Automatic missile guidance system

Claim 2

An automatic missile guidance system for guiding a missile along a line-of-sight to a target established by a human operator, said missile having guidance means comprising: a guidance unit for developing steering signals related to the deviation of said missile from said line-of-sight; means for transmitting said guidance signals from said guidance unit to said missile; and a source of pulsating radiant energy on said missile and directed to the rear thereof, said source of radiant energy having a predetermined pulsation frequency, said guidance unit being selectively responsive to said radiant energy at said predetermined pulsation frequency.

Claim 3

The automatic missile guidance system of claim 1 wherein said guidance unit has means for narrowing its field of view when said missile is proximate to said line-of-sight.

Claim 4

The automatic missile guidance system of claim 2 wherein said guidance unit has a radiant energy receiver thereon adapted to receive radiant energy from said source of pulsating radiant energy on said missile, said radiant energy receiving means having a large radiant energy detector disposed therein to receive radiant energy in any part of the field of view and a small radiant energy detector disposed therein, said small radiant energy detector being positioned to receive radiant energy in the central portion of the field of view of said radiant energy receiver, and switch means for switching between said large and said small radiant energy detectors in response to position of missile source image in field of view.

Claim 5

The automatic missile guidance system of claim 3 wherein said small radiant energy detector means has an output to said switch means to switch said switch means so that its small radiant energy detector means is switched to control said missile when the input radiance to said small radiant energy detection means exceeds a predetermined value.

Claim 6

The automatic missile guidance system of claim 4 wherein said source of pulsating radiant energy on said missile operates at a substantially constant frequency.

Claim 7

The automatic missile guidance system of claim 5 wherein said radiant energy receiving means on said guidance unit comprises a telescope having a wide field of view about an optical axis, a reticle disposed at the focus of said telescope concentric with and transverse to the axis thereof, means rotating said reticle about the axis of said telescope at a predetermined speed, said reticle having an opaque modulation pattern thereon to provide a substantially sinusoidally varying average transmissivity gradient circularly around said reticle and to provide a rapidly increasing depth-of-modulation gradient outward from the center of said reticle, said large radiant energy detector being disposed to receive radiant energy passed by said reticle, said small radiant energy detector being disposed in a position to intercept radiant energy passing through the central portion of said reticle.

Claim 8

The automatic missile guidance system of claim 3 wherein the output of said switch is connected to first and second phase detectors, for respectively detecting pitch and yaw of said missile, said phase detectors being connected to said missile to guide said missile.

Claim 9

The automatic missile guidance system of claim 7 wherein said means for transmitting said guidance signals from said guidance unit to said missile comprises at least one wire interconnected bEtween said guidance unit and said missile.

Claim 10

An automatic missile guidance system for guiding a missile along a line-of-sight to a target established by a human operator, said missile having guidance means comprising: a guidance unit for developing steering signals related to the deviation of said missile from said line-of-sight; means for transmitting said guidance signals from said guidance unit to said missile; and a source of pulsating radiant energy on said missile and directed to the rear thereof, said source of radiant energy having a predetermined substantially constant pulsation frequency, said guidance unit being selectively responsive to said radiant energy at said predetermined substantially constant pulsation frequency, said guidance unit having means for narrowing its field of view when said missile is proximate to said line-of-sight.

Claim 11

An automatic missile guidance system for guiding a missile along a line-of-sight to a target established by a human operator, said missile having guidance means comprising: a guidance unit for developing steering signals related to the deviation of said missile from said line-of-sight; means for transmitting said guidance signals from said guidance unit to said missile; and a source of pulsating radiant energy on said missile and directed to the rear thereof, said source of radiant energy having a predetermined substantially constant pulsation frequency, said guidance unit being selectively responsive to said radiant energy at said predetermined substantially constant pulsation frequency, said guidance unit having means for narrowing its field of view when said missile is proximate to said line-of-sight.

Claim 14

A guided missile system comprising: a self-propelled missile having steering means; a source of infrared energy pulsating at a substantially constant predetermined frequency disposed on said missile and directed rearwardly thereof; a visual telescope having an optical axis; an infrared telescope having an optical axis substantially aligned with the optical axis of said visual telescope and having a wide field of view; a reticle disposed at the focus of said infrared telescope concentric with and transverse to the axis thereof; means for rotating said reticle about the axis of said infrared telescope at a predetermined speed, said reticle being transparent to said pulsating infrared energy and having an opaque coating arranged in a modulation pattern thereon, said coating being disposed in a sinusoidally varying concentration ciRcularly around said reticle to provide a sinusoidal average transmissivity gradient circularly around said reticle, said coating being disposed in a varying radial concentration increasing outwardly to provide a rapidly increasing depth-of-modulation gradient near the center of said reticle; a condensing lens disposed adjacent said reticle; a large radiant energy detector disposed to receive radiant energy intercepted by said infrared telescope and passed by said reticle and said condensing lens; a light pipe disposed in the center of said condensing lens to intercept radiant energy passing through the central portion of said reticle; a small radiant energy detector disposed in said light pipe in a position to receive radiant energy intercepted thereby; an electromagnetic relay having a normally open contact; a normally closed contact; a switch arm and an actuating coil, said small radiant energy detector being electrically coupled to the normally open contact of said relay, said large radiant energy detector being electrically coupled to the normally closed contact of said relay; a first narrowband amplifier having its input electrically coupled to said small radiant energy detector and having a narrow passband centered around said predetermined frequency; a rectifier and filter connected to the output of said first narrowband amplifier, said filter having a predetermined charge and discharge time constant; a switch amplifier having its input electrically coupled to the output of said rectifier and filter and having its output connected to the actuating coil of said relay, said switch amplifier being biased to have a predetermined input threshold level above which said relay is energized and below which said relay is de-energized; a source of voltage that exceeds said threshold a predetermined time after the launching of said missile electrically coupled to the input of said switch amplifier; a second narrowband amplifier having its input coupled to the switch arm of said relay and having a narrow passband centered around said predetermined frequency; an automatic gain control circuit coupled to said second narrowband amplifier for maintaining signals at the output thereof at a constant amplitude; an amplitude modulation demodulator having its input coupled to the output of said second narrowband amplifier; a variable gain amplifier having its input coupled to the output of said demodulator, said variable gain amplifier having a gain that varies as a function of an applied control voltage; a gain control voltage source coupled to said variable gain amplifier and applying a control voltage thereto that gradually increases the gain of said variable gain amplifier from the time said missile is launched; a pair of phase detectors, each having signal inputs coupled to the output of said variable gain amplifier; a pair of coil and magnet assemblies associated with said reticle for developing periodic reference signals having phases related to the instantaneous angular position of said reticle, said reference signals being in phase quadrature with each other; a pair of squaring circuits, each having its input individually coupled to the output of a different one of said coil and magnet assemblies, the output of each of said squaring circuits being individually coupled to the reference input of a different one of said phase detectors; a pair of compensation networks, each having its input coupled to the output of a different one of said phase detectors; and a signal transmission circuit having its input coupled to the outputs of said compensation networks and its output coupled to said missile.

Claim 15

A guided missile system comprising: a self-propelled missile having steering means; a source of infrared energy pulsating at a substantially constant predetermined frequency disposed on said missile and directed rearwardly thereof; a visual telescope having an optical axis; an infrared telescope having an optical axis substantially aligned with the optical axis of said visual telescope and having a wide field of view; a reticle disposed at the focus of said infrared telescope concentric with and transverse to the axis thereof; means for rotating said reticle about the axis of said infrared telescope at a predetermined speed, said reticle being transparent to said pulsating infrared energy and having an opaque coating arranged in a modulation pattern thereon, said coating being disposed in a sinusoidally varying concentration ciRcularly around said reticle to provide a sinusoidal average transmissivity gradient circularly around said reticle, said coating being disposed in a varying radial concentration increasing outwardly to provide a rapidly increasing depth-of-modulation gradient near the center of said reticle; a condensing lens disposed adjacent said reticle; a large radiant energy detector disposed to receive radiant energy intercepted by said infrared telescope and passed by said reticle and said condensing lens; a light pipe disposed in the center of said condensing lens to intercept radiant energy passing through the central portion of said reticle; a small radiant energy detector disposed in said light pipe in a position to receive radiant energy intercepted thereby; an electromagnetic relay having a normally open contact; a normally closed contact; a switch arm and an actuating coil, said small radiant energy detector being electrically coupled to the normally open contact of said relay, said large radiant energy detector being electrically coupled to the normally closed contact of said relay; a first narrowband amplifier having its input electrically coupled to said small radiant energy detector and having a narrow passband centered around said predetermined frequency; a rectifier and filter connected to the output of said first narrowband amplifier, said filter having a predetermined charge and discharge time constant; a switch amplifier having its input electrically coupled to the output of said rectifier and filter and having its output connected to the actuating coil of said relay, said switch amplifier being biased to have a predetermined input threshold level above which said relay is energized and below which said relay is de-energized; a source of voltage that exceeds said threshold a predetermined time after the launching of said missile electrically coupled to the input of said switch amplifier; a second narrowband amplifier having its input coupled to the switch arm of said relay and having a narrow passband centered around said predetermined frequency; an automatic gain control circuit coupled to said second narrowband amplifier for maintaining signals at the output thereof at a constant amplitude; an amplitude modulation demodulator having its input coupled to the output of said second narrowband amplifier; a variable gain amplifier having its input coupled to the output of said demodulator, said variable gain amplifier having a gain that varies as a function of an applied control voltage; a gain control voltage source coupled to said variable gain amplifier and applying a control voltage thereto that gradually increases the gain of said variable gain amplifier from the time said missile is launched; a pair of phase detectors, each having signal inputs coupled to the output of said variable gain amplifier; a pair of coil and magnet assemblies associated with said reticle for developing periodic reference signals having phases related to the instantaneous angular position of said reticle, said reference signals being in phase quadrature with each other; a pair of squaring circuits, each having its input individually coupled to the output of a different one of said coil and magnet assemblies, the output of each of said squaring circuits being individually coupled to the reference input of a different one of said phase detectors; a pair of compensation networks, each having its input coupled to the output of a different one of said phase detectors; and a signal transmission circuit having its input coupled to the outputs of said compensation networks and its output coupled to said missile.

Claim 26

An interrupted radiation source comprising: a radiating member having a radiating surface; means adjacent said member for heating said radiating surface; driving means disposed adjacent said radiating member and having a shaft spaced away from and generally parallel to said radiating surface; and a plane interruption member of substantially the same size and shape as said radiating member and mechanically coupled at its edge to the shaft of said driving means for rotation thereby about an axis parallel with the plane surfaces of said interruption member, said interruption member being disposed to shield said radiating member twice during each revolution about said axis.

Claim 27

An interrupted radiation source comprising: a radiating member having a radiating surface; means adjacent said member for heating said radiating surface; driving means disposed adjacent said radiating member and having a shaft spaced away from and generally parallel to said radiating surface; and a plane interruption member of substantially the same size and shape as said radiating member and mechanically coupled at its edge to the shaft of said driving means for rotation thereby about an axis parallel with the plane surfaces of said interruption member, said interruption member being disposed to shield said radiating member twice during each revolution about said axis.

Claim 28

An interrupted radiation source comprising: a cylindrical housing sealed at one end by a heat-resistant disk; a pyrotechnic composition disposed inside said housing; an electrically operated firing squib disposed inside said housing in contact with said pyrotechnic composition; at least one piece of iron within said housing and embedded in said pyrotechnic composition; a speed-regulated motor secured to the outside of said housing and having its shaft spaced away from and parallel to the plane outer surface of said heat-resistant disk; and an interruption disk of substantially the same size as said heat-resistant disk and mechanically coupled at its circumference to the shaft of said motor for rotation thereby about an axis parallel with the plane surfaces of said interruption disk, said interruption disk being disposed to shield said heat-resistant disk twice during each revolution about said axis.

Claim 29

An interrupted radiation source comprising: a cylindrical housing sealed at one end by a heat-resistant disk; a pyrotechnic composition disposed inside said housing; an electrically operated firing squib disposed inside said housing in contact with said pyrotechnic composition; at least one piece of iron within said housing and embedded in said pyrotechnic composition; a speed-regulated motor secured to the outside of said housing and having its shaft spaced away from and parallel to the plane outer surface of said heat-resistant disk; and an interruption disk of substantially the same size as said heat-resistant disk and mechanically coupled at its circumference to the shaft of said motor for rotation thereby about an axis parallel with the plane surfaces of said interruption disk, said interruption disk being disposed to shield said heat-resistant disk twice during each revolution about said axis.

Claim 30

An interrupted radiation source comprising: a cylindrical housing sealed at one end by a molybdenum disk having a zirconium carbide coating; a pyrotechnic composition disposed inside said housing and composed of 56 percent iron oxide, 14 percent aluminum powder, 3 percent boron and 27 percent barium chromate; an electrically operated firing squib disposed inside said housing in contact with said pyrotechnic composition; at least one piece of iron within said housing and embedded in said pyrotechnic composition; a speed-regulated motor secured to the outside of said housing and having its shaft spaced away from and parallel to the plane outer surface of said molybdenum disk; and an interruption disk of substantially the same size as said molybdenum disk and mechanically coupled at its circumference to the shaft of said motor for rotation thereby about an axis parallel with the plane surfaces of said interruption disk, said interruption disk being disposed to shield said molybdenum disk twice during each revolution about said axis.

Claim 31

An interrupted radiation source comprising: a cylindrical housing sealed at one end by a molybdenum disk having a zirconium carbide coating; a pyrotechnic composition disposed inside said housing and composed of 56 percent iron oxide, 14 percent aluminum powder, 3 percent boron and 27 percent barium chromate; an electrically operated firing squib disposed inside said housing in contact with said pyrotechnic composition; at least one piece of iron within said housing and embedded in said pyrotechnic composition; a speed-regulated motor secured to the outside of said housing and having its shaft spaced away from and parallel to the plane outer surface of said molybdenum disk; and an interruption disk of substantially the same size as said molybdenum disk and mechanically coupled at its circumference to the shaft of said motor for rotation thereby about an axis parallel with the plane surfaces of said interruption disk, said interruption disk being disposed to shield said molybdenum disk twice during each revolution about said axis.

Claim 32

A reticle for amplitude modulating radiant energy comprising: a disk transparent to said radiant energy; a coating opaque to said radiant energy disposed on said disk in a pattern, said pattern comprising concentric circular opaque lines having a progressively varying width around said disk, increasing from a minimum at a first radial zone on said disk to a maximum at a second radial zone on said disk and decreasing to said minimum at said first radial zone, said first and second zones being 180* opposed.

Claim 33

A reticle for amplitude modulating radiant energy comprising: a disk transparent to said radiant energy; a coating opaque to said radiant energy disposed on said disk in a pattern, said pattern comprising concentric circular opaque lines having a progressively varying width around said disk, increasing from a minimum at a first radial zone on said disk to a maximum at a second radial zone on said disk and decreasing to said minimum at said first radial zone, said first and second zones being 180* opposed.

Claim 34

A reticle for amplitude modulating radiant energy comprising: a disk transparent to said radiant energy; a coating opaque to said radiant energy disposed on said disk in a pattern, said pattern comprising concentric circular opaque lines having a progressively varying width around said disk, increasIng from a minimum at a first radial zone on said disk to a maximum at a second radial zone on said disk and decreasing to said minimum at said first radial zone, said first and second zones being 180* opposed, said concentric circular opaque lines having a progressively increasing maximum width from the center of said disk to the circumference thereof, the spacing between adjacent ones of said concentric circular opaque lines in said second zone progressively decreasing from the center of said disk to the circumference thereof.

Claim 35

A reticle for amplitude modulating radiant energy comprising: a disk transparent to said radiant energy; a coating opaque to said radiant energy disposed on said disk in a pattern, said pattern comprising concentric circular opaque lines having a progressively varying width around said disk, increasIng from a minimum at a first radial zone on said disk to a maximum at a second radial zone on said disk and decreasing to said minimum at said first radial zone, said first and second zones being 180* opposed, said concentric circular opaque lines having a progressively increasing maximum width from the center of said disk to the circumference thereof, the spacing between adjacent ones of said concentric circular opaque lines in said second zone progressively decreasing from the center of said disk to the circumference thereof.

Claim 36

A radiant energy telescope having dual, concentric fields of view comprising: a cylindrical outer case having an entrance window at one end thereof; first and second objective lenses having a wide field of view and disposed within said case adjacent said window; a transparent image surface disposed within said case at the focus of said objective lens; a condensing lens disposed within said case adjacent said image surface; a large radiant energy detector disposed within said case at a location to receive radiant energy focused on said image surface and passed by said condensing lens; a light pipe disposed in the center of said condensing lens to intercept radiant energy passing through the central portion of said image surface; and a small radiant energy detector disposed within said light pipe in a position to receive radiant energy intercepted thereby.

Claim 37

A radiant energy telescope having dual, concentric fields of view comprising: a cylindrical outer case having an entrance window at one end thereof; first and second objective lenses having a wide field of view and disposed within said case adjacent said window; a transparent image surface disposed within said case at the focus of said objective lens; a condensing lens disposed within said case adjacent said image surface; a large radiant energy detector disposed within said case at a location to receive radiant energy focused on said image surface and passed by said condensing lens; a light pipe disposed in the center of said condensing lens to intercept radiant energy passing through the central portion of said image surface; and a small radiant energy detector disposed within said light pipe in a position to receive radiant energy intercepted thereby.

Claim 38

In an infrared tracker, apparatus for developing a signal indicative of the instantaneous angular position of a modulating reticle, said apparatus comprising: a cylindrical reticle holder of nonmagnetic material rotatably disposed in said infrared tracker and containing said modulating reticle; driving means mechanically coupled to said reticle holder for rotation thereof; a band of magnetic material fixed to the outside of said reticle holder, said band varying linearly in width from a maximum width to a minimum width; a pair of magnetic pole pieces, each disposed with an edge adjacent said band, the width of the adjacent edges of said pole pieces being substantially equal to the maximum width of said band; a permanent magnet having each of its poles individually magnetically coupled to a different one of said pole pieces; and a coil of wire wound around said permanent magnet.

Claim 39

In an infrared tracker, apparatus for developing a signal indicative of the instantaneous angular position of a modulating reticle, said apparatus comprising: a cylindrical reticle holder of nonmagnetic material rotatably disposed in said infrared tracker and containing said modulating reticle; driving means mechanically coupled to said reticle holder for rotation thereof; a band of magnetic material fixed to the outside of said reticle holder, said band varying linearly in width from a maximum width to a minimum width; a pair of magnetic pole pieces, each disposed with an edge adjacent said band, the width of the adjacent edges of said pole pieces being substantially equal to the maximum width of said band; a permanent magnet having each of its poles individually magnetically coupled to a different one of said pole pieces; and a coil of wire wound around said permanent magnet.