EP0319649A1 - Dispositif pour la détermination de l'angle de roulis - Google Patents

Dispositif pour la détermination de l'angle de roulis Download PDF

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Publication number
EP0319649A1
EP0319649A1 EP88112297A EP88112297A EP0319649A1 EP 0319649 A1 EP0319649 A1 EP 0319649A1 EP 88112297 A EP88112297 A EP 88112297A EP 88112297 A EP88112297 A EP 88112297A EP 0319649 A1 EP0319649 A1 EP 0319649A1
Authority
EP
European Patent Office
Prior art keywords
missile
sensor
roll angle
magnetic field
field sensor
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.)
Withdrawn
Application number
EP88112297A
Other languages
German (de)
English (en)
Inventor
Jens Dr. Seidensticker
Brigitte Nitsche
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.)
Rheinmetall Industrie AG
Original Assignee
Rheinmetall 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 Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of EP0319649A1 publication Critical patent/EP0319649A1/fr
Withdrawn legal-status Critical Current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
    • F41G7/24—Beam riding guidance systems
    • F41G7/26—Optical guidance systems
    • F41G7/266—Optical 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
    • F41G7/30—Command link guidance systems
    • F41G7/301—Details
    • F41G7/305—Details for spin-stabilized missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C17/00—Fuze-setting apparatus
    • F42C17/04—Fuze-setting apparatus for electric fuzes

Definitions

  • the invention relates to an arrangement for determining the roll angle position of a missile departing from a tube, as defined in the preamble of claim 1.
  • both the deviation of the actual path from the theoretical path and the roll angle position are determined, in order then to trigger the correction impulse in such a roll angle position that it counteracts the observed deviation (see e.g. DE-0S 25 43 606).
  • the roll angle position of the missile can be determined both optically and magnetically.
  • An optical roll angle position measurement has the disadvantage that it is sensitive to brightness and therefore z. B. at night or unfavorable environmental conditions (snow, blue sky) only allows incorrect measurements.
  • the roll angle position is determined magnetically
  • there is a magnetic field sensor in or on the missile which determines the roll angle position with respect to the earth's magnetic field, the sensitivity axis of which runs perpendicular to the flight direction. It takes advantage of the fact that the vector of the earth's magnetic field lies only horizontally above the earth's surface near the equator, while it is inclined to the earth in the other areas and therefore has a vertical component that can be used for measuring the roll angle position.
  • a sinusoidal signal is obtained via the magnetic field sensor due to the missile rotation around the flight axis, the maxima and minima of which are proportional to the magnetic vertical field of the earth, so that an "up-down" determination is possible.
  • the maximum magnetic field detected by the sensor no longer points vertically downwards but in a direction that is increasingly determined by the angle of inclination. For example, a flight in the east of Germany results in an error of 25 °.
  • the magnetic field sensors 11 and 12 are located in the interior of the missile 10. These magnetic field sensors can, for example, be sensors that utilize the magnetoresistive effect.
  • the first sensor 11 has only one sensitivity axis perpendicular to the flight direction, while the second magnetic field sensor 12 has two sensitivity axes lying in a plane perpendicular to the flight direction.
  • the corresponding sensors are commercially available and therefore do not need to be explained in more detail.
  • H denotes the field strength of the earth's magnetic field, which can be broken down into a vertical component H V and a horizontal component H H.
  • the inclination angle is marked with ⁇ , which lies between 60 and 70 ° in the FRG.
  • the reference signal received by the second magnetic field sensor 12 on the basis of the magnet 21 thus determines a specific angular position of the missile, which can be clearly assigned to the signal of the front sensor 11.
  • FIGS. 2a to 2d show the vertical magnetic field measured with the first sensor 11, where to denotes the time at which the sensor 11 emerges from the mouth of the tube 20 and the sensor amplitude A 11 corresponding to the respective magnetic field on the vertical axis is applied.
  • the voltage amplitudes A x and A y of the partial sensors of the sensor 12 are shown in FIGS. 2b and 2c.
  • Fig. 2d is that with the help of Eq. (1) determined angle ⁇ reproduced, which is 19 ° in the example shown.
  • the roll position determination of the projectile at any time on the trajectory is determined on the basis of the following consideration:
  • their signal or the amplitude signal A x ) serves as a trigger for the front sensor 11, which takes its measurement at this point in time and determines the speed ⁇ .
  • the angle of attack of the missile changes on a ballistic trajectory, but not the direction of flight. Therefore, only the amplitude of the sensor signal changes and not the phase position, so that the shape of the flight path has no influence on the roll position determination.
  • the phase position is thus evaluated according to the invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Navigation (AREA)
EP88112297A 1987-12-08 1988-07-29 Dispositif pour la détermination de l'angle de roulis Withdrawn EP0319649A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3741498 1987-12-08
DE19873741498 DE3741498A1 (de) 1987-12-08 1987-12-08 Anordnung zur ermittlung der rollwinkellage

Publications (1)

Publication Number Publication Date
EP0319649A1 true EP0319649A1 (fr) 1989-06-14

Family

ID=6342087

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88112297A Withdrawn EP0319649A1 (fr) 1987-12-08 1988-07-29 Dispositif pour la détermination de l'angle de roulis

Country Status (2)

Country Link
EP (1) EP0319649A1 (fr)
DE (1) DE3741498A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2236925A (en) * 1989-10-14 1991-04-17 Rheinmetall Gmbh Measuring rotational position of missile
EP0451122A2 (fr) * 1990-03-15 1991-10-09 Ab Bofors Détermination de l'angle de roulis
FR2742540A1 (fr) * 1994-03-25 1997-06-20 Rheinmetall Ind Gmbh Projectile avec un dispositif de correction de la trajectoire
WO2000026602A1 (fr) * 1998-10-29 2000-05-11 Bofors Missiles Ab Procede et dispositif permettant de determiner des angles d'inclinaison laterale
EP1813905A2 (fr) 2006-01-30 2007-08-01 Alliant Techsystems Inc. Orientation de rouleau utilisant une fusée à compteur de tours
WO2010108917A1 (fr) * 2009-03-24 2010-09-30 Dynamit Nobel Defence Gmbh Détermination de la vitesse initiale d'un projectile
EP2261591A1 (fr) * 2009-06-08 2010-12-15 Rheinmetall Air Defence AG Procédé de correction de la trajectoire d'une munition dirigée en phase finale

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19500993A1 (de) * 1995-01-14 1996-07-18 Contraves Gmbh Verfahren zum Bestimmen der Rollage eines rollenden Flugobjektes
DE19520115A1 (de) * 1995-06-01 1996-12-05 Contraves Gmbh Verfahren zum Bestimmen der Rollage eines rollenden Flugobjektes
DE10117920A1 (de) * 2001-04-10 2002-10-24 Continental Ag Mess- und Sensor-Verfahren und -Vorrichtung für die autonome Rotationswinkelerkennung

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3860199A (en) * 1972-01-03 1975-01-14 Ship Systems Inc Laser-guided projectile system
FR2320593A1 (fr) * 1975-08-04 1977-03-04 Realisations Applic Et Dispositif applicable aux engins guides ou pilotes pour l'obtention d'une reference de roulis
US4328938A (en) * 1979-06-18 1982-05-11 Ford Aerospace & Communications Corp. Roll reference sensor
DE3131394A1 (de) * 1981-08-07 1983-03-03 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Verfahren zur bestimmung der rotationslage eines rotierenden flugkoerpers mit hilfe des erdmagnetischen feldes
US4646990A (en) * 1986-02-18 1987-03-03 Ford Aerospace & Communications Corporation Magnetic roll sensor calibrator

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3860199A (en) * 1972-01-03 1975-01-14 Ship Systems Inc Laser-guided projectile system
FR2320593A1 (fr) * 1975-08-04 1977-03-04 Realisations Applic Et Dispositif applicable aux engins guides ou pilotes pour l'obtention d'une reference de roulis
US4328938A (en) * 1979-06-18 1982-05-11 Ford Aerospace & Communications Corp. Roll reference sensor
DE3131394A1 (de) * 1981-08-07 1983-03-03 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Verfahren zur bestimmung der rotationslage eines rotierenden flugkoerpers mit hilfe des erdmagnetischen feldes
US4646990A (en) * 1986-02-18 1987-03-03 Ford Aerospace & Communications Corporation Magnetic roll sensor calibrator

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2236925A (en) * 1989-10-14 1991-04-17 Rheinmetall Gmbh Measuring rotational position of missile
EP0451122A2 (fr) * 1990-03-15 1991-10-09 Ab Bofors Détermination de l'angle de roulis
EP0451122A3 (en) * 1990-03-15 1993-01-13 Ab Bofors Roll angle determination
US5233901A (en) * 1990-03-15 1993-08-10 Ab Bofors Roll angle determination
FR2742540A1 (fr) * 1994-03-25 1997-06-20 Rheinmetall Ind Gmbh Projectile avec un dispositif de correction de la trajectoire
US6572052B1 (en) 1998-10-29 2003-06-03 Saab Ab Process and device for determining roll angle
WO2000026602A1 (fr) * 1998-10-29 2000-05-11 Bofors Missiles Ab Procede et dispositif permettant de determiner des angles d'inclinaison laterale
EP1813905A2 (fr) 2006-01-30 2007-08-01 Alliant Techsystems Inc. Orientation de rouleau utilisant une fusée à compteur de tours
EP1813905A3 (fr) * 2006-01-30 2010-06-09 Alliant Techsystems Inc. Orientation de rouleau utilisant une fusée à compteur de tours
NO338136B1 (no) * 2006-01-30 2016-08-01 Alliant Techsystems Inc Rullingsorientering ved hjelp av omdreiningstellende tenner.
WO2010108917A1 (fr) * 2009-03-24 2010-09-30 Dynamit Nobel Defence Gmbh Détermination de la vitesse initiale d'un projectile
US8800359B2 (en) 2009-03-24 2014-08-12 Dynamit Nobel Defense GmbH Determination of the muzzle velocity of a projectile
EP2261591A1 (fr) * 2009-06-08 2010-12-15 Rheinmetall Air Defence AG Procédé de correction de la trajectoire d'une munition dirigée en phase finale

Also Published As

Publication number Publication date
DE3741498A1 (de) 1989-06-22

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