DE102015009661A1 - Method for converting an air-to-air guided missile - Google Patents

Abstract

The invention specifies a method for converting an air-to-air guided missile (2) with a seeker head (1), comprising a gimbal (8) attached to a rotatably mounted to the two gimbal axes axis of rotation (6) rotatably mounted rotor (1). 4), one at the intersection (29) of the two gimbal axes arranged infrared detector (28) rotatably connected to the rotor (4) beam optics (22), and an optical modulator (26) which is adapted to a beam path of Radiation optics (22) on the infrared detector (28) to guide, for an air-ground use, said optical modulator (26) by a non-rotatably connected to the gimbal (28) or non-rotatably connected to the rotor (4) relay Optical system (38) comprising a rod lens (40), and wherein the infrared detector (28) is replaced by a 4-quadrant detector (42) attached to the gimbal (8). The invention further mentions a correspondingly upgraded air-to-ground guided missile (2a).

Description

Two technologies are generally available for the stabilization and target tracking of a seeker head in a passive-infrared guided air-to-air LFK (guided missile). In a first system, the LFK has a double frame in which a target acquisition unit is suspended pivotally and slidably with respect to the LFK. In a second rotor-based system, a beam optics is attached to a rotatably mounted, gimballed rotor (eg "sidewinder"). The rotor in this case has a perpendicular to the axis of rotation aligned magnetic moment, so that it is on the one hand via drive coils in rotation displaceable, on the other hand, its axis of rotation can be tracked by means of alignment coils in the direction of the detected target.

In general, the rotor is intended to stabilize the optical axis of the target detection, and to be able to track it to the target independently of the LFK. The axis of rotation of the rotor is thus ideally aligned in the direction of the target, especially at the beginning of the flight, when the LFK due to the proximity to him supporting platform, z. As an aircraft or a helicopter, not yet steered itself. The LFK is then tracked according to the target orientation of the rotor.

In the original rotor-based system, the detector is pivotally suspended in the gimbal center, but unlike the beam optics, does not rotate with it. The detector is usually designed to provide only information about the total incident IR radiation power. An optical modulator arranged in the image plane of the beam optics ensures that the IR radiation power is greatest when an incident heat ray emitted by a target is parallel to the optical axis. The modulator may be part of the rotating beam optics and thus rotate with the rotor or be connected freely from rotation with the gimbal of rotor or beam optics.

Which system in a LFK ultimately is actually realized depends, among other things, on the dimensions of the LFK and, in particular, on the available installation space in its search head, but also on reasonable tax expenditure. While the suspension of a unit for target acquisition is technically more complicated to track, a rotor-based system usually has a considerably limited installation space for the beam optics and the detector.

A rotor-based system for target tracking usually seeks as a target a point-shaped heat source, which is imaged via the stabilized by the rotor beam optics on a cooled, rigidly mounted in the LFK infrared detector. However, the target detection of such a heat point is quite easy to fool with today's means, for. B. by so-called "IR decoys" in the form of a variety of torch-like sources of interference, which emits a target to be identified missile for its safety. A double-frame system has the advantage that a true imaging detection can be integrated there, which can detect such sources of interference significantly better by means of image analysis, for example via motion vectors of the heat sources. However, due to the limited installation space, a rotor-based system can only be upgraded to a limited extent with such electronics for detecting IR decoys. As a result, rotor-based, passive IR-guided air-to-air LRCs, which have long been established in the market and used by many forces, are becoming increasingly technically obsolete.

The invention is therefore based on the object to find a new application for a rotor-based air-air-LFK with heat-seeking IR target detection with minimal modifications, and possibly retool it so that it is set up suitable for the new intended use.

This object is achieved by the method with the features of the independent claim 1 and by the device with the features of claim 6. Advantageous and partly taken by itself inventive embodiments are the subject of the dependent claims.

The invention is based on an air-to-air LFK with a seeker head, which is attached to a gimbal, about a perpendicular to the two gimbal axes axis of rotation rotatably mounted rotor at the intersection of the two gimbal axes IR detector, one with the rotor rotatably connected beam optics and comprises an optical modulator, wherein the modulator is adapted to guide a beam path of the beam optics to the infrared detector. According to the invention, a method for converting the air-to-air LFK for air-ground use is proposed, wherein the optical modulator by a rotationally fixed with the gimbal or rotatably connected to the rotor, so in particular as part of the rotating with the rotor beam optics Relay optics is replaced, which includes a rod lens, and wherein the IR detector is replaced by a 4-quadrant detector, which is attached to the gimbal mounting. The rod lens of the relay optics is therefore, for example, rotation-free with the gimbal suspension connected or held directly in the rotor housing, so that it rotates with the rotor.

The infrared detector of the air-air-LFK can be arranged fixed or pivotable and gable with the gimbal suspension. The replacing 4-quadrant detector is arranged in particular in the inner frame of the gimbal and thus pivotally and with this gable. The optical modulator of the air-to-air LFK can be designed as a refractive modulator, and is designed such that radiation incident on its front side is imaged onto the IR detector with as little loss as possible. As a result, the intensity detected by the detector is higher, the more the beam optics are aligned in the direction of a heat source emitting in the spectral range of the IR detector. For this purpose, the optical modulator is usually arranged in the focal plane of the beam optics.

The rotor preferably has a magnetic moment perpendicular to the axis of rotation. As a result, the rotor can be set in rotation by means of magnetic coils suitably arranged in the seeker head. As a result of the rotation, the optical axis of the beam optics connected in a rotationally fixed manner to the rotor can be stabilized during operation of the LFK. By means of magnetic precession coils suitably arranged in the seeker head, the rotor can be aligned in the direction of the target in the air-to-air AFC by means of an output signal of the IR detector. The output signal in this case has a corresponding modulation with the rotational frequency of the rotor due to the propagation of an incident beam path through the co-rotating with the rotor optical modulator, when the axis of rotation is not aligned in the direction of the IR source and thus the target.

For an air-to-ground deployment, the optical modulator is now replaced by a relay optic having a rod lens and the IR detector replaced by a 4-quadrant detector. The use of relay optics allows the focus plane of the beam path to be placed directly on the 4-quadrant detector. The rod lens of the relay optics preferably has the highest possible refractive index with sufficient transparency in a desired spectral range. Advantageously, the entrance surface of the rod lens may be concave ground to allow the most compact possible focusing. The rod lens can be made of a transparent aluminum ceramic, z. B. IG6, be made. This allows a cylindrical shape of the rod lens due to the high refractive index. A concave grinding can thus be omitted. Due to the material properties of IG6, the rod lens is preferably to be introduced into a protective mount.

The invention is initially based on the recognition that a rotor-based LFK with a heat-seeking IR target detection in air-air deployment by IR decoys in the form of a variety of torch-like sources of interference, which emits a target to be identified missile for its safety is very easy to disturb. In order to be more suitable for the modern air combat, an LFK with heat-seeking IR target acquisition should therefore preferably be set up to identify such IR decoys as safely as possible and to neglect them in the target acquisition. This often requires complex data processing in the form of a time-resolved image analysis, for example, to be able to distinguish the IR decoys from the actual target - usually an aircraft or a helicopter - by means of a comparison with predefined movement patterns based on the movements of the heat sources in the field of view of the viewfinder.

In order to retrofit an already existing LFK concept for such a data processing, the LFK would have to provide additional electronic components for the additional calculations as well as an additional physical memory for the information to be entered beforehand (eg movement patterns). On the other hand, in many existing LFK systems, the IR detector present in the seeker head would not have sufficient optical resolution since often only the total power of the incident IR beam impinging on the detector is registered. Accordingly, another detection unit would be attached. In a rotor-based LFK, however, the installation space in the seeker head for such additional components is not given, which is why electronic retrofitting, if at all, is possible only with considerable development effort.

To expand the space could therefore be replaced by a rotor-free suspension according to the suspension of the beam optics in the rotor, which leads incident IR light to an optionally adapted detector. Such a suspension should also preferably have a device for stabilizing the optical axis of the beam optics, since the stabilization would be dispensed with by the centrifugal moment of the rotor. However, this would require a completely new design of the seeker head.

The invention now surprisingly recognizes that the said inconveniences can be avoided in the conversion when a rotor-based air-air LFK is retrofitted with heat-seeking IR target detection for air-to-ground use. Preferably, the target acquisition is hereby designed to track a target marked with a laser. The mark can here, for example from the carrier platform of the LFK - usually an airplane or a helicopter - made. Such a laser-assisted target acquisition in the air-to-air combat prohibits for strategic reasons, as a target marking required permanent visual contact with the enemy flying object should be avoided (so-called "dogfight situation") so as not to become an easy target itself. For this reason, as far as possible so-called "Fire &Forget" solutions are preferred in aerial combat, so that a conversion of said LFK for a laser-based target acquisition there would bring no real applicability. The danger of even providing a target is given only to a much lesser extent in the case of an air-to-ground deployment of the LFK, especially at higher altitudes (from approx. 2000 meters).

By converting an air-to-air LFK for the laser-assisted air-ground use is thus a system available, which compared to commonly used air-ground systems, such. B. Gleitbomben, has the advantage of showing by the active target mark a much lower risk of collateral damage. Due to the semi-active targeting by means of laser marking of the target - instead of an IR-based target acquisition - the use is not only limited to sufficient heat-emitting targets, but can, for example, protected and / or corresponding camouflaged targets such. B. Bunker sight. Since an existing LFK system is retrofitted for this purpose, the corresponding mechanical holding devices on the carrier platform as well as the electronic interfaces for controlling the LFK can be used without additional adjustments, whereby development effort and thus production costs can be saved. In addition, due to the small adjustments, the new system can be available at short notice.

Preferably, an air-to-air guided missile is retrofitted with an infrared detector designed as an IR point detector, the infrared point detector being replaced by a 4-quadrant detector attached to the gimbal. In this case, an IR point detector is understood to be an IR detector which, without itself providing further spatial resolution via an incident IR beam, only detects the power of the incident IR beam. Many air-to-air AFCs with rotor-based viewfinders, which are currently still in the contingents of various forces, have such an IR point detector in the seeker head.

The target acquisition and Zielnachführung by means of an IR point detector, however, is particularly easy to fool with modern means in air combat, for example via so-called "IR decoys" in the form of torch-like sources of interference. Since the IR point detector does not allow spatial resolution of the detected objects, the target acquisition can not sufficiently distinguish the IR exchange body from the originally desired air target - usually an airplane or a helicopter. Since there is insufficient space available in a rotor-based seeker to electronically improve the target detection by means of the detection or discrimination of IR decoys, the proposed method for rotor-based air-air-LCF with an IR point detector is particularly advantageous.

Appropriately, an air-to-air LFK is equipped with a Cassegrain optics comprehensive beam optics, the Cassegrain optics comprising a primary mirror and a curved, in particular perpendicular to the rotation axis or to the rotation axis curved, and / or inclined to the rotation axis secondary mirror, and wherein the curved and / or inclined secondary mirror is replaced by a plane or perpendicular to the axis of rotation secondary mirror. In other words, a curved secondary mirror is replaced by a flat secondary mirror. An inclined secondary mirror is replaced by a secondary mirror perpendicular to the axis of rotation. A curved and inclined secondary mirror is replaced by a flat or by a perpendicular to the axis of rotation secondary mirror. In this case, the mirror which respectively reflects an incident beam in the beam path as first or second mirror in the direction of the 4-quadrant detector is to be understood here as primary or secondary mirror. In another variant, the Cassegrain optics comprises a perpendicular to the axis of rotation aligned secondary mirror.

If the primary mirror and / or the secondary mirror are configured as rear surface mirrors, so that the optical path penetrates an optical glass during the reflection at the respective mirror, then preferably the respective primary and / or secondary mirror designed as a rear surface mirror can be replaced. Due to the dispersion of the optical glass through which the beam path leads to the reflective rear surface, a primary or secondary mirror designed as a rear surface mirror is to be adapted to the spectral range of the light to be detected in order to guide sufficiently high incident light in the frequency range to be detected to the detector in the beam path can. An IR detector equipped for heat target detection, as is widespread in an air-to-air LCF, often detects IR light in a spectral range with wavelengths greater than 2 μm for target detection.

If the air-to-air LFK is converted for laser-assisted air-to-ground use, the dispersive elements of the beam optics are preferably at the wavelength of the target mark used To tune Lasers. A variety of lasers commonly used for the target have a wavelength shorter than 1.5 μm. Due to the high spectral power density, for example, an Nd: YAG laser is often used whose emission focus is at 1064 nm, with further emissions taking place in the range from 1047 nm to 1079 nm. Preferably, therefore, dispersive elements of the beam optics are to be adapted to a corresponding change in the spectrum of the light to be detected.

Conveniently, an air-to-air LFK is retrofitted with a beam dome shielding the beam optics of the seeker head, the dome of the beam being replaced by a filter dome. The ray dome shields the beam optics of the seeker head in the air-to-air LFK against the outside world. In the region of the radiation to be detected for the target detection, which is frequently detected in a spectral range with wavelengths greater than 2 μm, the radiation dome has the highest possible transmission. The ray dome here is often formed as a spherical glass, wherein the center of the sphere is preferably selected at the intersection of the gimbal axes.

Due to the dispersion of the beam dome, the latter must preferably be replaced when the spectral range of the light to be detected for the target detection is changed such that the beam path experiences as few changes as possible. In order to increase the sensitivity of the target detection and target tracking, the radiant dome is replaced by an optical material which, in addition to the mentioned desired dispersion properties for the beam path suitable mechanical properties to the special requirements for strength and temperature resistance flying at up to two times the speed of sound missile suffice. In addition, the radiation dome is preferably also filtered in such a way that only in a narrow spectral band, for example of 200 nm, preferably of 100 nm around the wavelength of the laser to be used for the target mark, is there a significant transmission. The Befilterung can be actively applied to the filter dome. The filter dome is preferably formed here as a spherical glass, wherein the center of the sphere is preferably selected at the intersection of the gimbal axes.

Additionally or alternatively, further optical elements are advantageously also filtered. Since the beam optics co-rotate with the rotor during operation of the seeker head, high demands are placed on the uniformity of the optically active surfaces when filtering to the components of the beam optics, in order to avoid undesired modulations of the incident light. It is therefore preferable to undertake a filtering on non-rotating elements. This can be done - additionally or alternatively to the filter dome - on the rod lens of the relay optic itself or between the relay optics and the 4-quadrant detector or on this itself. Preferably, a narrow-band optical filter can be provided and set up in the region of the relay optics, which is appreciably transparent only in a comparatively narrow spectral range around the wavelength of the laser to be used for the target marking. Spectral ranges outside this band can preferably be filtered with a further filter glass, which is arranged in front of the relay optics. For example, a support lens of the missile is designed as a filter glass.

It proves to be advantageous if an air-to-air LFK with a detector cooler, which is thermally conductive connected to the IR detector, is converted, wherein the detector cooler is replaced by a signal post-amplifier, which with At least one signal connection to the 4-quadrant detector is provided, or in other words: instead of the detector cooler which is no longer required, a signal post-amplifier for the 4-quadrant detector is arranged in the installation space which has become vacant there. Preferably, the 4-quadrant detector is additionally followed by a signal preamplifier, which amplifies the signals of the 4-quadrant detector such that they can be supplied to the signal post-amplifier via the at least one signal connection. It is particularly clever if the 4-quadrant detector and the signal preamplifier are designed as a single unit in order to be able to optimally utilize the available installation space. The 4-quadrant detector can therefore be indirectly connected via the signal preamplifier or directly to the signal post-amplifier via the at least one signal connection. An IR detector often requires cooling in the scope of military targeting in order to have a sufficiently high sensitivity. For this purpose, a corresponding detector cooler is arranged in many existing systems, usually with respect to the beam path behind the detector, which is connected via a heat-conducting connection with the IR detector. The detector cooler is provided and arranged to keep the IR detector in a prescribed operating temperature range during operation of the LFK via the heat-conducting connection.

For the wavelengths of most lasers commonly used for targeting, the 4-quadrant detector, which replaces the IR detector, does not require cooling. In this case, the detector cooler can be omitted, freeing up additional space in the area behind the detector. In this space, a signal post-amplifier can now be arranged and provided with at least one signal connection to the 4-quadrant detector, wherein the signal post-amplifier is set to, during operation of the LFK an electronic signal which is output from the 4-quadrant detector to reinforce. The signal post-amplifier preferably transmits this amplified signal to an evaluation and / or target tracking electronics. The advantage of such a procedure is that, for reasons of space, the evaluation or target tracking electronics are arranged offset further to the rear of the LFK. Re-amplification with very weak signal currents can in this case prevent signal errors during the transmission from the 4-quadrant detector or from the signal preamplifier to the mentioned electronics. In this case, the postamplifier may preferably comprise a pulse amplifier which can be switched in its amplification. This allows an increase in the signal dynamic range.

The aforementioned object is also achieved by an air-ground LFK with a seeker head, this comprising a fixed to a gimbal, about a perpendicular to the two gimbal axes of rotation rotatably mounted rotor, arranged at the intersection of the two gimbal axes 4-quadrant Detector, a rotor optically coupled to the rotor optics, and a rotatably connected to the gimbal or non-rotatably connected to the rotor relay optics, which includes a rod lens, and is adapted to guide a beam path to the 4-quadrant detector. The advantages mentioned for the method for converting an air-to-air LFK for air-to-ground use and for the further developments of the method can be transferred analogously to the air-ground LFK. The 4-quadrant detector can be arranged here in a fixed position or pivotable and gable with the cardan suspension.

Appropriately, in this case, the beam optics on a Cassegrain optics, which includes a primary mirror and a secondary mirror. The beam path is in this case such that a beam incident from the outside is first reflected at the primary mirror and then at the secondary mirror and is guided to the 4-quadrant detector by means of the relay optics. Preferably, the primary mirror is designed as a parabolic mirror. The use of a Cassegrain optics makes it possible, with a very compact design, to focus a wide-angled incident beam on a comparatively small area, and is therefore particularly suitable for guiding the beam path to the relay optics. The relay optic is preferably incorporated in a center suppression of the primary mirror.

As it proves to be further advantageous if the Cassegrain optics has a support lens on which a fastening device is mounted, wherein the support lens is rotatably connected to the rotor, and wherein the secondary mirror is attached to the fastening device. The use of a carrier lens makes it possible to focus the beam path particularly on a particularly short optical path to the relay optics, so that the distance between the primary mirror and the secondary mirror can thereby be effectively shortened. As a result, the seeker can be constructed very compact. Preferably, the support lens is rotatably connected at its outer edge to the rotor, and preferably the fastening device is mounted in the region of the center of the support lens. The secondary mirror is suspended in such a way that its attachment no further carrier are required, which would cross the beam path. The fastening device is not detected by the beam path, but is in the range of the center suppression of the primary mirror, in which the relay optics is introduced.

An embodiment of the invention will be explained below with reference to a drawing. In each case show schematically:

1 FIG. 2 is a cross-sectional view of an air-to-air LFK with a rotor-based IR seeker; FIG.

2 in a cross-sectional view of the converted to air-ground use LFK after 1 , and

3 in a cross-sectional view of a detailed view of the relay optics and the 4-quadrant detector in the LFK after 2 ,

Corresponding objects are provided in all figures with the same reference numerals.

In 1 is a seeker head in a schematic cross-sectional view 1 an air-to-air LFK 2 shown. The LFK 2 is set up for an air-to-air mission. In the seeker's head 1 is a rotor 4 around a rotation axis 6 rotatable on a gimbal 8th suspended. The rotor 4 has a magnetic moment perpendicular to the axis of rotation 6 on. Rotationally with the rotor 4 connected is a Cassegrain optics 10 , which directly onto the rotor 4 applied parabolic primary mirror 12 and a secondary mirror 14 includes. The secondary mirror 14 is here on a fastening device 16 attached, which in the middle of a carrier lens 18 is integrated. The carrier lens 18 in turn is at its outer edge of a housing 20 held, which on the rotor 4 fixed in such a way that the primary mirror 12 the connection of the housing 20 on the rotor 4 surrounds. The Cassegrain optics 10 and the carrier lens 18 make up the together ray optics 22 , Outward is the seeker 1 through a ray dome 24 shielded, which is formed by a transparent in an IR spectral spherical glass.

An outside on the on the ray dome 24 incident beam is first at the primary mirror 12 and then at the secondary mirror 14 reflected, and then through the support lens 18 on an optical modulator 26 focused. The optical modulator 26 In this case, incident radiation is set up with as little loss as possible on an IR detector arranged behind it 28 to guide and thereby prevent unwanted defocusing of the beam as possible. The one in the intersection 29 the gimbal axes arranged IR detector 28 is through a detector cooler 30 which thermally conducts with the IR detector 28 is connected, cooled to operating temperature.

The seeker 1 has a frame 32 on, in which several magnetic drive coils 34 and a magnetic precession coil 36 are arranged. In the operation of the LFK 2 put the drive coils 34 the rotor 4 about its magnetic moment in a rotation about the axis of rotation 6 , For the target acquisition now becomes one of a target in the spectral range of the IR detector 28 emitted beam via the beam optics 22 and the optical modulator 26 to the IR detector 28 guided, and there detected as radiation power. The output signal of the IR detector 28 is forwarded to a not shown electronics. Is the optical axis of the beam optics 22 or the axis of rotation 6 of the rotor 4 not aligned exactly in the direction of the target, the incident IR radiation through the co-rotating optical modulator 26 modulates what is in the output of the IR detector 28 as a modulation with the rotational frequency of the rotor 4 is noticeable. This modulation of the output signal allows the electronics to determine correction values with which the precession coil 36 is to drive, so that the axis of rotation 6 or the optical axis is aligned in the direction of the target. The rotational movement of the rotor 4 stabilizes the optical axis against vibrations and other movements of the air-air-LFK 2 ,

For steering the air-to-air LFK 2 in the direction of the target, rudders or engines not shown in response to the output signal of the IR detector 28 controlled such that the longitudinal axis of the air-air LFK 2 through the precession coil 36 aligned in the target direction and by the rotation of the rotor 4 stabilized axis of rotation 6 , which coincide with the optical axis of the beam optics 22 coincident, tracked.

In 2 is a schematic cross-sectional view of an LFK 2a to 1 shown, which has been converted for an air-to-ground use. The optical modulator 26 is replaced by a relay optic 38 , which in particular by a rod lens 40 is formed. The exchanged relay optics 38 is present on the inner frame of the gimbal 8th attached, and thus not rotatable. However, it can also be used as part of ray optics 22 with the rotor 4 be made rotatable. Behind the rod lens 40 is the 4-quadrant detector 42 arranged, which the IR detector 28 replaced. In close proximity to 4-quadrant detector 42 there is a signal preamplifier 51 , The 4-quadrant detector and the signal preamplifier 51 form a compact unit, which on the inner frame of the gimbal 8th is attached. The signal preamplifier 51 amplifies the signals of the 4-quadrant detector 42 such that these have a signal connection 44 through the gimbal mounting 8th passed through and a variable in the amplification signal repeater 46 can be supplied to the post-amplification. The signal post-amplifier is in by the removal of the detector cooler 30 vacant space has been arranged.

When converting the LFK to 1 For air-to-ground use, all dispersive elements have to be exchanged because of the changed spectral range of the laser for target detection. This concerns in particular the carrier lens 18 if it is filtered for the IR range. However, there are also filterless variants, wherein the support lens 18 broadband is permeable. The ray dome 24 is through a spherical filter dome 48 replaced. The filter dome 48 In this case, it can be filtered in such a way as to allow the lowest possible radiation power from spectral regions to pass away from the laser used for the target marking. However, this is technically complex and expensive, so that it can be dispensed with.

For the air-ground use is now by the LFK 2a carrying plane from a target marked with a laser of a defined wavelength. The LFK 2a is then unlatched, and operated for safety of the aircraft until shortly after takeoff without steering. However, to avoid losing sight of the target, the optical axis in the seeker becomes 1 Already focused on the target, and by the rotation of the rotor 4 stabilized. Then, through the steering - over rudder or corresponding engines - the longitudinal axis of the LFK 2a followed by the optical axis. The signals of the 4-quadrant detector 42 , which provide information about the deviation of the optical axis of the direction of the target, can be used by an evaluation electronics not shown directly for driving the rudder or engines. The target tracking by means of a 4-quadrant detector is known in the art, and will not be explained in detail here.

For safety and to avoid deception and interference signals can be specified when marking the target, an irradiation pattern, which in the evaluation of the LFK 2a is stored for comparison. Is from the 4-quadrant detector 42 detected a beam in the spectrum of the laser used for the target, which does not specify the variations in the intensity specified in the irradiation pattern - eg. B. short, time-defined sequences of full power and dead times - has, the transmitter can discard such a signal as irrelevant for target detection, which increases security against deception maneuvers, but also against collateral damage.

In 3 is a detail view of the relay optics in a cross-sectional view 38 and the 4-quadrant detector 42 in the LFK 2a to 2 shown. The relay optics 38 and the 4-quadrant detector 42 are stationary in a sleeve 49 in the gimbal 8th attached. In the sleeve 49 is the rotor 4 over ball bearings 50 around the rod lens 40 rotatably mounted.

Although the invention has been illustrated and described in detail by the preferred embodiment, the invention is not limited by this embodiment. Other variations can be deduced therefrom by those skilled in the art without departing from the scope of the invention.

LIST OF REFERENCE NUMBERS

1

seeker

2

Air-to-LFK

2a

for air-to-ground use retrofitted LFK

4

rotor

6

axis of rotation

8th

Cardan suspension

10

Cassegrain optics

12

primary mirror

14

secondary mirror

16

fastening device

18

carrier lens

20

casing

22

ray optics

24

Strahlendom

26

optical modulator

28

IR detector

29

Intersection of the gimbal axes

30

detector cooler

32

frame

34

drive coil

36

Präzessionsspule

38

Relay optics

40

rod lens

42

4-quadrant detector

44

signal connection

46

Signal Postamplifier

48

filter dome

49

shell

50

ball-bearing

51

Signal preamplifier

Claims (8)

Method for converting an air-to-air guided missile ( 2 ) with a seeker head ( 1 ), comprising - one on a gimbal ( 8th ) and about an axis of rotation perpendicular to the two gimbal axes ( 6 ) rotatably mounted rotor ( 4 ), - one at the intersection ( 29 ) of the two gimbal axes arranged infrared detector ( 28 ), - one with the rotor ( 4 ) non-rotatably connected beam optics ( 22 ), and - an optical modulator ( 26 ), which is adapted to a beam path of the beam optics ( 22 ) on the infrared detector ( 28 ) for an air-to-ground deployment, the optical modulator ( 26 ) by a rotationally fixed with the gimbal ( 28 ) or rotatably with the rotor ( 4 ) relay optics ( 38 ), which is a rod lens ( 40 ) and wherein the infrared detector ( 28 ) through a 4-quadrant detector ( 42 ) which is attached to the gimbal ( 8th ) is attached. The method of claim 1, wherein an air-to-air missile ( 2 ) with an infrared detector designed as an infrared point detector ( 28 ) and wherein the infrared point detector is controlled by a 4-quadrant detector ( 42 ) which is attached to the gimbal ( 8th ) is attached. A method according to claim 1 or claim 2, wherein an air-to-air guided missile ( 2 ) with a Cassegrain optic ( 10 ) comprehensive radiation optics ( 22 ), the Cassegrain optics ( 10 ) a primary mirror ( 12 ) and a curved and / or to the axis of rotation ( 6 ), and wherein the curved and / or the axis of rotation ( 6 ) inclined secondary mirror by a plane or perpendicular to the axis of rotation ( 6 ) standing secondary mirror ( 14 ) is replaced. Method according to one of the preceding claims, wherein an air-to-air guided missile ( 2 ) with a ray optics ( 22 ) of the seeker head ( 1 ) shielding radiation dome ( 24 ) and wherein the radiation dome ( 24 ) through a filter dome ( 48 ) is replaced. Method according to one of the preceding claims, wherein an air-to-air guided missile ( 2 ) with a detector cooler ( 30 ), which conducts heat with the infrared detector ( 28 ), and wherein the detector cooler ( 30 ) by a signal post amplifier ( 46 ), which is connected to at least one signal connection ( 44 ) to the 4-quadrant detector ( 42 ). Air-to-ground guided missile ( 2a ) with a seeker head ( 1 ), comprising - one on a gimbal ( 8th ) attached to a vertical axis of rotation to the two gimbal axes ( 6 ) rotatably mounted rotor ( 4 ), - one at the intersection ( 29 ) of the two gimbal axes arranged 4-quadrant detector ( 42 ), - one with the rotor ( 4 ) non-rotatably connected beam optics ( 22 ), and - a non-rotatable with the gimbal ( 28 ) or rotatably with the rotor ( 4 ) relay optics ( 38 ), which is a rod lens ( 40 ), which is adapted to a beam path of the beam optics ( 22 ) to the 4-quadrant detector ( 42 ) respectively. Air-to-ground guided missile ( 2a ) according to claim 6, wherein the ray optics ( 22 ) a Cassegrain optic ( 10 ) having a primary mirror ( 12 ) and a secondary mirror ( 14 ). Air-to-ground guided missile ( 2a ) according to claim 7, wherein the Cassegrain optics ( 10 ) a carrier lens ( 18 ), to which a fastening device ( 16 ), wherein the support lens ( 18 ) rotatably with the rotor ( 4 ), and wherein the secondary mirror ( 14 ) on the fastening device ( 16 ) is attached.

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