EP0033279B1 - Leitsystem für Raketen mittels eines optischen Strahles - Google Patents

Leitsystem für Raketen mittels eines optischen Strahles Download PDF

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Publication number
EP0033279B1
EP0033279B1 EP81400103A EP81400103A EP0033279B1 EP 0033279 B1 EP0033279 B1 EP 0033279B1 EP 81400103 A EP81400103 A EP 81400103A EP 81400103 A EP81400103 A EP 81400103A EP 0033279 B1 EP0033279 B1 EP 0033279B1
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EP
European Patent Office
Prior art keywords
sight
missile
detector
transparent
sectors
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.)
Expired
Application number
EP81400103A
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English (en)
French (fr)
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EP0033279A1 (de
Inventor
Wladimir Koreicho
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.)
Societe Anonyme de Telecommunications SAT
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Societe Anonyme de Telecommunications SAT
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Publication of EP0033279A1 publication Critical patent/EP0033279A1/de
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    • 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

Definitions

  • the present invention relates to a machine guidance system comprising a source emitting a light beam whose axis defines the direction of sight, a modulation pattern placed on the path of the beam, means for producing a relative rotational movement between the target and beam, means arranged to provide an angular reference on the machine, and, on the machine, at least one detector and a calculation circuit for determining, from the detector output signal, the coordinates of the detector relative to the direction of sight, the control surfaces of the machine being actuated according to said coordinates in order to control the trajectory of the machine on the direction of sight.
  • French patent 2 339 832 discloses such a guidance system comprising, for the modulation of the beam, a rotating target in the form of a spiral. Measuring the illumination times of each detector makes it possible to determine the distance from the detector to the beam axis, since, given the shape of the target, the lighting duration is a function of the distance to the axis.
  • the duration of illumination is very variable compared to the total duration of measurement and in particular the duration of relative illumination is close to 100% on the axis of the beam and decreases as one s 'deviates from the axis until it is close to 0 at the edge of the field.
  • This is very disadvantageous in terms of the link budget because in this regard, the optimal value of the relative illumination duration is equal to 50%.
  • the present invention relates to a guidance system of the type described above, in which the relative illumination duration of the detector remains equal to 50% regardless of the position of the detector.
  • the present invention relates to a system of the type defined above, characterized in that the target is formed as the superposition of a first target divided into a transparent sector and a partially transparent semi-circular sector, and d '' a second target divided into four equal sectors, namely two transparent sectors and two partially transparent sectors, by two curves symmetrical with respect to the center of the target, of equation f (p, ⁇ modulo n) - 0, where p varies monotonically as a function of ⁇ , your modulation pattern thus comprising transparent, partially transparent and opaque sectors, delimited by symmetrical curves with respect to the center of the pattern and defining equal angles at the center whatever the radius considered of so that the relative illumination duration of the detector remains equal to 50% whatever its position.
  • the guidance system shown diagrammatically in FIG. 1 comprises a light source 1, for example a laser source emitting in the infrared such as a CO 2 laser.
  • a laser source emitting in the infrared
  • a continuous emission laser is used in the invention.
  • a light-emitting diode of the AsGa type is also possible to envisage using a light-emitting diode of the AsGa type as a source.
  • the beam emitted by the source 1 is amplitude modulated at a high frequency by an electro-optical modulator 2 which is designed to provide an angular reference.
  • the modulation frequency of the beam is modified in a determined manner, in synchronism with the rotation of the target described below.
  • the beam from the modulator 2 is modulated by a rotating target 3 driven in rotation at an angular speed o by a mechanism 4 and described in more detail below.
  • a relative rotational movement takes place between the test pattern 3 and the beam, one could also leave the test pattern fixed and rotate the beam for example by means of a Wollaston prism.
  • the resulting beam then passes through an emission optic 5.
  • the machine E goes towards the target C on which the beam is pointed. It carries one (or more) detector D which transforms the light radiation which it receives coming from source 1 into an electrical signal. Because the light beam is modulated, so is the electrical signal and the modulation principle, set out below, is such that the polar coordinates (p, 9) of detector D relative to the beam axis can be derived from the detector output signal.
  • the signals representing said coordinates are applied to the control circuit for the control surfaces provided on the vehicle, so as to control the trajectory of the vehicle on the beam axis.
  • the emission optics 5 is designed to keep the section of the beam projected at the detector substantially constant, and therefore the light power received by the detector.
  • Optics 5 is provided for this purpose with a zoom type device.
  • the test pattern 3 shown in FIG. 3 can be considered as the superposition of two test patterns 6 and 7 shown respectively in FIGS. 4a and 4b.
  • the first is made up of a transparent sector and a semi-transparent sector of semi-circular shape.
  • the resulting modulation component in the output signal of the detector D is the signal S 1 ( ⁇ t) (see fig. 5).
  • the processing circuit provided on the machine produces a reference signal R 1 ( ⁇ t) of the same frequency corresponding to the axis x H and it is clear that the polar angle 6 can be easily determined by measuring the phase shift between S 1 ( ⁇ t) and R 1 ( ⁇ t).
  • modulo n The corresponding modulation component is represented by the signal S 2 (mt) and it is easy to understand that the phase shift of S 2 (ot) with respect to a reference signal R 2 ( ⁇ t), whose frequency is double that of R 1 ( ⁇ t), is a function of the vector radius p. This phase shift is given by the relation
  • the signals S, and S 2 are easily deduced from the signal S ( ⁇ t) which is obtained at the output of the detector D after amplification and appropriate shaping.
  • test pattern in Figure 3 should not be considered as formed by the superposition of the patterns in Figures 4a and 4b, since the superposition of two semi-transparent sectors would not give complete opacity.
  • the patterns of Figures 4a and 4b are fictitious and are shown only for the purpose of explanation.
  • the duration of total illumination corresponding to the total of the angles at the center defined by the transparent sectors would be equal to the duration of semi-illumination, corresponding to the total of the angles in the center defined by the semi-transparent sectors, whatever the radius considered.
  • the relative illumination duration of the target of FIG. 3 is equal to 50% whatever the radius considered, this relative duration being equal to 100. ⁇ ET + 50.
  • ⁇ SE, ⁇ ET and ⁇ SE denoting the total of the center angles defined respectively by the transparent sectors and the semi-transparent sectors of the target.
  • the invention makes it possible to obtain a maximum signal variation, as well as a variation of the parameters p and ⁇ in also maximum measurement ranges.
  • Figures 6a and 6b illustrate another embodiment of the modulation means.
  • two patterns 14a and 14b are provided which are moved in a clocked fashion by a switching mechanism, not shown, so that the beam is modulated in turn by the pattern 14a and by the pattern 14b.
  • the two patterns are phase shifted by a given angle, which is equal to 90 ° in the example shown.
  • Means are of course provided for creating a rotational movement between the beam and the targets, for example an optical member rotating the beam or a mechanism for driving the targets in rotation in the same direction at the same angular speed ⁇ .
  • the components attributable to the respective patterns are deduced from the output signal of the detector D and their phase shift ⁇ a, ⁇ b is determined with respect to a reference signal.
  • Figs. 6a and 6b requires only one reference signal R ( ⁇ t) instead of two in the embodiment of figs. 3a and 3b. It is also more advantageous in terms of diffraction.
  • the curves delimiting the sectors are sections of Archimedes' spiral, which provides a linear relationship between p and 0.

Claims (5)

1. Flugkörper-Lenksystem mit einem Sender für ein Lichtbündel, dessen Achse die Zielrichtung definiert, einer in der Bahn des Lichtbündels angeordneten Modulationsblende, einer Einrichtung, um zwischen der Blende und dem Licntbündel eine relative Rotationbewegung zu erzeugen, einer Anordnung, um an den Flugkörper ein winkelbezogenes Bezugssignal zu liefern, und einem an dem Flugkörper befindlichen Empfänger und einer an dem Flugkörper befindlichen Rechnerschaltung, um, ausgehend von einem Ausgangssignal des Empfängers, die Koordinaten des Empfängers bezogen auf die Zielrichtung zu bestimmen, wobei das Steuersystem des Flugkörpers in Abhängigkeit von diesen Koordinaten betätigbar ist, um die Flugkörper-Flugbahn auf die Zielrichtung auszurichten, dadurch gekennzeichnet, daß die Blende durch Uberlagerung einer ersten Blende, die in einen halbkreisförmigen transparenten Sektor und einen halbkreisförmigen partiell transparenenten Sektor aufgeteilt ist, mit einer zweiten Blende gebildet ist, die von zwei bezogen auf das Blendenzentrum symmetrischen Linien mit der Gleichung f (p, 9 modulo n) = 0, wobei p monoton als Funktion von θ veränderlich ist, in vier gleiche, nämlich zwei transparente und zwei partiell transparente Flächen aufgeteilt ist, derart, daß die Modulationsblende somit transparente, partiell transparente und opake Abschnitte aufweist, die durch symmetrisch zum Blendenzentrum verlaufende Kurven begrenzt sind und gleiche Zentriwinkel definieren, welches auch immer der einzelne Lichtstrahl sei, derart, daß die relative Beleuchtungsdauer des Empfängers unabhängig von seiner Position stets gleich 50 3% beträgt.
2. Flugkörper-Lenksystem mit einem Sender für ein Lichtbündel, dessen Achse die Zielrichtung definiert, mindestens einer in der Bahn des Lichtbündels angeordneten Modulationsblende, einer Einrichtung, um zwischen der Blende und dem Lichtbündel eine relative Rotationsbewegung zu erzeugen einer Anordnung um an den Flugkörper ein winkelbezogenes Bezugssignal zu liefern und einem an dem Flugkörper befindlichen Empfänger und einer an dem Flugkörper befindlichen Rechnerschaltung, um, ausgehend von einem Ausgangssignal des Empfängers, die Koordinaten des Empfängers bezogen auf die Zielrichtung zu bestimmen, wobei das Steuersystem des Flugkörpers in Abhängigkeit von diesen Koordinaten betätigbar ist, um die Flugkörper-Flugbahn auf die Zielrichtung . auszurichten, dadurch gekennzeichnet, daß zwei Modulationsblenden vorgesehen sind, die axial symmetrisch angeordnet und relativ zueinander um einen bestimmten Winkel phasenversetzt sind und der Reihe nach eine aktive, das Lichtbündel auffangende Position einnehmen, wobei jede Blende jeweils durch eine Kurve mit der Gleichung f (p, 9 modulo n) - 0 bzw. eine Kurve mit der Gleichung f (p, -θ modulo n) - 0, wobei p monoton als Funktion von 0 veränderlich ist, in zwei indentische Flächen, eine transparente und eine opake Fläche, aufgeteilt ist, wobei diese Kurven symmetrisch zum Blendenzentrum sind und gleiche Zentriwinkel definieren, welches auch immer der einzelne Lichtstrahl sei, derart, daß die relative Beleuchtungsdauer des Empfängers unabhängig von seiner Position stets gleich 50 % beträgt.
3. Flugkörper-Lenksystem nach Anspruch 2, dadurch gekennzeichnet, daß die beiden Blenden in gleicher Richtung rotieren.
4. Flugkörper-Lenksystem nach Anspruch 2, dadurch gekennzeichnet, daß die beiden Blenden in entgegengesetzter Richtung rotieren.
5. Flugkörper-Lenksystem nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß jede der Kurven durch zwei Abschnitte einer archimedischen Spirale mit der Gleichung p - a 8 und p= -a 0 gebildet ist.
EP81400103A 1980-01-29 1981-01-26 Leitsystem für Raketen mittels eines optischen Strahles Expired EP0033279B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8001840A FR2474681A1 (fr) 1980-01-29 1980-01-29 Systeme de guidage d'engin par faisceau lumineux
FR8001840 1980-01-29

Publications (2)

Publication Number Publication Date
EP0033279A1 EP0033279A1 (de) 1981-08-05
EP0033279B1 true EP0033279B1 (de) 1986-11-05

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EP81400103A Expired EP0033279B1 (de) 1980-01-29 1981-01-26 Leitsystem für Raketen mittels eines optischen Strahles

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US (1) US4408734A (de)
EP (1) EP0033279B1 (de)
DE (1) DE3175568D1 (de)
FR (1) FR2474681A1 (de)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2539864B1 (fr) * 1983-01-20 1987-01-09 Telecommunications Sa Systeme de guidage d'engin par faisceau lumineux
DE3441921A1 (de) * 1984-11-16 1986-05-28 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Leitstrahl- und nachfuehreinrichtung
US5427328A (en) * 1985-02-12 1995-06-27 Northrop Grumman Corporation Laser beam rider guidance utilizing beam quadrature detection
GB8724077D0 (en) * 1987-10-14 1988-02-17 British Aerospace Roll orientation
US5685504A (en) * 1995-06-07 1997-11-11 Hughes Missile Systems Company Guided projectile system
US8536501B2 (en) * 2003-10-22 2013-09-17 The Boeing Company Virtually attached node
WO2006088687A1 (en) * 2005-02-07 2006-08-24 Bae Systems Information And Electronic Systems Integration Inc. Optically guided munition
WO2008112012A2 (en) * 2006-10-04 2008-09-18 Raytheon Company Supercapacitor power supply
DE102010004820A1 (de) * 2010-01-15 2011-07-21 Rheinmetall Air Defence Ag Verfahren zur Flugbahnkorrektur eines insbesondere endphasengelenkten Geschosses sowie Geschoss zur Durchführung des Verfahrens
IL236338B (en) * 2014-12-18 2018-12-31 Israel Aerospace Ind Ltd Guidance system and method

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Publication number Priority date Publication date Assignee Title
US3000255A (en) * 1955-05-31 1961-09-19 Lloyd A Iddings Scanning devices for optical search
DE977909C (de) * 1959-12-18 1972-11-02 Eltro Gmbh Einrichtung zur Koordinatenmessung
GB1071268A (en) * 1962-12-11 1967-06-07 Galileo Societa Per Azioni Off Guidance systems for vehicles and the like
GB1315351A (en) * 1963-05-10 1973-05-02 Eltro Gmbh Method and apparatus for determining co-ordinates
US3690594A (en) * 1964-05-20 1972-09-12 Eltro Gmbh Method and apparatus for the determination of coordinates
FR2339832A1 (fr) * 1976-01-27 1977-08-26 Emile Stauff Perfectionnements apportes au guidage d'un projectile vers son objectif
US4014482A (en) * 1975-04-18 1977-03-29 Mcdonnell Douglas Corporation Missile director
US4243187A (en) * 1978-05-01 1981-01-06 Mcdonnell Douglas Corporation Missile director with beam axis shift capability

Non-Patent Citations (1)

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Title
Livre de C. Lebasse IC. Héméry "Géométrie" (1962), éd. Fernand Nathan, page 214 *

Also Published As

Publication number Publication date
FR2474681B1 (de) 1983-12-23
DE3175568D1 (en) 1986-12-11
FR2474681A1 (fr) 1981-07-31
EP0033279A1 (de) 1981-08-05
US4408734A (en) 1983-10-11

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