US2931300A - Radiant-energy projectile detonating system - Google Patents

Radiant-energy projectile detonating system Download PDF

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Publication number
US2931300A
US2931300A US767450A US76745047A US2931300A US 2931300 A US2931300 A US 2931300A US 767450 A US767450 A US 767450A US 76745047 A US76745047 A US 76745047A US 2931300 A US2931300 A US 2931300A
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United States
Prior art keywords
aerial
energy
valve
radiant
translator
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Expired - Lifetime
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US767450A
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English (en)
Inventor
Lord William Burton Housley
Tomlin George Maurice
Turner Henry Cobden
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C13/00—Proximity fuzes; Fuzes for remote detonation
    • F42C13/04—Proximity fuzes; Fuzes for remote detonation operated by radio waves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/12—Primers; Detonators electric
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S11/00—Systems for determining distance or velocity not using reflection or reradiation
    • G01S11/02—Systems for determining distance or velocity not using reflection or reradiation using radio waves
    • G01S11/023—Systems for determining distance or velocity not using reflection or reradiation using radio waves using impedance elements varying with distance

Definitions

  • one object of the invention is to provide an antiaircraft shell or rocket, the detonation of which is effected upon the approach of the shell or rocket to a target, so that a so-called proximity burst is achieved.
  • a second object of the invention is to provide a fusing means for an aerial bomb, torpedo, mortar shell or the like whereby the bomb, shell or the like is arranged to burst prior to impact with a target to achieve a maximum blast and/or fragmentation effect in the target area.
  • the signal radiated from the aerial which is preferably a half wave aerial
  • the aerial'from a body of sufficient electrical conductivity when the distance between the aerial and the body is half or multiples of a half wave length of the emitted radiation, approximately 180 out of phase.
  • the emitted signal and the received phase-displaced signal cause two-of-phase currents to build up on the aerial.
  • the effective aerial impedance rises rapidly to a peak as in a resonance circuit, the vector sum of the current flowing in the ity of the reflector and to a lesser extent on the other physical characteristics of the reflector.
  • An object of the present invention is to utilize the phenomenon of thechange of effective impedance for controlling purposes for projectiles.
  • means for controlling the detonation and/ or release of a projectile comprise in combination an aerial system adapted to rad1ate to change of effective impedance of said aerial system a signal from a suitable oscillator and means responsive Patented Apr. 5, 1960 ice due to receipt of reflected radiation thereon, adapted to exert the desired control.
  • the means responsive to change of effective aerial impedance are made variably critical in response in such manner that the control effected thereby is dependent on a critical distance between the aerial and the reflecting body.
  • means for controlling detonation and/or release of a projectile comprise in combination an aerial system adapted to radiate a modulated signal from a suitable oscillator and demodulating and amplifying means, responsive to change of effective aerial impedance clue to receipt of modulated reflected radiation thereon, adapted to exert or effect the desired control.
  • means for controlling the detonation and/or release of a projectile comprise in combination at least two aerial systems each adapted to radiate signals from separate oscillators and to receive radiation reflected by a distant reflector, the wave length of the radiation from said oscillators being different submultiples of a predetermined value, amplifying circuits connected to said oscillators to amplify changes of effective aerial impedance due to receipt of reflected radiation on the respective aerial systerms, the circuits being so interconnected that a control may be effected only at specific distances between the aerial systems and the reflector.
  • Fig. 1 is a schematic circuit diagram of a radiant-energy projectile detonating system embodying the present invention in a particular form
  • Figs. 2 and 3 are schematic circuit diagrams representing modified forms of the invention.
  • valve V is connected in a Hartley oscillator circuit, which may oscillate at any frequency between 10 and 600 megacycles and a half or quarter wave aerial A is tightly coupled to the oscillating circuit so that substantially maximum power is dissipated therefrom.
  • the valve V is supplied from a volt high-tension battery B the cathode of the valve V being connected to the battery B, through a resistance R
  • the valves V and V constitute a DC. amplifier the grids of which are connected through a bias battery B to the cathode of the valve V and the anodes of which are connected through the winding of a relay R the energization of which effects a desired control such as the arming of a projectile by any of various well-understood procedures, for example by actuating a solenoid operated detonating plunger.
  • the cathodes of the valves V and V are supplied from an individual battery B and are directly connected at one end to a tapping of the resistance R If now the aerial approaches or is approached by a reflector, as the distance between the reflector and the aerial becomes a multiple of the half Wave length of the transmitted signal then as mentioned above, the effective impedance of the aerial rises rapidly, consequently the oscillator anode current also increases rapidly. Accordingly the voltage drop across the resistance R increases; the filaments of the valves V and V then assume an increased negative potential with respect to the grids, of these valves causing a large increase of current through these valves.
  • the effect is enhanced in that the increase of anode current through the valves V and V and that part of the resistance R; between the tap and the negative end of the battery B increases the voltage drop over the said part of the resistance R Consequently, an initial relatively small change in the anode current of the valve V will cause a relatively large change in the anode current of the valves V V
  • the relay having the winding R in series with the anodes of the valves V and V can be made to close at any suitable current value to effect the desired control.
  • the effective change of impedance of the aerial is reduced with increase of the distance between aerial and reflector; accordingly the relay can be made critical in operation at any predetermined distance in half wave lengths between aerial and reflecting body by an adjustment of the battery B Alternatively, the wave length of the signal can be made relatively so long that the relay operates when the distance between aerial and reflector is one-half wave length.
  • valve V may be replaced by a gas or vapour filled relay device.
  • the wave length of the radiated wave-signal energy is small with relation to the distance between the aerial and the reflector, continuous relative movement of the reflector and aerial toward or away from one another produces cyclic changes of the aerial impedance between maximum and minimum values.
  • the period of this cyclic change of the aerial impedance varies with the velocity at which the aerial and reflector approach toward or recede from one another.
  • the device R in the anode circuit of the valves may be of a. type adapted to indicate the frequency of the amplified potential and may be calibrated in terms of the velocity of relative movement between the aerial and reflector.
  • V is an oscillator valve oscillating at a frequency such that the wave length is a multiple or submultiple of the distance or distances at which control is to be effected or some fraction such as half, twice, etc. of the distance.
  • V is a low-frequency oscillator valve oscillating at some audio frequency such as 1,000 cycles per second.
  • the signal from the valve V is caused to modulate the highfrequency oscillator V the system shown being Heising modulation although any other type can be employed.
  • the valve V is an anode bend rectifier connected so as to measure the high-frequency voltage between the aerial and the earth.
  • the valve V is a low-frequency amplifying valve which can be either a triode or multi-electrode valve connected so as to amplify the signal from the valve V
  • the reflected signal from the earth or other object, proximity to which is to cause the desired control causes a change in high-frequency voltage on the aerial and this change causes a change in voltage applied to the grid of the valve V
  • the valve V rectifies the high-frequency voltage and produces a low-frequency signal as the result of the rectification in the anode circuit.
  • a change in voltage from the original voltage impressed on the valve V is amplified by the valve V and the desired control may be effected by relay means connected in the anode circuit of the valve V
  • the fact that the control is excited by means utilizing an audiofrequency signal ensures that the amplification used may be quite as high as is necessary, and gains of 20,000 are easily possible.
  • V is an oscillator valve oscillating at such a frequency that the half wave length is some fraction of the distance at which control is to be effected.
  • V is a triode rectifying valve with a meter in the anode circuit whereby a measure of the high-frequency voltage developed between the aerial and the chassis may be obtained for test purposes,
  • V is a low-frequency amplifying valve connected as a DC. amplifier.
  • V is a further oscillator valve oscillating at such a frequency that the half wave length is some fraction of the distance at which control is to be effected, this fraction being different from that applying to V V is a triode valve connected similarly to the triode V and the valve V is a further low-frequency amplifying valve connected as a DC. amplifier.
  • the voltage developed across the anode load of the valve V is applied as bias to the grid of the valve V
  • the reflected signals from the object cause changes in high-frequency voltages on the aerials connected to the valve V and V
  • This causes changes in the DC. voltage applied to the grid of the valve V and corresponding variations in the anode current of this valve.
  • a controlling unit in accordance with the invention is incorporated in a shell or rocket to ensure detonation of the shell or rocket in the proximity of a target.
  • the said target may be airborne, seaborne or on the ground.
  • the invention is, however, particularly applicable as a means for controlling the detonation of an antiaircraft shell or rocket in the proximity of an airborne target.
  • the unit may be arranged in the bomb or torpedo in place of the normal impact detonator in such a manner that the bomb will be exploded prior dissemination, will be a maximum.
  • the controlling device in accordance with the invention can be housed in the finned tail casing of the bomb.
  • the aerial system may then be constituted by short rods arranged for transport between opposite fins of the bomb' tail adapted, after release of the bomb to be moved, for example by spinner means, into operative positions at right angles to the bomb.
  • the body and/or the tail unit and/ or the nose assembly of the bomb, shell, rocket or the like may constitute the aerial system.
  • apparatus in accordance with the invention may be employed for control of the release and/ or detonation of a torpedo from a torpedo-carrying aircraft.
  • a device in accordance with the invention is provided in a torpedo-carrying aircraft to control the release of a torpedo
  • the arrangement is such that the pilot of the aircraft having preset the height above the sea at which the torpedo is to be launched has then only to bring his aircraft in the correct attitude toward the sea and, at the critical distance, the torpedo is released.
  • a radiant-energy projectile detonating system comprising, means including a radiant-signal translator for generating wave-signal energy and for radiating said energy to a remote object which returns to said translator radiant energy having a frequency approximately equal to that of said first-mentioned radiant energy, said translator and said object having during operation of said system relative movement effecting a change of phase between the wave-signal energy radiated and received by said translator whereby the impedance of said translator varies with said movement, means effectively responsive to variations of impedance of said translator for deriving a control effect, and a projectile detonating arrangement responsive to said control effect for detonating a projectile.
  • a radiant-energy projectile detonating system comprising, an oscillator for generating wave-signal energy, an antenna relatively tightly coupled to said oscillator for radiating said energy therefrom to a remote object which returns to said antenna radiant energy having a frequency approximately equal to that of said first-mentioned radiant energy, said antenna and said object having during operation of said system relative movement effecting a change of phase between the wave-signal energy radiated and received by said antenna whereby the impedance of said antenna varies with said movement, means effectively responsive to variations of impedance of said antenna for deriving a control effect, and a projectile detonating arrangement responsive to said control etfect for detonating a projectile.
  • a radiant-energy projectile detonating system comprising, a vacuum-tube oscillator for generating wavesignal energy, an antenna relatively tightly coupled to said oscillator for radiating said energy therefrom to a remote object which returns to said antenna radiant energy having a frequency approximately equal to that of said firstmentioned radiant energy, said antenna and said object having during operation of said system relative movement effecting a change of phase between the wave-signal energy radiated and received by said antenna whereby the impedance of said antenna and thereby the space current of said oscillator vary with said movement, a resistor included in the space-current energising circuit 6 of said oscillator to derive from the space current thereof a control voltage, and a projectile detonating arrangement including a relay device responsive to said control voltage for detonating a projectile.
  • a radiant-energy projectile detonating system comprising, means including a radiant-signal translator for generating wave-signal energy and for radiating said energy to a remote object which returns to said translator radiant energy having a frequency approximately equal to that of said first-mentioned radiant energy, said translator and said object having during operation of said system relative movement toward one another to effect a change of phase between the wave-signal energy radiated and received by said translator whereby the impedance of said translator varies with said movement, means effectively responsive to variations of impedance of said translator for deriving a control effect having a magnitude increasing with said movement, and a projectile detonating arrangement responsive to a predetermined value of the increasing magnitude of said control effect for detonating a projectile.
  • a radiant-energy projectile detonating system comprising, a source of modulation signals, means including a radiant-signel translator for generating wave-signal energy modulated by the signal of said source and for radiating said energy to a remote object which returns to said translator correspondingly modulated radiant energy having a frequency approximately equal to that of said first-mentioned radiant energy, said translator and said object having during operation of said system relative movement effecting a change of phase between the wave-signal energy radiated and received by said translator whereby the impedance of said translator and the intensity of energy radiated thereby vary with said movement, means for deriving the modulation components of the wavesignal energy applied to said translator to derive a control effect, and a projectile detonating arrangement responsive to said control effect for detonating a projectile.
  • a radiant-energy projectile detonating system comprising, means including a radiant-energy translator for generating wave-signal energy and for radiating said energy to a remote object which returns to said translator radiant energy having a frequency approximately equal to that of said first-mentioned radiant energy, said translator and said object having during operation of said system relative movement toward one another to effect a change of phase between the wave-signal energy radiated and received by said translator whereby the impedance of said translator varies with said movement, means effectively responsive to variations of impedance of said translator for deriving a control effect having a magnitude increasing with said movement, and a projectile detonating arrangement having a critical response to said control effect for effecting at a critical distance between said translator and said object a control which detonates a projectile.
  • a radiant-energy projectile detonating system comprising: a pair of wave-signal oscillators having individual antennas coupled thereto for generating and radiating individual wave-signal energies, of individual different frequencies, to a remote object which returns to said antennas radiant energy having frequencies approximately equal to those of said first-mentioned wave-signal energies; the wave lengths of said first-mentioned wave signals being different submultiples of a predetermined value and said antennas and said object having during operation of said system relative movement effecting a change of phase between the wave-signal energy radiated and received by each of said antennas whereby the impedance of said each antenna varies with said movement; means effectively responsive to variations of impedance of each of said antennas for deriving individual controls effects; and a projectile detonating arrangement responsive jointly to said control effects for effecting at predetermined distances between said antennas and said object detonation of a projectile.
  • a radiant-energy projectile detonating system comprising, a source of modulation of signals of relatively low frequency, means including a radiant-signal translator for generating higher frequency wave-signal energy modulated by the signal of said source and for radiating said modulated energy to a remote object which returns to said translator radiant energy having a frequency approximately equal to that of said first-mentioned radiant energy, said higher frequency Wave-signal energy having a wave length which is a multiple or submultiple of a distance between said radiant-signal translator and said object and said translator and object having during operation of said system relative movement efiecting a change of phase between the wave-signal energy radiated and received by said translator whereby the impedance ,of said translator varies with said movement, means coupled to said first-mentioned means for deriving the modulation components of the wave-signal energy applied to said translator to derive a control effect, and a projectile detonating arrangement including amplifying means responsive to said control elfect for detonating a projectile
  • control effect deriving means comprises a vacuum tube which includes a control electrode and is biased to provide anode-circuit rectification and in which there is applied to said control electrode of said vacuum tube a relatively large negative bias potential.
  • a radiant-energy projectile detonating system comprising, means including a radiant-signal translator for generating wave-signal energy and for radiating said energy to a remote object which returns to said translator radiant energy having a frequency approximately equal to that of said first-mentioned radiant energy, said translator and said object having during operation of said system relative movement toward one another eifecting a change of phase between the wave-signal energy radiated and received by said translator whereby the impedance of said translator varies with said movement, means efiectively responsive to variations in impedance of said translator for deriving a control potential, and a projectile detonating arrangement including a gas-filled electrondischarge device responsive to a critical value of said control potential corresponding to a critical distance between said translator and said object for providing an abrupt control to efiect the detonation of a projectile.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Geophysics And Detection Of Objects (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Aerials With Secondary Devices (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
US767450A 1940-06-11 1947-08-08 Radiant-energy projectile detonating system Expired - Lifetime US2931300A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB10153/40A GB585911A (en) 1940-06-11 1940-06-11 Improvements in and relating to electric relay and/or controlling systems

Publications (1)

Publication Number Publication Date
US2931300A true US2931300A (en) 1960-04-05

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US767450A Expired - Lifetime US2931300A (en) 1940-06-11 1947-08-08 Radiant-energy projectile detonating system

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US (1) US2931300A (fr)
BE (1) BE483740A (fr)
FR (1) FR952126A (fr)
GB (2) GB585911A (fr)
IT (1) IT454124A (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3327631A (en) * 1962-10-08 1967-06-27 Giannini Controls Corp Flight vehicle position sensing system
US3594792A (en) * 1967-10-11 1971-07-20 Emi Ltd Proximity sensing devices
US3913485A (en) * 1962-08-07 1975-10-21 Us Navy Active passive fuzing system
US4119039A (en) * 1961-05-29 1978-10-10 The United States Of America As Represented By The Secretary Of The Army Fuze system
US4185560A (en) * 1962-01-31 1980-01-29 Mayer Levine Fore and aft fuzing system
US6681700B1 (en) * 1970-07-31 2004-01-27 Alenia Marconi Systems Limited Capacitive fuses for missiles

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4195294A (en) * 1956-11-15 1980-03-25 The United States Of America As Represented By The Secretary Of The Navy Dual channel proximity fuze
US2992422A (en) * 1957-07-01 1961-07-11 Gen Mills Inc Method and system for determining miss distance
US4192245A (en) * 1958-05-14 1980-03-11 The United States Of America As Represented By The Secretary Of The Navy Guiding means for self-propelled torpedoes

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1756462A (en) * 1924-04-18 1930-04-29 Jenkins Charles Francis Altimeter
US1969537A (en) * 1928-11-17 1934-08-07 Gen Electric Method and means for determining altitude from aircraft
US1987587A (en) * 1928-01-16 1935-01-08 Rca Corp Electrical device and method of determining distances
US1987588A (en) * 1929-09-27 1935-01-08 Rca Corp Altimeter
US2022517A (en) * 1928-11-17 1935-11-26 Gen Electric Radio echo altimeter
US2248727A (en) * 1939-12-09 1941-07-08 Howard M Strobel Signaling system
US2259982A (en) * 1939-09-29 1941-10-21 Gen Electric Radio distance meter
US2279695A (en) * 1938-05-03 1942-04-14 Secretan Kenyon Electrical device for indicating or determining distances
US2403567A (en) * 1942-01-13 1946-07-09 Jr Nathaniel B Wales Electrically energized fuse
GB581911A (en) * 1942-10-07 1946-10-29 Cornelius Constantinus Vanderh Improvements in or relating to the winding of bobbin-spun artificial threads
US2505418A (en) * 1948-03-26 1950-04-25 Wood John Mfg Co Inc Hose reeling mechanism

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1756462A (en) * 1924-04-18 1930-04-29 Jenkins Charles Francis Altimeter
US1987587A (en) * 1928-01-16 1935-01-08 Rca Corp Electrical device and method of determining distances
US1969537A (en) * 1928-11-17 1934-08-07 Gen Electric Method and means for determining altitude from aircraft
US2022517A (en) * 1928-11-17 1935-11-26 Gen Electric Radio echo altimeter
US1987588A (en) * 1929-09-27 1935-01-08 Rca Corp Altimeter
US2279695A (en) * 1938-05-03 1942-04-14 Secretan Kenyon Electrical device for indicating or determining distances
US2259982A (en) * 1939-09-29 1941-10-21 Gen Electric Radio distance meter
US2248727A (en) * 1939-12-09 1941-07-08 Howard M Strobel Signaling system
US2403567A (en) * 1942-01-13 1946-07-09 Jr Nathaniel B Wales Electrically energized fuse
GB581911A (en) * 1942-10-07 1946-10-29 Cornelius Constantinus Vanderh Improvements in or relating to the winding of bobbin-spun artificial threads
US2505418A (en) * 1948-03-26 1950-04-25 Wood John Mfg Co Inc Hose reeling mechanism

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4119039A (en) * 1961-05-29 1978-10-10 The United States Of America As Represented By The Secretary Of The Army Fuze system
US4185560A (en) * 1962-01-31 1980-01-29 Mayer Levine Fore and aft fuzing system
US3913485A (en) * 1962-08-07 1975-10-21 Us Navy Active passive fuzing system
US3327631A (en) * 1962-10-08 1967-06-27 Giannini Controls Corp Flight vehicle position sensing system
US3594792A (en) * 1967-10-11 1971-07-20 Emi Ltd Proximity sensing devices
US6681700B1 (en) * 1970-07-31 2004-01-27 Alenia Marconi Systems Limited Capacitive fuses for missiles

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Publication number Publication date
FR952126A (fr) 1949-11-09
GB585911A (en) 1947-02-28
GB600351A (en) 1948-04-07
IT454124A (fr)
BE483740A (fr)

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