction indicator can have an alignment element that aligns the rays of an approximately point-shaped light source in parallel or expands the cross-section of a bundle of already parallel rays.
  • the alignment element can be a parabolic mirror that deflects and parallelizes the radiation of a central radiator so that its beam cross-section is larger than the radiating element of the central radiator.
  • alignment elements such as parabolic mirrors or coupling elements made of a glass fiber, are also possible for an actively radiating element. In general, any parallel radiating element is possible.
  • the direction finder can contain an active or a passive radiator. If the direction finder is passive, it can absorb radiation and transmit it to the seeker head, for example as a mirror or as a tube through which the radiation is sufficiently parallelized due to the length of the tube. For this, the ratio of length to inner diameter should be more than 1000.
  • the flight path, waypoints or target data can be given to the missile depending on a reference position of the launch platform.
  • This can refer to a reference point or a reference unit of the launch platform, e.g. a reference navigation unit.
  • the direction sensor is arranged as close to the reference point as possible. It is particularly advantageous if the direction sensor is arranged directly on the reference unit, in particular directly on a reference navigation unit of the launch platform.
  • the direction indicator is aligned in a defined manner to a reference navigation unit of the launch platform.
  • this can also be understood to mean that the reference beam, in particular the parallel beam, emanating from the direction indicator is aligned in a defined manner to the reference navigation unit.
  • this direction can be taken into account when initializing the missile's attitude information.
  • correctly recording the missile's alignment is more important than correctly recording the missile's position on the launch platform.
  • the three directional dimensions of the alignment are therefore important, or in other words the three rotational dimensions in which the missile, e.g. its longitudinal axis, is aligned.
  • the direction determination of the reference radiator only takes into account tilts of the missile around spatial axes that are not parallel to the reference beam.
  • the reference beam is chosen so that tilts can be recorded in the two directions in which the alignment tolerances are most significant for initialising the position. This will usually be the rolling direction and lateral tilt on a launch rail to which the missile may be held, or e.g. B. a lateral tilt relative to a wall of a canister in which the missile can be held, or a tilt of such a canister and thus of the missile relative to the launch platform.
  • the reference beam is particularly advantageous if it runs transversely, particularly preferably perpendicularly, to the direction of the greatest alignment tolerance.
  • a beam direction of the direction sensor is aligned transversely to the longitudinal direction of the missile. Transverse can include a deviation of up to 30° from the vertical, in particular a maximum of 10°.
  • a lateral alignment tolerance of the missile on the launch rail can be detected particularly precisely if a beam direction of the direction sensor is aligned in the lateral direction of a launch rail on the launch platform for the missile.
  • a tolerance of up to 30°, in particular a maximum of 10° can be included.
  • the launch platform usually carries several missiles, for example in a canister, or it carries several canisters each containing one missile.
  • the attitude initialization for several, in particular for all, missiles present.
  • each one initializing missile has a view of a direction indicator. For this to happen, it is not absolutely necessary for each of the seeker heads to see the reference beam before the first missile is launched. It is sufficient if each missile sees the reference beam before its own launch, for example if another missile has been launched that obscures the view of the reference beam.
  • the need for a firing sequence - as described above - can be avoided if several missiles move through the reference beam during launch and locate it. This is possible if the missiles are arranged in a plane in which their longitudinal axes also lie.
  • the reference beam can run a little offset from the seeker heads in the launch direction. For example, the beam runs 10 cm above several seeker heads of several missiles. Before launch, the beam is not visible to any or not all of the seeker heads. However, during launch, the seeker head moves through the reference beam, which is visible for a short period of time to the seeker head just flying through the beam and its direction can be determined.
  • the launch platform and a beam direction of the direction sensor can run in the launch direction in front of their seeker heads.
  • This variant has the advantage that the firing sequence of several missiles arranged one behind the other can be freely selected. In this case, the reference beam is only visible for a relatively short period of time to determine the orientation. This method can also be used when the missiles are launched from individual, sealed canisters.
  • attitude initialization it is advantageous if each missile has its own direction sensor. Before launch, each of the missiles or the associated seeker head can see its direction sensor or element and determine its direction. Alternatively, there are multiple direction sensors for a larger number of missiles. In this case, at least one of the direction sensors is assigned to several missiles.
  • attitude initialization is for a beam from the direction sensor to be split by a beam splitter, e.g. by mirrors and/or several glass fibers, into several reference beams to several seeker heads.
  • the provision of several direction sensors has the further advantage that a missile can use its seeker head to determine its orientation relative to the launch platform in three dimensions around all three spatial axes using several direction sensors.
  • at least two direction sensors are arranged in different directions to the missile or its seeker head and can be localized by the seeker head.
  • the beam directions are expediently linearly independent of one another. It is possible for several missiles to be assigned to one or each of them to be assigned to one direction sensor, so that the number of direction sensors can be kept low.
  • direction indicators there are several direction indicators, each of which has several seeker heads in its beam direction.
  • one seeker head can obscure another, but the rear seeker head can be cleared of view by the front one moving forward.
  • FIG 1 a seeker head of a missile illuminated by a direction finder
  • FIG 2 four missiles in a launch platform, the seeker heads of which are in the beam of a direction finder,
  • FIG 3 four missiles whose seeker heads are located below a beam of a direction finder
  • FIG 4 a director that generates beam parallelism with a parabolic mirror
  • FIG 5 the illumination of a seeker head by a passive direction indicator
  • FIG 6 four missiles on launch rails and a direction indicator seen from above
  • FIG 7 a seeker head illuminated by two direction indicators from two directions
  • FIG 8 four missile seeker heads, each illuminated by its own direction indicator
  • FIG 9 four seeker heads illuminated by several direction indicators without shadowing
  • FIG 10 four seeker heads, each illuminated by several direction sensors.
  • FIG 1 shows a missile 2, of which only the tip with a seeker head 4 is shown for the sake of clarity.
  • the missile 2 is held on a launch platform 6, which is only indicated schematically, in which the missile 2 hangs on a launch rail not shown in FIG 1.
  • the launch platform 6 can have a canister on a vehicle, for example a ship or a land vehicle, in which the missile 2 was transported.
  • the launch platform 6 comprises a reference unit 8, which can be a reference navigation unit that contains a programmable computing unit 10 that receives and/or determines target data and passes it on to a programmable control unit 12 of the missile 2.
  • This data includes a flight direction in which the missile 2 should fly after a launch or advance from the launch platform 6.
  • the control unit 12 controls the flight of the missile 2 by means of a navigation solution that is based on an initial position of the missile 2 in space, which must therefore be known relative to a reference position.
  • the reference position can be the position of the reference unit 8 of the launch platform 6 and thus also the orientation of the launch platform 6 itself, the position of which is known by corresponding sensors 14.
  • the alignment tolerances of the missile 2 in the launch platform 6 can be so large that the current position of the missile 2 deviates significantly from the initial position assigned to it by the computing unit 10.
  • This initial position error can have a significant positioning error during the flight of the missile 2, so that the actual flight of the missile 2 deviates significantly from its target flight. In the worst case, the missile 2 does not reach its mission target.
  • the launch platform 6 is equipped with a direction sensor 16a.
  • FIGS. 1 to 10 show various direction sensors 16a - 16f, which are identified with the same reference number and different reference letters. When describing properties that are common to all direction sensors 16a - 16f, the reference letter is omitted below.
  • the direction sensor 16 has a reference direction that can be formed by a reference beam 18.
  • the reference beam 18 is an electromagnetic beam, for example in the infrared or visible wavelength range.
  • the reference beam 18 has a reference direction and is formed from parallel beams that are directed in this reference direction.
  • the reference direction can be fixed relative to the launch platform 6 and is known in particular to the computing unit 10 and/or the control unit 12 and can also be recognized by the seeker head 4. Since the seeker head 4 is able to recognize the reference direction with high precision, the missile 2 knows its own orientation in the launch platform 6 implicitly or explicitly. It can use this when processing the Include movement specifications and thus fly correctly in the manner assigned to it. Or the current orientation of the missile 2 is communicated to the computing unit 10, which adapts its movement specifications to this orientation and passes them on to the missile 2 in an adapted form. To determine the current orientation of the missile 2 relative to the launch platform 6, the directional data of the reference beam 18, i.e. the direction in which the seeker head 4 detects the reference beam 18, is sufficient.
  • the direction can contain one or more angles of incidence of its radiation into the seeker head 4.
  • the reference beam 18 can be electromagnetic radiation emitted by the directional sensor 16.
  • the directional sensor 16 can generate this actively, e.g. using a laser, or pass it on passively, e.g. using a mirror or a radiation channel.
  • the direction indicator 16 can be an active or passive radiator.
  • the reference beam 18 should be a parallel beam of electromagnetic radiation, to whose wavelength the search head 4 is sensitive.
  • the direction indicator 16a is a parallel radiator that emits its reference beam 18 in exclusively parallel radiation, as indicated in FIG. 1 by the parallel arrows.
  • the reference beam 18 of the direction indicator 16 falls into the search head 4 and is imaged by it onto its detector in a sharp point, from whose position on the detector the reference direction can be determined.
  • the direction indicator 16 is aligned in a defined manner with respect to the reference unit 8 of the launch platform 6, whereby this can be achieved by knowing the reference direction, e.g. relative to the launch platform 6.
  • a loose mechanical connection 20 of the missile 2 to the launch platform 6 is converted into an electromagnetic connection with a low tolerance by means of a fixed mechanical connection 22 with a low tolerance and the electromagnetic bridge to the seeker head 4, with which the current orientation of the missile 2 in the launch platform 6 can be recognized and taken into account.
  • the direction indicator 16 is rigidly connected to the reference unit 8, in particular if it is attached directly to the reference unit 8.
  • the seeker head 4 can determine the reference direction and from this its own orientation in the launch platform 6 - i.e. relative to the launch platform 6. To do this, it aligns its optics 24 so that the reference beam 18 falls into the optics 24 and can be processed to determine the direction.
  • the alignment can be carried out in advance, for example by the control unit 12 knowing - e.g. through data transmitted in advance to the control unit 12 - from which direction the reference beam 18 is to be expected, or by searching for the reference beam 18 by pivoting the optics 24.
  • the launch platform 6 expediently informs the missile 2 when the reference beam 18 or the direction indicator 16 is visible, so that the direction determination can be triggered in this way without the direction indicator 16 always having to be visible.
  • the reference beam 18 or the visibility of the direction indicator 16 can be provided with a code, for example with a radiation code of the reference beam 18, such as a fixed flashing frequency.
  • FIG 2 shows several missiles 2 in the launch platform 6, which is also only indicated schematically here, which contains the reference unit 8 and a direction indicator 16b, which can be designed like the direction indicator 16a or in a different design.
  • the following description is essentially limited to the differences from the embodiment in FIG 1, to which reference is made with regard to the same features and functions. In order to avoid having to repeat what has already been described, all features of a previous embodiment are generally adopted in the following embodiment without being described again, unless features are described as differences from the previous embodiment.
  • the direction indicator 16b is aligned such that its reference beam 18 would pass through all seeker heads 4 of the missiles 2 if it were not shaded by another seeker head 4.
  • FIG 2 shows how the individual missiles 2 are not aligned exactly parallel to one another, but are attached to the launch platform 6 with a relatively large alignment tolerance, i.e. their alignment differs from one another.
  • This alignment tolerance relates to all three directional dimensions, or in other words to all three rotational dimensions. It can also relate to the three translational dimensions, which are less important, however, so they will not be discussed further below.
  • the seeker heads 4 are all in the line of the reference beam 18. If there is a shadow, the reference beam 18 would initially only be visible to the seeker head 4 closest to the direction indicator 16b, so that it can initialize its alignment. Only after this missile 2 has been launched can the seeker head 4 closest to it see the direction indicator 16b and thus determine the direction of the reference beam 18 and its output. direction. In this arrangement, the order in which the missiles 2 are launched from the launch platform 6 is therefore fixed so that each seeker head 4 has a clear view of the direction indicator 16b before launch. First, the missile 2 closest to the direction indicator 16b is launched, then the next missile 2, and so on, up to the missile 2 furthest away from the direction indicator 16b.
  • the reference beam 18 is located in the launch direction or longitudinal direction in front of the seeker heads 4 of the missiles 2 in the launch platform 6, specifically in the extension of the longitudinal direction of the missiles 2.
  • the direction indicator 16b is therefore not visible to any of the seeker heads.
  • the missiles 2 fly through the reference beam 18 with their seeker heads 4, so that this is visible to each of the seeker heads 4 for the time they fly through.
  • the order of launches is irrelevant here, as long as two missiles 2 do not launch so close together that one shadows the other during its flight through the reference beam 18.
  • FIG 4 shows a direction indicator 16c with a radiation source 26 and a parabolic mirror 28 which is illuminated by the radiation source 26.
  • the radiation source 26 can be a central radiator which therefore emits its rays from a center in a spherical or partially spherical manner, for example an incandescent radiator.
  • the rays of the essentially point-shaped radiation source 26 which is located in the focus of the parabolic mirror 28 are aligned parallel by the parabolic mirror 28 and directed as an expanded reference beam 18 to several seeker heads 4 of the launch platform 6 so that - although parallel - it falls into several seeker heads 4 at the same time, the direction of incidence being identical for all seeker heads 4.
  • the beam guide 29 can be directed at its other end towards any radiation visible to the seeker head 4, such as ambient radiation or a warm surface of the launch platform 6, as long as the beam intensity is sufficient to be detected by the seeker head 4.
  • the cross-sectional shape of the reference beam 18 can be predetermined and shaped in a characteristic way, for example as a cross, so that this pattern can be easily distinguished from ambient radiation.
  • the patterning due to the cross-sectional enlargement eliminates the need for strict parallelism of the reference beam 18, which results in an enlargement of the image of the reference beam 18 on the detector.
  • the reference direction can only be determined by pattern recognition combined with a predetermined and easily recognizable reference point of the pattern, e.g. the intersection point of two perpendicular lines.
  • This principle can be applied to any direction indicator 16.
  • a passive direction indicator 16d the area surrounding the reference beam 18 should be darkened so that the reference beam 18 is sufficiently clearly visible against the dark background.
  • a radiation source 26 can be placed on the beam guide 29 in order to increase the radiation intensity. This radiation source 26 does not have to be a component of the direction indicator 16d. And its optionality is indicated in FIG 5 by its dotted representation.
  • FIG 6 shows the configuration of the embodiment from FIG 2 from above, i.e. opposite to the launch direction of the missiles 2.
  • the missiles 2 are each attached to their launch rail 30, whereby considerable variations in the roll alignment and also tilting of the missiles 2 are visible.
  • the fields of view of the seeker heads 4 are all aligned with the direction indicator 16b in order to be able to recognize the reference beam 18 immediately after it has been released by the shadowing.
  • the reference beam 18 runs - apart from the shadowing - through all seeker heads 4.
  • the distance direction 32 which is aligned in the direction of the distance of a missile 2 from its launch rail 30, and the lateral direction 34, which is aligned perpendicular to the distance direction 32 and to the longitudinal direction of the missile 2.
  • the alignment tolerances in one direction are not position tolerances but rotation tolerances, i.e. alignment tolerances about an axis, in the lateral direction 34 about a transverse axis.
  • the orientation or alignment tolerance of the missile 2 in the rolling direction and in the lateral direction 34 can be detected by the reference beam 18 in the lateral direction 34.
  • the rotation axes with respect to which alignment tolerances can be determined are shown by a corresponding representation in Fig. 6.
  • the comparatively small alignment tolerance, or in other words misalignment or deviation from nominal alignment to actual alignment, in the distance direction 32 cannot be detected with this beam alignment because it does not cause a change in the position of the focal point of the reference beam 18 on the detector, but rather a rotation of the focal point.
  • the seeker head 4 is illuminated by several direction indicators 16, whereby their design can be designed in any form from one of the embodiments.
  • the alignment tolerance in the distance direction 32 can also be detected, i.e. around a rotation axis that runs from left to right in the plane of the paper in FIG 7 (see corresponding representation of the rotation axis in FIG 7).
  • the alignment tolerances can be detected in all three spatial directions if the alignment of the two reference directions to each other or to the launch platform 6 or another direction is known. The larger the sine of the angle between the two reference beams 18, the more precisely the alignment of the missile 2 can be detected.
  • each seeker head 4 or missile 2 has its own directional sensor 16, which only illuminates the seeker head 4 assigned to it with parallel beams.
  • this configuration is similar to that of FIG 4, although the parabolic mirror 28 can be dispensed with and instead several directional sensors 16 are used, expediently in the form of parallel radiators.
  • the alignment of the reference beams 18 can be parallel to one another, as shown in FIG 8, although this is not absolutely necessary as long as the reference directions are all known.
  • one reference beam 18 can also illuminate several seeker heads 4 as long as the beams of the reference beam 18 are parallel.
  • FIG 9 shows an embodiment based on the principle of FIG 7, but with several missiles 2, so that each seeker head 4 is exposed to multiple radiation as in FIG 7.
  • the configuration from FIG 9 requires only two directional sensors 16e. These are each equipped with a beam splitter that splits the essentially parallel radiation into several directions. It is important that the beams of a directional sensor 16e only hit a seeker head 4 in one direction, so that the beam splitting shades the other seeker heads 4. In addition, all reference directions of all reference beams 18 must be known, as well as the assignment of the individual reference directions to the search heads 4. This design is easier to calibrate than the embodiments in FIG. 4 and FIG. 8, since only the small beam splitters have to be aligned precisely.
  • the optics 24 of the search heads 4 are aligned so that the reference beams 18 fall in from both reference directions. If the field of view is too small for this, the optics 24 must be turned towards the two reference beams 18 one after the other in order to record their directions one after the other.
  • FIG 10 combines the principles of FIG 6 and FIG 7.
  • Several seeker heads 4 - in FIG 10 only 2 each, but there can be more - are arranged in a reference beam 18, with the associated shadowing.
  • the seeker heads 4 are all illuminated from two directions - except for the shadows - so that the three-dimensional orientation can be determined.
  • the launch of a missile 2 arranged further forward in the reference beams 18 opens up the view of two seeker heads located behind it onto the reference beams 18.
  • the arrangement can be implemented with several active direction sensors 16, so that each reference beam 18 is generated by a direction sensor 16.
  • a single actively radiating element 36 is sufficient, which supplies the direction sensors 16f with radiation via two optical conductors 38, for example glass fibers, by connecting them to the actively radiating element 36.
  • the direction sensors 16f can be decoupling elements that decouple part of the radiation falling through their optical conductor 38 and emit it as their reference beam 18.
  • List of reference symbols Missile Seeker Launch platform Reference unit Processing unit Control unit Sensors af Direction indicator Reference beam Connection Connection optics Radiation source Parabolic mirror Beam guidance Launch rail Distance direction Lateral direction Element optical conductor

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

L'invention concerne un procédé pour faire fonctionner un missile (2) sur une plate-forme de lancement (6). Afin de permettre au missile (2) de suivre de manière fiable la trajectoire requise après lancement, le missile (2) détermine son orientation par rapport à la plate-forme de lancement (6) au moyen de sa tête de recherche (4) et d'un capteur de direction (16a-16f) de la plate-forme de lancement (6).
EP24703321.0A 2023-02-09 2024-02-01 Procédé pour faire fonctionner un missile sur une plate-forme de lancement Pending EP4662454A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102023000398.0A DE102023000398A1 (de) 2023-02-09 2023-02-09 Verfahren zum Betrieb eines Lenkflugkörpers an einer Startplattform
PCT/EP2024/052442 WO2024165405A1 (fr) 2023-02-09 2024-02-01 Procédé pour faire fonctionner un missile sur une plate-forme de lancement

Publications (1)

Publication Number Publication Date
EP4662454A1 true EP4662454A1 (fr) 2025-12-17

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EP (1) EP4662454A1 (fr)
DE (1) DE102023000398A1 (fr)
WO (1) WO2024165405A1 (fr)

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Publication number Priority date Publication date Assignee Title
DE1211407B (de) * 1962-04-12 1966-02-24 Litton Industries Inc Azimutbezugseinrichtung mit Schnelleinstellung in eine vorgeschriebene Azimutrichtung
DE1938714A1 (de) * 1969-07-30 1971-02-04 Seybold Dr Ing Rolf Startverfahren fuer Raketen und aehnliche Flugkoerper und Vorrichtung zur Durchfuehrung dieses Verfahrens
DE2411790C3 (de) * 1974-03-12 1978-06-29 Precitronic Gesellschaft Fuer Feinmechanik Und Electronic Mbh, 2000 Hamburg Verfahren und Waffensystem zur Bekämpfung von Oberflächenzielen
DE3622064A1 (de) * 1986-07-01 1988-01-21 Messerschmitt Boelkow Blohm Einrichtung zur automatischen optischen azimut-ausrichtung
DE4223531C2 (de) * 1992-07-17 1994-10-20 Bodenseewerk Geraetetech Einrichtung zur Führung eines aus einem Werfer abgeschossenen, angetriebenen Flugkörpers
US8552836B2 (en) * 2008-10-20 2013-10-08 The Boeing Company System and method for coupling a component to a vehicle
IL227982B (en) * 2013-08-15 2018-11-29 Rafael Advanced Defense Systems Ltd Missile system with navigation capability based on image processing
US10948293B2 (en) * 2017-05-23 2021-03-16 Omnitek Partners Llc Polarized radio frequency (RF) roll, pitch and yaw angle sensors and orientation misalignment sensors
CN211234453U (zh) * 2020-01-19 2020-08-11 西安深瞳智控技术有限公司 一种导引头性能测试装置
CN112325709A (zh) * 2020-11-03 2021-02-05 西安航天动力技术研究所 一种用于导弹导引头便携式目标空间运动特性模拟平台

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