DE102007003699B3 - Optical window in an infrared homing head - Google Patents

Optical window in an infrared homing head

Info

Publication number
DE102007003699B3
DE102007003699B3 DE200710003699 DE102007003699A DE102007003699B3 DE 102007003699 B3 DE102007003699 B3 DE 102007003699B3 DE 200710003699 DE200710003699 DE 200710003699 DE 102007003699 A DE102007003699 A DE 102007003699A DE 102007003699 B3 DE102007003699 B3 DE 102007003699B3
Authority
DE
Germany
Prior art keywords
window
missile
homing head
angle
optical window
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.)
Active
Application number
DE200710003699
Other languages
German (de)
Inventor
Günther Riedl
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, DE
Original Assignee
LFK-Lenkflugkorpersysteme GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by LFK-Lenkflugkorpersysteme GmbH filed Critical LFK-Lenkflugkorpersysteme GmbH
Priority to DE200710003699 priority Critical patent/DE102007003699B3/en
Application granted granted Critical
Publication of DE102007003699B3 publication Critical patent/DE102007003699B3/en
Application status is Active legal-status Critical
Anticipated expiration legal-status Critical

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/20Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22Homing guidance systems
    • F41G7/2253Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/20Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22Homing guidance systems
    • F41G7/2213Homing guidance systems maintaining the axis of an orientable seeking head pointed at the target, e.g. target seeking gyro
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/20Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22Homing guidance systems
    • F41G7/2273Homing guidance systems characterised by the type of waves
    • F41G7/2293Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38Range-increasing arrangements
    • F42B10/42Streamlined projectiles
    • F42B10/46Streamlined nose cones; Windshields; Radomes

Abstract

Compliance with a radial angular offset between the optical axis of a homing head of a missile and the solder on the optical window in the missile tip allows a reflection-free image capture of the homing head.

Description

  • The The invention relates to a arranged in the tip of a missile and around the Longitudinal axis of the missile driven rotatably mounted optical window for a rotatably and pivotally mounted infrared homing head.
  • From the DE 41 12 140 C2 a missile has become known which has a pivotable seeker head at the tip, which is surrounded by a rotatable about the missile longitudinal axis mounted dome. The dome is made of an infrared transparent material in the form of a multi-sided pyramid. The individual facets of the pyramid are formed by plane-parallel plates, which are permeable to infrared radiation. The dome is covered over a major part of his coat by a non-translucent and mechanically highly resilient outer skin. The outer skin leaves only a small window, which is slightly larger than the field of view of the Zielsuchkopfes.
  • at The known construction is depending on the location of the homing head in terms of of the window in the cathedral possible, the optical axis of the homing head is perpendicular to one of the plane-parallel plates of the dome is aligned. This will be the resulting reflections detected by the homing head, which so-called Ghosting evoke the evaluation of the image considerably difficult. There is no indication as to how Adjustment of available resources the reflections of the window for the homing seeker can be made ineffective.
  • The DE 44 42 134 A1 describes a seeker, in which the yaw-squint angle of the line of sight is adjusted by tracking the roll of the missile small. Furthermore, the seeker window consists of several facets, so that always the perpendicular of a window has an angular offset about the roll axis to the line of sight.
  • The EP 0 482 353 A2 relates to a seeker head for a missile, in which the line of sight of the seeker head is pivoted during scanning in such a way that it always intersects the optical window at the same point.
  • It is therefore an object of the invention to provide an arrangement of an optical Window for one at the top of a missile arranged homing head to find which the detection of reflections in the direction of the optical axis of the homing head avoids.
  • According to the invention, this object is achieved in that the window has a flat surface, that between the optical axis of the homing head and the solder on the surface of the optical window is always an angular offset by an angle α about the longitudinal axis of the Fugkörpers, and
    the angle α is slightly larger than half the field angle of the homing head.
  • Out the fact that the solder on the window surface never with the optical axis of the homing head coincides but always forms a small angular offset to the optical axis, There is the advantage that at no time of operation one of the window surface originating reflection can disturb the useful signal of the homing head.
  • Especially it is advantageous if the angular offset by the deviation the optical axis to the solder on the surface of the optical window in the puncture point the optical axis by an angle greater than half the field angle of the homing head is determined. This determines the necessary window size. Furthermore, the use of windows is advantageous with a flat surface possible, with which economic advantages can be achieved.
  • One embodiment The invention is illustrated in the drawing and will be described below described in more detail. Show it:
  • 1 : A missile tip with a rotatable optical window according to the prior art,
  • 2 : A missile tip with a rotatable optical window in an arrangement according to the invention.
  • The arrangement of a rotatable seats 11 According to the above-described prior art is in the 1 shown. The 1 shows a partial longitudinal section through the top 11 a missile 1 , Centrally located in this tip is an infrared homing head, which is not shown in the figure for reasons of clarity. Its location is through the point 4 determined by the optical axis 3 of the homing head regardless of its orientation 3a . 3b on a target Z always runs. The homing head is mounted in a known manner for tracking its image field on a target Z rotatable and pivotable.
  • The summit 11 is about the hull of the missile 1 swiveling 12 stored and is via an unspecified drive 13 if necessary driven and positioned accordingly. In the top 11 is an optical window 2 installed, the window surface obliquely with respect to the longitudinal axis 5 of the missile 1 is arranged. The larger diameter of the approximately oval window is, as in the 1 well recognizable, chosen so large that the optical axis 3 . 3a as far as can be pivoted, that they finally with the longitudinal axis 5 of the missile 1 falls together. In the opposite direction is the usable area in which the optical axis 3b can be pivoted following the target Z, for example, limited by the position shown, in which the edge of the field angle just not yet with that through the point 4 running solder on the surface of the window 2 coincides. This critical angle depends on the angle of attack of the optical window. When exceeding the critical angle, the unwanted reflections occur at the surface of the window 2 which are to be avoided by means of the invention.
  • This just described disadvantage of the known arrangement of the optical window is avoided by means of a configuration according to the invention, as described in the 2 is shown.
  • According to the invention, the optical window 2 the optical axis 3 of the targeted to the target Z aligned search head offset offset by a small angle α. The angle α is the angle to which the window 2 around the longitudinal axis 5 of the missile 1 opposite the optical axis 3 of the homing head is rotated in the radial direction 12 is. This will be in every position of the optical axis 3 . 3a . 3b a reflection from the surface of the optical window 2 avoided in the direction of the homing head.
  • In The practice has a size of the angle α in the area of ± 10% the field angle of the homing head well proven.
  • This offset is caused by the fact that the window 2 in the top 11 of the missile is mounted, which faces the fuselage of the missile 1 rotatable 12 is stored. The twisting of the tip 11 opposite the fuselage of the missile 1 done with the help of a drive 13 which will not be explained in detail here, since suitable embodiments are known for this purpose.
  • The drive is dependent on the predetermined by the homing head position of the optical axis 3 the Zielsuchkopfes so controlled that always a small angle α between the Lot L on the window 2 and the optical axis 3 . 3a . 3b is complied with. This means geometrically that the lot L and the optical axis 3 . 3a . 3b only at the piercing point of the optical axis 3 can cut through the window. It is irrelevant which angle the optical axis 3 . 3a . 3b to the longitudinal axis 5 of the missile occupies. It is possible without restriction, the rotation of the window with respect to the optical axis 3 . 3a . 3b to be set forwards or backwards. In the case of a rotating missile, the tracking of the window works 2 while maintaining an angular offset to the optical axis in the same way as in a non-rotating missile.
  • Of the Angle α is Naturally dependent from the field angle of the homing head. So that no shading of it is the detectable image area of the homing seeker useful, the angle α something greater than to choose half the field angle.
  • It is also possible, the angle of attack of the window relative to the longitudinal axis 5 of the missile within certain limits. If the angle is increased, the long side of the approximately oval window can be made slightly shorter while the short side will be slightly wider.

Claims (2)

  1. In the top ( 11 ) of a missile ( 1 ) and about the longitudinal axis ( 5 ) of the missile ( 1 ) rotatable driven ( 12 . 13 ) stored optical window ( 2 ) for a rotatably and pivotably mounted infrared homing head, characterized in that the window ( 2 ) has a flat surface that between the optical axis ( 3 . 3a . 3b ) of the homing head and the solder (L) on the surface of the optical window ( 2 ) always an angular offset by an angle (α) about the longitudinal axis ( 5 ) of the missile, and that the angle (α) is slightly greater than half the field angle of the homing seeker.
  2. Optical window according to claim 1, characterized in that the window ( 2 ) an asymmetrically shaped boundary ( 2a ) having.
DE200710003699 2007-01-25 2007-01-25 Optical window in an infrared homing head Active DE102007003699B3 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE200710003699 DE102007003699B3 (en) 2007-01-25 2007-01-25 Optical window in an infrared homing head

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DE200710003699 DE102007003699B3 (en) 2007-01-25 2007-01-25 Optical window in an infrared homing head
ITMI20080023 ITMI20080023A1 (en) 2007-01-25 2008-01-09 Optical window in a head for seeking a target IR
GB0801143A GB2446052B (en) 2007-01-25 2008-01-22 Optical window for an infra-red homing head
FR0850432A FR2911951B1 (en) 2007-01-25 2008-01-24 Optical window of infrared searching head.

Publications (1)

Publication Number Publication Date
DE102007003699B3 true DE102007003699B3 (en) 2008-10-02

Family

ID=39166162

Family Applications (1)

Application Number Title Priority Date Filing Date
DE200710003699 Active DE102007003699B3 (en) 2007-01-25 2007-01-25 Optical window in an infrared homing head

Country Status (4)

Country Link
DE (1) DE102007003699B3 (en)
FR (1) FR2911951B1 (en)
GB (1) GB2446052B (en)
IT (1) ITMI20080023A1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8259291B2 (en) 2009-06-04 2012-09-04 Raytheon Company Multi-band seeker with tiltable optical/receiver portion

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0482353A2 (en) * 1990-10-25 1992-04-29 Bodenseewerk Gerätetechnik GmbH Viewfinder for scanning a visual field
DE4112140C2 (en) * 1991-04-13 1993-07-15 Bodenseewerk Geraetetechnik Gmbh, 7770 Ueberlingen, De
DE4442134A1 (en) * 1994-11-26 1996-05-30 Bodenseewerk Geraetetech Steering loop for missiles

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4244540A (en) * 1978-09-21 1981-01-13 The United States Of America As Represented By The Secretary Of The Navy Spectral discrimination system for an optical seeker
US6356396B1 (en) * 2000-02-01 2002-03-12 Raytheon Company Optical system having a generalized torus optical corrector
DE10313136B4 (en) * 2003-03-29 2017-05-11 Diehl Defence Gmbh & Co. Kg Seeker head with pitch-yaw inner gimbal system
DE102004024859A1 (en) * 2004-05-19 2005-12-15 Diehl Bgt Defence Gmbh & Co. Kg Optical arrangement for a seeker head

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0482353A2 (en) * 1990-10-25 1992-04-29 Bodenseewerk Gerätetechnik GmbH Viewfinder for scanning a visual field
DE4112140C2 (en) * 1991-04-13 1993-07-15 Bodenseewerk Geraetetechnik Gmbh, 7770 Ueberlingen, De
DE4442134A1 (en) * 1994-11-26 1996-05-30 Bodenseewerk Geraetetech Steering loop for missiles

Also Published As

Publication number Publication date
GB2446052B (en) 2011-08-10
FR2911951A1 (en) 2008-08-01
FR2911951B1 (en) 2013-11-08
GB0801143D0 (en) 2008-02-27
ITMI20080023A1 (en) 2008-07-26
GB2446052A (en) 2008-07-30

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Legal Events

Date Code Title Description
8364 No opposition during term of opposition
R081 Change of applicant/patentee

Free format text: FORMER OWNER: LFK-LENKFLUGKOERPERSYSTEME GMBH, 86529 SCHROBENHAUSEN, DE

Owner name: MBDA DEUTSCHLAND GMBH, DE

Effective date: 20130307