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Патент USA US3077608

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Feb.‘ 12., 1963
c. w. JACKLE
3,077,598
MARKER GENERATOR
Filed Oct- 29. 1959
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RECORDER
180°
270°
360°
90°
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FINDER
a
RECEIVER
b
C
INVENTOR.
CARL
W. JACKLE
3,7?,598
brats
i
Patented Feb. 12, 1963
2
1
The resultant signal from rotor 23 is coupled through
3,077,598
a peak detector and a wave shaping circuit comprising a
MARKER GENERATGR
crystal diode 27, a resistor 28, and a shunt capacitor 29
Carl W. Jackie, Willow Grove, Pa., assignor to the United
and applied across a load impedance comprising a resistor
States of America as represented by the Secretary of
31. The crystal detector in conjunction with the time
constant of the R-C network functions to pass only peak
amplitude signals as is known in the art.
in the illustrated embodiment of the invention there is
provided a reference pulse generator which comprises a
The invention described herein may be manufactured
cylindrical yoke member 32 supporting a permanent mag
and used by or for the Government of the United States
net 33 and mechanically coupled to shaft 24-. A pickup
of America for governmental purposes without the pay
coil 34- having one terminal thereof connected to ground
ment of any royalties thereon or therefor.
and the other terminal thereof connected to load resistor
The present invention relates to a marker generator and
31 is located closely adjacent to the path of rotation of
more particularly to a marker generator which in com 15 magnet 33 whereby a pulse is induced in pickup coil 34
bination with other elements may be utilized to monitor
once during each complete rotation of shaft 24.
the Navy
Filed Oct. 2%, 1959, Ser. No. 849,694
9 Claims. (Cl. 343-118)
(Granted under Title 35, US. Code (1952), see. 2&6)
the performance of airborne direction ?nding equipment
There is further shown in FIG. 1 a direction ?nder re
of the type wherein there is provided a radio or radar di
ceiver 35 having the input circuit thereof electrically cou
rection ?nder receiver coupled to a rotatable antenna.
pled to a rotatable antenna .36 which is mechanically cou
The marker generator of the present invention com 20 pled to shaft 25 for joint rotation with rotor 23 and mag
prises a synchro system including a synchro transmitter, a
net 33. The video or audio output signal from receiver
driven synchro control transformer, and wave shaping cir
35 is coupled through a clipper and wave shaping circuit
cuits, wherein a pulse is generated once during each revo
lution of the synchro control transformer rotor corre
comprising a crystal diode 37, a capacitor 38 and a choke I
3§ and applied to load resistor 31.
The signals appearing across load resistor 31 may if
transmitter rotor. There is further provided a reference
desired be coupled to a recorder ‘ill which preferably may
pulse generator including a driven element coupled to the
be of the magnetic tape type. Alternatively, or in addi
synchro control transformer rotor and to the rotatable
tion, the output signals appearing across resistor 31 may
antenna of the direction ?nder receiver for conjoint rota
be conventionally coupled to an oscilloscope (not shown)
tion, and means to terminate the marker generator, refer 30 or appropriately coupled to the display system of the direc
ence pulse generator, and direction ?nder receiver out
tion ?nder receiver.
put signals in a common load impedance, whereby the
The mode of operation of the present invention may
signals may be recorded or displayed on a common time
best be understood by reference to the waveforms of
base. The time displacement of the signals provides true
FIGS. 2a, 2b and 2c.
35
Each time rotor 23 assumes an angular position orthog
and relative bearing information.
It is therefore an object of the present invention to pro
onal to the angular position of rotor 13, maximum carrier
vide a system operable to monitor the operation of direc
signal is induced in rotor 23. The phase of the carrier
tion ?nding equipment.
signal induced in rotor 23 reverses each time the rotor
It is another object of the invention to provide a novel 40 rotates through an angular position coincident with the
marker generator particularly useful in a system of the
angular position of rotor 13. During alternate half revo
type described in the next preceding object.
lutions of rotor 23 the phase of the carrier signal cou
It is still another object of the present invention to pro
plcd directly thereto through resistor 26 will be in phase
vide a novel marker generator wherein a chain ‘of pulses
opposition to the carrier signal induced therein. Accord
is generated corresponding in time to the angular position
ingly, as may be seen by reference to FIG. 20, maximum
sponding in time to the angular position of the synchro 25
of a shaft.
carrier output signal will be provided by the synchro por
Other objects and many of the attendant advantages of
this invention will be readily appreciated as the same be
comes better understood by reference to the following de
tailed description when considered in connection with the 50
tion of the marker generator only once during each revo
lution of rotor 23. As may be seen by reference to FIG.
2b the peak detector and wave shaping circuits described
above convert the maximum carrier signals to a chain of
pulses, the time of occurrence of which varies in accord
ance with the angular position of rotor 13.
accompanying drawings wherein:
H6. 1 is a circuit diagram of an embodiment of the
invention, and
FIGS. 2a, 2b, and 2c depict illustrative waveforms oc
curring in the circuit of FIG. 1.
Referring now to FIG. 1, there is shown a marker gen
erator which comprises a synchro transmitter 11 provided
with a stator 12 and a rotor 13. Rotor 13 is electrically
The angular position of yoke 32 on shaft 24 may pref
erably be adjusted whereby a pulse is generated in coil
55 34 each time the axis of antenna 36 coincides with the
aircraft heading.
FIG. 2c depicts, from left to right, the reference (head
ing), marker generator (compass), and video (signal in
coupled to a pair of terminals 14, 16 to be energized by
tercept) pulses appearing across resistor 31 plotted on a
a carrier signal applied thereto and mechanically coupled 60 common time scale to indicate the time relationship
to an indicator 17 by an angularly positionable shaft 13.
therebetween.
In a contemplated use of the invention, the portions
In the illustrated embodiment of the invention, the
time displacement between the heading and compass
thus far described may comprise part of the compass sys
tem of an aircraft. Accordingly, in this embodiment of
pulses is proportional to the true heading of the aircraft;
the invention, rotor 13 is angularly positioned in accord 65 the time displacement between the heading and signal
intercept pulses is proportional to the relative bearing
ance with the true heading of the aircraft.
Stator 3.2 of synchro transmitter 11 is coupled to stator
of a radiating target with respect to the aircraft; and,
the time displacement between the compass and signal
22 of a synchro control transformer 21 which is provided
intercept pulses is proportional to the true bearing to
with a rotor 23 mechanically coupled by a shaft 2d to a
driven shaft 25 for continuous rotation.
70 the radiating target.
Obviously many modi?cations and variations of the
Rotors 13, 23 are connected in parallel by a resistor 2-6
present invention are possible in the light of the above
whereby a portion of the carrier signal applied to termi
teachings. It is therefore to be understood that within
nals 14, 16 is directly applied to rotor 23.
8,077,698
7
4
3
the scope- of the appended claims, the invention may be
practiced otherwise than as speci?cally described.
What is claimed is:
in parallel, a load impedance, a peak detector and wave
shaping circuit, and circuit means coupling the rotor
1. In an aircraft, a system operable to monitor the
peak detector and wave shaping circuit to said‘load im
pedance; a reference pulse generator coupled to said
performance of airborne‘ direction finding equipment
winding of said synchro control transformer through said
comprising: a direction ?nder receiver coupled to a ro
driven element operable to generate a pulse once during
tatable antenna operable to provide an intercept signal,
each rotation of said driven element; and circuit means
a heading pulse generator coupled to said antenna oper
. coupling said reference pulse to said load impedance.
able to generate a reference pulse at the time the axis of
6. The combination of claim 5 including recorder-display
the antenna is aligned withthe aircraft heading, a com 10 means coupled to be energized by the signals applied to
pass pulse generator coupled to the compass system of
said load impedance. ,
the aircraft operable to generate a pulse displaced in
7. In combination: a marker generator comprising a
time with respect to said reference pulse in accordance
pair of input terminals adapted to be coupled. to a source
with the true heading of the aircraft, a load impedance,
of carrier voltage, a synchro transmitter having a stator
circuit means coupling said reference and compass pulses 15 and having a rotor with the windings thereof coupled to
in common with the intercept signal from said receiver
said input terminals, means mechanically coupling said
' to said'load impedance, and'recorder-display means?couf
rotor to an angularly' positionable member, a- synchro con?
pled to be energized ‘by the signals applied to said load
trol transformer, having a rotor and having a stator with
impedance‘.
the windings thereof coupled to the stator windings of
2. The combination of claim 1 wherein said compass 20 said synchro transmitter, a rotatable driven element, means
pulse generator comprises: a pair of input terminals
adapted to ‘be coupled to a’ source of carrier voltage, a
synchro transmitter having a stator and having a rotor
with the windings thereof coupled to said input termi
mechanically coupling‘. said synchro control transformer
rotor to said driven element for continuous rotation, an
impedance coupling the windings of said rotors in parallel,
a load‘ impedance, a peak detector and wave shaping cir
nals, means mechanically coupling said rotor to the com 25 cuit, and‘ circuit means coupling the rotor Winding of
pass system of said aircraft, a synchro control trans
said synchro control transformer through said' peak de
former having a- rotor and having a stator with the wind
tector and wave shaping circuit to said load impedance;
ings thereof coupled to the stator windings of said syn‘
chro transmitter, a rotatable driven element mechanical
and a reference pulse generator comprising a cylindrical
yoke mechanically coupled to said driven element for
1y coupled to said antenna, means mechanically coupling 30 rotation therewith, a permanent magnet, supported at the
said- synchro control transformer rotor to said driven
element for continuous rotation with said antenna, an
impedance coupling the windings of said rotors in paral
periphery of said‘ yoke, a pickup coil mounted closely ad
jacent the path of rotation of said magnet, and circuit
means coupling said pickup coil to said load impedance.
lel, -a peak detector and wave shaping circuit, and cir
8. The combination of claim 7 including a recorder-dis
cuit means coupling the rotor winding of said synchro .35 play means coupled to be energized by the signals applied
control transformer through said peak detector and 'wave
to said load impedance.
'
shaping circuit to said load impedance.
9. In an aircraft, the combination comprising: a com
3. The combination of claim 2 wherein said heading
pass pulse' generator comprising a pair of ‘input terminals
pulse generator comprises: a cylindrical yoke member
adapted to be coupled to a source of carrier voltage, a
mechanically coupled to said driven element and sup 40 synchro transmitter having a stator and having a rotor
porting a permanent magnet at the periphery thereof,
with the windings thereof coupled to said input terminals,
‘and a pickup coil mounted closely adjacent the path of
means mechanically coupling said rotor to the compass
motion of said magnet and electrically coupled to said
system of said aircraft, a'synchro control transformer
load impedance.
having
a rotor and having a stator with the windings there
'4. A marker generator comprising: a pair of input 45 of coupled to the stator windings of said synchro trans
terminals adapted to ‘be coupled to a source of carrier
mitter, a rotatable driven element, means mechanically
voltage, a synchro transmitter having a stator and hav
coupling said synchro control transformer rotor to said
ing a rotor with the windings thereof coupled to said in
driven element for continuous rotation, an impedance
put terminals, means mechanically coupling said rotor
coupling the windings of said rotors in parallel, a load
to an angularly positionable member, a synchro control
impedance, a peak detector and wave shaping circuit,
transformer having a rotor and having a stator with the
and circuit means coupling the rotor winding of said
windings thereof coupled to the stator windings of said
synchro control transformer through said peak detector
synchro transmitter, a rotatable driven element, means
and Wave shaping circuit to said load impedance; at refer
mechanically coupling said synchro control transformer
ence pulse generator comprising a cylindrical yoke me
rotor to said driven element for continuous rotation, an 55 chanically coupled to said driven element for rotation
impedance coupling the windings of said rotors in paral
therewith, a permanent magnet supported at the periphery
lel, a load impedance, a peak detector and wave shaping
of said yoke, a pickup coil mounted closely adjacent the
circuit, and circuit means coupling the rotor winding of
path of motion of said magnet, and circuit means coupling
said synchro control transformer through. said peak de
said pickup coil to said load impedance; and recorder-dis
tector and wave shaping circuit to said load impedance. 60 play means coupled to be energized by the signals applied
5. In combination: a marker generator comprising a
to said load impedance.
pair of input terminals adapted to be coupled to a source
of carrier voltage, a synchro transmitter having a stator
References Cited in the tile of this patent
and having a rotor with the windings thereof coupled to
UNITED STATES PATENTS
said input terminals, means mechanically coupling said 65
rotor to an angularly positionable member, a synchro
2,624,043
Gerwin et al. ________ __ Dec. 30, 1952
control transformer having a rotor and having a stator
with the windings thereof coupled to the stator windings
of said synchro transmitter, a rotatable driven element,
means mechanically coupling said synchro control trans 70
2,688,130
2,907,029
2,953,020‘
Whitaker et al _________ .._ Aug. 31, 1954
O’Meara ct al _________ __ Sept. 29, 1959
Hunt ______________ __ Sept. 20, 1960
546,350
Canada ____________ __ Sept. 17, 1957
FOREIGN PATENTS
vformer rotor to said driven element for continuous rota
tion, an impedance coupling the windings of said rotors
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