U.S. patent number 3,614,025 [Application Number 04/745,644] was granted by the patent office on 1971-10-19 for machine guiding system.
This patent grant is currently assigned to Compagnie Generale D'Electricite. Invention is credited to Henry Maillet.
United States Patent |
3,614,025 |
Maillet |
October 19, 1971 |
MACHINE GUIDING SYSTEM
Abstract
Determining the instantaneous position of a rotating machine
moving at high speed along a trajectory path by impinging a fine
light beam of generally flat form which rotates about an axis
parallel to the direction of light propagation onto a plurality of
detectors carried by the rotating machine in a plane perpendicular
to the trajectory axis and measuring the time intervals separating
the generated signals.
Inventors: |
Maillet; Henry (Sceaux,
FR) |
Assignee: |
Compagnie Generale
D'Electricite (Paris, FR)
|
Family
ID: |
8635383 |
Appl.
No.: |
04/745,644 |
Filed: |
July 17, 1968 |
Foreign Application Priority Data
|
|
|
|
|
Jul 19, 1967 [FR] |
|
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PV 114 851 |
|
Current U.S.
Class: |
244/3.13;
244/3.11; 244/3.16 |
Current CPC
Class: |
F41G
7/305 (20130101); F41G 7/266 (20130101) |
Current International
Class: |
F41G
7/20 (20060101); F41G 7/26 (20060101); F41G
7/30 (20060101); F41g 009/00 (); F41g 007/00 ();
F41g 007/14 () |
Field of
Search: |
;244/3.13,3.16 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Borchelt; Benjamin A.
Assistant Examiner: Webb; Thomas H.
Claims
What is claimed is:
1. A system to establish data concerning the instantaneous position
of a moving machine relative to an instantaneous theoretical
trajectory materialized by a light beam, comprising: a light beam
emitter capable of emitting a fine beam of generally flat form
which emitter rotates about an axis parallel to the direction of
propagation of the light waves, three detectors disposed on the
moving machine and in a plane substantially perpendicular to said
axis, means for measuring the time intervals separating the signals
produced by the detectors when they are successively scanned by the
rotating light beam, and means for determining the sequence of the
excitation of said detectors, the sequence of excitation and the
time intervals being indicative of the instantaneous position of
the machine relative to the axis of the revolving light beam.
2. The system as claimed in claim 1 wherein said spaced detectors
disposed on said moving machine define a polygon.
3. The system as claimed in claim 2 wherein said polygon is a
square.
4. The system as claimed in claim 1 in which said light beam
emitter comprises a laser.
5. The system as claimed in claim 1 in which said measuring means
is carried by the moving machine.
6. The system as claimed in claim 1 further comprising calculating
means for calculating the distance of the axis of the moving
machine relative to the axis of rotation of the light beam as a
function of the time interval values.
7. The system as claimed in claim 6 wherein said calculating means
is installed at a fixed position, remote from said moving machine
and said system further includes wireless communicating means
carried by said calculator means and said moving machine, whereby
the values of said time intervals are transmitted from said moving
machine to said calculator means and control signals are
transmitted from said calculator means back to said moving
machine.
8. The system as claimed in claim 1 further including calculating
means for calculating from the signals emitted by the detectors,
the amplitude and direction of the correction to be applied to the
trajectory of the moving machine, the amplitude of the correction
to the trajectory of the moving machine being substantially
inversely proportional to the time interval separating the first
signal from the last signal applied by the detectors during one
revolution of the light beam.
9. The system as claimed in claim 1 wherein the machine comprises a
moving body being rotated about an axis substantially parallel to
that of the light beam and wherein the rotational speed of said
beam is substantially larger than the rotational speed of said
machine.
10. The system as claimed in claim 1 in which said light beam
emitter comprises a laser focused on a revolving slot.
11. The system as claimed in claim 1 further comprising a Wollaston
prism for achieving rotation of said light beam.
12. The system as claimed in claim 1 further comprising an afocal
optical system for rotating said light beam, said afocal optical
system including cylindrical lenses intersecting at 90.degree..
13. The system as claimed in claim 1 in which said light beam
emitter comprises an afocal optical system with means providing a
continuously variable divergence as a function of the distance of
the moving body from the emitter.
14. The system as claimed in claim 1 wherein said light beam
emitter comprises at least one gas lens of variable focal
length.
15. The method of guiding a moving body in relation to a
rectilinear theoretical trajectory path, said method comprising:
emitting a fine light beam of relatively flat form to define the
trajectory path, rotating the body about an axis parallel to the
direction of propagation of the light rays, intercepting the light
beam successively by at least three detectors disposed on said
moving body in a plane substantially perpendicular to the axis of
said light beam, with the detectors being distributed in said plane
in accordance with a regular polygon, measuring the sequence of
excitation of said detectors and the time intervals separating the
successive signals emitted by the detectors, and modifying the
trajectory of the moving body in response to the sequence of
excitation and the value of said time intervals.
16. The method of guiding a moving body in relation to a
rectilinear theoretical trajectory path as claimed in claim 15
further comprising the steps of: comparing the time intervals in
order to identify the detector which has been excited by the light
beam after the longest time interval, calculating the distance of
the center of gravity of the polygon from the axis about which the
light beam is rotating as a function of the value of said time
intervals, and modifying the trajectory of the moving body by
imparting to it a movement pulse, the direction of which is
substantially that of the tangent to the circle in which are
inscribed the detectors at the point at which the identified
detector is situated and in which the amplitude is a direct
function of the distance of the moving body from said axis.
Description
The present invention relates to a system and a method of guiding
moving bodies, or to a system permitting a moving body to
self-establish the information concerning its position in relation
to a predetermined trajectory.
The invention is applicable to any mobile machine, such as a land
vehicle or marine vessel, a drilling vehicle or an aircraft, such
as an airplane or propelled rocket, or even to ballistic
missiles.
The present invention is preferably applicable to moving bodies
carrying means enabling them to change their trajectory, but this
invention can also be applied to moving bodies which do not have
such means but which, for any particular purpose, have systems
which need to receive at any moment data concerning the position of
the moving body with respect to a given trajectory.
There are known systems which make it possible to determine the
position of a machine or to guide the movement of a machine by
means of a light beam. Certain of them use rotating eccentric beams
which strike detectors placed on the machine with the measurement
of the variations in luminous intensity making it possible to
calculate approximately the displacement of the machine in relation
to the axis of rotation of the light beam. One such system,
described in the article "Optical Guidance of Vehicles," published
in the journal "Measurement and Control," Mar., 1964, does not
permit accurate results to be obtained and can in fact only be
applied to slow vehicles, such as machines used in public
works.
It is also known from French Pat. No. 1,466,437 (granted the Dec.
12, 1966), to provide a projectile guiding system which comprises
means for obtaining a guiding "light channel" by means of four flat
laser beams.
The known systems do not resolve the problems which arise in a
satisfactory manner, because they are all based on measurements of
luminous intensity or of detection of modulation of a light
wave.
The present invention has for its object to provide a guiding
system in which the efficiency is not a function of any variations
in the luminous intensity of a beam.
The system according to the present invention comprises a light
beam emitter of the laser type, capable of emitting a beam of
generally flat form which rotates about an axis parallel to the
direction of propagation of the light waves, and a plurality of
light ray detectors disposed on a machine in a plane substantially
perpendicular to this axis. The relative disposition of the
detectors preferably defines a regular polygon and the measurement
of the time intervals separating the pulses produced by the
detectors scanned by the said rotating beam determines the position
of the machine in relation to the axis, which thus constitutes a
reference trajectory.
According to one feature of the present invention, the detectors
are arranged in such a manner as to supply a calibrated electric
pulse when they detect the passage of the light beam, and the
machine comprises an electronic data processing arrangement which
measures the time intervals between the pulses emitted by the
detectors, and the electronic arrangement is connected to the means
for controlling modification in trajectory of the machine.
According to another feature of the invention, the machine
comprises four detectors disposed at the apices of a square, the
trajectory-modifying means being such that the machine receives a
movement pulse directed parallel to the tangent to the circle
passing through the four detectors at the point where the detector
lies which has sent the first pulse of the series of four pulses
forming a measurement sequence.
The invention will now be made clear by the detailed examination of
one embodiment of the invention, given as a nonlimiting example, in
which the machine is a flying missile of the ground-to-air or
ground-to-ground type.
The invention will be described by reference to the accompanying
drawings, in which:
FIG. 1 is a diagrammatic view of a ground-to-ground engagement,
according to the system of the present invention;
FIG. 2 is a section of the laser beam used in the system of FIG.
1;
FIG. 3 is a diagrammatic view of a missile provided with photonic
detectors arranged according to the invention;
FIG. 4 is a schematic representation of various relative positions
of the missile and of the propagation axis of the laser beam;
FIG. 4a represents the diagram of electric pulses supplied by the
detectors for the positions of the missile of FIG. 4;
FIG. 5 is a schematic view of a similar representation to that of
FIG. 4;
FIG. 5a is a schematic representation of various relative positions
of the missile and of the propagation axis of the laser beam;
FIG. 6 is a schematic view of a calculation of the intensity of the
intensity of the movement pulse;
FIG. 7 is a schematic representation of a missile including a
detector system;
FIG. 8 is a schematic representation of a missile including means
for communicating with the ground; and
FIG. 9 is a schematic representation of an optical system for use
with the present invention.
As shown in FIG. 1, a laser emitter 11, located in the vicinity of
a firing point, sends a laser beam 12 in the direction of the
target 13, towards which missile 10 is directed. The cross section
20 of the beam 12, that is, its section through a plane P
perpendicular to the axis of propagation, is represented in FIG. 2.
The cross section 20 is preferably narrow and elongated and,
bearing on the trace 0 in the plane P of the beam propagation axis,
turns about this axis in the plane P at a constant angular velocity
w.sub.o.
As one example, this beam has a length D of several meters and a
mean width d of a few centimeters, preferably smaller than 10
centimeters.
As shown in FIG. 3, the missile carries four light detectors
indicated at 1 to 4, placed at the four apices of a square, of
which the plane is perpendicular to the missile axis and of which
the center is on the axis. The trace of this axis in the plane of
the square formed by the detectors is designated by .OMEGA. in FIG.
3. The detectors will preferably be placed at the ends of four
ailerons of the missiles and staggered by 90.degree..
In general, the missile turns on itself during its flight at an
angular velocity w.sub.10.
The angular velocity w.sub.o of rotation of the laser beam is
preferably chosen to be very much higher than the angular velocity
w.sub.10 of rotation of the missile 10 about its axis, so as to be
able to assume that this latter remains relatively stationary in
rotation during one revolution of the laser beam.
The detectors 1 to 4 are arranged in such manner that each emits a
calibrated electric pulse every time that they detect the passage
of the laser beam.
The guiding principle according to the invention is as follows:
With the missile following its trajectory in the direction towards
the target, the rotation laser beam scans the detectors and, during
one revolution of the beam, the four detectors each receive, one
after the other, a certain quantity of light and each emits an
electric signal one after the other and in the same order.
FIG. 4 represents diagrammatically, in a plane perpendicular to the
axis of the laser emitter, the trace 20 of the laser beam, the four
detectors 1, 2, 3 and 4 at the apices of a square, the trace 0 of
the laser emitter axis and the trace .OMEGA. of the missile
axis.
It is clearly shown in FIG. 4 that, with the laser beam turning
about the point 0, the first detector which receives the signal is
that which is on the arc AB of the circle C passing through the
detectors, seen from the point .OMEGA. at a right angle, and such
that A, B and 0 are aligned.
In the case of FIGS. 4 and 5, it is the detector 1 which first
intercepts the beam.
FIG. 4a represents, as a function of time t, the diagram of the
pulses supplied by the four detectors during several passages of
the laser beam, on the hypothesis that w.sub.10 is very small as
compared with w.sub.o.
If the missile was placed exactly on the trajectory of the laser
ray, that is to say, if the trace 0 was inside the square formed by
the detectors 1, 2, 3 and 4, the pulses would be regularly spaced
and distributed in the order 1, 2, 3, 4 (see FIGS. 5 and 5a).
In the case of FIG. 4, it is clearly seen that consideration of the
time intervals separating the signals of one measuring sequence or
the signals of several measuring sequences makes it possible to
determine the relative position of the missile in relation to the
trace 0; in actual fact, the circle C having a constant diameter,
the measurement of an angle, such as 104 or 103, permits of
calculating the distance 0.OMEGA..
On the other hand, it is pointed out that the identification of the
detector which supplies the first signal of a measuring sequence
makes it possible to determine with a good approximation the
direction of the spot where is situated the trace 0 in relation to
the trace .OMEGA. of the missile. Actually, it can be seen that, in
the case of FIG. 4, the tangent 1a to the point 1 of the circle C
is pointed parallel to the direction .OMEGA.0 with an error smaller
than 45.degree..
Whatever may be the position of the missile relative to the trace 0
of the beam, the direction of the movement to be given to the
missile in order to return it to its perfect trajectory as
materialized by the axis 12 is substantially that of the tangent to
the circle C at the point where is situated the detector giving an
electric pulse terminating the largest of the time intervals
between pulses in a given measuring sequence. This rule is valid,
even if the trace 0 of the beam is inside the circle C passing
through the four detectors, as is shown by FIGS. 5 and 5a which
illustrate this case.
Referring to FIGS. 7 and 8, if the missile has an electronic
arrangement which permits of measuring (with time measure means 15)
the different time intervals and the direction control means 14
permitting the trajectory to be modified, it is possible to
elaborate a control signal for a modification of the trajectory,
tending to bring the missile back towards the perfect trajectory
materialized by the beam 12. According to the invention, the
missile comprises an electronic arrangement for measuring (with
time measure means 15) and comparing (with comparator 16) the time
intervals separating the pulses supplied by the detector 1, 2, 3
and 4 during one or more revolutions of the beam.
The information concerning the distance .OMEGA.0 is obtained by
measuring the intervals separating the signals from one another,
while the direction according to which the trajectory is to be
corrected is obtained by the comparison of the various time
intervals, which permits identifying the detector which has
supplied the signal terminating the largest of the four time
intervals corresponding to one revolution of the light beam.
In a modified embodiment, in which a measuring sequence is limited
to the reception of four successive electric pulses, the electronic
arrangement for comparison of the intervals can be omitted.
In actual fact, if it is known to extract a sequence of four
signals (either by extracting this sequence from a series of
measurements, or by using an emitter which would only make the beam
turn for one revolution), it is known that the maximum time
interval separating two pulses is T/4, T being the period of
revolution of the revolving beam. Consequently, if there are
considered four consecutive signals of the same sequence, defining
three time intervals, or even if these three intervals are small
than T/4 and it is the first signal which determines the start of a
sequence, or even if one of the intervals and one only will be
greater than T/4, then in this case it is the signal terminating
this time interval which is to be a commencement of sequence.
From the time intervals separating the electric pulses, an
electronic arrangement 17 is able to establish a signal of which
the amplitude is a function of the distance of the trace .OMEGA. of
the missile axis from the trace 0 of the beam axis. Actually, by
referring to FIG. 6, showing the relative position of the missile
(represented by its four detectors positioned at the points A, B, C
and D and by the point .OMEGA.) and of the beam 12, it is seen that
the distance 0.OMEGA. can be easily expressed as a function of the
angles .theta..sub.1 =2.pi./Tt.sub.1, where t.sub.1 is the time
interval separating the electric pulses due to the passage of the
beam onto the detectors A and B, and .theta..sub.2 =2.pi./Tt.sub.2,
t.sub.2 being the time interval separating the electric pulses due
to the passage of the beam onto the detectors B and C, T being the
period of revolution of the beam.
Actually, if D is the diameter of the circle passing through A, B,
C and D, the following relationships exist: OA.sup.2 +OB.sup.2 -2
OA.sup.. OBcos.theta..sub.1 =D.sup.2 /2 OB.sup.2 +OC.sup.2
-2OB.sup.OA OCcos.theta..sub.2 =D.sup.2 /2 OA.sup.2 +OC.sup.2 -2OA
.sup.. OCcos(.theta..sub.1 +.theta..sub.2)=D.sup.2 0.OMEGA..sup.2
=1/2(OA.sup.2 +OC.sup.2 -D.sup.2 /2)
Electronic arrangements 15, 16, 17 of conventional type are known
which are capable of establishing a signal proportional to 0.OMEGA.
from the measured values t.sub.1 and t.sub.2. These electronic
arrangements comprise in known manner shaping and calibrating means
for the electric pulses supplied by the detectors, means for
measuring 15 and for comparing 16 time intervals separating these
pulses and calculating members 17 functioning as an analogue or
digital system.
As mentioned in the introduction to the present specification, the
system according to the invention is applicable to a large number
of particular cases. The data given by the detectors can be
elaborated to a greater or lesser extent by means on board the
moving body (see FIG. 7), and can be transmitted by radio (emitter
18) or any other transmission means to fixed control systems or
monitors 19 which, in their turn, transmit orders to receiver 21 on
the moving body (see FIG. 8).
According to a preferred modification of the invention, illustrated
in FIG. 7, the moving body comprises means for processing this data
and for using it directly for controlling the functioning of means
which permit the trajectory of the moving body to be modified.
In the case of a flying machine, equipped with a propulsion unit,
or of a ballistic missile following a predetermined trajectory, the
trajectory-modifying means can be ailerons or systems known as "jet
deflectors."
The data processing systems 17 on board the machine can easily
calculate the distance of the machine from the trace 0 of the light
beam axis and the direction in which the point 0 is situated in
relation to a fixed direction of the machine, this direction being
the tangent 1a defined with reference to FIGS. 4 and 5.
Thus, the system according to the invention has the advantage of
permitting a correction of trajectory in a direction associated
with a detector identified by the control circuit of the machine,
whatever may be the position of the machine rotating about itself,
and it is thus unnecessary to have on board the machine a vertical
reference, as for example, a gyroscopic arrangement.
The trajectory correction control signal can be established after a
certain number of revolutions of the light beam, and this makes it
possible to obtain a signal which takes into account possible
errors and which can also take into account slow variations of the
trajectory. In other words, the signal can be different, according
to the case where the distance between the machine and the
theoretical trajectory is constant, or the case where the spacing
between the machine and the theoretical trajectory varies
continuously in one direction or the other.
If a trajectory correction is made with each revolution of the
light beam, there will be obtained a data rhythm 1/T, T being the
revolution period of the beam, and it is possible with advantage to
choose a frequency of revolution having a value from 10 to 500
c.p.s. preferably 100 c.p.s.
As the trajectory correction is carried out by movement pulses
imparted to the machine, the calculation of the distance of the
latter from its perfect trajectory then makes it possible to adjust
the value of this pulse, which can, for example, be proportional to
this distance.
In a modification, the movement pulse is chosen to be inversely
proportional to the time separating the first pulse from the last
pulse during one revolution of the beam. This method is less
accurate than the foregoing, but it is easier to carry into
effect.
The flat revolving laser beam can be obtained in various ways: for
example, by focusing on a slot of suitable dimensions, turning
about the optical axis of the laser at a speed of rotation equal to
the desired speed of rotation of the beam, or revolving
arrangements are even known which comprise special prisms, such as
the Wollaston prisms, the slot remaining movable. Such known
devices are generally shown by element 22 in FIG. 9.
It is also possible to achieve this by means of an afocal system 23
having two cylindrical lenses intersecting at 90.degree. such that
the system is afocal in all directions, but with a variable ratio
thus producing a beam of flat form. This afocal system is driven so
as to rotate about its axis. It is advantageous for the detectors
to receive, apart from adsorption, the same quantity of light with
the passage of the beam, whatever may be the distance of the laser
emitter from the machine. In order to effect a correct quantitative
correction, it is necessary for the divergence of the beam to be
adjustable so that the section of the beam through a plane
perpendicular to its propagation axis at the location where the
machine is situated is constant. It is possible to provide the
laser beam emitter with a device by which it is possible to obtain
a divergence variable as a function of time, knowing the speed of
displacement of the machine. This can be achieved by using an
afocal arrangement as described above, provided with means for
continuously achieving derangement by displacement of the lenses or
by relative rotation of these lenses upon reception of orders from
conventional ranging or control means. It is also possible to
obtain arrangements having variable divergence by using gas lenses
by which it is possible to vary the focal lengths by acting on the
pressure of the gas or on the nature of the gas.
The invention is not in any way limited to the embodiment described
and illustrated, which has only been given by way of example. In
particular, without departing from the scope of the invention, it
is possible to introduce modifications as regards detail, to change
certain arrangements or to replace certain means by equivalent
means.
* * * * *