U.S. patent number 3,743,217 [Application Number 05/189,656] was granted by the patent office on 1973-07-03 for infrared control system for missile teleguiding.
This patent grant is currently assigned to Societe Anonyme de Telecommunications. Invention is credited to Jean Paul Turck.
United States Patent |
3,743,217 |
Turck |
July 3, 1973 |
INFRARED CONTROL SYSTEM FOR MISSILE TELEGUIDING
Abstract
A missile guidance system using a laser beam and comprising, in
a ground station, optical means having an optical axis for aiming
at said device; a laser beam transmitter and a laser beam receiver
having parallel axes, means for measuring the angular difference
between said optical and parallel axes, means for measuring other
angular differences defining the position of the missile with
respect to the transmitted laser beam; means for deducing from the
measurement of first-named angular difference tracking orders for
the missile; and means for deriving navigation control signals from
all said angular differences and for transmitting said control
signals to said missile via said transmitted laser beam.
Inventors: |
Turck; Jean Paul (Paris,
FR) |
Assignee: |
Societe Anonyme de
Telecommunications (Paris, FR)
|
Family
ID: |
9063125 |
Appl.
No.: |
05/189,656 |
Filed: |
October 15, 1971 |
Foreign Application Priority Data
|
|
|
|
|
Oct 22, 1970 [FR] |
|
|
7038163 |
|
Current U.S.
Class: |
244/3.16;
89/1.8 |
Current CPC
Class: |
F41G
7/303 (20130101); F41G 7/30 (20130101); G01S
17/66 (20130101) |
Current International
Class: |
F41G
7/20 (20060101); G01S 17/66 (20060101); F41G
7/30 (20060101); G01S 17/00 (20060101); F42b
007/00 (); F42b 015/10 (); F42b 007/18 () |
Field of
Search: |
;244/3.14,3.16 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Borchelt; Benjamin A.
Assistant Examiner: Webb; Thomas H.
Claims
What I claim is:
1. A teleguidance system for guiding a missile to a target by means
of a laser beam and comprising, in a ground station: means for
optically aiming at said target having an optical aiming axis; a
laser beam transmitter and a laser beam receiver having parallel
optical axes; means for measuring the angular difference between
said optical aiming axis and parallel axes, means for measuring
other angular differences defining the position of said missile
relatively to said optical axis of said transmitted laser beam;
means for deriving from the measurement of the first-mentioned
angular difference tracking orders for the missile, such orders
acting in the direction common to said parallel axes; and means for
deriving control signals from all such angular differences and for
transmitting such signals via said laser beam transmitter to
navigation control means provided on board the missile,
characterized in that said missile has a rear reflector which
reflects some of the light of said transmitted beam to said beam
receiver where such light is received by a photodetector (21); and
said beam transmitted by said transmitter is doubly modulated in a
modulator (11) energized by a generator (24) of permanent
modulating signals and by said photodetector (21) through a
processing circuit (26, 38) for preparing control signals, the
latter circuit being energized from said photodetector (21) and via
connections (27-30, FIG. 4) fed from said means for measuring the
angular difference between said aiming axis and parallel axes, so
that said control signal processing circuit (26, 38) fed from said
modulator (11) and connections (27-30) delivers to said modulator
(11) said control signals transmitted to said on-board navigation
control means.
2. A teleguidance system according to claim 1, characterized in
that an on-board photodetector carried by said missile energizes a
chain of electronic circuits comprising at least one decoder of the
modulation signals of the beam received by said photodetector, said
decoder energizing said on-board navigation means.
3. A teleguidance system according to claim 1, characterized in
that said processing circuit comprises a coder (38) converting
signals output by a computer (26) in analog form into digital
signals applied to said modulator (11); and said missile comprises
a further photodetector energizing a decoder converting into analog
signals the control signals received in digital form by said
further photodetector.
Description
This invention relates to a system for the guidance by remote
control of self-propelled missiles towards a target from a sighting
and firing station which also controls the missile path. For
instance, the missile can in a weapon system have an explosive
charge and be of use for attacking moving ground vehicles under the
control of a ground firing station.
In a prior art system of this kind, the missile control
instructions were deduced from the angular difference between the
sighting direction of the missile seen from the sighting station
and the direction from the aiming station to the target. To find
out this difference, means for locating the missile were placed
beside the aiming line of sight for the target, the axes of the
missile locator and of the target aiming device being kept parallel
to one another. The missile had at its rear tracers emitting an
infra-red radiation, and the missile locator had a lens which forms
at its focal point the image of the missile tracers on the
sensitive surface of a photodetector element. A light modulator was
disposed in the missile locator and having the form of a rotating
disk having equal and alternate transparent and opaque sectors, the
disk center sweeping a circular orbit around the infra-red optical
axis, modulates the infra-red beam received from the missile. The
photodetector element therefore delivered a frequency-modulated
alternating current whose frequency swing and phase (the phase
being defined as the time of appearance of the maximum or minimum
frequency relatively to an origin of the cycle) depend upon the
difference between the coordinates of the tracer-produced image and
the optical axis of the locator. Designating by b the angle between
the observer to missile direction and the observer to target
direction, an electronic circuit produced signals proportional to
cos.b and to sin.b respectively and these signals were
retransmitted electrically to the missile and acted on the
direction control elements thereof. A control loop extending from
the missile to the aiming station and back to the missile was
therefore provided which kept the missile on the target direction.
The U.S. Pat. specification No. 2.967.247 discloses the operation
of the light modulator. It is well known that the function of the
tracers is to increase the range of the teleguidance system by
increasing the contrast between the missile and its environment.
However, in some circumstances many very bright spots may appear in
the field of the teleguidance system, with the result of infra-red
dazzle and misses.
There are other problems connected with retransmission to the
missile of the ground signals prepared in dependence upon the
instantaneous value of the angular difference between the observer
to missile direction and the observer to target direction. If radio
waves are used, secrecy is sometimes unsatisfactory and the enemy
may effectively interfere. If conductive wires are attached to the
missile, the same cannot travel faster than the fastest speed at
which the wires can unwind satisfactorily, and so wired systems are
unsuitable for modern fast missiles.
It is also known for the firing station to have a source which can
be modulated by the brightness of the missile and for the same to
have optical reflectors such as catadiopters or totally reflecting
tetrahedric prisms. The rear of the missile then becomes a
secondary source of modulated radiation which helps to improve the
performance of the missile locator.
In the system according to the invention, a light source of this
kind can, with advantage, be an infra-red laser, simply because an
infra-red laser can be modulated simulataneously by a wide
frequency band of signals serving as control signals and by
low-frequency sinusoidal missile identification signals. Control
signals can therefore be transmitted to the missile by modulation
of the laser beam. The system gives some secrecy in the
transmission of tracking orders and helps to protect the
tele-guidance system from interference.
The rear of the missile therefore has an optical reflecting surface
for the doubly modulated infra-red light transmitted by the
firing-station laser, plus photodetector means for such light. The
missile has movement control by signals collected at the output of
a chain of electronic circuits connected to the photodetector cell
or means, the same bing disposed in a non-reflecting part at the
rear of the missle, the chain of electronic circuits comprising at
least one detector of the control signals which modulate the
received infrared light.
The beam of the laser at the firing station tracks the missile
under the control of known control means. Disposed at the firing
station beside the light source is a receiver for the infra-red
radiation reflected by the rear of the missile, the receiver
forming part of the missile locator, the optical axes fo the light
source and of the receiver being parallel to one another and
rigidly associated with one another. The receiver energizes the
beam tracking control system which processes the incoming data into
tracking control signals acting on the common direction of the
latter optical axes.
One way of producing these modulations is to combine with the laser
a modulator, such as a Pockels effect modulator, which modulates
the laser beam simultaneously with low-frequency sinoidal wave
serving to identify reflected radiation from the missile and with
the missle navigation conrol signals. The latter signals are
supplied by a computer on the basis of incoming data -- i.e., on
the basis of the signals delivered by the receiver and on the basis
of the measured angle between the direction of the aforesaid common
optical axis and the direction of the target sighting axis taking
due account of the observer-to-missile distance determined, e.g.,
by a timer which starts up at the deparature of the missile, whose
variation of the speed in relation to time is known.
The invention will now be described in detail with reference to the
accompanying drawings wherein :
FIG. 1 is a geometric diagram to explain the system for
tele-guidance of a missile towards a target according to the
invention;
FIG. 2 shows the light modulator of the tracking and locating
facility;
FIGS. 3a and 3b are diagrams of signal wave forms to help explain
FIG. 2;
FIG. 4 shows the ground teleguidance system;
FIG. 5 shwos the mounting frame, with two degrees of freedom, of a
laser beam transmitting and receiving mirror and of the sighting
means, and
FIG. 6 shows the missile direction control circuits.
Referring to FIG. 1, there can be seen a flying missile E, a target
C moving along trajectory or path T and a coordinate system Oxyz, O
denoting the aiming, firing and control station. The plane xOy is
sych as to contain the straight line OC. The missile E is projected
on the plane xOy at a place E.sub.xy and on the straight line OC at
a point e.
The angle a = EOC is the angular difference between the
observer-to-missile direction and the observer-to-target direction.
The length of the straight line eE represents the distance
separating the missile from the aiming axis. This distance can be
broken down into two componenents X and Y, X being perpendicular to
the aiming axis OC and Y being perpendicular to the xOy. The forces
which the steering gear must apply to the missile are porportional
to cos.b and sin.b, b being the angle shown in FIG. 1.
FIG. 2 shows the light modulator of the tracker and locator; as is
apparent, the light modulator is placed before a detector cell
(photo-detector) and rotates in front of the photocathode
thereof.It is assumed in FIG. 2 that the light modulator is
stationary and that the image of the missile describes a circle.
The reference direction pp1 is parallel to the straight line
eE.sub.xy of FIG. 1. The point M is the image of the missile
assumed to be in alignment with the observer-to-missile direction,
while the point M' is the image of the missile assumed to be out of
alignment with such direction. The signal which is shown in FIG. 3a
and which is a constant-frequency rectangular wave signal
corresponds to the point M, and the frequency-modulated signal of
FIG. 3b corresponds to the point M'. Clearly, the frequency swing
is a measure of the out-of-alignment angle of the missile -- i.e.,
the apex angle of the cone whose axis is the infra-red beam axis
and one generatrix of which passes through the missile; the
interval between the time t.sub.m of the maximum or minimum of the
instantaneous frequency and the time t.sub.o at which the point M'
crosses the straight line PP1 measures the angle of rotation of
such generatrix around the axis.
When the frequency swing and this period of time are nil
simulataneously, the missile is aligned on the beam. If in addition
the beam axis and aiming axis are parallel to one another, the
missile is aligned on the target.
Referring now to FIGS. 4 and 5, there can be seen an infra-red
CO.sub.2 laser 10, a Pockels effect modulator 11, an optical beam
collimator 12, reflecting mirrors 13, 14 and a large mirror 15
mounted with two degrees of rotational freedom -- one for bearing
and one for elevation - in an appropriate mechanical system. Rigs
in which only the mirror for transmitting and receiving the laser
beam can rotate with 2 .degree. of freedom and in which the actual
laser and the light receiver are stationary are fimiliar in the art
and need not be described in detail here. Mirror 15 tranmsits the
laser beam to the missile E. The beam is reflected by the missile
rear reflector and directed by mirror 15 to a parabolic reflecting
mirror 16 which focuses the beam at its focal point. A mirror 17
reflects the beam through an infra-red filter 20 towards a
direction detection cell 21. Disposed therebefore is the light
modulator 22 which has been described with reference to FIG. 2 and
whose rotational axis sweeps a uniform circular orbit around the
center of the photocathode of cell 21.
A low-frequency sinusoidal generator 24 is connected to the laser
modulator 11.
Advantageously, the photo-sensitive surface of cell 21 is composed
of a mixture of mercury and cadmium tellurides. The signal output
by cell 21 goes to a computer 26 which also receives the bearing
and elevation angle signals of mirror 15 and the signals for the
corresponding angles of the aiming axis of the sight 39 (FIG. 5),
the reception being through the agency of position sensors 27-30
which are disposed, i.e., through the agency of universal
suspensions, on the bearing and elevation shafts. From these data
the computer 26 calculates the angle a, the angle b, the components
sin.b and cos.b and the bearing and elevation components of the
beam corresponding to the conical differences (angle at the cone
apex and angle around the cone of the ground-station-to-missile
direction). The latter components are supplied to bearing and
elevation servomotors 31, 32 respectively of mirror 15, and the
components sin.b and cos.b are applied to an encoder 38 which
converts them into binary code and which is connected to the
modulator 11. Navigation instruction data are therefore transmitted
to the missile by laser modulation.
Referring to FIG. 6, there can be seen at the rear of the missile a
rear reflector 33 and a photodetector 34, the same being connected
to a decoder 35 which is connected to two amplifiers 36, 37
operating in known manner the rudders and elevators
respectively.
The invention has been described with reference to a complete
embodiment, but variants which can readily be conceived by the
skilled addressee are of couse possible and fall under this
invention as defined in the following claims. For instance, the
tracking control loop, instead of comprising an error signal
detector in the form of a light modulator associated with a
de-tector cell, could comprise an error signal detectr in the form
of an image dissection detector cell.
* * * * *