US3501113A - Rotating beam missile guidance system - Google Patents

Rotating beam missile guidance system Download PDF

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Publication number
US3501113A
US3501113A US695278A US3501113DA US3501113A US 3501113 A US3501113 A US 3501113A US 695278 A US695278 A US 695278A US 3501113D A US3501113D A US 3501113DA US 3501113 A US3501113 A US 3501113A
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US
United States
Prior art keywords
missile
axis
detector
pattern
fins
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 - Lifetime
Application number
US695278A
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English (en)
Inventor
Gordon J R Maclusky
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.)
BAC AND BRITISH AEROSPACE
BAE Systems PLC
Original Assignee
British Aircraft Corp Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by British Aircraft Corp Ltd filed Critical British Aircraft Corp Ltd
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Publication of US3501113A publication Critical patent/US3501113A/en
Assigned to BRITISH AEROSPACE PUBLIC LIMITED COMPANY reassignment BRITISH AEROSPACE PUBLIC LIMITED COMPANY CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). EFFECTIVE JAN. 2, 1981 Assignors: BRITISH AEROSPACE LIMITED
Assigned to BAC AND BRITISH AEROSPACE reassignment BAC AND BRITISH AEROSPACE ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: BRITISH AIRCRAFT CORPORATION LIMITED,
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F41G7/266—Optical guidance systems for spin-stabilized missiles

Definitions

  • a missile is guided by a beam radiated in the required direction of flight.
  • the beam comprises a rotating pattern of radiation.
  • the missile is rotated about its axis during flight and a radiation detector is mounted on the missile oflset with respect to its axis of rotation.
  • the detector output includes a frequency modulated component which is used to guide the missile back towards the beam pattern axis.
  • the object of the present invention is to provide a beam-riding system which is relatively simple and is insensitive to all effects producing only amplitude modulation of the beam.
  • this is achieved by guiding the missile in a pattern of infra-red, visible or ultra-violet radiation which is rotating about an axis leading to the target and by providing in the missile means for rotating the missile about its axis during flight, a detector, responsive to the radiation, which is mounted on the missile offset with respect to the missile axis, and means receiving the detector output and responsive to the frequency modulation of the latter resulting from the rotation of the radiation pattern and the rotation of the offset detector to adjust flight path controls and hereby to steer the missile towards the pattern axis.
  • the rotating radiation pattern may be provided by means of a projector, external to the missile, for aiming a beam of infra-red, visible or ultra-violet radiation at the target and a rotary pattern device for splitting the beam crosssection into sectors and for rotating the sector pattern.
  • the frequency modulation occurs when the missile is offset with respect to the beam axis because the circular movement of translation of the detector is in the same direction as that of the sector pattern for one-half of the missiles rotary movement and is opposite to the motion of the sector pattern for the other half of its rotary movement.
  • sector pattern is not intended to restrict the pattern to sectors defined by the radii of a circle and that it will include, for example, the case in which the patterning device includes a number of curved sections extending from its centre to its periphery.
  • the invention thus provides a simple means of guiding a missile along the beam. It is not necessary to use a roll reference gyroscope in the missile and this allows a veiy high launch acceleration to be used without danger of damage to the gyro or of causing it to develop excessive drift.
  • the modulation of the detected signal is frequency or phase modulation, the system is insensitive to all effects producing only amplitude modulation of the radiation, such as atmospheric and smoke attenuation and variation of distance between the missile and the beam projector.
  • FIGURE 1 illustrates the missile in the radiation pattern
  • FIGURE 2 projector
  • FIGURE 3 is a block diagram of the missile flight control system
  • FIGURE 4 shows a simple form of actuator for the missile elevators.
  • FIGURE 1 there is shown a missile 1 travelling into the plane of the paper and a beam axis 2 towards which the missile is to be deflected.
  • the beam of flight along which the missile is to be steered towards the target is assumed to have its axis perpendicular to the plane of the paper.
  • This beam is split by a rotating pattern device into a large number of sectors, of which only about one half are shown in the drawing, which rotate about the beam axis at a constant frequency. It will be seen that the missile is offset with res ect to the beam axis in this example on the side on which the sectors have been shown.
  • the missile carries two arms 5a and 5b which have at their ends a light-sensitive detector 3 and a balance weight 4 respectively. It is also provided with fins 6 and 7 which turn about an axis transverse to the longitudinal axis of the missile and thereby control the flight path of the missile. The movements of the fins to control the deflection of the missile towards the beam axis are superimposed on equal and opposite standing fin angles which produce a rotation of the missile about its axis. In the example shown in FIGURE 1 the rotations of the sector pattern and the missile are both clockwise.
  • the detector Since the missile is offset with respect to the beam axis, the detector will find itself moving in the same direction as the portion of the sector pattern in which it is located as it traverses the outer portion of the pattern and in the opposite direction as it traverses the portion of the pattern which is nearer to the beam axis. Consequently, the number of sectors of light through which the detector 3 passes in a given period is less while the detector is traversing the outer side of the beam than when moving through the portion of the beam which is nearer to the beam axis. As a result, the output of the detector 3 is modulated in frequency and phase.
  • the missile includes a control unit containing circuits which convert the modulated signal from the detector into a waveform which, after amplification, controls the movement of the fins 6 and 7. As the missile is spinning about its own axis these fins must be given an oscillatory movement at the frequency of rotation of the missile in order to steer the missile towards the beam axis and this frequency is also the frequency at which the output of the detector 3 is frequency modulated.
  • the sector projector is shown diagrammatically in FIGURE 2, in which radiation from a source contained in a projector casing 11 passes through a sector mask 12 driven by a motor 13 and falls on a lens 14.
  • the rotating sector mask acts to divide the light into sectors which rotate about the axis of the beam.
  • the signal from the radiation detector 3 passes through an amplifier 15 to a limiter and frequency modulation detector circui- 16. If the missile path is not on the axis of the rotating beam, the lightsensitive detector will produce a signal of varying fre quency and the frequency modulation detector 16 will generate a corresponding amplitude-varying signal for the actuation of the fins 6 and 7 to superimpose oscillatory angular movements on to the standing angles of the fins to cause translation of the missile towards the pattern axis.
  • the direction of movement of the missile depends on the phase relationship between the oscillatory angular movements and the rotation of the missile about its own axis and therefore the phase relationship between the signals generated by the light-sensitive detector and the rotation of the missile.
  • the frequency of the out put of the light-sensitive detector 3 will be a maximum as it crosses a line joining the missile axis and the beam axis, between these two axes, and a minimum at a point 180 distant from this; the frequency modulation detector will consequently generate maximum signals of opposite polarities corresponding to the passage of the light-sensitive detector 3 through these two points.
  • the standing angle of incidence of fin 6 is increased and that of fin 7 is reduced and for the other half the standing angle of incidence of fin 7 is increased and that of fin 6 is reduced.
  • the signals from the detector are already varying at the required frequency of oscillation of the fins and that once a suitable phase relationship is obtained between the fin oscillatory movement and the waveform of the same frequency at the output of the frequency modulator detector, the phase of the waveform is automatically correct for ensuring that wherever the missile is located in the pattern the corresponding oscillatory movement of the fins will deflect the missile towards the beam axis.
  • the signals from the frequency modulation detector 16 are therefore simply passed through an amplifier 17 to an actuator unit 18 for angularly adjusting the fins.
  • FIGURE 4 A simple form of fin actuator is shown in FIGURE 4.
  • the fins 6 and 7 are attached to a crankshaft 21 at standing angles which will provide the required missile rotation.
  • a solenoid 19 causes an armature 29 to oscillate in a cyclic manner, causing a corresponding turning movement of the crankshaft 21. In turn this causes cyclically varying angular movement of the fins 6 and 7, adding to the standing angle of one and subtracting from that of the other in opposite half-cycles.
  • the solenoid 19 When the solenoid 19 is de-energised the return spring causes the cranked shaft and the fins to return to their original position which is determined by the stop 22.
  • Phasing errors resulting from time delays in the control unit or fin actuators can be corrected by rotating the axes of fins 6 and 7 about the missile axis relative to the original position perpendicular to a line joining the lightsensitive detector 3 and the counterweight 4.
  • the frequency modulation of the guidance signal depends only on the distance of the missile from the guidance axis and is independent of the distance of the missile down the beam from the projector.
  • the invention can be applied, for example, to a projectile of the apelooka kind.
  • the arms 5a and 5b and the fins 6 and 7 fold away within the body contour for launching but pivot outwards as soon as the projectile has left the launching tube.
  • the sector pattern rotates with an angular velocity greater than that of the missile.
  • the sector velocity is 60 revolutions per second and the missile angular velocity 15 revolutions per second.
  • the beam is split into 50 sectors.
  • the guidance scheme described above will also operate if the angular velocity of the missile is greater than that of the sector pattern, and/or if the missile rotates in the opposite direction to the sector pattern.
  • a short range missile including: flight path controls adjusted to rotate the missile about its axis during flight; a detector which is responsive to infrared, visible or ultraviolet radiation and which is mounted on the missile offset with respect to its axis of rotation so that when the missile is flying in a rotating pattern of radiation and is offset with respect to the axis of rotation of the pattern the detector output will include a frequency modulated component; and means responsive to the frequency modulation of the detector output and arranged to additionally adjust the flight path controls in response to the frequency modulation for steering the missile towards the pattern axis.
  • a missile guidance system for guiding a missile having flight path controls and means for rotating the missile about its axis during flight, the system including: a pro jector external to the missile for aiming a beam of infrared, visible or ultra-violet radiation at the target and a rotary pattern device for splitting the beam cross-section into sectors and for rotating the sector pattern; a detector responsive to the radiation which is mounted on the missile offset with respect to the missile; and means receiving the detector output and responsive to the frequency modulation of the latter resulting from the rotations of the sector pattern and the detector to adjust the flight path controls in response to the frequency modulation and thereby to steer the missile towards the beam axis.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US695278A 1963-12-12 1968-01-02 Rotating beam missile guidance system Expired - Lifetime US3501113A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB49227/63A GB1164272A (en) 1963-12-12 1963-12-12 Improvements in Guidance Systems for Projectiles or Missiles.

Publications (1)

Publication Number Publication Date
US3501113A true US3501113A (en) 1970-03-17

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ID=10451612

Family Applications (1)

Application Number Title Priority Date Filing Date
US695278A Expired - Lifetime US3501113A (en) 1963-12-12 1968-01-02 Rotating beam missile guidance system

Country Status (3)

Country Link
US (1) US3501113A (enrdf_load_stackoverflow)
FR (1) FR1587315A (enrdf_load_stackoverflow)
GB (1) GB1164272A (enrdf_load_stackoverflow)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4195799A (en) * 1975-12-29 1980-04-01 Fuji Jukogyo Kabushiki Kaisha System for guiding flying vehicles with light beam
US4243187A (en) * 1978-05-01 1981-01-06 Mcdonnell Douglas Corporation Missile director with beam axis shift capability
US4299360A (en) * 1979-01-30 1981-11-10 Martin Marietta Corporation Beamrider guidance technique using digital FM coding
US4300736A (en) * 1979-08-17 1981-11-17 Raytheon Company Fire control system
US4399961A (en) * 1981-04-27 1983-08-23 The United States Of America As Represented By The Secretary Of The Army Tone burst reticle beamrider missile guidance
US4696441A (en) * 1986-05-06 1987-09-29 The United States Of America As Represented By The Secretary Of The Army Missile referenced beamrider
US5259568A (en) * 1984-01-17 1993-11-09 Werkzeugmaschinenfabrik Oerlikon-Buehrle Ag Command optics
US5348249A (en) * 1993-01-11 1994-09-20 Hughes Missile Systems Company Retro reflection guidance and control apparatus and method
US5533692A (en) * 1979-01-30 1996-07-09 Oerlikon-Contraves Ag Beamrider guidance system using digital phase modulation encoding
US5848763A (en) * 1997-09-03 1998-12-15 The United States Of America As Represented By The Secretary Of The Army Retro-encoded missile guidance system
EP2128555A3 (de) * 2008-01-18 2010-02-17 Diehl BGT Defence GmbH & Co.KG Verfahren zur Ermittlung der Rollwinkellage eines rotierenden Flugkörpers
US20120292432A1 (en) * 2010-01-15 2012-11-22 Jens Seidensticker Method for correcting the trajectory of a projectile, in particular of a terminal phase-guided projectile, and projectile for carrying out the method

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2404942A (en) * 1940-11-06 1946-07-30 Rca Corp Steering device
US3255984A (en) * 1963-06-13 1966-06-14 Sanders Associates Inc Beam riding guidance system

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2404942A (en) * 1940-11-06 1946-07-30 Rca Corp Steering device
US3255984A (en) * 1963-06-13 1966-06-14 Sanders Associates Inc Beam riding guidance system

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4195799A (en) * 1975-12-29 1980-04-01 Fuji Jukogyo Kabushiki Kaisha System for guiding flying vehicles with light beam
US4330099A (en) * 1975-12-29 1982-05-18 Fuji Jukogyo Kabushiki Kaisha System for guiding flying vehicles with light beam
US4243187A (en) * 1978-05-01 1981-01-06 Mcdonnell Douglas Corporation Missile director with beam axis shift capability
US5533692A (en) * 1979-01-30 1996-07-09 Oerlikon-Contraves Ag Beamrider guidance system using digital phase modulation encoding
US4299360A (en) * 1979-01-30 1981-11-10 Martin Marietta Corporation Beamrider guidance technique using digital FM coding
US4300736A (en) * 1979-08-17 1981-11-17 Raytheon Company Fire control system
US4399961A (en) * 1981-04-27 1983-08-23 The United States Of America As Represented By The Secretary Of The Army Tone burst reticle beamrider missile guidance
US5259568A (en) * 1984-01-17 1993-11-09 Werkzeugmaschinenfabrik Oerlikon-Buehrle Ag Command optics
US4696441A (en) * 1986-05-06 1987-09-29 The United States Of America As Represented By The Secretary Of The Army Missile referenced beamrider
US5348249A (en) * 1993-01-11 1994-09-20 Hughes Missile Systems Company Retro reflection guidance and control apparatus and method
US5848763A (en) * 1997-09-03 1998-12-15 The United States Of America As Represented By The Secretary Of The Army Retro-encoded missile guidance system
EP2128555A3 (de) * 2008-01-18 2010-02-17 Diehl BGT Defence GmbH & Co.KG Verfahren zur Ermittlung der Rollwinkellage eines rotierenden Flugkörpers
US20120292432A1 (en) * 2010-01-15 2012-11-22 Jens Seidensticker Method for correcting the trajectory of a projectile, in particular of a terminal phase-guided projectile, and projectile for carrying out the method
US8558151B2 (en) * 2010-01-15 2013-10-15 Rheinmetall Air Defence Ag Method for correcting the trajectory of a projectile, in particular of a terminal phase-guided projectile, and projectile for carrying out the method

Also Published As

Publication number Publication date
DE1431217A1 (de) 1970-04-09
DE1431217B2 (de) 1973-01-25
GB1164272A (en) 1969-09-17
FR1587315A (enrdf_load_stackoverflow) 1970-03-20

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Owner name: BRITISH AEROSPACE PUBLIC LIMITED COMPANY, DISTRICT

Free format text: CHANGE OF NAME;ASSIGNOR:BRITISH AEROSPACE LIMITED;REEL/FRAME:004080/0820

Effective date: 19820106

Owner name: BRITISH AEROSPACE PUBLIC LIMITED COMPANY

Free format text: CHANGE OF NAME;ASSIGNOR:BRITISH AEROSPACE LIMITED;REEL/FRAME:004080/0820

Effective date: 19820106

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Owner name: BAC AND BRITISH AEROSPACE, BROOKLANDS RD., WEYBRID

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:BRITISH AIRCRAFT CORPORATION LIMITED,;REEL/FRAME:003957/0227

Effective date: 19811218