close

Вход

Забыли?

вход по аккаунту

?

Патент USA US3046411

код для вставки
July 24, 1962
E. M. FELDMAN ET AL
3,046,401
AIRCRAFT VELOCITY RECORDING DEVICE
Filed Feb. 29, 1960
3 Sheets-Sheet 1
Fig. 1
BIAS
M?
517
5'
OSCILLATOR
SENSOR
=
42?
43
4a
46?
SENSOR
‘J
v
2
56;
P.S.N.
~
GENERATOR
Ps N
>
TRIGGER
~
GATE +_ COUNT ER
SWITCHING
MEANS
‘IS-‘1
A
SENSOR
'
44
1“
59')
TRIGGER
LL
14
53
'
'
GENERATOR
473
J
RESET
{49
BIAS
52
I
597 1
54
'
Hg. 5
.
'
=
' INVENTORS
EDWARD M. FELDMAN
DAVID
F. GOUL
l
July 24, 1962
E. M. FELDMAN ETAL
3,046,401
AIRCRAFT VELOCITY RECORDING DEVICE
Filed Feb. 29, 1960
3 Sheets-Sheet 2
37
H"
INVENTORS
EDWARD M. FELDMAN
DAVID F. GOULD
39
13
I
\\ \\\‘
\
‘
| 1 l | | I l mu unumu»v
AGENT
July 24, 1962
3,046,401
E. M. FELDMAN ET AL
AIRCRAFT VELOCITY RECORDING DEVICE
Filed Feb. 29, 1960
3 Sheets-Sheet 3
mi 891 STAR
OUTP
STOP
581
79,E
43
gm
INVENTORS
EDWARD M. FELDMAN
DAVID F. GOULDII
OUTP
/
United States Patent A”ice
1
'
>
3,046,401
Patented July 24, I962
2
3,046,461
AIRCRAFT VELOCITY RECORDING DEVICE
Edward M. Feldman, Baederwood, and David F.
Gould II, Newtown, Pa., as'signors to the United States
of America as represented by the Secretary of the Navy
Filed Feb. 29, 1960, Ser. No. 11,936
10 Claims. (Cl. 250—83.3)
(Granted under Title 35, US. Code (1952), see. 266)
when the ?elds of view thereof are obscured by a portion
of a landing aircraft, for example the nose cone thereof.
In night carrier operations the radiation detectors may be
energized by any convenient aircraft borne heat source
such as an incandescent lamp mounted on the nose cone of
the aircraft. According to an important feature of the
invention the con?guration of the radiation detectors is
such as to provide anarrow ?eld of view in the direction
of the path of-motion of the aircraft or other object.
The invention described herein may be manufactured 10 Means may be provided to align the sensors whereby the
and used by or for the Government of the United States
planes symmetrically passing through the ?elds of view
of America for governmental purposes Without the pay- ,
thereof are parallel and preferably transverse to the path
ment of any royalties thereon or therefor.
of motion of the object.
The present invention relates to a velocity recording de
It may be appreciated that the sensors emit a pulse when
vice and more particularly to an electronic velocity indicat
the ?elds of view thereof are pentrated by a moving ob
ing system which, while not limited thereto, is particularly
adapted to record the velocity of aircraft landing on a
ject.v The remainder of theillustrative embodiment, to
be brie?y described below, functions to determine the time
carrier.
In order to evaluate carrier arresting gear, aircraft per
interval between the occurrence of pulses from the sensors.
Since the sensors and the ?elds of view thereof are spaced
formance, and aircraft operational criteria, there exists 20 a known distance apart, the»velocity of the object may
a requirement for a system to determine and record the
engagement velocity of aircraft making carrier landings.
easily be computed.
'
The sensors may be connected by cable to high gain,
_ The system in order to meet the" above stated requirement
low noise ampli?ers. A portion of the output signals
must be capable of operating under conditions of adverse
from the ampli?ers may be coupled to the input circuits
weather, shock and vibration, and radiant energy or elec 25 of trigger generators while the output circuits thereof may
trical interference. To be useful the system must be easy
be coupled to the control input of an ‘electronic gating
to maintain, simple to operate, and must be capable of
circuit. A stable oscillator or other clock signal source
providing accurate and repeatable data at high data rates.
may be coupled to the signal input of the gating circuit
Known'systems such as Doppler radar, light systems,
and the output, signal therefrom may be applied to a
and high speed camera systems are de?cient in various re~ 30 counter having digital read-out. Appropriate reset means
spects particularly when utilized as above described.
may be provided for the counter if desired. In addi
Doppler radar systems are capable of providing reliable
tion, ithmay sometimes be desirable to provide shaping
performance at relatively high data rates, but are char
networks connected between the ampli?ers and the trigger
acterized by being complex, expensive, and relatively
generators in order to provide an input signal or more
difficult to maintain. Further, operational considerations 35 appropriate waveshape to the'trigger generators.
preclude the use of Doppler radar speci?cally and ex
It is therefore an object of the present invention to
elusive for the purpose described. Thus, the design
provide a simple, inexpensive, accurate, and reliable
parameters of the radar apparatus cannot feasibly be
velocity recording device that is easy to maintain and is
optimized in order to provide for ideal performance of
capable of operating under severe environmental condi
a speci?c function.
40 tions with little performance degradation.
Light systems require complex and expensive optics in
order to provide reliable performance with acceptable
It is a further and more speci?c object of the present
invention to provide a device of the character described
accuracy.
adapted to determine and record the velocity of landing
Such systems are particularly and adversely '
affected by errors in the alignment of the various com
aircraft.
ponents which make up the system. In addition, the per 45
It is a further and still more speci?c object of the present
formance of such systems is adversely affected by less
invention to provide a device of the character described
than ideal environmental conditions.
adapted to determine and record the engaging velocity
Camera systems of acceptable quality are complex, ex
of aircraft landing on a carrier.
pensive, and, like light systems, the performance thereof
degrades to an unacceptable degree when employed under
adverse environmental conditions. Further such systems
are not easily adapted for use in monitoring night carrier
operations.
'
Other objects and many of the attendant advantages
of this invention will be readily appreciated as the same
become better understood by reference to the following
detailed description when considered in connection with
the accompanying drawings wherein:
The present invention substantially overcomes the noted
FIG. 1 depicts symbolically a contemplated use of the
de?ciencies in the above discussed prior art and provides 55 invention;
a simple, reliable, and accurate velocity recording device
FIG. 2 is a view in elevation illustrating certain struc
that is characterized by being inexpensive to construct and
tural features of one embodiment of the invention;
simple to maintain and, in addition, provides a system the
FIG. 3 is a partial horizontal section taken along line
performance of which is little affected by the severe en
3-3 of FIG. 2;
’
. vironrnental conditions experienced, for example, in car 60
FIG. 4 is a simpli?ed view of a radiation detector which
rier operations.
may be employed in embodiments of the invention;
According to one embodiment of the invention there
FIG. 5 is a block diagram of an electrical system which
is provided one or more pairs of sensors, each compris
may be employed in practicing the invention; and
ing a radiation detector mounted with simple optics, spaced
FIG. 6 is ‘a detailed circuit diagram further illustrating
a known distance apart along the path of motion of the 65
portions of the electrical system shown in FIG. 5.
object the velocity of which is to be determined. For
Referring now to FIG. 1 of the drawings, there is shown
example, the sensors may be mounted at the edge of the
an aircraft symbolically represented by arrow 11 traversing
?ight deck of a carrier parallel to the center line of the
a ?ight path 12 preparing to land upon the ?ight deck 13
deck and adjacent the ?rst arresting cable. Preferably the
radiation detectors may have enhanced spectral response 70 of an aircraft carrier, further details of which are omitted
for simplicity. A pair of sensors 14, 16, indicated sym
in the infrared region whereby in day carrier operations
they may be energized by background sky radiation except
bolically in FIG. 1, are disposed along the edge of ?ight
3,046,401
4
deck 13 a known distance apart, parallel to center line 17
upon a target temporarily erected, for example, adjacent
thereof, and adjacent the ?rst arresting cable (not shown).
center line 17 of deck 13.
It is to be understood that detector 2.2 has previously
In order to avoid measuring errors consequent to
changes in the aspect of the landing aircraft it is desired
that the sensors be capable of operating when the ?elds
of view thereof are penetrated by the relatively small
area nose Icone portion of the landing aircraft or by a
radiant energy source mounted thereon. For this pur
pose sensors 14, 16 are each constructed to provide an
extremely narrow ?eld of view in the direction of the
?ight path of the aircraft as indicated in FIG. 1 by the
reference numerals 17, 18. The manner in which the
desired ?eld of view is obtained according to the inven
tion will be explained below.
I
'
According to a contemplated embodiment of the inven
tion sensors 14, 16 include radiation detectors having
maximum spectral response in the infrared region. The
performance of such detectors is adversely affected and
the detectors may become damaged when direct solar
radiation impinges thereon. Since at times the aircraft
carrier may need to be positioned whereby direct solar
radiation may impinge on sensors 14, 16 is may be de
sirable to provide a second pair of sensors 14’, 16' simi
been aligned whereby the long dimension of the sensitive
portion thereof is disposed symriietricaily with respect to
the axis of optical system 19, for example, in a substan
tially vertical position if the system is to be employed to
measure horizontal velocity components.
While only sensor 14 has been described, it is to be un
derstood that sensors 14’, 1%, and 16’ may be substantially
identical to sensor l4 and thus will not be speci?cs ly de
scribed.
Referring now to FIG. 5, which illustrates in block di
agram form an electrical system which may be employed
to practice the present invention, there is shown a switch
ing means 42 coupled to sensors 14, i4’, i6, and 16' to
permit selection of the desired sensor pair. The signals
from the selected sensor pair are coupled through switch
ing means 42 to a pair of low noise, high gain ampli?ers
43, Lid which include differentiating ‘means in the input cir“
cuits thereof for a purpose to be described below.
The circuit thus far described is shown in more detail
in FIG. 6 which will be later discusse 1.
larly disposed along the edge of ?ight deck 13‘ opposite
Pulse shaping networks 156, 47 may be coupled between
the output circuits of ampli?ers 43, 44 and the input cir
sensors 14, 16 and having ?elds of view as indicated by
cuits of trigger generators 48, 4-9 in order to provide an
reference numerals 17', 18»' in FIG. 1.
input signal of appropriate Waveshape to the trigger gen
Referring now to FIGS. 2 through 4, which together
illustrate certain structural features of one embodiment of
erators.
Trigger generators 48, 49 are provided ‘with bias cir
the invention, there is shown a sensor 14 comprising a
simple collimating optical system 19 threaded onto or 30 cuits comprising potentiometers Si, 52 and variable re
sistors 53, 54 in order to select the magnitude of the input
otherwise affixed to a ?anged cylindrical support member
signal ‘at which trigger generators 48, 49 will provide trig
21. A radiant energy detector generally indicated by the
reference numeral 22 is affixed as by screws to support
gering pulses. The trigger generators may comprise any
member 21 in the focal plane of optical system 19. As
best seen in FIG. 4, detector 22 includes adjacent layers
of gold or other conductive material 23, 24 adhered to
suitable circuit known to the prior art such as a Schmidt
nonconductive ?anged base portion 26 and separated by
an elongated photoconductive layer 27 which may, for
example, be lead sulphide which has a maximum spectral
The trigger pulses from trigger generators 48, 49 may
trigger circuit and will not therefore be described in de—
tail.
be coupled to the control input circuits of an electronic
, gating circuit 56 of any suitable type and theoutput sig
response to radiant energy having a wavelength between 40 nal from a stable oscillator 57 may be coupled to the sig
approximately .25 and 3.5 microns. The conductors of a
nal input circuit of gate 56.
A standard pulse or cycle counter 58 of the type which
coaxial cable 28 are connected to terminals 29‘, 31 which
provides a digital read-out is coupled to receive the gated
are soldered or otherwise conductively affixed to portions
23, 24 of detector 22. Terminals 29, 31 may be enclosed
output signal from ‘gate 56. Conventional manual or
automatic time delay reset means 59 may be provided in
by a protective cup-shaped member 32 and the sensor may
be mounted within a housing 33 in any suitable manner.
order to zero counter 58.
In the embodiment illustrated support member 21 is fas
tened by screws to housing 33.
By way of example, optical system 19‘ may have a focal
Referring now to FIG. 6, ‘which illustrates certain por
tions of the electrical system of FIG. 5 in more detail, it
may be seen that by operation of ‘manually operable switch
42 sensor pairs 14,16 or 14', in’ may be respectively
length of one inch and the sensitive area 27 of detector 22
may be % mm. by 12 mm. These dimensions will pro—
'vide a ?eld of view 1 foot by 30 feet at a distance of 55
feet. With proper bias the detector will provide a usable
output when one percent of the ?eld of view thereof is ob
scured in day operations. For night operations the energy
received from a 32 candlepower incandescent lamp will
provide more than adequate response.
The sensors are aligned whereby the planes which con
tain the optical axes and the long dimensions of the sensi—
tive elements thereof are parallel and preferably trans
verse to the ?ight path of the aircraft.
coupled through networks comprising capacitors '71, 71’
and resistors 72, 72’ to amplifier stages ‘7'3, 73' of ampli
?ers 43, 44.
The values of capacitors 71, 711' and resistors 72, 72-’
are chosen whereby the networks function as differentia
tors to prevent operation of the circuit in response to slow
moving objects or in response to random changes in am
bient radiation levels and to provide both a positive and
a negative pulse input to ampli?ers 43,
4 which in re
In order to permit alignment of sensor 14 in the ver~
sponse thereto provide corresponding ampli?ed positive
and negative output signals.
Ampli?er stages 73, 73’ provide low noise ampli?cation
tical plane, housing 33 may be journaled in a trunnion
member 31!- and may be held in an ‘adjusted position as by
ing as plates respectively coupled through resistors 74, 74'
a friction lock mechanism 36.
to a source of positive potential.
In a similar ‘manner, in
order to permit alignment of the sensor in a horizontal
plane, trunnion member 34 may be journaled in a base
member 37 and held in an adjusted position as by a fric
tion lock mechanism 38. Base member 37 in turn may
be bolted or otherwise securely fastened to a base plate
39 which may be welded to deck 13.
To facilitate the alignment procedure, a telescope 41
may be provided and secured ‘to housing 33 in any con
venient manner. Desired alignment of the sensor may
with moderate gain with the screen grids thereof function
It is to be understood that the con?guration of ampli?er
stages 73, ‘73’ has been selected since for carrier applica
tions of the present invention in order to avoid interfer
ence from adjacent radio or radar equipment or other
electrical systems it has been found desirable to provide
no ampli?cation at the situs of the sensors and to locate
the remainder of the system remotely from the sensors in
an area where adequate shielding can be provided. The
connection between the sensors and the remainder of the
easily be accomplished by sighting through telescope 41 75 system may be made by coaxial cables.
spanner
'
Continuing with the description of FIG. 6, it may be
D
In addition it is obvious that many modi?cations and
variations of the present invention are possible in the
light of the above teachings. It is therefore to be under
stood that within the scope of the appended claims, the
invention may be practiced otherwise than as speci?cally
seen that manually operable switch 42 functions also to
apply bias voltages to the photoconductive portions of the
selected sensor pair through resistors 75, 75’.
The output signals from ampli?er stages 73, 73' may be
coupled through networks comprising capacitors '76, 76’
and resistors 77, 77’ to high gain ampli?er stages comprsi
described.
v
What is claimed is:
ing pentodes 78, 7 ’ provided with plate resistors 79, '79’
1. A velocity recording device comprising: a pair of
coupled to 13+. The screen grids of pen-todes 78, 78’ are
sensors adapted to be spaced a known distance apart along
coupled respectively in a conventional manner to biasing 10 the path of motion of an object the velocity of which is
networks comprising resistors ‘dd, 81’ and capacitors S2,
S2’.
to be determined, each of said sensors comprising an op~
tical system, and a member having a planar surface in the
‘
The connections between ampli?ers 43, 44‘ and pulse
focal plane of said optical system, said member includ
shaping networks 46, '47 may be made by low impedance
ing an elongated radiant energy sensitive element sym
coaxial cables. Accordingly, to provide a low impedance 15 metrically disposed on said planar surface with respect to
output from ampli?ers 43,‘ 44, the output signals from am~
said optical axis; means to align said sensors whereby the
pli?er stages 78, 73' may be coupled through networks
planes which respectively contain the optical axis of a
comprising capacitors 83, 83’ and resistors 84, 84' to cath
sensor and the long dimension of the element thereof are
ode follower circuits com-prising parallel connected triode
parallel; differentiating means coupled to said elements;
sections 86, 87 and 86’, 87’ which are respectively pro
ampli?er means having the input circuit thereof coupled
vided with cathode resistors 88, 88’. It is to be under
to said dilferentiating means; trigger generating means
stood that the triode sections may be replaced by single
having the input circuit thereof coupled to the output cir
triodes of appropriate types.
cuit of said ampli?er means; a timing signal source; gat
Start and stop output terminals 89, 39' are respectively
ing circuit means having the input'circuits thereof respec
coupled to cathode resistors ‘88, 8%’ via coupling capaci 25 tively coupled to said timing signal source and to the out
tors 91, 91’ and to pulse shaping networks 46, 47.
put circuit of said trigger generating means; and counter
Having thus described an embodiment of the invention,
means having the input circuit thereof coupled to the out
the mode of operation thereof will now be set forth.
put circuit of said gating circuit means.
In day carrier operations the photoconductive portions
2. A velocityv recording device comprising: a pair of
of sensors 14, 16, or 14', 16', as the case may be, are 30 sensors adapted to be spaced a known distance apart along
' the path of motion of an object the velocity of which is to
of view of the sensors are successively obscured, for ex
be determined, each of said sensors comprising an optical
ample, by the nose cone of an aircraft, the resistances
system, and a member having a planar surface in the focal
energized by background sky radiation. When the ?elds
of the photoconductive portions thereof increase causing
positive pulses (in the circuit con?guration shown) to be
plane of said optical system, said member including an
successively coupled through differentiating networks 71,
spectral response to radiant energy having wavelengths be
tween approximately 0.25 and 3.5 microns symmetrically
disposed on said planar surface with respect to said opti
cal axis; means to align said sensors whereby the planes
elongated photoconductive element having enhanced
72, and 71’, 72’ to ampli?ers 43, 44. The ampli?ed and
shaped pulse outputs cause successive actuation of trig
ger generators 48, 49. The occurrence of a ‘trigger pulse
from trigger generator 48 opens gate 56 permitting signals 40 which respectively contain the optical axis of a sensor and
from stable oscillator 57 to be coupled to counter 58,
the long dimension of the element thereof are parallel;
while the occurrence of a pulse from trigger generator 49
differentiating means coupled to said elements; ampli
closes the gate isolating oscillator 57 from counter 58.
?er means having the input circuit thereof coupled to said
It is to be understood that trigger generators 48, 49‘ and
differentiating means; trigger generating means having the
gate 56 may be arranged to operate upon either positive
input circuit thereof coupled to the output circuit of said
or negative signals. By virtue of the operation of dif
ampli?er means; a timing signal source; gating circuit
ferentiating networks 71, 72, and 71', 72' both positive
and negative signals are supplied from ampli?ers 43, 44.
means having the input circuits thereof respectively
coupled to said timing signal source and to the output
The time interval between the occurrence of triggers
circuit of said trigger generating means; and counter means
from trigger generators 48, 49 is indicated by the number
having the input circuit thereof coupled to the output cir
of cycles which counter 58 receives from oscillator 57.
This value of multiples or submultiples'thereof is visibly
indicated indigital form by the counter.- By reference to
previously prepared tables, the operator may easily con
vert the cycle or pulse count thus displayed representing
the above-mentioned time interval into aircraft velocity.
Operation of reset means 59 prepares the system for
recording the velocity of the next landing aircraft,
The system functions to monitor night carrier opera
cuit of said gating circuit means.
3. A velocity recording device comprising: a pair of
sensors adapted to be spaced a known distance apart in a
direction parallel to the path of motion of an object the
velocity. of which is to be determined, each of said sensors
comprising an optical system, and a member having a
planar surface in the focal plane of said optical system,
said member including an elongated radiant energy sensi
tive element symmetrically disposed on said planar sur
tions in a similar manner. When the ?elds of view of the 60 face with respect to said optical axis; means to align each
selected sensor pair are successively penetrated by a nose
of said sensors whereby the planes which contain the axes
cone mounted incandescent lamp or other heat source the
of the optical portions thereof and the long dimensions
sensors emit successive negative pulses. Since the sys
of said elements are parallel to each other and transverse
tem is not polarity sensitive, the subsequent mode of op
to the path of motion of said object; differentiating means
eration thereof is as above described.
65 coupled to said elements; ampli?er means having the input
The high gain provided by, ampli?ers 43, .44 permits
circuit thereof coupled to said differentiating means; trig
ger generating means having the input circuit thereof
operation on- the initial portions of the signals obtained
respectively from-the sensors thus minimizing any errors
coupled to the output circuit of said ampli?er means; a
timing signal source; gating circuit means having the in
occasioned by dissimilarities in the waveshapes of the sig
nals.
70 put circuits thereof respectively coupled to said timing sig
While the invention has been described for use in
nal source and to the output circuit of said trigger generat
measuring and recording aircraft engagement velocities,
ing means; and counter means having the input circuit
many other uses are possible, for example, measuring cata
thereof coupled to the output circuit of said gating circuit
pult velocities and measuring missile or other vehicle
velocities.
'
means.
75
4. A velocity recording device comprising: a pair of
spas/rot
6
sensors adapted to be spaced a known distance apart in
a direction parallel to the path of motion of an object the
velocity of which is to be determined, each of said sensors
comprising an optical system, and a member having a
planar surface in the focal plane of said optical system,
said member including an elongated photoconductive ele
8
an aircraft landing on a carrier comprising: a ?rst pair
of sensors spaced a known distance apart along one edge
of the ?ight deck of said carrier parallel to the center
line of said deck adjacent an arresting gear cable thereon,
and a second pair of sensors similarly disposed along said
flight deck opposite from said ?rst pair of sensors, each
of said sensors comprising an optical system, and a mem
ment having enhanced spectral response to radiant energy
er ‘having a planar surface in the focal plane of said
having Wavelengths between approximately 0.25 and 3.5
optical system, said member including an elongated radi
microns symmetrically disposed on said planar surface
with respect to said optical axis; means to align each of 10 ant energy sensitive element symmetrically disposed on
said planar surface with respect to said optical axis; means
said sensors whereby the planes which contain the axes
to align each sensor pair whereby the planes which re
of the optical portions thereof and the long dimensions of
spectively contain the optical axis of ‘a sensor and the
said elements are parallel to each other and transverse to
long dimension of the element thereof are parallel and
the path of motion of said object; differentiating means
transverse to the center line of said deck; differentiating
coupled to said elements; ampli?er means having the in
means; ampli?er means having an input circuit coupled
put circuit thereof coupled to said differentiating means;
to said differentiating means; switching means operable
trigger generating means having the input circuit thereof
to selectively couple the elements of said ?rst or said
coupled to the output circuit of said ampli?er means; a
second pair of sensors to said differentiating means; trig
timing signal source; gating circuit means having the in
put circuits thereof respectively coupled to said timing 20 ger generating means having the input circuit thereof
coupled to the output circuit of said ampli?er means; a
signal source and to the output circuit of said trigger
timing signal source; gating circuit means having the
generating means; and counter means having the input
input circuits thereof coupled to said timing signal source
circuit threof coupled to the output circuit of said gating
and to the output circuit of said trigger generating means;
circuit means.
and counter means having the input circuit thereof cou
5. A velocity recording device comprising: a pair of
pled to the output circuit of said gating circuit means.
sensors adapted to be spaced a known distance apart in
8. A device for recording the engagement velocity of
a direction parallel to the path of motion of an object
an aircraft landing on a carrier comprising: a ?rst pair
the velocity of which is to be determined, each of said
of sensors spaced. a known distance apart along one edge
sensors comprising an optical system, and ‘a member hav
of the ?ight deck of sm'd carrier parallel to the center
ing a planar surface in the focal plane of said optical
line of said deck adjacent an arresting gear cable thereon,
system, said member including an elongated radiant energy
and a second pair of sensors similarly disposed along
sensitive element symmetrically disposed on said planar
said flight deck opposite from said ?rst pair of sensors,
surface with respect to said optical axis; means to align
each of said sensors comprising an optical system, and
each of said sensors whereby the planes which contain
a member having a planar surface in the focal plane
‘the axes of the optical portions thereof and the long di
of said optical system, said member including an elon
mensions of said elements are parallel to each other and
gated pho-toconductive element having enhanced spectral
transverse to the path of motion of said object; dif
response to radiant energy having wavelengths between
ferentiating means coupled to said elements; ampli?er
approximately 0.25 and 3.5 microns symmetrically dis
means having the input circuit thereof coupled to said
posed on said planar surface with respect to said optical
differentiating means; trigger generating means having
axis; means to align each sensor pair whereby the planes
the input circuit thereof coupled to the output circuit of
which respectively contain the optical axis of a sensor
said ampli?er means; an oscillator; gating circuit means
and the long dimension of the element thereof are par
having the input circuits thereof respectively coupled to
allel and transverse to the center line of said deck; dif
said oscillator and to the output circuit of said trigger
ferentiating means; ampli?er means having an input cir
generating means; a cycle counter providing digital read
cuit coupled to said differentiating means; switching
out and having the input circuits thereof coupled to the
means operable to selectively couple the elements of said
output circuit of said gating circuit means; and reset
means for said counter.
6. A velocity recording device comprising: a pair of
sensors adapted to be spaced a known distance ‘apart in
‘a direction parallel to the path of motion of an object
the velocity of which is to be determined, each of said
?rst or said second pair of sensors to said differentiating
means; trigger generating means having the input circuit
thereof coupled to the output circuit of said ampli?er
means; a timing signal source; gating circuit means hav
ing the input circuits thereof coupled to said timing signal
source and to the output circuit of said trigger generating
means; and counter means having the input circuit thereof
ing a planar surface in the focal plane of said optical
coupled to the output circuit of said gating circuit means.
system, said member including ‘an elongated photocon~
9. A device for recording the engagement velocity of
ductive element having enhanced spectral response to
an aircraft landing on a carrier comprising: a ?rst pair
radiant energy having wavelengths between approximately
of sensors spaced a known distance apart along one edge
0.25 and 3.5 microns symmetric-ally disposed on said
of the ?ight deck of said carrier parallel to the center
planar surface with respect to said optical axis; means
to align each of said sensors whereby the planes which 60 line of said deck adjacent an arresting gear cable thereon,
and a second pair of sensors ‘similarly disposed along
contain the ‘axes of the optical portions thereof and the
said flight deck opposite from said ?rst pair of sensors,
long dimensions of said elements are parallel to each
each of said sensors comprising an optical system, and
other and transverse to the path of motion of said object;
a member having a planar surface in the focal plane of
‘differentiating means coupled to said ‘elements; ampli?er
said optical system, said member including an elongated
means having the input circuit thereof coupled to said
radiant energy sensitive element symmetrically disposed
differentiating means; trigger generating means having the
on said planar surface with respect to said optical axis;
input circuit thereof coupled to the output circuit of said
sensors comprising an optical system, and a member hav
vampli?er means; an oscillator; gating circuit means having
the input circuits thereof respectively coupled to said
oscillator and to the output circuit of said trigger generat
ing means; a cycle counter providing digital read-out and
having the input circuit thereof coupled to the output cir
cuit of said gating circuit means; and reset means for said
counter.
7. A device for recording the engagement velocity of
means to align each sensor pair whereby the planes which
respectively contain the optical axis of a sensor and the
long dimension of the element thereof are parallel and
transverse to the center line of said deck; differentiating
means; ampli?er means having an input circuit coupled
to said ‘differentiating means; switching means operable
to selectively couple the elements ‘of said ?rst or said
second pair of sensors to said differentiating means; trig
3,046,401
ger generating means having the input circuit thereof
coupled to the output circuit of said ampli?er means; an
oscillator; gating circuit means having the input circuits
thereof respectively coupled'to said oscillator and to the
output circuit of said trigger generating means; a cycle
counter providing digital read-out and having the input
circuit thereof coupled to the output circuit of said gating
circuit means; and reset means for said counter.
10. A device for recording the engagement velocity of
10
which respectively contain the optical axis of a sensor
and the long dimension of the element thereof are par
allel and transverse to the center line of said deck; dif
ferentiating means; ampli?er means having an input cir
cuit coupled to said di?erentiating means; switching
means operable to selectively couple the elements of said
?rst or said second pair of sensors to said di?erentiating
means; trigger generating means having the input circuit
thereof coupled to the output circuit of said ampli?er
an aircra?t landing on a carrier comprising: a ?rst pair 10 means; an oscillator; gating circuit means having the input
of sensors spaced a known distance apart along one edge
of the ?ight deck of said carrier parallel to the center
line of said deck adjacent an ‘arresting gear cable thereon,
and a second pair of sensors similarly disposed along
circuits thereof respectively coupled to said oscillator and
to the output circuit of said nigger generating means; a
cycle counter providing 1digital read-out and having the
input circuit thereof coupled to the output circuit of said
said flight deck opposite from said ?rst pair of sensors, 15 gating circuit means; and reset means for said counter.
each of said sensors comprising an optical system, and
a member having a planar surface in the focal plane of
References Cited in the file of this patent
said optical system, said member including an elongated
UNITED STATES PATENTS
photoconductive element having enhanced spectral re
2,866,373
sponse to radiant energy having wavelengths between 20 2,918,581
approximately ‘0.25 and 3.5 microns symmetrically dis
2,944,151
posed on said planar surface with respect to said optical
2,975,284
axis; means to align each sensor pair whereby the planes
2,992,330
Doyle .et al ___________ __ Dec. 30,
Willey et a1 ___________ ___ Dec. 22,
Whitney et al ___________ ___ July 5,
Osborne _____________ _. Mar. 14,
Cooper et a1 ___________ __ July 11,
1958
1959
1960
1961
1961
Документ
Категория
Без категории
Просмотров
0
Размер файла
981 Кб
Теги
1/--страниц
Пожаловаться на содержимое документа