Guidance devices

Claim 2

In a missile guidance system, that improvement which comprises, a missile having a rotatable section, a fin on the section adapted to rotate the section as the missile passes through the air and to steer the missile when the cone section is braked, an optical slit on the section, an electrical generator rotated by the section, means responsive to radiation from a target received by said slit to short the generator, thus providing a brake on the section so that the fin will steer the missile toward the source of radiation.

Claim 3

In a missile guidance system as claimed in claim 1 in which the means for shorting the generator includes a photo sensitive sensor for receiving the radiation and adapted to send a pulse in response thereto, means for amplifying the pulse and means responsive to the amplified pulse for shorting the generator.

Claim 4

A guidance system according to claim 2 in which means for shorting further include a reflecting means for receiving the infrared radiation passing through the slit and reflecting said radiation on to the photosensitive sensor.

Claim 5

In a missile guidance system, a missile having a rotatable nose cone, a fin on said nose cone adapted to rotate the nose cone about the longitudinal axis of the missile and to steer the missile in a direction perpendicular to the longitudinal axis when the cone is braked relative to the missile, an electrical generator in the missile coupled to the nose cone, an optical slit on said nose cone positioned at an angle to said fin and in line with the direction of the steering force, a photosensitive element in said missile adapted to receive radiation passing through the slit and to send a pulse in response thereto, means to amplify said pulse and means responsive to said amplified pulse to send a pulse of reverse polarity to said generator, thus braking the generator, nose cone and fin so as to steer the missile toward the source of radiation.

Claim 6

In a missile guidance system, a missile having a rotatable nose cone, a fin on said nose cone adapted to rotate the nose cone about the longitudinal axis of the missile and to steer the missile in a direction perpendicular to the longitudinal axis when the cone is braked relative to the missile, an electrical generator in the missile coupled to the nose cone, an optical slit on said nose cone positioned at an angle to said fin and in line with the direction of the steering force, a photosensitive element in said missile adapted to receive radiation passing through the slit and to send a pulse in response thereto, means to amplify said pulse and means responsive to said amplified pulse to send a pulse of reverse polarity to said generator, thus braking the generator, nose cone and fin so as to steer the missile toward the source of radiation.

Claim 7

A guidance system according to claim 4 in which the fin is an NACA foiled cowl mounted on a strut, the median line of the cowl being positioned 180° from the slit.

Claim 8

Means for guiding a missile toward an infrared radiation emitting source comprising, a rotatable nose cone, an optical slit on said nose cone and a fin on said nose cone adapted to rotate said nose cone when the missile moves through the air and to steer the missile in a direction perpendicular to the line of flight when the nose cone is mechanically coupled to the missile, an infrared sensor in the missile adapted to receive infrared radiation passing through said slit and to emit a pulse in response thereto, a generator coupled to the nose cone so as to rotate therewith and means responsive to said pulse so as to short the generator thus braking the generator and causing said mechanical coupling to provide a steering force to be exerted on the missile toward the source of infrared radiation.

Claim 9

Means for guiding a missile toward an infrared radiation emitting source comprising, a rotatable nose cone, an optical slit on said nose cone and a fin on said nose cone adapted to rotate said nose cone when the missile moves through the air and to steer the missile in a direction perpendicular to the line of flight when the nose cone is mechanically coupled to the missile, an infrared sensor in the missile adapted to receive infrared radiation passing through said slit and to emit a pulse in response thereto, a generator coupled to the nose cone so as to rotate therewith and means responsive to said pulse so as to short the generator thus braking the generator and causing said mechanical coupling to provide a steering force to be exerted on the missile toward the source of infrared radiation.

Claim 10

A target seeking guidance system for missiles comprising, an element rotatable about the longitudinal axis of the missile having means to receive emanation from a target during a portion of each revolution of the element and air foil means adapted to rotate said element and to produce a steering action in the direction of the emanation receiving means, means responsive to emanation received by said receiving means to brake the action of the rotatable element so as to steer the missile toward the target in response to said emanation.

Claim 11

A target seeking guidance system for missiles comprising, an element rotatable about the longitudinal axis of the missile having means to receive emanation from a target during a portion of each revolution of the element and air foil means adapted to rotate said element and to produce a steering action in the direction of the emanation receiving means, means responsive to emanation received by said receiving means to brake the action of the rotatable element so as to steer the missile toward the target in response to said emanation.

Claim 12

A guidance system according to claim 7 in which the emanation is infrared radiation.

Claim 13

A guidance system according to claim 7 in which the emanation is visible light.

Claim 14

A guidance system according to claim 7 in which the emanation is sonic vibrations.

Claim 15

A guidance system according to claim 7 in which the emanation is ultrasonic vibrations.

Claim 16

A target seeking missile guidance system adapted to be mounted on a missile comprising a sensor adapted to produce a control signal when subjected to a selected form of target emitted emanation, a scanning device mounted to rotate about the longitudinal axis of the missile and to pass such emanation originating from a portion only of a potential target area to the sensor whereby the whole potential target area is scanned progressively on each revolution of the scanning device, means to rotate the scanning device, steering means normally ineffective to steer the missile, means responsive to a signal produced by the sensor for activating said steering means to steer the missile toward a target while the sensor is receiving emanation from such target, and means operative following initial scanning of a potential target area for suppressing sensor signals induced by all scanned targets except the target emitting the maximum emanation.

Claim 17

A target seeking missile guidance system adapted to be mounted on a missile comprising a sensor adapted to produce a control signal when subjected to a selected form of target emitted emanation, a scanning device mounted to rotate about the longitudinal axis of the missile and to pass such emanation originating from a portion only of a potential target area to the sensor whereby the whole potential target area is scanned progressively on each revolution of the scanning device, means to rotate the scanning device, steering means normally ineffective to steer the missile, means responsive to a signal produced by the sensor for activating said steering means to steer the missile toward a target while the sensor is receiving emanation from such target, and means operative following initial scanning of a potential target area for suppressing sensor signals induced by all scanned targets except the target emitting the maximum emanation.

Claim 18

A target seeking guidance system adapted to be mounted on a missile comprising target sensing means responsive to emanation of a predetermined character normally emitted by potential targets of a preselected type for generating a target signal whenever it receives emanation of such character, means facing forwardly of the missile and having a span of less than 180° circumferentially of the missile for passing such target emanation to said responsive means when the passing means directly faces a target and intersects a plane including the longitudinal axis of the missile and a target lying within a scanning cone of predetermined angle extending forwardly of the missile symmetrically about the projected longitudinal axis of the missile, means for rotating the passing means about the longitudinal axis of the missile to scan a potential target area and to pass all such emanation emitted by potential targets in said area as the passing means rotates, steering means operative when activated to apply a steering force to the missile steering control means responsive to target signals for activating said steering means for the duration of each target signal to apply a steering force to the missile in a direction to steer the missile toward the target emitting the emanation to which the sensing means is responding to generate a target signal, and target selection means for comparing all target signals generated during one revolution of the passing means and thereafter suppressing all but the strongest of such target signals whereby the missile is steered toward a single selected target.

Claim 19

A target seeking guidance system adapted to be mounted on a missile comprising target sensing means responsive to emanation of a predetermined character normally emitted by potential targets of a preselected type for generating a target signal whenever it receives emanation of such character, means facing forwardly of the missile and having a span of less than 180° circumferentially of the missile for passing such target emanation to said responsive means when the passing means directly faces a target and intersects a plane including the longitudinal axis of the missile and a target lying within a scanning cone of predetermined angle extending forwardly of the missile symmetrically about the projected longitudinal axis of the missile, means for rotating the passing means about the longitudinal axis of the missile to scan a potential target area and to pass all such emanation emitted by potential targets in said area as the passing means rotates, steering means operative when activated to apply a steering force to the missile steering control means responsive to target signals for activating said steering means for the duration of each target signal to apply a steering force to the missile in a direction to steer the missile toward the target emitting the emanation to which the sensing means is responding to generate a target signal, and target selection means for comparing all target signals generated during one revolution of the passing means and thereafter suppressing all but the strongest of such target signals whereby the missile is steered toward a single selected target.

Claim 20

Apparatus according to claim 13 wherein the missile has a rotatable nose cone and said passing means comprises a narrow slit in said nose offset from the longitudinal axis of the missile.

Claim 21

Apparatus according to claim 13 wherein said guidance system includes a rotatably mounted nose cone on the missile, said rotating means comprises an aerodynamic fin on the nose cone skewed with respect to the longitudinal axis of the missile, a generator is mounted on the missile to supply power to the system and is coupled to the nose cone to be driven thereby, said steering means comprises means rotatable with the nose for generating a net instantaneous side thrust on the missile by reaction with the air and means controlled by said emanation responsive means for applying a braking action to the generator for the duration of target emanation received by such responsive means to increase the time during which such side thrust is operative in a particular direction.