# Signal Transceiver Transit Times and Propagation Delay Corrections for Ranging and Georeferencing Applications

Authors: P. Kaufmann; P. L. Kaufmann; S. V. D. Pamboukian; R. Vilhena de Moraes
Journal: Mathematical Problems in Engineering
 (2012)

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## Abstract

The accuracy of ranging measurements depends critically on the knowledge of time delays undergone by signals when retransmitted by a remote transponder and  due to propagation effects. A new method determines these delays for every single pulsed signal transmission. It utilizes four ground-based reference stations, synchronized in time and installed at well-known geodesic coordinates and a repeater in space, carried by a satellite, balloon, aircraft, and so forth. Signal transmitted by one of the reference bases is retransmitted by the transponder, received back by the four bases, producing four ranging measurements which are processed to determine uniquely the time delays undergone in every retransmission process. A minimization function is derived comparing repeater’s positions referred to at least two groups of three reference bases, providing the signal transit time at the repeater and propagation delays, providing the correct repeater position. The method is applicable to the transponder platform positioning and navigation, time synchronization of remote clocks, and location of targets. The algorithm has been demonstrated by simulations adopting a practical example with the transponder carried by an aircraft moving over bases on the ground.


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## Body

## 1. Introduction

A very well-known principle to determine indirectly the distance of a remote object utilizes the echo of a retransmitted signal. When applied to electromagnetic signals the accuracy of this method depends entirely on the knowledge of temporal effects due to four principal causes: (a) the signal speed propagation the medium causing path length variations; (b) propagation time at instruments, cables and connectors at the transmission; (c) propagation time at instruments, cables and connectors at the final reception; (d) time of signal transit at the remote transponder, which distance is to be determined.The cause (a) is generally well described by models for propagation in various media (ionosphere, troposphere) as well as in space (see e.g., [1–6], and references therein). The path length variations, however, depends on the elevation angle the object (carrying a repeater) is seen from the bases, which needs to be determined.Causes (b) and (c) are measured directly, with the high accuracy depending on the quality of the instruments that are utilized. The cause (d) however is undetermined since the remote object, carrying the transponder, is inaccessible for direct measurements. It undergoes changes in its internal signal propagation physical characteristics, which can change with time, or for each sequence of signals used to determine its distance. There are various long distance wireless transmission options using electromagnetic waves, such as the radio waves. The signals are sent to great distances using retransmission repeating links. At these links the signals are received, may or may not be stored or processed, be amplified, and then retransmitted at a frequency which may be the same, or different from the incoming frequency. As mentioned before, the signal transit time at the transponder is affected by several sources.Other known time changes on fast moving transponders may be neglected for velocities≪ the speed of light, because they produce effects much smaller in comparison to propagation and delays at the repeater. We refer to Doppler path change caused by frequency shifts in the direction of the repeater [7] and to relativistic effects relative to the reference system containing the sites to which the distances are to be determined, which become further accentuated when the satellites move over distinct gravity potentials relative to the geoid [8, 9].On the other hand, passive transponders, such as the signal scattering reflection by meteor trails in the VHF frequency band [7], may undergo significant phase delays which need to be taken into account for distance measurements.The precise knowledge of the time changes at each signal interaction at the transponder is an essential requirement for accurate ranging measurements, and applications in remote positioning, navigation, and time synchronization.The new method to determine delays compares the positions of a repeater in space referred to at least two distinct sets of three of the four reference bases on the ground, with known geographic coordinates. A range of tentative possible delay values is set in advance. For a single time-coded transmitted signal calculations of the repeater’s position are performed for different values assigned to the delays for each set of three reference bases on the ground. We show that the delays become determined as the repeater’s positions converge to the same value in relation to at least two distinct sets of three out of four ground-based reference bases, for every single time-coded transmitted pulse.


## 2. Time Delays Derived from the Repeater Positioning Referred to Ground Bases

The original concept system to determine a repeater’s position in space adopted three reference ground bases and a transponder of radio signals in space. It could be a passive natural radio reflection by meteor trails in the sky [10], or active signal repeaters carried by space platforms [11]. A geometric calculation method has been proposed for particular situations and when all time delays are known in advance [12]. The complete resolving algorithm for those systems, irrespective from any particular geometry, has been developed [13]. This algorithm, however, is totally dependent on the previous knowledge of signal time changes at the repeater in space, and on time delays due to propagation in the medium (atmosphere, ionosphere), which in practice are not known.A new method to determine the time variations at a repeater and signal propagation, for every signal interaction has been developed [14]. It overcomes the main difficulty limiting the practical use of the methods described before. The new system utilizes four reference bases on the ground (instead of three in the previous systems), A, B, C, and D, as illustrated in Figure 1, where R is the repeater in space, and P a target. All bases, and target P, are synchronized in time, to the best attainable accuracy.Figure 1
Simplified diagram showing the four reference bases on the groundA, B, C, D, the repeater R in the sky and the target P.At a given time, a coded signal is transmitted by reference baseA, received and retransmitted by R, received back at A, at reference bases B, C, and D, as well as at target P. The ranging measurements obtained for that given instant can be written as
(2.1)AR(δR,ΔpdAR)=(ΔtA-δAt-δAr-δR)(c2)-ΔpdAR,BR(δR,ΔpdAR,ΔpdBR)=(ΔtB-δAt-δBr-δR)c-AR(δR)-ΔpdBR-ΔpdAR,CR(δR,ΔpdAR,ΔpdCR)=(ΔtC-δAt-δCr-δR)c-AR(δR)-ΔpdCR-ΔpdAR,DR(δR,ΔpdAR,ΔpdDR)=(ΔtD-δAt-δDr-δR)c-AR(δR)-ΔpdDR-ΔpdAR,PR(δR,ΔpdAR,ΔpdPR)=(ΔtP-δAt-δPr-δR)c-AR(δR)-ΔpdPR-ΔpdAR,
which are dependent on the time delay at the repeater δR and on the respective propagation paths delays ΔpdAR, ΔpdBR, ΔpdCR, ΔpdDR, and ΔpdPR. AR, BR, CR, DR, and PR are the distances of bases A, B, C, D and of the target P to the repeater R, respectively, expressed as a function of time variations caused by the signal transit at the repeater δR, and corrected for the respective propagation path delays. ΔtA, ΔtB, ΔtC, ΔtD, and ΔtP are the time differences effectively measured at bases A, B, C, and D, as well as at the target P, respectively, with respect to their clocks; δAt is the time variation due to signal transit in circuits and cables when transmitted from base A, previously measured and known; δAr, δBr, δCr, δDr, and δPr are the time variations due to the signal transits on circuits and cables when received at bases A, B, C, D, and P, respectively, previously measured and known; c is the speed in free space of the electromagnetic waves that transport the coded time signal.Since the repeater’s position in the sky is not known in advance, the time variationsδR at the repeater and the path delays are, in practice, determined simultaneously. As we determine δR, the approximate repeater’s position is determined, and consequently the elevation angles seen from each one of the four bases are defined. These are needed to evaluate the propagation path delays for each distances AR, BR, CR, and DR. A propagation model in the medium must be selected to derive the delays and obtain the fully corrected repeater’s position. Therefore the values for path delays ΔpdAR, ΔpdBR, ΔpdCR, and ΔpdDR are added to the system of (2.1), which become a function of δR only. The value of ΔpdPR will be found similarly but afterwards, when the target position is to be determined.The coordinates of the repeater platformR are defined in the reference system illustrated in Figure 2. The system of (2.1) expressed as a function of δR only can be resolved using the known nonrecursive algorithm [13], after which
(2.2)xR(δR)={[AR(δR)]2-[BR(δR)]2+AB2}[2AB],yR(δR)={{[r1(δR)]2-[r2(δR)]2}[2yC]}+yC2,zR(δR)={[r1(δR)]2-[yR(δR)]2}1/2,
where
(2.3)[r1(δR)]2=[AR(δR)]2-[xR(δR)]2,[r2(δR)]2=[CR(δR)]2-[xC-xR(δR)]2.
On the other hand, adding the measurements obtained with bases A, B and D we get
(2.4)xR′(δR)={[AR(δR)]2-[BR(δR)]2+AB2}[2AB](equaltoxR(δR)insystem(2.2)),yR′(δR)={{[r1′(δR)]2-[r2′(δR)]2}[2yD]}+yD2,zR′(δR)={[r1′(δR)]2-[yR′(δR)]2}1/2,
where
(2.5)[r1′(δR)]2=[AR(δR)]2-[xR′(δR)]2(equalto[r1(δR)]2)insystem(2.3),[r2′(δR)]2=[DR(δR)]2-[(xD-xR′(δR)]2.
The two pair of systems of (2.2) and (2.3), and (2.4) and (2.5) allow us to find the differences in position for the repeater as a function of δR [14]:
(2.6)f(δR)=|[xR(δR),yR(δR),zR(δR)]-[xR′(δR),yR′(δR),zR′(δR)]|2=[xR(δR)-xR′(δR)]2+[yR(δR)-yR′(δR)]2+[zR(δR)-zR′(δR)]2.
The minimum value obtained for f(δR) with varying values of δR can be found by a number of well-known numerical calculation methods, such as by iterative procedures or by successive approximations, as it will be shown in the simulations later in this paper. The accuracy of δR determinations will be in the limit of the instrumental accuracies utilized for the coordinate’s determination with the two system of (2.2) and (2.3), and (2.4) and (2.5). The same procedure may be repeated simultaneously, using measurements at bases A, C, and D, improving the accuracy by averaging the two independent estimates for δR.Figure 2
Spherical and Euclidean coordinate systems for the reference bases,A, B, C, and D, the repeater, R and the target P.The path delays for each distanceAR, BR, CR, and DR, caused by propagation in the medium, ΔpdAR, ΔpdBR, ΔpdCR, and ΔpdDR, are derived at the same time redoing the calculations using the respective elevation angles the repeater is seen from each one of the four bases, which were determined within a good approximation in the first set of calculations as a function of δR only.The path delays are estimated by adopting an adequate propagation model, which differ for the frequency band used for the coded time signals transmissions. At higher SHF and EHF radio bands, for example, the corrections are primarily due to propagation in the lower atmosphere [2].The path delay corrections can be approximated using a plane parallel model for the atmosphere
(2.7)Δpd=cτatmsinH,
where c is the speed of light, τatm the atmosphere zenith delay, and H the repeater’s elevation angle with respect to the horizon as seen from the ground bases and by the target. At low frequency bands, at VHF and UHF and to a certain extent at L-band, the path delay corrections are mostly caused by propagation in the upper atmosphere, ionosphere, and plasmasphere [3].


## 3. Applications

### 3.1. Repeater’s Navigation

The values ofδR and of ΔpdAR, ΔpdBR, ΔpdCR, and ΔpdDR found with this method are introduced in the system of (2.2) or (2.4) to obtain the repeater’s actual coordinates, for each coded time interaction. The navigation of the platform is immediately derived from successive repeater’s positions determinations.


### 3.2. Synchronism of a Remote Clock

Every transmitted coded time signal will be also received at other targets, as the exampleP given in Figure 1. Assuming that the position coordinates of P is known, once the coordinates of the repeater R are determined, the segment PR becomes known in advance. Therefore the discrepancy between the local clock at P and the time received from the clock at the transmitter A can be written as
(3.1)ΔtP=ARc+PRc+δAt+δR+δPr+ΔpdAR+ΔpdPR,
where the segments AR and PR are measured by ranging, δAt and δPr are experimentally determined and known, and δR, ΔpdAR, and ΔpdPR are determined by the method described here. The clock time correction at P, needed for synchronization will be Δtp-Δp, where Δp is the theoretical correct time expected for the clock at position P.One example to illustrate this application is shown in Figure3. A repeater R is transported by an airplane, which is within the field of view of several actuators labeled L, M, N which geographic positions are known. These may be telecommunications retransmitters which essential requirement is to operate synchronized to prevent cross-talks and mutual message garbling interferences. The precision of clock corrections can be close to the accuracy attained in the synchronization of reference bases A, B, C, and D.Figure 3
A time signal repeaterR carried by an aircraft referred to reference bases A, B, C, and D, can synchronize remote actuators at known geographic positions L, M, and N.


### 3.3. Remote Target Location

We shall now assume that the remote targetP (Figure 2) coordinates are not known and should be determined by this method. The distance from the repeater R, PR, can be determined by a single time interaction, provided that (a) the clock at P is sufficiently well synchronized with respect to the reference bases A, B, C, and D and (b) the temporal change of the coded time signal at the repeater δR and the propagation path delays are determined accordingly to the method demonstrated here. The coordinates of P can be determined univocally by obtaining four different measurements of its distance to the repeater R, located at four distinct positions and instants, provided that the respective repeaters’ positions are not part of a straight line. The analytical procedures are the same given by Kaufmann et al. [13]. The calculations expressed by (2.1), (2.2), and (2.3) are repeated referring to one set of three reference bases, including A where the time code transmitter is located (i.e., A, B, C, or A, B, D, or A, C, D). We obtain the equations for four spheres which intersections give the coordinates of the target P.


## 3.1. Repeater’s Navigation

The values ofδR and of ΔpdAR, ΔpdBR, ΔpdCR, and ΔpdDR found with this method are introduced in the system of (2.2) or (2.4) to obtain the repeater’s actual coordinates, for each coded time interaction. The navigation of the platform is immediately derived from successive repeater’s positions determinations.


## 3.2. Synchronism of a Remote Clock

Every transmitted coded time signal will be also received at other targets, as the exampleP given in Figure 1. Assuming that the position coordinates of P is known, once the coordinates of the repeater R are determined, the segment PR becomes known in advance. Therefore the discrepancy between the local clock at P and the time received from the clock at the transmitter A can be written as
(3.1)ΔtP=ARc+PRc+δAt+δR+δPr+ΔpdAR+ΔpdPR,
where the segments AR and PR are measured by ranging, δAt and δPr are experimentally determined and known, and δR, ΔpdAR, and ΔpdPR are determined by the method described here. The clock time correction at P, needed for synchronization will be Δtp-Δp, where Δp is the theoretical correct time expected for the clock at position P.One example to illustrate this application is shown in Figure3. A repeater R is transported by an airplane, which is within the field of view of several actuators labeled L, M, N which geographic positions are known. These may be telecommunications retransmitters which essential requirement is to operate synchronized to prevent cross-talks and mutual message garbling interferences. The precision of clock corrections can be close to the accuracy attained in the synchronization of reference bases A, B, C, and D.Figure 3
A time signal repeaterR carried by an aircraft referred to reference bases A, B, C, and D, can synchronize remote actuators at known geographic positions L, M, and N.


## 3.3. Remote Target Location

We shall now assume that the remote targetP (Figure 2) coordinates are not known and should be determined by this method. The distance from the repeater R, PR, can be determined by a single time interaction, provided that (a) the clock at P is sufficiently well synchronized with respect to the reference bases A, B, C, and D and (b) the temporal change of the coded time signal at the repeater δR and the propagation path delays are determined accordingly to the method demonstrated here. The coordinates of P can be determined univocally by obtaining four different measurements of its distance to the repeater R, located at four distinct positions and instants, provided that the respective repeaters’ positions are not part of a straight line. The analytical procedures are the same given by Kaufmann et al. [13]. The calculations expressed by (2.1), (2.2), and (2.3) are repeated referring to one set of three reference bases, including A where the time code transmitter is located (i.e., A, B, C, or A, B, D, or A, C, D). We obtain the equations for four spheres which intersections give the coordinates of the target P.


## 4. Simulations

### 4.1. The Performance of the New System and Process

A new software has been developed to demonstrate the method performance and simulate practical measurements [15]. For the application we used the programming language of MATLAB software, version R2010a [16].As a practical example, we conceived a regional framework, with a transponder carried by an aircraft. To represent the ground-based reference bases we have selected four cities in São Paulo state, Brazil: São Paulo, Itú, Campinas, and Bragança Paulista. The city of Atibaia, in the same state, has been selected to simulate the targetP. The known locations for each city are shown in Table 1. The bases, target, and estimated location for the repeater are shown in map given in Figure 4. The aircraft with the transponder was flying at an altitude of about 6 km close to the city of Jundiaí, also shown in Figure 4. For simulation purpose, we arbitrarily assigned four positions for the aircraft/repeater, shown in Table 2.Table 1
Geographic precise locations and altitudes of reference bases and target used in simulations, illustrated in Figure5.
City
Element
Latitude
Longitude
Altitude (m)
São Paulo
BaseA
−23°32′51′′
−46°37′33′′
730
Itú
BaseB
−23°15′51′′
−47°17′57′′
583
Campinas
BaseC
−22°54′20′′
−47°03′39′′
855
Bragança Paulista
BaseD
−22°57′07′′
−46°32′31′′
817
Atibaia
TargetP
−23°07′01′′
−46°33′01′′
803Table 2
The repeater’s positions and altitudes carried by an aircraft, over the city of Jundiaí (see Figure5).
City
Positions
Latitude
Longitude
Altitude (m)
Jundiaí
Position 1
−23°11′11′′
−46°53′03′′
5761
Jundiaí
Position 2
−23°11′11′′
−46°59′03′′
6000
Jundiaí
Position 3
−23°15′11′′
−46°53′03′′
6200
Jundiaí
Position 4
−23°15′11′′
−46°59′03′′
6800Figure 4
A Google map showing the preselected cities used in simulations, with reference basesA, B, C, and D and the target P. The repeater R is carried by an aircraft flying around the indicated city.To proceed with simulations the position coordinates shown in Tables1 and 2 were converted into the ECEF (Earth-Centered, Earth-Fixed) coordinates system, using datum WGS84 [17–19] for the reference ellipsoid. The location of a point in this system can be done in coordinates (x,y,z). The origin of axes (0,0,0) is the center of the Earth, the axis Z points to the North, axis X points to Greenwich meridian (where latitude = 0 degrees). The altitude is taken as the distance perpendicular and above the surface of the ellipsoid [17–19]. The flow diagrams utilized in the new software applications are shown in Figures 5 and 6.Flow diagrams showing the main routine (a), the target position calculation, (b) and clock synchronization (c).
(a)
(b)
(c)Figure 6
Flow diagram to calculate the transit time at the repeater, the path delays, and the repeater’s position at four instants.For the simulations we have adopted a fixed value for the well-measured delays due to the signal passing through the electronics, cables, and connectors, both on transmission and on reception at each reference base and at the target. The same value was adopted for all prefixed delays,δAt, δAr, δAr, δBr, δCr, δDr, δPr=0.0001 ms.In order to compare with the simulated calculations, we have preestablished estimated values for the transmission times from the emitting base to the repeater, from the repeater to the reference bases and the target, for every successive repeater’s positions. Adopting a hypothetical delay at the repeater equal to 200 ns (δR), c=299792458 m/s, the total times (ΔtA, ΔtB, ΔtC, ΔtD, and ΔtP) can be calculated the following system of equations (derived from (2.1)):
(4.1)ΔtA=AR(δR)c+AR(δR)c+δAt+δR+δAr,ΔtB=AR(δR)c+BR(δR)c+δAt+δR+δAr,ΔtC=AR(δR)c+CR(δR)c+δAt+δR+δAr,ΔtD=AR(δR)c+DR(δR)c+δAt+δR+δAr,ΔtP=AR(δR)c+PR(δR)c+δAt+δR+δAr,
where the path delays were neglected in this step of the simulations. Adopting the information on the reference bases positions, delays at the bases, and transmission times, it was possible to simulate the whole process and determine the time delay at the repeater and its positions at four successive instants. Once the repeater’s positions are determined it was possible to simulate the target position determination.The first step was to calculate the repeater’s position at the initial instant, using basesA, B, and C, according to (2.2) and (2.3), and adopting a given initial value for δR. In the next step the calculation was repeated using bases A, B, and D, according to (2.4) and (2.5), and, similarly, using bases A, C, and D. We will find three different positions for the repeater (R1, R2, and R3) for each adopted value of δR. The error in the repeater’s positioning has been calculated by the following equation:
(4.2)error=∥R1-R2∥+∥R2-R3∥+∥R3-R1∥.This calculation (also known as objective function) has been repeated several times, for different adopted values ofδR, using the MATLAB fmincon function, which provides the error minimization. The minimization process has been done starting with an initial value for δR and setting an upper and lower range for its variation. For this simulation we have adopted an initial value of 1 μs, with lower and upper limits of 0 and 100 μs, respectively. The correct time delay δR at the repeater is found at the end of the minimization process.The whole process has been repeated for three more positions of the repeater, to allow the target position determination, using the known algorithm [13]. The results obtained were very close to the real preestablished values. The delay obtained at the repeater was of 199.999995 ns, very close to the preestablished value to obtain the transmission times (that was of 200 ns). The minimization process gave repeater’s position error of about 0.001 mm.Tables3 and 4 show the simulated position calculations for the repeater and for the target, respectively. Comparing these results with the preestablished values set in Tables 1 and 2, we can see that the approximations are very good. The error in the target altitude, for example, is only 0.002 mm. Errors in latitude and longitude are less than 10−8 arcseconds. These initial calculations demonstrate the functionality of the method.Table 3
Simulated calculations for the repeater’s positions, corrected for transit times and path delays added.
City
Positions
Latitude
Longitude
Altitude (m)
Jundiaí
Position 1
−23°11′10.99999999973079′′
−46°53′03.00000000022578′′
5761.0000008372590
Jundiaí
Position 2
−23°11′10.99999999990985′′
−46°59′03.00000000035880′′
6000.0000002672896
Jundiaí
Position 3
−23°15′11.00000000065677′′
−46°53′03.00000000022578′′
6200.0000010607764
Jundiaí
Position 4
−23°15′11.00000000052887′′
−46°59′03.00000000110060′′
6800.0000007525086Table 4
Simulated calculations for the target position, corrected for transit times at the repeater and path delays added.
City
Latitude
Longitude
Altitude (m)
Atibaia
−23°07′00.99999999971089′′
−46°33′00.99999999755028′′
803.00000067241490


### 4.2. Estimate of Path Delays

The time delays due to the signal propagation in the medium were introduced in the following step. For the present simulations we shall assume radio frequencies in the range of several GHz (e.g., in the S band), for which the delays are dominated by propagation in the terrestrial troposphere. They can be approximately described by (2.7). We have assumed with Honma et al. [2] a typical sea level Δpd of about 2.3 m, for the dry component only. The calculations of delays at the repeater, of the repeater’s position, and propagation path delays relative to each base were simulated by simultaneous iterations since there variable are interdependent.With the initially adopted path delay equal to zero, the successive approximations in the minimization process allowed the determination ofδR, for which the repeater’s position was determined, as well as the elevation angles the repeater was observed from each reference base, and the respective path delay length calculated. The path delay lengths were then added to obtain a new position for the repeater. The process has been repeated until obtaining the convergence of values. Details on this process are shown in the flow diagram of Figure 6. Comparing the values found in this phase with the preestablished values we find that the approximations remain excellent, with discrepancies in the repeater’s position and in the target position less than 10−3 mm (see Tables 3 and 4).


### 4.3. Clock Synchronism

The time of arrival of the transmitted time coded signal at a target with known coordinates permits the synchronization of the clock at that location. The time elapsed for the coded time signal to travel from the instant of transmission to the target at known position can be calculated using (3.1). The obtained time difference can be used to synchronize the target’s clock to the clock at the transmitting base.The results obtained from simulations are excellent. Assuming the clocks of the system perfectly synchronized, the ideal error at the receiving location is practically zero (i.e., less than 10−15 nanoseconds).


### 4.4. Estimate of Uncertainties

The practical source of uncertainties of the determinations is related to errors in clocks and/or in delays miscalculations. The two sources can be added together within a certain range of uncertainty.To perform simulations on the clocks (and/or delays) uncertainties, we first set the determinations ofδR and of path delays using the system and method described above. We have next generated random values for clock/delay uncertainties at the four reference bases and at the target, within a plausible time interval. The propagation of errors due to the clock synchronism uncertainties on the repeater’s position, on the target location and on the clock synchronism, are exhibited in Figure 7 for ±5 ns, as an example. The plots correspond to 1000 randomly generated delay values, for four repeater’s positions. For each delay it was determined the repeater’s position, the target position and the clock synchronization accuracy. The most typical errors found for clock uncertainties of ±5 ns are of less than 2 meters in the repeater’s position, of tens of meters for the target location, and of few ns on clock synchronization.Example of errors caused by clock uncertainties, which may include the path delays errors, for a range of ±5 ns. In (a) the effect in the repeater position; (b) the error on the target location; (c) the error in clock synchronization.
(a)
(b)
(c)


### 4.5. Concluding Remarks

The present georeferencing system and method of calculations, using four reference bases at known locations on the ground and a remote transponder in space, permits the calculations of time delays of signals transiting by the repeater, and other caused by the signal propagation in the medium. The system and method allows the navigation of the repeater, remote target positioning and remote clock synchronization with very high accuracy. The simulations demonstrate the analytical performance of proposed algorithm on practical application with a transponder carried by an aircraft. The main sources of uncertainties are the clocks synchronism at the reference bases and the target.The main scope of the system presented here is to make available an alternate method based on a concept distinct from other well-known georeferencing systems, such as the GPS and similar systems (which reference bases are at the satellites in the sky) and the Doppler based methods (based on velocity and range measured with respect of low orbit satellites moving in relation to the targets). The new method may serve as a backup for the existing systems, at situations that require double checking of georeferencing parameters, but it can also function independently from the other.Therefore the comparison between the simulated results obtained here with the new system and other systems must be taken as just illustrative, partial, and preliminary. The Doppler based systems, such Argos [20] require long time to make position determinations, because many measurements must be taken as the satellite moves to produce the location cones. The position uncertainties for a target, or inversely, for the satellite, are of the order or larger than hundred meters. The accuracy can be improved processing data for several orbital passes. These systems are not applicable for remote clock synchronization. The GPS system typical target positioning accuracies without processing are of the order of 15–30 meters [21]. The GPS clock synchronization best accuracies for civilian “unauthorized” are in the sub microsecond [22, 23]. It can be considerably improved with receivers employing dual frequency receivers [24]. The simulation of new method presented here, assumed arbitrarily a base and target clock synchronization ±5 ns. In this condition the method simulated performance is superior for remote clock synchronization. The target position determined with the new method requires four successive measurements (for a single repeater) exhibiting inaccuracies larger compared to GPS. However, it could be considerably improved, setting a better base and target clock synchronization. The comparison to GPS is not applicable for the repeater positioning, which is characteristic of the new method presented here.A relevant application for this new system is the preliminary determination of satellite orbits. Assuming a repeater placed in an artificial satellite and a favorable geometry its position can be determined for every time mark interaction with the same errors or uncertainties found for repeaters at lower altitudes, shown here. A study on satellite orbital applications is currently being developed for future publication.


## 4.1. The Performance of the New System and Process

A new software has been developed to demonstrate the method performance and simulate practical measurements [15]. For the application we used the programming language of MATLAB software, version R2010a [16].As a practical example, we conceived a regional framework, with a transponder carried by an aircraft. To represent the ground-based reference bases we have selected four cities in São Paulo state, Brazil: São Paulo, Itú, Campinas, and Bragança Paulista. The city of Atibaia, in the same state, has been selected to simulate the targetP. The known locations for each city are shown in Table 1. The bases, target, and estimated location for the repeater are shown in map given in Figure 4. The aircraft with the transponder was flying at an altitude of about 6 km close to the city of Jundiaí, also shown in Figure 4. For simulation purpose, we arbitrarily assigned four positions for the aircraft/repeater, shown in Table 2.Table 1
Geographic precise locations and altitudes of reference bases and target used in simulations, illustrated in Figure5.
City
Element
Latitude
Longitude
Altitude (m)
São Paulo
BaseA
−23°32′51′′
−46°37′33′′
730
Itú
BaseB
−23°15′51′′
−47°17′57′′
583
Campinas
BaseC
−22°54′20′′
−47°03′39′′
855
Bragança Paulista
BaseD
−22°57′07′′
−46°32′31′′
817
Atibaia
TargetP
−23°07′01′′
−46°33′01′′
803Table 2
The repeater’s positions and altitudes carried by an aircraft, over the city of Jundiaí (see Figure5).
City
Positions
Latitude
Longitude
Altitude (m)
Jundiaí
Position 1
−23°11′11′′
−46°53′03′′
5761
Jundiaí
Position 2
−23°11′11′′
−46°59′03′′
6000
Jundiaí
Position 3
−23°15′11′′
−46°53′03′′
6200
Jundiaí
Position 4
−23°15′11′′
−46°59′03′′
6800Figure 4
A Google map showing the preselected cities used in simulations, with reference basesA, B, C, and D and the target P. The repeater R is carried by an aircraft flying around the indicated city.To proceed with simulations the position coordinates shown in Tables1 and 2 were converted into the ECEF (Earth-Centered, Earth-Fixed) coordinates system, using datum WGS84 [17–19] for the reference ellipsoid. The location of a point in this system can be done in coordinates (x,y,z). The origin of axes (0,0,0) is the center of the Earth, the axis Z points to the North, axis X points to Greenwich meridian (where latitude = 0 degrees). The altitude is taken as the distance perpendicular and above the surface of the ellipsoid [17–19]. The flow diagrams utilized in the new software applications are shown in Figures 5 and 6.Flow diagrams showing the main routine (a), the target position calculation, (b) and clock synchronization (c).
(a)
(b)
(c)Figure 6
Flow diagram to calculate the transit time at the repeater, the path delays, and the repeater’s position at four instants.For the simulations we have adopted a fixed value for the well-measured delays due to the signal passing through the electronics, cables, and connectors, both on transmission and on reception at each reference base and at the target. The same value was adopted for all prefixed delays,δAt, δAr, δAr, δBr, δCr, δDr, δPr=0.0001 ms.In order to compare with the simulated calculations, we have preestablished estimated values for the transmission times from the emitting base to the repeater, from the repeater to the reference bases and the target, for every successive repeater’s positions. Adopting a hypothetical delay at the repeater equal to 200 ns (δR), c=299792458 m/s, the total times (ΔtA, ΔtB, ΔtC, ΔtD, and ΔtP) can be calculated the following system of equations (derived from (2.1)):
(4.1)ΔtA=AR(δR)c+AR(δR)c+δAt+δR+δAr,ΔtB=AR(δR)c+BR(δR)c+δAt+δR+δAr,ΔtC=AR(δR)c+CR(δR)c+δAt+δR+δAr,ΔtD=AR(δR)c+DR(δR)c+δAt+δR+δAr,ΔtP=AR(δR)c+PR(δR)c+δAt+δR+δAr,
where the path delays were neglected in this step of the simulations. Adopting the information on the reference bases positions, delays at the bases, and transmission times, it was possible to simulate the whole process and determine the time delay at the repeater and its positions at four successive instants. Once the repeater’s positions are determined it was possible to simulate the target position determination.The first step was to calculate the repeater’s position at the initial instant, using basesA, B, and C, according to (2.2) and (2.3), and adopting a given initial value for δR. In the next step the calculation was repeated using bases A, B, and D, according to (2.4) and (2.5), and, similarly, using bases A, C, and D. We will find three different positions for the repeater (R1, R2, and R3) for each adopted value of δR. The error in the repeater’s positioning has been calculated by the following equation:
(4.2)error=∥R1-R2∥+∥R2-R3∥+∥R3-R1∥.This calculation (also known as objective function) has been repeated several times, for different adopted values ofδR, using the MATLAB fmincon function, which provides the error minimization. The minimization process has been done starting with an initial value for δR and setting an upper and lower range for its variation. For this simulation we have adopted an initial value of 1 μs, with lower and upper limits of 0 and 100 μs, respectively. The correct time delay δR at the repeater is found at the end of the minimization process.The whole process has been repeated for three more positions of the repeater, to allow the target position determination, using the known algorithm [13]. The results obtained were very close to the real preestablished values. The delay obtained at the repeater was of 199.999995 ns, very close to the preestablished value to obtain the transmission times (that was of 200 ns). The minimization process gave repeater’s position error of about 0.001 mm.Tables3 and 4 show the simulated position calculations for the repeater and for the target, respectively. Comparing these results with the preestablished values set in Tables 1 and 2, we can see that the approximations are very good. The error in the target altitude, for example, is only 0.002 mm. Errors in latitude and longitude are less than 10−8 arcseconds. These initial calculations demonstrate the functionality of the method.Table 3
Simulated calculations for the repeater’s positions, corrected for transit times and path delays added.
City
Positions
Latitude
Longitude
Altitude (m)
Jundiaí
Position 1
−23°11′10.99999999973079′′
−46°53′03.00000000022578′′
5761.0000008372590
Jundiaí
Position 2
−23°11′10.99999999990985′′
−46°59′03.00000000035880′′
6000.0000002672896
Jundiaí
Position 3
−23°15′11.00000000065677′′
−46°53′03.00000000022578′′
6200.0000010607764
Jundiaí
Position 4
−23°15′11.00000000052887′′
−46°59′03.00000000110060′′
6800.0000007525086Table 4
Simulated calculations for the target position, corrected for transit times at the repeater and path delays added.
City
Latitude
Longitude
Altitude (m)
Atibaia
−23°07′00.99999999971089′′
−46°33′00.99999999755028′′
803.00000067241490


## 4.2. Estimate of Path Delays

The time delays due to the signal propagation in the medium were introduced in the following step. For the present simulations we shall assume radio frequencies in the range of several GHz (e.g., in the S band), for which the delays are dominated by propagation in the terrestrial troposphere. They can be approximately described by (2.7). We have assumed with Honma et al. [2] a typical sea level Δpd of about 2.3 m, for the dry component only. The calculations of delays at the repeater, of the repeater’s position, and propagation path delays relative to each base were simulated by simultaneous iterations since there variable are interdependent.With the initially adopted path delay equal to zero, the successive approximations in the minimization process allowed the determination ofδR, for which the repeater’s position was determined, as well as the elevation angles the repeater was observed from each reference base, and the respective path delay length calculated. The path delay lengths were then added to obtain a new position for the repeater. The process has been repeated until obtaining the convergence of values. Details on this process are shown in the flow diagram of Figure 6. Comparing the values found in this phase with the preestablished values we find that the approximations remain excellent, with discrepancies in the repeater’s position and in the target position less than 10−3 mm (see Tables 3 and 4).


## 4.3. Clock Synchronism

The time of arrival of the transmitted time coded signal at a target with known coordinates permits the synchronization of the clock at that location. The time elapsed for the coded time signal to travel from the instant of transmission to the target at known position can be calculated using (3.1). The obtained time difference can be used to synchronize the target’s clock to the clock at the transmitting base.The results obtained from simulations are excellent. Assuming the clocks of the system perfectly synchronized, the ideal error at the receiving location is practically zero (i.e., less than 10−15 nanoseconds).


## 4.4. Estimate of Uncertainties

The practical source of uncertainties of the determinations is related to errors in clocks and/or in delays miscalculations. The two sources can be added together within a certain range of uncertainty.To perform simulations on the clocks (and/or delays) uncertainties, we first set the determinations ofδR and of path delays using the system and method described above. We have next generated random values for clock/delay uncertainties at the four reference bases and at the target, within a plausible time interval. The propagation of errors due to the clock synchronism uncertainties on the repeater’s position, on the target location and on the clock synchronism, are exhibited in Figure 7 for ±5 ns, as an example. The plots correspond to 1000 randomly generated delay values, for four repeater’s positions. For each delay it was determined the repeater’s position, the target position and the clock synchronization accuracy. The most typical errors found for clock uncertainties of ±5 ns are of less than 2 meters in the repeater’s position, of tens of meters for the target location, and of few ns on clock synchronization.Example of errors caused by clock uncertainties, which may include the path delays errors, for a range of ±5 ns. In (a) the effect in the repeater position; (b) the error on the target location; (c) the error in clock synchronization.
(a)
(b)
(c)


## 4.5. Concluding Remarks

The present georeferencing system and method of calculations, using four reference bases at known locations on the ground and a remote transponder in space, permits the calculations of time delays of signals transiting by the repeater, and other caused by the signal propagation in the medium. The system and method allows the navigation of the repeater, remote target positioning and remote clock synchronization with very high accuracy. The simulations demonstrate the analytical performance of proposed algorithm on practical application with a transponder carried by an aircraft. The main sources of uncertainties are the clocks synchronism at the reference bases and the target.The main scope of the system presented here is to make available an alternate method based on a concept distinct from other well-known georeferencing systems, such as the GPS and similar systems (which reference bases are at the satellites in the sky) and the Doppler based methods (based on velocity and range measured with respect of low orbit satellites moving in relation to the targets). The new method may serve as a backup for the existing systems, at situations that require double checking of georeferencing parameters, but it can also function independently from the other.Therefore the comparison between the simulated results obtained here with the new system and other systems must be taken as just illustrative, partial, and preliminary. The Doppler based systems, such Argos [20] require long time to make position determinations, because many measurements must be taken as the satellite moves to produce the location cones. The position uncertainties for a target, or inversely, for the satellite, are of the order or larger than hundred meters. The accuracy can be improved processing data for several orbital passes. These systems are not applicable for remote clock synchronization. The GPS system typical target positioning accuracies without processing are of the order of 15–30 meters [21]. The GPS clock synchronization best accuracies for civilian “unauthorized” are in the sub microsecond [22, 23]. It can be considerably improved with receivers employing dual frequency receivers [24]. The simulation of new method presented here, assumed arbitrarily a base and target clock synchronization ±5 ns. In this condition the method simulated performance is superior for remote clock synchronization. The target position determined with the new method requires four successive measurements (for a single repeater) exhibiting inaccuracies larger compared to GPS. However, it could be considerably improved, setting a better base and target clock synchronization. The comparison to GPS is not applicable for the repeater positioning, which is characteristic of the new method presented here.A relevant application for this new system is the preliminary determination of satellite orbits. Assuming a repeater placed in an artificial satellite and a favorable geometry its position can be determined for every time mark interaction with the same errors or uncertainties found for repeaters at lower altitudes, shown here. A study on satellite orbital applications is currently being developed for future publication.



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*Source: 595823-2012-10-17.xml*