US3761180A - Synchronously gated active night sight - Google Patents

Synchronously gated active night sight Download PDF

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US3761180A
US3761180A US00291511A US3761180DA US3761180A US 3761180 A US3761180 A US 3761180A US 00291511 A US00291511 A US 00291511A US 3761180D A US3761180D A US 3761180DA US 3761180 A US3761180 A US 3761180A
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beacon
sight
night sight
gated
synchronizing signal
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R Maxwell
J Tallet
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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
    • F41G7/30—Command link guidance systems
    • F41G7/301—Details
    • F41G7/303—Sighting or tracking devices especially provided for simultaneous observation of the target and of the missile

Definitions

  • ABSTRACT 52 us. C1 356/152, 178/DIG. 21, 356/5,
  • a night Sight employing a gated image intensifier is p- 244/313 2444316 erated in conjunction with an amplitude-modulated 51 lnt. c1.
  • Field of Search 250/203 R; for illuminating the target The seuree is Pulsed and the 7 131 2 35 4 5 152; 24 43 3 intensifier tube gated on for the target return magnet attached illumination such times that the amplitude 5 References Cited modulated beacon intensity is at a low level for UNITED STATES PATENTS minimium viewing interference.
  • a class of guided missiles has been developed for tactical use which employs a command-to-line-of-sight mechanization.
  • a sight line to a target is established with an optical sight.
  • the missile is guided by means of an optical error sensing device which measures the error or deviation of the missile from the desired line of sight and furnishes command signals to the missile control system by means of an encoder and data link; thereby causing the missile to follow the line of sight to the target.
  • a beacon is placed on the missile.
  • This beacon usually comprises an amplitude-modulated source of optical radiation.
  • the modulation provides a signature which permits the tracker to discriminate against unmodulated sources such as sunlight reflections from random objects in the tracker field of view.
  • the optical spectrum of the beacon may be such that it can be seen by the eye. In daylight conditions the use of an optical filter would be satisfactory in reducing the beacon brightness to a tolerable level without inhibiting the ability of the gunner to maintain his line of sight on the target.
  • the degree of optical filtering necessary to reduce the beacon intensity to a tolerable level may also reduce the overall light level to a value which would seriously inhibit the trackers ability to see the target.
  • the instant invention solves this problem.
  • the beacon Since the beacon is amplitude-modulated, the radiant intensity varies with time from a very low value (essentially zero) to a peak value during each cycle.
  • the tube can be gated on for very short periods of time such that it is on at the time that the beacon radiant intensity is at its lowest value.
  • the gating of the night sight is, therefore, so synchronized with the beacon modulation that the beacon irradiance at the night sight is kept at a tolerable value.
  • the gating of the image intensifier results in a reduction in the time during which the target is observed, the average radiant intensity from the target and scene is reduced.
  • a pulsed illumination source is employed. The source is pulsed to illuminate the target and the image intensifier gating is timed so that the sight is gated on at the time that the radiant energy of the illuminated target returns to the night sight.
  • an optical radiant intensity sensor is employed. This sensor responds to the beacon modulation and provides means for sensing the time at which the beacon intensity is at its lowest value, thereby providing the necessary information for the synchronization of illuminator and gating.
  • FIG. I shows the optical tracking and guidance of a I
  • FIG. 3 depicts the time-history relationship of the beacon modulation, illuminator pulse and the image intensifier tube gating pulse.
  • a visual sight Id providing a line of sight is associated with an optical tracker II.
  • Visually sighting to target I2 aligns the boresight axis of the optical tracker with this target.
  • the optical tracker receives amplitude-modulated radiant pulses from a beacon I3 on missile II.
  • the optical tracker I I having error sensing means therein measures the error or deviation of the missile from the desired line of sight.
  • a command encoder I5 receives error signals from the tracker II and provides command signals to a command transmitter Id which sends the corrective signals to the missile Ml thereby causing it to follow the desired line of sight to the target.
  • the sight M which is a synchronized active night sight, can be described as follows.
  • the beacon modulation waveform is sensed by a beacon modulation detector 20.
  • the detected signals are sent to a crossing detector and time delay in element 2I.
  • Electronic circuits comprising the crossing detector in element 2I detect the time at which the beacon radiant intensity has decreased to percent of its peak value.
  • a time delay of one-quarter of the modulation period is used to generate a synchronizing pulse.
  • This synchronizing pulse triggers a pulsed illuminator 22 by way of a PRF generator 23 when the beacon radiant intensity is near it lowest level.
  • the pulsed illuminator could, for example, comprise a narrow spectral bandwidth source such as gallium arsenide or gallium aluminum arsenide.
  • the illuminator optical pulse is transmitted to the target I2 and reflected therefrom to the night sight 25.
  • a range time delay 24!- operating in response to a signal from the PRF generator 23 provides a signal to the gated night sight 25 to gate the image intensifier tube on just as the optical pulse returns from the target.
  • Additional beacon suppression is provided by a narrow optical bandpass filter 2b which passes the pulsed illuminator energy but not the radiant energy of the beacon.
  • the time-history of FIG. 3 shows the illuminator pulse generated after the one-quarter modulation period delay, and the image tube gate pulse being generated at the time of the returning reflected target pulse.
  • the device of the instant invention could, for example, incorporate a second generation image intensifier tube employing a single photoemissive photocathode, a microchannel plate amplifier and a single phosphor screen; such tube providing speed of response and peak pulse capabilities compatible with the overall system requirements of this device.
  • An optical command-to-line-of-sightguidance system having an active night sight for use with a missile having an amplitude-modulated beacon of optical radiation thereon, said system comprising:
  • said electronic cirphotoresponsive means for detecting the radiant en- 5 cuit means includes further means for establishing a ergy amplitude of the missile beacon;
  • electronic circuit means including means for determining the time at which the beacon amplitude has decreased to a pre-determined level from its peak amplitude and for generating a synchronizing signal thereat;
  • a gated night sight capable of being gated on in response to an applied signal
  • range time delay means responsive to a signal derived from said synchronizing signal to gate on the gated night sight; whereby the night sight is gated on time delay in said synchronizing signal; said time delay being on the order of one-quarter of the beacon modulation period.
  • said generator further activating said range time delay for gating on said night sight.

Abstract

A night sight employing a gated image intensifier is operated in conjunction with an amplitude-modulated tracking beacon on a missile and a pulsed light source for illuminating the target. The source is pulsed and the intensifier tube gated on for the target return magnet attached illumination such times that the amplitude modulated beacon intensity is at a low level for minimium viewing interference.

Description

United States Patent [1 1 Maxwell, Jr. et al.
SYNCHRONOUSLY GATED ACTIVE NIGHT SIGHT [451 Sept. 25, 1575 3,219,826 11/1965 Letaw, Jr. 244/3.16 3,478,212 11/1969 Turck r 250/203 R 3,467,773 9/1969 Heckman, .lr.... 178/68 2,930,894 3/1960 Bozeman 244/3.13
Primary Examiner-Benjamin A. Borchelt Assistant Examiner-S. C. Buczinski [22] Filed; Sept, 22, 1972 Attorney-llarry M. Saragovitz et al. [21] Appl. No.: 291,511
[57] ABSTRACT 52 us. C1 356/152, 178/DIG. 21, 356/5, A night Sight employing a gated image intensifier is p- 244/313 2444316 erated in conjunction with an amplitude-modulated 51 lnt. c1. Gtllc 3/03 treekihg heeeeh on a missile and a pulsed light some [58] Field of Search 250/203 R; for illuminating the target The seuree is Pulsed and the 7 131 2 35 4 5 152; 24 43 3 intensifier tube gated on for the target return magnet attached illumination such times that the amplitude 5 References Cited modulated beacon intensity is at a low level for UNITED STATES PATENTS minimium viewing interference.
3,640,628 2/1972 Jones 244/3. 16 41 Claims, 3 Drawing Figures 1 22 23 I PULSED PRF I2 ILLUIVIINATOR GENERATOR 1 1 1 TARGET I a 1 GATED RANGE NIGHT TIME SlGHT DELAY I 1 L i BEACON I I BEACON CROSSING f 7 MODULATION DETECTOR a I I3 DETECTOR TIME DELAY PAIENIED E Z 3,781.1 80
' sum 2 OF 2 BEACON RADIANT INTENS'TY ILLUMINATOR PULSE REFLECTED TARGET I PULSE /IMAGE TUBE 4--RANGE DELAY GATE PULSE BACKGROUND OF THE INVENTION A class of guided missiles has been developed for tactical use which employs a command-to-line-of-sight mechanization. A sight line to a target is established with an optical sight. After launch toward the target, the missile is guided by means of an optical error sensing device which measures the error or deviation of the missile from the desired line of sight and furnishes command signals to the missile control system by means of an encoder and data link; thereby causing the missile to follow the line of sight to the target.
In order to provide a tracking source for the optical tracker, a beacon is placed on the missile. This beacon usually comprises an amplitude-modulated source of optical radiation. The modulation provides a signature which permits the tracker to discriminate against unmodulated sources such as sunlight reflections from random objects in the tracker field of view.
The optical spectrum of the beacon may be such that it can be seen by the eye. In daylight conditions the use of an optical filter would be satisfactory in reducing the beacon brightness to a tolerable level without inhibiting the ability of the gunner to maintain his line of sight on the target.
However, ifa night sight is to be used with such a missile system, the degree of optical filtering necessary to reduce the beacon intensity to a tolerable level may also reduce the overall light level to a value which would seriously inhibit the trackers ability to see the target. The instant invention solves this problem.
SUMMARY OF THE INVENTION Since the beacon is amplitude-modulated, the radiant intensity varies with time from a very low value (essentially zero) to a peak value during each cycle.
If a night sight, which employs a gated image intensitier tube is used, the tube can be gated on for very short periods of time such that it is on at the time that the beacon radiant intensity is at its lowest value. The gating of the night sight is, therefore, so synchronized with the beacon modulation that the beacon irradiance at the night sight is kept at a tolerable value.
Since the gating of the image intensifier results in a reduction in the time during which the target is observed, the average radiant intensity from the target and scene is reduced. In order to provide the necessary target radiant intensity a pulsed illumination source is employed. The source is pulsed to illuminate the target and the image intensifier gating is timed so that the sight is gated on at the time that the radiant energy of the illuminated target returns to the night sight.
In order to provide a synchronizing signal to the illuminator and gated image intensifier tube, an optical radiant intensity sensor is employed. This sensor responds to the beacon modulation and provides means for sensing the time at which the beacon intensity is at its lowest value, thereby providing the necessary information for the synchronization of illuminator and gating.
BRIEF DESCRIPTION OF THE DRAWINGS FIG. I shows the optical tracking and guidance of a I FIG. 3 depicts the time-history relationship of the beacon modulation, illuminator pulse and the image intensifier tube gating pulse.
DESCRIPTION OF THE PREFERRED EMBODIMENT In FIG. I, a visual sight Id providing a line of sight is associated with an optical tracker II. Visually sighting to target I2 aligns the boresight axis of the optical tracker with this target. The optical tracker receives amplitude-modulated radiant pulses from a beacon I3 on missile II. The optical tracker I I having error sensing means therein measures the error or deviation of the missile from the desired line of sight. A command encoder I5 receives error signals from the tracker II and provides command signals to a command transmitter Id which sends the corrective signals to the missile Ml thereby causing it to follow the desired line of sight to the target.
Turning to Figure 2, we see, diagrammatically, the sight III of the instant invention and the associated beacon suppression components. The sight M, which is a synchronized active night sight, can be described as follows. The beacon modulation waveform is sensed by a beacon modulation detector 20. The detected signals are sent to a crossing detector and time delay in element 2I. Electronic circuits comprising the crossing detector in element 2I detect the time at which the beacon radiant intensity has decreased to percent of its peak value. A time delay of one-quarter of the modulation period is used to generate a synchronizing pulse. This synchronizing pulse triggers a pulsed illuminator 22 by way of a PRF generator 23 when the beacon radiant intensity is near it lowest level. The pulsed illuminator could, for example, comprise a narrow spectral bandwidth source such as gallium arsenide or gallium aluminum arsenide. The illuminator optical pulse is transmitted to the target I2 and reflected therefrom to the night sight 25. A range time delay 24!- operating in response to a signal from the PRF generator 23 provides a signal to the gated night sight 25 to gate the image intensifier tube on just as the optical pulse returns from the target. By these means, the target is observed when the beacon radiant intensity is at its lowest value resulting in minimum viewing interference by the beacon I3.
Additional beacon suppression is provided by a narrow optical bandpass filter 2b which passes the pulsed illuminator energy but not the radiant energy of the beacon.
The time-history of FIG. 3 shows the illuminator pulse generated after the one-quarter modulation period delay, and the image tube gate pulse being generated at the time of the returning reflected target pulse.
The device of the instant invention could, for example, incorporate a second generation image intensifier tube employing a single photoemissive photocathode, a microchannel plate amplifier and a single phosphor screen; such tube providing speed of response and peak pulse capabilities compatible with the overall system requirements of this device.
While a preferred embodiment of the invention has been disclosed, it should be clear that variations and alterations thereof can be made while remaining within the scope of the invention which is only limited by the following claims.
We claim:
1. An optical command-to-line-of-sightguidance system having an active night sight for use with a missile having an amplitude-modulated beacon of optical radiation thereon, said system comprising:
when the beacon amplitude is at a low level and the pulsed illumination reflected from said target has returned to said night sight.
2. The system of claim 1 wherein said electronic cirphotoresponsive means for detecting the radiant en- 5 cuit means includes further means for establishing a ergy amplitude of the missile beacon;
electronic circuit means including means for determining the time at which the beacon amplitude has decreased to a pre-determined level from its peak amplitude and for generating a synchronizing signal thereat;
means for generating an illumination pulse along the line of sight toward a missile target in response to said synchronizing signal;
a gated night sight capable of being gated on in response to an applied signal;
range time delay means responsive to a signal derived from said synchronizing signal to gate on the gated night sight; whereby the night sight is gated on time delay in said synchronizing signal; said time delay being on the order of one-quarter of the beacon modulation period.
3. The system of claim 2, further including a pulse repetition frequency generator for receiving said synchronizing signal and utilizing said synchronizing signal for triggering the illumination pulse, said generator further activiating said range time delay for gating on said night sight;
said generator further activating said range time delay for gating on said night sight.
4. The system of claim 3 including a narrow bandpass filter associated with said gated night sight.
. UNITED STATES PATENT OFFICE CERTIFICATE 0F CORRECTION Patent No. 3,761,180 Dated 25 September 1973 Inventor-(S) Richard F. Maxwell, Jr. and Jose E. Tallet It is certified that error appears in the above-identified patent and that said Letters Patent are hereby corrected as shown below:
On the front page, between data. elements and 22] insert -83] Assignee: The United States of America as represented by the Secretary of the Army".
Signed and sealed this 19th day of March 1974.
(SEAL Attestz' v I EDWARD 'M.FLETCH ER, JR. c. MARSHALL DA'NN Attesting Officer Commissioner of Patents *ORM Po-1osq (10-69) USCOMM-DC 60376-P69 t 0.5. GOVERNMENT pamrmc OFFICE I969 o-aas-au UNITED STATES PATENT OFFICE CERTIFICATE OF CORRECTION Patent No. 3,761,180 Dated 25 September 1973 Inventor(s) Richard F. Maxwell, Jr. and Jose E. Tallet It is certified that error appears in the above-identified patent and that said Letters Patent are hereby corrected as shown below:
on the front page, between data elements [75] and 22] insert -[73] Assignee: The United States of America as represented by the Secretary of the Army-n Signed and sealed this 19th day of March 1974.
(SEAL) Attest:
EDWARD M.FLETCHER,'JR. c. MARSHALL DA'NN Attesting Officer Commissioner of Patents ORM PQAOSQ (10-69) USCOMM-DC 60376-P69 u.s. GOVERNMENT rnmnuc ornc: I969 o-ass-Ju

Claims (4)

1. An optical command-to-line-of-sight guidance system having an active night sight for use with a missile having an amplitudemodulated beacon of optical radiation thereon, said system comprising: photoresponsive means for detecting the radiant energy amplitude of the missile beacon; electronic circuit means including means for determining the time at which the beacon amplitude has decreased to a prEdetermined level from its peak amplitude and for generating a synchronizing signal thereat; means for generating an illumination pulse along the line of sight toward a missile target in response to said synchronizing signal; a gated night sight capable of being gated on in response to an applied signal; range time delay means responsive to a signal derived from said synchronizing signal to gate on the gated night sight; whereby the night sight is gated on when the beacon amplitude is at a low level and the pulsed illumination reflected from said target has returned to said night sight.
2. The system of claim 1 wherein said electronic circuit means includes further means for establishing a time delay in said synchronizing signal; said time delay being on the order of one-quarter of the beacon modulation period.
3. The system of claim 2, further including a pulse repetition frequency generator for receiving said synchronizing signal and utilizing said synchronizing signal for triggering the illumination pulse, said generator further activiating said range time delay for gating on said night sight; said generator further activating said range time delay for gating on said night sight.
4. The system of claim 3 including a narrow bandpass filter associated with said gated night sight.
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Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3900175A (en) * 1972-06-26 1975-08-19 Bofors Ab Guidance system for an anti-aircraft missile
US4269121A (en) * 1974-08-12 1981-05-26 The United States Of America As Represented By The Secretary Of The Navy Semi-active optical fuzing
US4474343A (en) * 1981-05-04 1984-10-02 Hughes Aircraft Company Jitter compensating scene stabilizing missile guidance system
US4600305A (en) * 1984-08-20 1986-07-15 The United States Of America As Represented By The Secretary Of The Army Dynamic energy centroid locator and processor (declp)
FR2583523A1 (en) * 1985-06-17 1986-12-19 Aerospatiale SYSTEM FOR LOCATING A MOBILE.
US4732349A (en) * 1986-10-08 1988-03-22 Hughes Aircraft Company Beamrider guidance system
USRE33287E (en) * 1980-02-04 1990-08-07 Texas Instruments Incorporated Carrier tracking system
US4967270A (en) * 1989-05-08 1990-10-30 Kaman Aerospace Corporation Lidar system incorporating multiple cameras for obtaining a plurality of subimages
FR2653562A1 (en) * 1989-10-23 1991-04-26 Aerospatiale SYSTEM FOR LOCATING A MOBILE.
DE3812984C1 (en) * 1988-04-19 1991-07-18 Eltro Gmbh, Gesellschaft Fuer Strahlungstechnik, 6900 Heidelberg, De Continuously locating and guiding missile or aircraft - measuring laser radiation returned from on-board reflector using transceiver goniometer unit
US5034810A (en) * 1989-12-07 1991-07-23 Kaman Aerospace Corporation Two wavelength in-situ imaging of solitary internal waves
US5231401A (en) * 1990-08-10 1993-07-27 Kaman Aerospace Corporation Imaging lidar system
US5270780A (en) * 1991-09-13 1993-12-14 Science Applications International Corporation Dual detector lidar system and method
US5519209A (en) * 1994-06-15 1996-05-21 Alliedsignal Inc. High range resolution active imaging system using a high speed shutter and a light pulse having a sharp edge
US6260792B1 (en) * 1981-05-04 2001-07-17 Raytheon Company Tracking and guidance system with modulated missile-mounted laser beacon

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2930894A (en) * 1954-07-13 1960-03-29 Republic Aviat Corp Optical sighting and tracking device
US3219826A (en) * 1963-10-07 1965-11-23 Raytheon Co Target tracking guidance system with false signal detecting means
US3467773A (en) * 1966-11-07 1969-09-16 Us Navy Television monitoring system for penetrating a light backscattering medium
US3478212A (en) * 1966-01-27 1969-11-11 Telecommunications Sa Aiming system for the remote guidance of self-propelled missiles toward a target
US3640628A (en) * 1969-12-18 1972-02-08 Hughes Aircraft Co Electro-optical target acquisition blanking system

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2930894A (en) * 1954-07-13 1960-03-29 Republic Aviat Corp Optical sighting and tracking device
US3219826A (en) * 1963-10-07 1965-11-23 Raytheon Co Target tracking guidance system with false signal detecting means
US3478212A (en) * 1966-01-27 1969-11-11 Telecommunications Sa Aiming system for the remote guidance of self-propelled missiles toward a target
US3467773A (en) * 1966-11-07 1969-09-16 Us Navy Television monitoring system for penetrating a light backscattering medium
US3640628A (en) * 1969-12-18 1972-02-08 Hughes Aircraft Co Electro-optical target acquisition blanking system

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3900175A (en) * 1972-06-26 1975-08-19 Bofors Ab Guidance system for an anti-aircraft missile
US4269121A (en) * 1974-08-12 1981-05-26 The United States Of America As Represented By The Secretary Of The Navy Semi-active optical fuzing
USRE33287E (en) * 1980-02-04 1990-08-07 Texas Instruments Incorporated Carrier tracking system
US4474343A (en) * 1981-05-04 1984-10-02 Hughes Aircraft Company Jitter compensating scene stabilizing missile guidance system
US6260792B1 (en) * 1981-05-04 2001-07-17 Raytheon Company Tracking and guidance system with modulated missile-mounted laser beacon
US4600305A (en) * 1984-08-20 1986-07-15 The United States Of America As Represented By The Secretary Of The Army Dynamic energy centroid locator and processor (declp)
FR2583523A1 (en) * 1985-06-17 1986-12-19 Aerospatiale SYSTEM FOR LOCATING A MOBILE.
EP0206912A1 (en) * 1985-06-17 1986-12-30 AEROSPATIALE Société Nationale Industrielle Position finding system for a moving object
US4732349A (en) * 1986-10-08 1988-03-22 Hughes Aircraft Company Beamrider guidance system
DE3812984C1 (en) * 1988-04-19 1991-07-18 Eltro Gmbh, Gesellschaft Fuer Strahlungstechnik, 6900 Heidelberg, De Continuously locating and guiding missile or aircraft - measuring laser radiation returned from on-board reflector using transceiver goniometer unit
US4967270A (en) * 1989-05-08 1990-10-30 Kaman Aerospace Corporation Lidar system incorporating multiple cameras for obtaining a plurality of subimages
EP0425355A1 (en) * 1989-10-23 1991-05-02 AEROSPATIALE Société Nationale Industrielle Position finding system for a moving object
US5081345A (en) * 1989-10-23 1992-01-14 Societe Anonyme Dite: Aerospatiale Societe Nationale Industrielle System for locating a moving object using matrix detector and time integration
FR2653562A1 (en) * 1989-10-23 1991-04-26 Aerospatiale SYSTEM FOR LOCATING A MOBILE.
US5034810A (en) * 1989-12-07 1991-07-23 Kaman Aerospace Corporation Two wavelength in-situ imaging of solitary internal waves
US5231401A (en) * 1990-08-10 1993-07-27 Kaman Aerospace Corporation Imaging lidar system
US5270780A (en) * 1991-09-13 1993-12-14 Science Applications International Corporation Dual detector lidar system and method
US5519209A (en) * 1994-06-15 1996-05-21 Alliedsignal Inc. High range resolution active imaging system using a high speed shutter and a light pulse having a sharp edge

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