CA1254292A - Passive ranging of an airborne emitter by a single non-maneuvering or stationary sensor - Google Patents

Abstract

ABSTRACT OF THE DISCLOSURE

Method for passively determining the range to a target from a test platform. The method comprises travelling at a constant velocity a course in the test platform which is straight; detecting at the platform the presence of an energy signal radiating from the target, and sampling said energy signal at three discrete times.
Generating for each of said energy signal samples a first detection signal responsive to its angle of arrival at the platform, and a second detection signal responsive to its frequency on arrival at the platform; and storing said detection signals. The range to the target is then determined utilizing the stored detection signals and the test platform velocity and position; then generating a target indication signal representative of the range of the target.

Description

, NON-MANEUVERING OR STATIONARY SENSOR
The present invention relates to measuring the range of moving targets, and more particularly, to a method of passively measuring the ranqe of moving targets from a single test platform which is either stationary, or moving at a constant velocity along a linear trajectory. ~
Various passive ranging systems and methods .
have been previously developed. In a passive ranging system the position of a target, such as an aircraft or ship, is typically determined from radiant signals emanating from the target itself~ rather than echo signals developed from radiant energy being transmitted towards the target, as in active ranging systems.
Generally, the systems and methods previously developed involve the use of a variety of optical, electromagnetic and acoustic sensors, as well as the use of cooperating ground based receiving and transmitting stations.
Many such systems also require a plurality of cooperating !,, 20 sensor units, and cross-correlation equipment. Such `
syst~ms are generally complex, and often include operating ~-~
limitations such as the ability to sense only continuously emitted signals, or the inability to be effective against targets moving at a velocity greater than the velocity ~
25 of the observing vehicle itself. -~:
Many of the problems associated with prior passive ranging systems and methods have been overcome by the passive ranging methods described in U.S. Patent No. a,l79,697 (the '697 patent), issued December 18, 1979 in the name of the present inventor, Martin Golinsky, ~

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- ~Sd~9~2 1 and in U.S. Patent ~l,558,323 (the '323 patent) also in the name of the present inventor. Both the '697 patent and the '323 patent disclose passive ranging methods which permit the range to an emitter target to be deter-mined from a single moving vehicle, commonly referred to as a test platform.
In the method disclosed in the '697 patent, a single measuring aircraft is constrained to fly along a curved trajectory at a constant speed, while simulta-neously performing a sequence of passive bearing measure-ments of the target aircraft relative to itself. Such measurements produce a geometric pattern of intersecting rays which provides the data for mathematical calculations used to determine the target's range.
In the method disclosed in the '323 patent a single measuring aircraft is again used, however, it is constrained to fly along a linear trajectory at a non-constant speed (i.e., under acceleration or decelera-tion), while also simultaneously performing a sequenceof passive bearing measurements of the target aircraft relative to itself. Again such measurements are used to produce a geometric pattern of intersecting rays which also provides the data for a mathematical solution to the target's range.
Although both of these methods are valid and useful for certain applications, there are other applications where it would be desirable to passively measure the range of a target emitter without a test 3 platform having to meet the travel constraints imposed 25~ 2 1 by these prior methods. For example, it is desirable for any aircraft traveling in a normal manner, i.e., traveling along a linear trajectory at a constant velocity, to be able to readily measure the range to other aircraft without going off its assigned course or changing its normal air speed. Similarly, it is also desirable for a stationary test platform, such as an air traffic control tower, or a hovering helicopter, which are incapable of satisfying the travel constraints of the prior methods, to also be able to measure the range to other aircrafts.
The foregoing problem is overcome, and other advantages are provided by a ranging method utilizing a succession of bearing and frequency measurements .
obtained at discrete periods of time from a radiant signal emitted by a target vehicle. In accordance with the invention, only a single measuring vehicle or test platform is required to accomplish the ranging process. The test platform carries a sensor of radiation emitted by a target vehicle. The emitted radiation may be pulsed or continuous. The sensor, which may include an array antenna, beam forming circuitry provides bearing and frequency information about the source of radiation which is ~.
25 utilized to determine the range to the target aircraft. ~`
The velocity and direction of travel of the emitter may then also be calculated from this information.
The method of the present invention provides for the linear movement of a radiant energy sensor ~30 at a constant velocity. At discrete times during its ,. ~

1 displacement electrical circuitry connected to the sensor provides for a sampling of the radiant energy signal transmitted by the emitter target. As a result of the combined movement of the target and sensor there is produced a geometric pattern of rays of received radiation. The bearing angles and frequencies of these rays of radiation are measured and then arithmetically combined to provide the range to the target vehicle relative to the sensor.
10Although the present invention is described herein with reference to the tracking of aircraft, it should be understood that the method is equally applicable to ships employing sonic sensors and to satellites employing optical sensors. It should also be noted that certain assumptions utilized in the aforementioned Golinsky patent and application `
are also valid here. Specifically, the target whose range is to be determined is not maneuvering, and the ;
test aircraft is at a long range from the target so 20 tnat they may be considered to be in the same horizontal -plane.
In the accompanying drawings, Fiqure 1 is an illustration of a moving vehicle, shown as a test air-craft, carrying a sensor for receiving a radiant ^
energy signal emitted by a target vehicle, also shownas an aircraft.
Figure 2 is a block diagram of a passive ranging system for use with the passive ranging method of the present invention.
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1 Figure 3 is a geometric diagram which illu-strates the relationship between the target aircraft and the moving test aircraft at discrete point of detection.
Figure 4 is a geometric diagram which illu-strates the relationship between the target aircraft and a stationary test platform a~ a single point of detection. .
Figure 1 illustrates a typical scenario involvingthe method of the present inven~ion. A moving target 20, depicted as an aircraft which emits electromagnetic lQ radiation, is shown traveling along a flight path 22.
The path 22 is assumed to be a ~traight line, while the velocity of the target is assumed to be constant.
A test platform 24, also depicted as an aircraft, carries a sensor 26 of the electromagnetic radiation 15 emitted by target 20. The test platform, which is '~
also shown to be moving along a straight path 28, ~;-is constrained to operate at a constant velocity. ~
Figure 2 illustrates an apparatus which -`
could be used in implementing the present invention, and 20 indicates how this apparatus is to be connected. .`
When a target, such as aircraft 20, emits an --energy signal, such as a radar pulse, the test aircraft 24 receives the signal through its antenna 30, after `
which it is channeled into a passive detection system `,7 32 measuring bearing and received frequency of the emitted signal. Systems of this type are available from amnufacturers such as Litton Industries, Amecom Division. Litton Model No. ALR-73, is an example of such a passive detection system.

S ~' ~5~92 1 The test platform 24 also includes a navigation system 34, a tracking system 36 and a display 38. The navigation system 34 and the tracking system 36 employ well p known circuitry and are available from manufacturers such 5 as Litton Industries. Examples of these systems include Litton's navigation system ASN-92 and Litton's tracking computer OL-77/ASQ. The tracking system is capable of accomplishing the steps of the mathematical calculations required to carry out the method of the present invention as -10 hereinafter described. In the preferred embodiment of the invention this system is used, although it should be understood that a dedicated system may also be employed. Thus, where the calculations are performed by the tracking system, the present invention only requires systems already aboard many 15 test aircrafts, and therefore, it offers distinct advantages over systems which require additional bulky and expensive equipment.
Figure 3 illustrates the fundamental concept of the present invention. Vector AC shown therein represents the 20 trajectory of test platform 24, while Vector DF represents the trajectory of target emitter 20. The test platform travels along vector AC at a constant velocity, Vp, so as to cross points A, B and C at times Tl, T2 and T3, respectively.
Similarly, target 20 is assumed to travel along Vector DF
25 at a constant velocity, Vt, so as to cross points D, E and at times Tl, T2 and T3, respectively. In the diagram shown in Figure 3, the time intervals between Tl and T2, and T2 and T3 are taken as being equal. Thus, the distances AB and BC traveled by the test platform during these time periods 30 are equal, while the distances DE and EF traveled by the -~
emitting target during these same periods, are also equal.

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1 The assumption of equal time intervals, and therefore, equal distances, is made only for the convenience of explaining the concept of the present invention. In actuality, however, the time between T1 and T2, and T2 and T3 need not be equal, and 5 the distances traveled during such time periods by the platform and taxget also need not be equal.
Referring now to Figure 3 in combination with Fi~ure 2, the sensor 26 of test platform 24 samples the radiant signal emitted by target 20 as the test platform lO crosses point A, B and C. At each of these points, the passive detection system 32 aboard the platform utilizes such samples to measure the bearing to the target aircraft 20, and the frequency of the emitter signal upon its arrival at the platform. Once these samples have been obtained, and 15 their bearings and frequencies have been measured, tracking system 36 utilizes this data to mathematically calculate the range to target 20, as hereinafter described.
In contrast to the passive ranging methods described in the aforementioned patents 4,179,697 and 4,553,323 in 20 which measurements were required at four points along the platform's trajectory, it should be noted that the method of the present invention only requires three measurements to be made along the trajectory of the test platform. However, in the present invention since frequency measurements are 25 required in addition to the bearing measurements utilized in the previous methods, a total of six observables are used in determining a target's range, in contrast to the four observables used in the previous methods.
For purposes of describing the method of the 3O present invention, the values of the bearing and frequency measurements taken at times T1, T2 and T3 are designated as l' fl; 2' f2; and 03, f3, respectively. Generally, the ~2~ 9i~ `~
1 three measure~ bearing angles will differ in value because of the geoinetry of the flight paths o~ the test platform and the target emitter. Similarly, the measured frequencies will also vary, even if the frequency transmitted by the ~' 5 emitter is constant, because of changing doppler shifts.
At point A, the measured frequency ~1 can be defined as follows:
-.

fl fo + ~ [Vt cos ~ + Vp sin ~1] (1) -where fQ equals the transmission frequency of the emitter ;~
~presently unknown); -~ equals the transmitted wavelength;
15 --equals the angle between a bearing line, AD, to the emitter and the target velocity Vector DF;
81 equals the measured bearing;
Vp equals the platform velocity (which is known by virtue of onboard navigation system 34); and 20 Vt equals the velocity of the target aircraft (presently unknown). :
The right side of equation (1) represents the one-way doppler shift of the transmission frequency fO. ~
Similar equations can be developed to define frequencies ~-25 f2 and f3. Thus t~hen test platform 24 is at points B and C, the respective measured frequencies, f2 and f3, are defined by the following equations f2 = fo + 1 [Vt cos (~ + ~1 2) + V sin ~2] (2) f3 = fo + ,` [Vt cos ~. + l 3) + Vp sin 03]
(3) .~ ~
- 9 - ~
-~5~92 ~;

1 where

2 equals the measured bearing at point B
03 equals the measured bearing at point C
l 2 equals ~ 2 5 ~1 3 equals l ~ 3 ,~
and the other parameters have been previously defined. All `
angles are measured positive in a counter--clockwise direction. :~-Thus, in Figure 3, 03 would have a negative value.
Previous equations 1-3, set forth above, contain ~.
10 three unknowns, ~ , Vt and fO. These equations can, therefore, --be solved for these unknowns, yielding the following equations:

fO= f1Sin 32,3~f2Sin ~1 3+f3sin ~1 2 1,2 ~1~3+5in ~2,3 + Vp (sin 03sin 4 c (4) sin 02sin ~1 3+sin ~lsin ~2,3) where -~-2,3 ~2 ~ ~3, and 20 c equals the velocity of propagation of electromagnetic waves :

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cos ~1 2 \ f -f - V f sin o2 = tan~l , ~ c ,. '' i ~1,2 (5) _. ~ __ `:

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--10-- .~;, ~5~g2 1 The value of ~ can be readily solved because every variable on ~;
the riqht side of equation 5 is ]cnown by reason of the fact that fO has been calculated using equation 4. It should be noted that by retaining the signs of the numerator and 5 denominator of the argument, the usual angular ambiguity associated with the arc tangent is resolved.
The last unknown Vt is determined from the following `~
equation: ~`

-lG ^~-" ~ c -Vp sin ~1 r~
cos (6) Having calculated the values of the unknowns Vt and ~ , and knowing the time interval T between measurements (which equals the time periods between Tl and T2, and T2 and T3), it is '`
then possible to solve for the unknown ranges from the test 20 platform 24 to the target aircraft 20, i.e., AD, BE and CF
shown in Figure 3. Thus, DE = EF = VtT (7) while, AB = BC = VpT (8 ) AB 2 (9) sln ~1 2

3 GD = DE sin (r+ 1,2 (10) sin ~1,2 ~, - 1 1- ``;~

l Therefore, the range to targe-t 20 a-t point A is AD which is defined as follows:
1 t.
AD = AG + GD = sin l 2 [AB cos ~2 + DE sin (' + ~1,2)] (11~ --where all quantities on the right side of equation 11 are known.
Similarly, the range to target 20 at points B and C is BE and ~
CF, respectively. They are defined as follows: ;

BE = EG + GB = sin ~ [AB cos 1 ( 12) CF = CJ + JF = sin O [AB cos 1 (13) Thus, the solutions to equations 11, 12 and 13 represent the 15 ranges at any sample points A, B and C from a test platform to a moving emitter where the test platform is traversing a linear course at a constant velocity. Once this range information has been calculated, it can be used to determine the velocity and direction of travel of the emitter target using the standard 20 on-board systems of the test platform. i-Figure 4 illustrates the fundamental concept of the ~-present invention where the test platform is stationary.
E~amples of this type of application include an air traffic control tower, a hovering helicopter, or an anchored ship. :
25 Here, since the velocity of the test platform is zero, Vp is set equal zero in equations 1, 2 and 3. Notwithstanding this, the method of determining the range to the emitter target at points D, E and F is still the same. AD, BE and CF then represent ranges from a common point A to the moving emitter, 3 since points B and C are now co-located with point A.

~, ~ 1 2-- :r , 1 To improve the accuracy of the calculated range ,~
in the presence of measurement errors, the measurements made at times T2 and T3 may be used with a fourth measurement to update the range calculation. This updating may be continued 5 for as long as desired.
It is obvious that the present invention can be used in a number of military applications. It should be noted, however, that in addition to such military applications, the present invention may also be used in commercial applications 10 such as, for example, an aid to air traffic control. In such applications, the transmission frequency, fO, would be known. As such, only two sample points, e.g., A and B, rather than three would then be needed, resulting in a reduced time interval required to determine the applicable range to the 15 target emitter.
The calculations used to carry out the inventicn can be performed in essentially real time on different sets of -three measurements, where each set is determined by the passive detection system to have resulted from a distinct emitter. --~
2G Therefore, the number of emitters that may be positioned by the technique is limited only by the number of allocated track files in the tracking system.
It is to be understood that a number of variations may be made in the invention without departing from its 25 spirit and scope. The terms and expressions which have been employed are used in a descriptive and not a limiting sense, ~;
and no intention of excluding equivalents of the invention i-described and claimed is made.

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Claims (15)

The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:

1. A method of passively determining the range to a target from a test platform comprising:
causing the test platform to travel on a straight course at a constant velocity, detecting at the platform the presence of an energy signal radiating from the target, and sampling said energy signal at three discrete times;
generating for each of said energy signal samples a first detection signal responsive to its angle of arrival at the platform, and a second detection signal responsive to its frequency on arrival at the platform;
storing said detection signals;
determining the range to the target utilizing said stored detection signals and said test platform velocity and position; and generating a target indication signal representative of the range of the target.

2. A method as recited in Claim 1 wherein the step of determining the range to the target comprises:
calculating said energy signal's transmission frequency;
calculating an angle between a bearing line to the target and the target's course at a first of said discrete sample times utilizing said transmission frequency;

calculating the target's velocity utilizing said calculated angle; and determining the range to the target utilizing said calculated angle and said target velocity.

3. A method as recited in Claims 1 or 2 wherein said test platform is stationary so that its velocity is equal to zero.

4. A method as recited in Claims 1 or 2 wherein said energy signal's transmission frequency is known, and wherein said energy signal is, therefore, sampled at only two discrete times.

5. A method as recited in Claims 1 or 2 wherein the test platform and the target are at essentially the same altitude, and wherein both are flying horizontally.

6. A method as recited in Claims 1 or 2 wherein the step of sampling comprises receiving a continuously generated energy signal.

7. A method as recited in Claims 1 or 2 wherein the step of sampling comprises receiving pulsed energy signals.

8. A method as recited in Claims 1 or 2 wherein the step of sampling comprises receiving a continuously generated radar signal.

9. The method as recited in Claims 1 or 2 wherein the step of sampling comprises receiving a pulsed radar signal.

10. The method as recited in Claims 1 or 2 wherein the step of sampling comprises receiving a continuously generated energy signal of the class of signals consisting of optical frequency signals and sonic signals.

11. The method as recited in Claims 1 or 2 wherein the step of sampling comprises receiving a pulsed energy signal of the class of energy signals consisting of optical frequency signals and sonic signals.

12. A method of passively determining the range to an airborne target from a test aircraft comprising:
traversing a linear path in the test aircraft, at a constant velocity;
sampling at the test aircraft a radio signal emitted by the target at three discrete times;
generating for each of said samples a first detection signal responsive to its angle of arrival at the test aircraft, and a second detection signal responsive to its frequency on arrival at the test aircraft;
determining the range to the airborne target utilizing said first and second detection signals and said test aircraft velocity; and generating a target indication signal representative of the range to the target.

13. A method as recited in claim 12 wherein said radio signal's transmission frequency is known, and wherein said radio signal is, therefore, sampled at only two discrete times.

14. A method as recited in Claim 12 wherein said test aircraft is stationary so that its velocity is equal to zero.

15. A method as recited in Claim 12 wherein the test aircraft and the airborne target are at essentially the same altitude, and wherein both are flying horizontally.