Scanning interferometer-beam rider guidance system

Claim 2

A missile guidance system including, in combination with a missile and a source of electromagnetic energy, said source being remote from the missile and projecting a guiding beam, means for maintaining the missile in and under the control of said beam, said means including an antenna mounted on the missile and a receiver connected to the antenna, a steering vane on the missile, a servo for controlling the vane, said servo being responsive to signals entering the receiver through the antenna from the beam, switching means between the receiver and the servo, means in the missile for searching for a target, and means controlled by said last mentioned means and operable in response to a signal reflected from an acquired target for actuating said switching means whereby operation of the servo will be transferred from the first-mentioned means to the reflectedsignal operated means for controlling the vane or guiding the missile into the target.

Claim 3

In combination with a guided missile, a guidance system including a receiver carried by the missile, a steering vane-operating servo system carried by the missile and controlled by said receiver, whereby beamed signals impinging on said receiver will cause the receiver to actuate the servo system to maintain the missile in the beam, a second receiver carried by the missile and responsive to signals reflected from a target being tracked by the beam, and means for switching the control of the servo system to the second receiver when said reflected signals exceed a predetermined amplitude, said last mentioned means including target search and acquisition apparatus controlled by pulses from the first receiver.

Claim 4

In combination with a guided missile, a guidance system including a receiver carried by the missile, a steering vane-operating servo system carried by the missile and controlled by said receiver, whereby beamed signals impinging on said receiver will cause the receiver to actuate the servo system to maintain the missile in the beam, a second receiver carried by the missile and responsive to signals reflected from a target being tracked by the beam, and means for switching the control of the servo system to the second receiver when said reflected signals exceed a predetermined amplitude, said last mentioned means including target search and acquisition apparatus controlled by pulses from the first receiver.

Claim 5

In a missile guidance system, a missile, a beam-riding receiver, an antenna system carried by said missile and connected to said receiver, a steering vane controlling servo, means connected with the receiver whereby said receiver actuates said servo in response to signals beamed on a target, to keep the missile in the beam, a homing receiver in the missile, a second antenna system in the missile and connected to said homing receiver, said homing receiver being responsive to signals reflected from the target, and means for switching said servo from control by the beam-riding receiver to control by the homing receiver upon increase of the amplitude of the reflected signals to a value above a preset level, for guiding the missile into the target.

Claim 6

In a missile guidance system, a missile, a beam-riding receiver, an antenna system carried by said missile and connected to said receiver, a steering vane controlling servo, means connected with the receiver whereby said receiver actuates said servo in response to signals beamed on a target, to keep the missile in the beam, a homing receiver in the missile, a second antenna system in the missile and connected to said homing receiver, said homing receiver being responsive to signals reflected from the target, and means for switching said servo from control by the beam-riding receiver to control by the homing receiver upon increase of the amplitude of the reflected signals to a value above a preset level, for guiding the missile into the target.

Claim 7

In a missile guidance system, a missile, a beam-riding receiver carried by the missile, an antenna system connected to said receiver, a vane-operating servo system carried by the missile and controlled by the receiver, said servo system functioning to maintain the missile in a beam of electromagnetic energy tracking a target, a homing receiver carried by the missile, a second antenna on the missile and connected to the homing receiver, said homing receiver being responsive to signals reflected by the target, and apparatus operated by an impulse from the first receiver for switching control of the servo system to operation in response to target-reflected signals, whereby the missile will be guided into the target.

Claim 8

In a missile guidance system, a missile, a beam-riding receiver carried by the missile, an antenna system connected to said receiver, a vane-operating servo system carried by the missile and controlled by the receiver, said servo system functioning to maintain the missile in a beam of electromagnetic energy tracking a target, a homing receiver carried by the missile, a second antenna on the missile and connected to the homing receiver, said homing receiver being responsive to signals reflected by the target, and apparatus operated by an impulse from the first receiver for switching control of the servo system to operation in response to target-reflected signals, whereby the missile will be guided into the target.

Claim 9

In a missile guidance system as recited in claim 4, wherein said apparatus includes means on the beam-riding receiver for providing timed pulses, and means utilizing said pulses for determining the optimum time for switching control of the servo system.

Claim 10

In a missile guidance system as recited in claim 5, wherein said last mentioned means includes a search unit, a time modulator, and a time discriminator including a gate, said search unit, time modulator and time discriminator being interconnected and said time discriminator being connected to the homing receiver.

Claim 11

In a missile guidance system, a missile, a receiver carried by the missile and providing reference impulses, an antenna system carried by the missile and connected to the receiver, a vane controlling servo system connected to the receiver, said servo system being operated by the receiver upon receipt by said receiver of energy from an electromagnetic beam, homing guidance apparatus including a homing receiver carried by the missile, a pair of antennas on the missile and connected to the homing receiver, a phase shifter connected between the last mentioned antennas and providing interferometer scanning action of signals in a target area, means operated by an impulse from the first-mentioned receiver for searching for and acquiring a target in the area, means for stopping operation of said last-mentioned means upon acquisition of a target, and means for switching the servo system from the first mentioned receiver to said homing guidance apparatus upon target acquisition for guiding the missile into the target.

Claim 12

In a missile guidance system, a missile, a receiver carried by the missile and providing reference impulses, an antenna system carried by the missile and connected to the receiver, a vane controlling servo system connected to the receiver, said servo system being operated by the receiver upon receipt by said receiver of energy from an electromagnetic beam, homing guidance apparatus including a homing receiver carried by the missile, a pair of antennas on the missile and connected to the homing receiver, a phase shifter connected between the last mentioned antennas and providing interferometer scanning action of signals in a target area, means operated by an impulse from the first-mentioned receiver for searching for and acquiring a target in the area, means for stopping operation of said last-mentioned means upon acquisition of a target, and means for switching the servo system from the first mentioned receiver to said homing guidance apparatus upon target acquisition for guiding the missile into the target.

Claim 13

A missile guidance system including, in combination with a missile having a receiver, an antenna on the missile and connected to the receiver, said antenna conducting to said receiver signals from a beam of electromagnetic energy searching a target area, a steering control servo system having a steering vane, and means connecting the receiver to the servo system and including a relay, said receiver producing reference timing pulses and said receiver and servo system maintaining the missile in the beam; missile homing guidance apparatus comprising a homing receiver, an antenna on the missile for conducting to said homing receiver signals reflected from a target, a time discriminator, a time modulator receiving pulses from the first mentioned receiver and feeding delayed pulses to the time discriminator, said discriminator including a gate, a search and data memory unit coupled to the discriminator and to the modulator and operable for positioning the gate for sampling target-reflected signals from the homing receiver, whereby the range ahead of the missile will be searched for an acceptable target, an envelope detector coupled to the time modulator, time discriminator and receiver, means coupled to the envelope detector and operable for arresting operation of the searching process upon acquisition of an acceptable target, means coupled to said detector and to said last mentioned means for providing homing control signals, and means including said last mentioned means and said relay for switching control from said first mentioned receiver to said missile homing guidance apparatus, whereby the missile will be guided into the accepted target.

Claim 14

A missile guidance system including, in combination with a missile having a receiver, an antenna on the missile and connected to the receiver, said antenna conducting to said receiver signals from a beam of electromagnetic energy searching a target area, a steering control servo system having a steering vane, and means connecting the receiver to the servo system and including a relay, said receiver producing reference timing pulses and said receiver and servo system maintaining the missile in the beam; missile homing guidance apparatus comprising a homing receiver, an antenna on the missile for conducting to said homing receiver signals reflected from a target, a time discriminator, a time modulator receiving pulses from the first mentioned receiver and feeding delayed pulses to the time discriminator, said discriminator including a gate, a search and data memory unit coupled to the discriminator and to the modulator and operable for positioning the gate for sampling target-reflected signals from the homing receiver, whereby the range ahead of the missile will be searched for an acceptable target, an envelope detector coupled to the time modulator, time discriminator and receiver, means coupled to the envelope detector and operable for arresting operation of the searching process upon acquisition of an acceptable target, means coupled to said detector and to said last mentioned means for providing homing control signals, and means including said last mentioned means and said relay for switching control from said first mentioned receiver to said missile homing guidance apparatus, whereby the missile will be guided into the accepted target.

Claim 15

In a missile guidance system, a missile, means on the missile for maintaining said missile in a beam of electromagnetic energy searching a target area, said means including a receiver producing reference timing pulses and a steering vane controlling servo system; homing guidance apparatus including a time modulator receiving reference timing pulses from said receiver and generating delayed gating pulses, a time discriminator including a gate, a homing receiver supplying target-reflected signals to the gate, a search and data memory unit cooperating with said modulator and discriminator for searching the range ahead of the missile for a target, search stop apparatus for stopping the search process upon target acquisition, an envelope detector for operating the search stop apparatus upon target acquisition, in response to a signal passing through the gate, and means for switching operation of the servo mechanism to respond to signals from the homing receiver after target acquisition.

Claim 16

In a missile guidance system, a missile, means on the missile for maintaining said missile in a beam of electromagnetic energy searching a target area, said means including a receiver producing reference timing pulses and a steering vane controlling servo system; homing guidance apparatus including a time modulator receiving reference timing pulses from said receiver and generating delayed gating pulses, a time discriminator including a gate, a homing receiver supplying target-reflected signals to the gate, a search and data memory unit cooperating with said modulator and discriminator for searching the range ahead of the missile for a target, search stop apparatus for stopping the search process upon target acquisition, an envelope detector for operating the search stop apparatus upon target acquisition, in response to a signal passing through the gate, and means for switching operation of the servo mechanism to respond to signals from the homing receiver after target acquisition.

Claim 17

In a missile guidance system, a missile, means on the missile and initially maintaining said missile in a beam of electromagnetic energy searching a targeT area, and means on the missile and responsive to signals reflected from a target in the area for guiding the missile into said target after said missile has reached the vicinity thereof, said last mentioned means including a servo system initially under the control of said first mentioned means, apparatus under control of said first-mentioned means and operative for searching for and acquiring the target, means for stopping operation of said apparatus upon target acquisition, and means for switching servo system control to said second mentioned means after target acquisition.

Claim 18

In a missile guidance system, a missile, means on the missile and initially maintaining said missile in a beam of electromagnetic energy searching a targeT area, and means on the missile and responsive to signals reflected from a target in the area for guiding the missile into said target after said missile has reached the vicinity thereof, said last mentioned means including a servo system initially under the control of said first mentioned means, apparatus under control of said first-mentioned means and operative for searching for and acquiring the target, means for stopping operation of said apparatus upon target acquisition, and means for switching servo system control to said second mentioned means after target acquisition.

Claim 19

A missile guidance system as recited in claim 10, wherein said last mentioned means includes a homing receiver, an interferometer antenna system connected to the homing receiver, a relay for operating the servo system control switching, and apparatus operated by the homing receiver for actuating the relay.

Claim 20

A missile guidance system as recited in claim 11, wherein said relay actuating apparatus includes a detector connected with the homing receiver, and stabilization and error detection circuits connected between the detector and the relay.

Claim 21

A missile guidance system as recited in claim 11, wherein said relay actuating apparatus includes an amplifier and a time delay circuit connected between the relay and the means for stopping operation of the target search and acquisition apparatus.

Claim 22

A missile guidance system as recited in claim 9, wherein said envelope detector includes means for supplying a pulse constituting a homing guidance signal, means for providing an automatic gain control voltage for the homing receiver, and means for supplying a voltage for operating the search stop apparatus.

Claim 23

A missile guidance system as recited in claim 9, wherein said time modulator includes a multi-vibrator coupled to the first mentioned receiver and receiving the reference timing pulses therefrom, an integrator coupled to the multivibrator, a blocking oscillator, and a diode comparator connected between the blocking oscillator and the integrator, said comparator supplying range voltage to the search and data memory unit and said blocking oscillator supplying a gate control voltage to the time modulator.

Claim 24

A missile guidance system including, in combination with a missile having a receiver, and a steering control servo system connected with the receiver, said receiver initially cooperating with the servo system for keeping the missile in a beam of electromagnetic energy searching a target area, said receiver having a source of reference pulses, means for searching the range ahead of the missile for a target in the area, said means including a homing receiver, a gate and apparatus operable partially by said reference pulses for intermittently opening the gate, and apparatus for utilizing a signal reflected from an acceptable target and passing the gate for assuming control of the missile from the first mentioned receiver when the missile approaches the vicinity of said acceptable target, whereby said missile will be guided into the target.

Claim 25

A missile guidance system including, in combination with a missile having a receiver, and a steering control servo system connected with the receiver, said receiver initially cooperating with the servo system for keeping the missile in a beam of electromagnetic energy searching a target area, said receiver having a source of reference pulses, means for searching the range ahead of the missile for a target in the area, said means including a homing receiver, a gate and apparatus operable partially by said reference pulses for intermittently opening the gate, and apparatus for utilizing a signal reflected from an acceptable target and passing the gate for assuming control of the missile from the first mentioned receiver when the missile approaches the vicinity of said acceptable target, whereby said missile will be guided into the target.

Claim 26

A missile guidance system as recited in claim 16, wherein said last mentioned apparatus includes a time modulator emitting delayed gating pulses, a search and data memory unit comprising a double integrator, and a time discriminator, said search and data memory unit setting said time discriminator for successive ranges of target position and aligning the gate to a target signal, said time modulator, time discriminator and search and data memory unit being interconnected.

Claim 27

A missile guidance system as recited in claim 17, including additionally an envelope detector consisting of a blocking oscillator and a cathode follower, means for stopping operation of the range search means, and means supplying a homing signal pulse for operating the missile servo system, said envelope detector supplying a search stop signal to the range search stopping means, automatic gain control voltage to the homing receiver and a keying pulse to the hOming signal pulse supply means.

Claim 28

In a missile guidance system, means for searching the range beyond a predetermined minimum distance ahead of a traveling missile for a target, and means operable by said first mentioned means for removing the minimum range restriction from the range searching means upon target acquisition, said first mentioned means being actuated by a pulse signal emitted from a point remote from the missile.

Claim 29

In a missile guidance system, means for searching the range beyond a predetermined minimum distance ahead of a traveling missile for a target, and means operable by said first mentioned means for removing the minimum range restriction from the range searching means upon target acquisition, said first mentioned means being actuated by a pulse signal emitted from a point remote from the missile.

Claim 30

In a guided missile, a guidance system including means for causing the missile to follow a target-tracking beam of electromagnetic energy emitted from a point remote from the missile until said missile reaches the vicinity of a target, said beam containing a reference signal, and means on the missile and operated by said reference signal and by signals reflected from the target for causing the missile to be guided into the target.

Claim 31

In a guided missile, a guidance system including means for causing the missile to follow a target-tracking beam of electromagnetic energy emitted from a point remote from the missile until said missile reaches the vicinity of a target, said beam containing a reference signal, and means on the missile and operated by said reference signal and by signals reflected from the target for causing the missile to be guided into the target.