EP0331804A2 - Projectile à guidage en phase terminale - Google Patents

Projectile à guidage en phase terminale Download PDF

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Publication number
EP0331804A2
EP0331804A2 EP88120227A EP88120227A EP0331804A2 EP 0331804 A2 EP0331804 A2 EP 0331804A2 EP 88120227 A EP88120227 A EP 88120227A EP 88120227 A EP88120227 A EP 88120227A EP 0331804 A2 EP0331804 A2 EP 0331804A2
Authority
EP
European Patent Office
Prior art keywords
projectile
detector
phase
window
gyro
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP88120227A
Other languages
German (de)
English (en)
Other versions
EP0331804B1 (fr
EP0331804A3 (fr
Inventor
Bernd Dulat
Hellmuth Moebes
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.)
Bodenseewerk Geratetechnik GmbH
Original Assignee
Bodenseewerk Geratetechnik 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 Bodenseewerk Geratetechnik GmbH filed Critical Bodenseewerk Geratetechnik GmbH
Publication of EP0331804A2 publication Critical patent/EP0331804A2/fr
Publication of EP0331804A3 publication Critical patent/EP0331804A3/fr
Application granted granted Critical
Publication of EP0331804B1 publication Critical patent/EP0331804B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—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
    • 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
    • F41G7/2213—Homing guidance systems maintaining the axis of an orientable seeking head pointed at the target, e.g. target seeking gyro
    • 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
    • F41G7/222—Homing guidance systems for spin-stabilized 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
    • F41G7/2253—Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target

Definitions

  • the invention relates to a projectile-guided projectile for firing from a cannon.
  • DE-C-36 44 456 shows a floor with an optically transparent window and a central spike.
  • US-A-4 500 051 shows a projectile shot from a cannon with an air-bearing finder.
  • the floor has a rear stabilization and middle wings, which are controlled by detector signals.
  • DE-A-34 38 544 shows an optical viewfinder with a Cassegrain system.
  • US-A-4 155 521 shows a projectile with a gimbal-mounted view finder and an air-bearing gyro.
  • the invention is based on the object of directing a projectile which is shot from a cannon, in particular an armored cannon, onto a movable target.
  • the projectile is accelerated extremely strongly for a short time during the launch. Steering means have to endure this high acceleration. A high lateral acceleration must be achievable in the steering phase. However, the air resistance of the projectile must not be impaired in such a way that this impairs the range of use of the projectile that has no propulsion after being fired. To meet a demanding steering law, the steering means must have an inertial reference. Only a small volume is available for the steering means. The high speed of the projectile in the supersonic area leads to heating.
  • air-bearing gyroscopes are known. Finders with a Cassegrain system are known. It is known to perform an image rotation by means of a wedge and thus in connection with a further circular scanning movement to perform a rosette scan of a visual field. Spikes in high speed missiles are known. Both a rear stabilization and a central wing control are known for missiles. And it is known to impart a rolling movement (swirl) to a projectile.
  • the claimed combination of measures achieves the task of creating a final phase control for a projectile shot down by a cannon under the unfavorable conditions described above.
  • the mentioned measures of the invention work together to achieve the object.
  • the viewfinder is designed as a gyro so that an inertial reference is available for the steering. Since the projectile is subjected to extreme accelerations when launched, the gyro is air-borne. Any other Storage would be destroyed at high accelerations. However, it has been shown that an air-bearing gyro survives these accelerations and is then functional. An air-bearing gyroscope allows only limited squint angles. The projectile must therefore be aimed exactly at the target. The transverse accelerations that occur during target tracking must not be applied by an angle of attack of the projectile, as is the case with some other missiles. Such an angle of attack could cause the viewfinder to lose the target due to the limited squint angle.
  • a middle wing control consists of paired wings in a cross arrangement in the center of gravity of the floor. These wings can be swiveled by steering signals via servomotors. It has been shown that when using such a mid-wing control, the transverse accelerations required for steering the projectile into the target can be applied without the viewfinder losing the target with his squint angle limited by the air-bearing gyroscope.
  • This middle wing control also allows the use of a spike. Compared to conventional viewfinder domes, the spike significantly reduces the drag. This is very important at the high speeds of the projectile and even makes it possible to provide such a projectile with a viewfinder.
  • a prerequisite for the use of a spike is that the projectile flies in the steering phase without any significant angle of attack. Otherwise the spike would have an aerodynamically unfavorable effect. This behavior is achieved anyway by the middle wing control because of the limited squint angle of the viewfinder.
  • a spike has the advantage that the damming temperature at the viewfinder window is reduced by the spike converting the straight compression shock into an oblique shock with high conversion of kinetic energy into thermal energy. This leads to less thermal shock load on the window material.
  • the lower temperature at the viewfinder window is favorable for detectors that respond to infrared radiation and improves the detection range of the system.
  • a spike requires the use of imaging optics of the viewfinder, which are not disturbed by the spike.
  • Such an imaging optic is a Cassegrain system.
  • a Cassegrain system also has a relatively high acceleration resistance.
  • Complicated scanning mechanisms have to be eliminated due to the high accelerations. It takes advantage of the fact that all projectiles perform a more or less strong rolling movement if they are not stabilized with particular control effort.
  • This is used according to the invention for visual field scanning.
  • the imaging optics mounted on the gyro perform a relatively fast scanning movement. This expediently occurs in that the air-bearing gyro is excited to a controlled nutation movement. A second, slower scanning movement is caused by the rolling movement of the Get bullet.
  • a wedge is provided instead of the usual dome as an optical window, which is delimited by two flat surfaces. This quasi-flat window carries the spike. This results in better imaging properties and a circular image movement relative to the detector, which complements the rosette scan with the movement of the imaging optics.
  • Embodiments of the invention are the subject of the dependent claims.
  • the floor 10 has a viewfinder at the top.
  • the viewfinder 12 carries a spike 14.
  • the gas supply 16 for the air storage of a gyro 18 is arranged behind the viewfinder 12.
  • the gyro 18 forms an essential part of the finder 12.
  • Behind the gas supply 16 there is a battery 20 for the power supply.
  • An assembly 22, which contains a rudder control system and the associated power electronics, is connected to the battery 20.
  • the viewfinder electronics 24 are located behind them.
  • a warhead 26 and a detonator 28 are arranged in the end part of the projectile 10.
  • the battery 20 feeds the viewfinder, the power electronics and the rudder control system and the viewfinder electronics. Tail stabilization is achieved by tail units 30 in the area of the end part.
  • control surfaces 32 are provided in a cross-wing arrangement, which bring about a central wing control.
  • the control surfaces 32 are retracted at the end and are extended in the steering phase. Since the control surfaces are located in the area of the center of gravity of the projectile 10, transverse forces can thus be generated for the steering without a significant angle of attack of the projectile occurring.
  • the control surfaces 32 are actuated by the rudder control system in assembly 22, which is controlled by the viewfinder electronics 24 via the power electronics.
  • the viewfinder electronics 24 receives and processes signals from the viewfinder 12.
  • the viewfinder 12 is shown in an enlarged scale in FIG.
  • the gyro 18 of the finder 12 is mounted in a spherical bearing surface 34 by means of an air bearing. Air storage is a known technique and is therefore not described in detail here. A stream of compressed gas is introduced into the bearing surface, so that the spherical outer surface 18 is kept floating on an air layer.
  • the gyro 18 is driven electrically or pneumatically by a stator winding 36.
  • the gyro 18 rotates around a bullet-proof detector column 38. Infrared-sensitive detectors 40 are located on the end face of the detector column 38.
  • the detector column 38 contains a cooling device by means of which the detectors 40 are cooled.
  • the gyroscope 18 carries an imaging optics 42 in the form of a Cassegrain system with an annular concave mirror 44 as the primary mirror and a mirror 46 arranged at a distance in front of it as the secondary mirror. As shown in FIG. 3, from the object which is practically infinite, via the annular concave mirror 44 and the mirror 46 to the detector 40. The mirror 46 is held on the gyro 18 via a stable mirror carrier 48.
  • the imaging optics 42 execute a circular scanning movement. This is achieved in that the gyro 18 is excited with the imaging optics to a controlled nutation movement.
  • the viewfinder 12 is closed by a flat window 54.
  • the window 54 is made of infrared casual material.
  • the window is wedge-shaped and is delimited by plane surfaces 58 and 60.
  • the control surfaces 32 are provided with a twist such that the projectile performs a continuous rolling movement.
  • the beam path for the imaging optics 42 is deflected and thus the point of the scanned field of view detected by the detector 40 is changed. If the projectile is rolling, an annular region of the field of view around the projectile axis would be scanned without the scanning movement of the imaging optics 42. However, this relatively slow scanning movement caused by the rolling movement of the projectile is superimposed on the fast scanning movement of the imaging optics 42. This results in a rosette scan as indicated in Fig.4.
  • the individual "leaves" 62 of the rosette are traversed by the nutation movement of the gyroscope 18 and the resulting relatively rapid scanning movement of the imaging optics 42.
  • the rolling movement of the projectile 10 causes a superimposed, slower rotation along the scanning circle 64 due to the wedge rotating therewith.
  • the fact that several detectors 40 are provided means that an annular strip 66 is scanned with each leaf 62 of the rosette, that is to say with each nutation revolution of the gyroscope 18, as shown in Fig.4.
  • the window 54 carries the spike 14. This reduces the flow resistance of the projectile 10. The flow is partially deflected by window 54, thereby reducing heating.

Landscapes

  • 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)
  • Telescopes (AREA)
EP88120227A 1988-03-09 1988-12-03 Projectile à guidage en phase terminale Expired - Lifetime EP0331804B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3807725A DE3807725A1 (de) 1988-03-09 1988-03-09 Endphasengelenktes geschoss
DE3807725 1988-03-09

Publications (3)

Publication Number Publication Date
EP0331804A2 true EP0331804A2 (fr) 1989-09-13
EP0331804A3 EP0331804A3 (fr) 1991-07-31
EP0331804B1 EP0331804B1 (fr) 1994-10-19

Family

ID=6349248

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88120227A Expired - Lifetime EP0331804B1 (fr) 1988-03-09 1988-12-03 Projectile à guidage en phase terminale

Country Status (3)

Country Link
US (1) US4917330A (fr)
EP (1) EP0331804B1 (fr)
DE (2) DE3807725A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2746494A1 (fr) * 1996-03-23 1997-09-26 Bodenseewerk Geraetetech Tete chercheuse pour des missiles ou des projectiles
FR2782554A1 (fr) * 1993-07-30 2000-02-25 Bodenseewerk Geraetetech Tete chercheuse ou autodirecteur pour missiles guides ou projectiles
US8354626B2 (en) 2009-06-23 2013-01-15 Diehl Bgt Defence Gmbh & Co. Kg Optical system for a missile, and method for imaging an object

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4033948A1 (de) * 1990-10-25 1992-04-30 Bodenseewerk Geraetetech Sucher zur abtastung eines gesichtsfeldes
DE4226024C1 (fr) * 1992-08-06 1993-07-15 Bodenseewerk Geraetetechnik Gmbh, 7770 Ueberlingen, De
DE19953701C2 (de) 1999-11-08 2002-01-24 Lfk Gmbh Verfahren und Vorrichtungen zur Verminderung von Druck und Temperatur auf der Vorderseite eines Flugkörpers bei Überschallgeschwindigkeit
IL143694A (en) 2001-06-12 2006-10-31 Geo T Vision Ltd Projectile fuse imaging device and method
US7943914B2 (en) * 2003-05-30 2011-05-17 Bae Systems Information And Electronic Systems Integration, Inc. Back illumination method for counter measuring IR guided missiles
US7718936B2 (en) * 2004-06-03 2010-05-18 Lockheed Martin Corporation Bulk material windows for distributed aperture sensors
US7295947B2 (en) * 2004-09-10 2007-11-13 Honeywell International Inc. Absolute position determination of an object using pattern recognition
US7289902B2 (en) * 2004-09-10 2007-10-30 Honeywell International Inc. Three dimensional balance assembly
US7274439B2 (en) * 2004-09-10 2007-09-25 Honeywell International Inc. Precise, no-contact, position sensing using imaging
US7340344B2 (en) * 2004-09-10 2008-03-04 Honeywell International Inc. Spherical position monitoring system
US20060054660A1 (en) * 2004-09-10 2006-03-16 Honeywell International Inc. Articulated gas bearing support pads
US7617070B2 (en) * 2004-09-10 2009-11-10 Honeywell International Inc. Absolute position determination of an object using pattern recognition
US7698064B2 (en) * 2004-09-10 2010-04-13 Honeywell International Inc. Gas supported inertial sensor system and method
US7458264B2 (en) * 2004-09-10 2008-12-02 Honeywell International Inc. Generalized inertial measurement error reduction through multiple axis rotation during flight
US7366613B2 (en) * 2004-09-10 2008-04-29 Honeywell International Inc. RF wireless communication for deeply embedded aerospace systems
US7647176B2 (en) * 2007-01-11 2010-01-12 Honeywell International Inc. Method and system for wireless power transfers through multiple ports
US7425097B1 (en) 2007-07-17 2008-09-16 Honeywell International Inc. Inertial measurement unit with wireless power transfer gap control
US7762133B2 (en) * 2007-07-17 2010-07-27 Honeywell International Inc. Inertial measurement unit with gas plenums
US7671607B2 (en) * 2007-09-06 2010-03-02 Honeywell International Inc. System and method for measuring air bearing gap distance
US8686326B1 (en) * 2008-03-26 2014-04-01 Arete Associates Optical-flow techniques for improved terminal homing and control
US8921748B2 (en) * 2011-05-19 2014-12-30 Lockheed Martin Corporation Optical window and detection system employing the same
US9568280B1 (en) 2013-11-25 2017-02-14 Lockheed Martin Corporation Solid nose cone and related components
DE102014002822A1 (de) * 2014-02-26 2015-08-27 Diehl Bgt Defence Gmbh & Co. Kg Verfahren zum Start eines Lenkflugkörpers und Flugkörpersystem
US9534868B1 (en) 2014-06-03 2017-01-03 Lockheed Martin Corporation Aerodynamic conformal nose cone and scanning mechanism

Citations (5)

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US4155521A (en) * 1975-12-08 1979-05-22 The Singer Company Cannon launched platform
US4500051A (en) * 1972-10-06 1985-02-19 Texas Instruments Incorporated Gyro stabilized optics with fixed detector
DE3438544A1 (de) * 1984-10-20 1986-04-24 Bodenseewerk Geraetetech Optischer sucher
EP0233080A2 (fr) * 1986-02-11 1987-08-19 Raytheon Company Autodirecteur infrarouge
DE3644456C1 (de) * 1986-12-24 1988-01-21 Rheinmetall Gmbh Geschoss

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US2816721A (en) * 1953-09-15 1957-12-17 Taylor Richard John Rocket powered aerial vehicle
US2990699A (en) * 1958-12-08 1961-07-04 Specialties Dev Corp Cooling apparatus
US4009393A (en) * 1967-09-14 1977-02-22 General Dynamics Corporation Dual spectral range target tracking seeker
US3920200A (en) * 1973-12-06 1975-11-18 Singer Co Projectile having a gyroscope
US4004754A (en) * 1974-07-11 1977-01-25 The United States Of America As Represented By The Secretary Of The Army High-speed, high-G air bearing optical mount for Rosette scan generator
US4034807A (en) * 1975-08-12 1977-07-12 Edgar N. Prince Inside pipe wiper
US4009848A (en) * 1975-10-15 1977-03-01 The Singer Company Gyro seeker
US4039246A (en) * 1976-01-22 1977-08-02 General Dynamics Corporation Optical scanning apparatus with two mirrors rotatable about a common axis
DE2921228C3 (de) * 1979-05-25 1981-11-26 Bodenseewerk Gerätetechnik GmbH, 7770 Überlingen Zielsuchkopf für einen Flugkörper
DE2923547C2 (de) * 1979-06-09 1981-04-09 Bodenseewerk Gerätetechnik GmbH, 7770 Überlingen Zielsuchvorrichtung für Flugkörper
US4413177A (en) * 1981-11-30 1983-11-01 Ford Motor Company Optical scanning apparatus incorporating counter-rotation of primary and secondary scanning elements about a common axis by a common driving source
DE3505198C1 (de) * 1985-02-15 1986-07-24 Bodenseewerk Gerätetechnik GmbH, 7770 Überlingen Vorrichtung zur Abtastung eines Gesichtsfeldes
DE3642683A1 (de) * 1986-12-13 1988-06-16 Bodenseewerk Geraetetech Kryostat zur kuehlung eines detektors

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4500051A (en) * 1972-10-06 1985-02-19 Texas Instruments Incorporated Gyro stabilized optics with fixed detector
US4155521A (en) * 1975-12-08 1979-05-22 The Singer Company Cannon launched platform
DE3438544A1 (de) * 1984-10-20 1986-04-24 Bodenseewerk Geraetetech Optischer sucher
EP0233080A2 (fr) * 1986-02-11 1987-08-19 Raytheon Company Autodirecteur infrarouge
DE3644456C1 (de) * 1986-12-24 1988-01-21 Rheinmetall Gmbh Geschoss

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2782554A1 (fr) * 1993-07-30 2000-02-25 Bodenseewerk Geraetetech Tete chercheuse ou autodirecteur pour missiles guides ou projectiles
FR2746494A1 (fr) * 1996-03-23 1997-09-26 Bodenseewerk Geraetetech Tete chercheuse pour des missiles ou des projectiles
US8354626B2 (en) 2009-06-23 2013-01-15 Diehl Bgt Defence Gmbh & Co. Kg Optical system for a missile, and method for imaging an object

Also Published As

Publication number Publication date
EP0331804B1 (fr) 1994-10-19
DE3851880D1 (de) 1994-11-24
US4917330A (en) 1990-04-17
EP0331804A3 (fr) 1991-07-31
DE3807725A1 (de) 1989-09-21

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