# Simultaneous Altitude and RCS Estimation with Propagation Attenuation in Bistatic HFSWR

Authors: Zhao Kongrui; Yu Changjun; Zhou Gongjian; Quan Taifan
Journal: International Journal of Antennas and Propagation
 (2013)

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## Abstract

High frequency surface wave radar (HFSWR) is traditionally unable to detect target altitude information. To simultaneously estimate the target altitude and radar cross-sections (RCS) with bistaticT/R-R HFSWR, a novel estimation model is proposed with the variation of the propagation attenuation, and the target echoes are utilized to construct the measurement equation. The presented model is completely observable to the target state, which can contribute to preferable estimation results. In order to improve the estimation accuracy, a centralized fusion model is adopted to fuse four measurement vectors. Simulations and practical examples demonstrate the effectiveness of the proposed estimation model.


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## Body

## 1. Introduction

High frequency surface wave radar (HFSWR) transmits vertically polarized electromagnetic waves to track ships and aircrafts at ranges of several hundreds of kilometers [1, 2]. It has been extensively applied to exclusive economic zone surveillance [3, 4] and remote sensing [5–8]. The use of the frequencies makes it difficult to form a narrow beam on elevation; HFSWR is traditionally unable to detect the target altitude information.Many altitude estimation methods have been proposed for monostatic radar. However, all of these models are low observable; the incorrect initial altitude value would lead to large estimation errors. In order to eliminate this drawback, [9] proposed an autonomous multiple model method named Height-parameterized extended kalman filter (HPEKF) for 3D tracking with monostatic 2D radar. It was inspired by the range-parameterized EKF in bearing only tracking. In HPEKF, the main idea is that the altitude interval of interest is divided into a number of subintervals, and each subinterval deals with an independent EKF. The target state and covariance are obtained by performing weighted sum of individual estimates and covariance matrix, respectively. It means that the initial state is represented by a Gaussian mixture, each mixture component is initialized by an assumed initial altitude and tracked with an EKF. It is worthwhile to note that some of the EKFs will lead to divergence without mixture step between the independent components. In order to alleviate the drawbacks of the incorrect initialization, an initial altitude estimator with Newton iteration method was presented [10], which assumes that the aircraft flies with nearly constant velocity and altitude, and it hardly meets the real flying situation. This method can provide an accurate initial state when the measurement errors are small. Nevertheless, it is sensitive to the measurement errors, which will lead to worse results in HFSWR. An extend Kalman filter (EKF) method was proposed to estimate the altitude and RCS real time in [11]; the measurement equation is constructed with the target echo amplitude, which is the function of altitude and RCS. This model has several serious flaws; it is low observable and sensitive to the initial state. The filter would lead to divergence if the model is initialized with large error.Multilateration method and maximum likelihood estimation are two common approaches to estimate target altitude in bistatic radar system [12, 13]. Although multilateration method is intuitive to compute the altitude of aircraft, the result usually fluctuates intensely. Maximum likelihood estimation could reach a theoretical optimal solution; the flaw is that it converges slowly and cannot provide a global optimum in most cases. Besides, these prevailing methods could not provide an approach to estimate the radar cross-section (RCS) of aircraft.The RCS of aircraft is also essential to the target classification. Little attention has been paid to the RCS estimation in HFSWR field. Current aircraft tracking methods are mainly based on range, azimuth, and radial velocity information; it is hardly able to extract the aircraft RCS without incorporating the target echo information and propagation attenuation of ground wave. The target echoes can be represented as the function of propagation attenuation and RCS, and there are different propagation attenuations at corresponding altitudes. The two properties could provide an altitude and RCS estimation capability.In this paper, a simultaneous altitude and target RCS estimation model is proposed through the variance of propagation attenuation. The amplitude of target echoes is utilized to construct the measurement equation, which is the nonlinear function of the altitude and RCS. Four measurement vectors are established with range, azimuth, and echo amplitude. Centralized fusion EKF model is adopted to further improve the estimation performance. Monte Carlo simulations illustrate the effectiveness and benefits of this proposed model.The rest of the paper is presented as follows. Section2 analyzes the relation between ground wave propagation attenuation and target altitude. A simultaneous altitude and RCS estimation model is described with centralized fusion estimation model in Section 3. In Section 4, Monte Carlo simulations and practical examples are performed to demonstrate the benefits of the proposed estimation model. Section 5 concludes the paper.


## 2. HF Ground Wave Propagation Attenuation

FromT/R-R HFSWR equation, the echo amplitude corresponding to T/R station can be defined as
(1)Ptr=PtGt1lb2(Rt,h)σt(λ2/4π)Gr,
where Pt is the transmitted signal amplitude and Gt and Gr are the gains of transmitter and receiver, respectively. lb(·) represents the ground wave propagation attenuation, Rt is the target range to T/R station, and h denotes the target altitude. The wavelength of HFSWR is λ, and σt is the target RCS corresponding to T/R station. Equation (1) in log can be expressed as
(2)Ptr(dB)=-20log(lb(Rt,h))+10log(σt)+10log(C),
where
(3)C=PtGtGr(λ2/4π).If the radar parameters are fixed,C represents a constant.The echo amplitude corresponding toR station is presented as
(4)Prr=PtGt1lb(Rt,h)σr(λ2/4π)1lb(ρ-Rt,h)Gr,
where σr and ρ are the RCS and the range sum corresponding to R station, respectively. Equation (4) in log can be expressed as
(5)Prr(dB)=-10log(lb(Rt,h))-10log(lb(ρ-Rt,h))+10log(σr)+10log(C).From (1) and (5), it shows that the echoes of an aircraft are the function of target RCS and propagation attenuation. The attenuation is related to the radar wavelength and the altitude of the target; it can be written as
(6)lb=20log|U0U|,
where U0 is the Hertz vector and U is the Hertz vector of free space. In order to analyze the propagation attenuation of the ground wave, Rotheram attenuation model is utilized [14, 15].Whend>0.4λ1/3a2/3 and h1≤h2<λ2/3a1/3, the Hertz vector can be defined as
(7)U=exp(-jkdm0)adsin(d/a)(wd+ww+wg),
where a is the Earth’s radius and h1 and h2 are the antenna’s height and target altitude, respectively. m0 is the modified refractive index of the ground. wd represents the direct wave, ww is the reflected wave in the limit Δ→∞, and Δ denotes the normalized surface impedance. wg represents the combined reflected and surface waves.Under the conditions thatd>0.4λ1/3a2/3 and h1≤h2<λ2/3a1/3, the Hertz vector is expressed as
(8)U=8πk3exp(-jπ/2)asin(d/a)×∑exp(-jkdSn)Ψ(2)(Sn,0)g(2)(Sn,H1)g(2)(Sn,0)g(2)(Sn,H2)g(2)(Sn,0),
where the quantity Ψ(2)(Sn,0) is the excitation factor for the nth mode. g(2)(S,H) is defined as the outgoing-wave height-gain function. H1 and H2 are the modified height of h1 and h2, respectively.If the target altitude is high, the Hertz vector is computed with geometrical-optics formulas; it is computed as(9)U=U1+U3,d≤dt,U=U2+U3,d>dt,
where dt is the transformation distance in which U1=U2.U1 is the direct ray when d≤dt, U2 represents the direct ray with d>dt, and U3 is defined as the reflected ray.The relations between propagation attenuation and different target altitudes are illustrated in Figure1, in which the radar frequency is 14 MHz. The target altitude varies from 0.5 km to 3 km and the range is changing from 50 km to 140 km.Figure 1
Propagation attenuation with different altitude.The propagation attenuation in Figure1 is computed by Rotheram attenuation model, which includes the effect of the atmospheric refraction. From Figure 1, it demonstrates that the propagation attenuation varies depending on target altitude, and there will be large propagation attenuation when the aircraft is low flying. While the altitude increases, the attenuation is weakened. As the propagation attenuation is the function of the range and altitude of the aircraft, therefore, the target echo amplitude is also relevant to target altitude and RCS. The radar would receive a more weakened echo when the aircraft is low flying. With these aforementioned properties, a simultaneous RCS and altitude estimation model is ready to be constructed in bistatic T/R-R HFSWR.


## 3. Simultaneous Altitude and RCS Fusion Estimation Model

In this section, a novel model would be established to estimate the target altitude and RCS. The state vector is defined as(10)X(k)=[x(k),vx(k),y(k),vy(k),z(k),vz(k),Xcmn(k)σt(k),vσt(k),σr(k),vσr(k)]T,
where x(k), y(k), and z(k) are the target positions along x, y, and z directions at time k. vx(k), vy(k) and vz(k) represent the velocities in three directions, respectively. σt(k) and σr(k), are the target RCS corresponding to the T/R and R stations at time k; the rates of change of RCS are denoted as vσt(k) and vσr(k), respectively.The state equation is given by(11)X(k)=FX(k-1)+v(k-1),
where F∈R10×10 is the state transition matrix. v(k-1) represents the zero mean Gaussian random process noise with known covariance Q(k-1). In order to improve the estimation accuracy, four measurement vectors are established:
(12)Z1(k)=[Rt(k),ρ(k),θt(k),Ptr,Prr]T,Z2(k)=[Rt(k),ρ(k),θr(k),Ptr,Prr]T,Z3(k)=[Rt(k),θr(k),θt(k),Ptr,Prr]T,Z4(k)=[ρ(k),θr(k),θt(k),Ptr,Prr]T.It demonstrates that the target echoes information is incorporated into the measurements. The abovementioned four measurements are the nonlinear functions of stateX(k). The measurement equation for each measurement vector can be modeled as
(13)Zi(k)=hi(X(k))+wi(k),
where hi(·) denotes the nonlinear measurement function. Consider that wi(k), i=1,2,3,4 are assumed to be mutually independent zero mean Gaussian random noises with known covariance Ri(k). That means that
(14)E[wi(k)wjT(k)]=0,i≠j,i,j=1,2,3,4.
The range and azimuth information can be expressed as the functions of the state. They are denoted as
(15)Rt(k)=(x(k)-xt)2+(y(k)-yt)2+(z(k)-zt)2,ρ(k)=(x(k)-xr)2+(y(k)-yr)2+(z(k)-zr)2ρ(k)=+Rt(k),θr(k)=arctan(y(k)-yrx(k)-xr),θt(k)=arctan(y(k)-ytx(k)-xt),
where (xt,yt,zt) and (xr,yr,zr) are the locations of T/R and R stations. θt(k) and θr(k) represent the azimuths corresponding to T/R and R stations, respectively. For each measurement vector, (11) and (13) define the estimation model of target altitude and RCS.An appropriate fusion of four measurements can contribute to higher accuracy of estimation; therefore, the centralized extended Kalman filter estimator is adopted to fuse four measurements. The fused state can be expressed as(16)X^(k,k)=X^(k,k-1)+∑i=1NKi[Zi(k)-hi(X^(k,k-1))],
where N is the number of measurement vectors and Ki denotes the filter gain of ith measurement vector. The sate prediction at time k is written as
(17)X^(k,k-1)=FX^(k-1,k-1).The updated state covariance can be expressed as(18)P-1(k,k)=P-1(k,k-1)+∑i=1N[Pi-1(k,k)-Pi-1(k,k-1)],(19)Pi-1(k,k)=Pi-1(k,k-1)+Hi(k)TRi(k)-1Hi(k),(20)P(k,k-1)=FP(k-1,k-1)FT+Q(k-1),(21)Pi(k,k-1)=FPi(k-1,k-1)FT+Q(k-1),
where Pi(k,k) and Pi(k,k-1) are the updated sate covariance and prediction covariance associated with ith measurement vector, respectively.


## 4. Simulations

In order to evaluate the performance of the proposed model, a dynamic scenario is assumed. TheT/R and R stations are located at (0,0,0) and (50 km, 0, 0), respectively. The initial position of the aircraft in x-y plane is (50 km, 50 km); flight altitude is defined as 7 km, 8.5 km, and 10 km, respectively. The velocities of the aircraft in x, y, and z directions are 150 m/s, 150 m/s, and 0 m/s. T=10s represents the time interval of measurement sampling. During the observation period, we assume the airplane of interest to be S27, which is simulated by FEKO software. In the flight scenario, the aircraft is flying away from the T/R station. As the attitude angle corresponding to T/R station is nearly a constant, the RCS is assumed to be 23 dB for simplicity. A Gaussian noise will be added in the state equation to model the fluctuation of the RCS. The RCS corresponding to R station changes at different attitude angles (a Gaussian noise will also be added to the state equation to model the fluctuation of RCS); it is presented in Figure 2.Figure 2
The RCS value at different attitude angle.The variances of target range and azimuth are defined to be 500 m and 1°. The flight trajectory inx-y plane is denoted in Figure 3.Figure 3
Flight trajectory inx-y plane.The root mean squared errors (RMSE) of the target altitude is depicted in Figure4. RCS corresponding to the T/R and R stations are displayed in Figures 5 and 6.Figure 4
RMSE of altitude.Figure 5
RMSE of RCS corresponding to theT/R station.Figure 6
RMSE of RCS corresponding to theR station.In Figure4, it demonstrates that the proposed method can estimate the altitude of aircraft with high accuracy. The RMSE of the altitude could converge to less than 700 m within 15 measurement intervals. The RMSE of altitude would have a significant decrement when target altitude increases; the reason is that posteriori Cramer-Rao lower bound (CRLB) on altitude is smaller at higher altitude. The estimator also provides preferable results of RCS estimation; RMSE of the RCS is less than 0.5 dB. The results in Figures 5 and 6 also show that there would be a smaller RMSE of RCS when target altitude increases, but it does not present a great improvement. It is that when the flying altitude becomes higher, ground wave attenuation is close to the atmospheric propagation attenuation gradually, the attenuation arising from seawater gets vanished, which leads to lower resolution of attenuation at high altitude.The measurement errors have a great impact on the accuracy of the altitude estimation. The RMSE of altitude at three different measurement errors of range is presented in Figure7; the range error is denoted as sigmR. Figures 8 and 9 demonstrate the impact of azimuth and echo amplitude errors on altitude estimation. sigmA represents the azimuth error, and sigmP is the error of echo amplitude.Figure 7
RMSE of altitude at different range errors.Figure 8
RMSE of altitude at different azimuth errors.Figure 9
RMSE of altitude at different errors of echo amplitude.In Figures7 and 8, it concludes that the range and azimuth errors perform a considerable impact on accuracy of altitude estimation. The results are deteriorating with the growth of range and azimuth errors. However, the accuracy of altitude is nearly invariable under three different errors of echo amplitude, which is depicted in Figure 9. The reason is that target range and azimuth information are sufficient to the altitude estimation, for which the echo amplitude information is redundant. Though the echo amplitude does not have remarkable impact on the estimation accuracy of altitude, it is essential for the RCS estimation. Inaccurate echo amplitude would result in a large estimation error of RCS. Figure 10 demonstrates the relationship between RMSE of RCS and different errors of echo amplitude.Figure 10
RMSE of RCS corresponding toT/R station at different errors of echo amplitude.In order to demonstrate the effectiveness of the proposed method, the altitude and RCS estimation results are showed compared with the traditional method [11], which are depicted in Figures 11 and 12. In the simulations, the airplane is assumed to be flying at an altitude of 10 km, and the variances of target range and echo amplitude are 500 m and 0.5 dB, respectively.Figure 11
RMSE results of altitude between the traditional method and the proposed method.Figure 12
RMSE results of RCS between the traditional method and the proposed method.From the altitude results of Figure11, it shows that the proposed method outperforms the traditional method. The RMSE of the altitude keeps nearly a constant, which cannot converge to a considerable result. However, the proposed method provides preferable altitude estimation under the circumstances of large initialization errors. It is that the proposed model is completely observable to the altitude and RCS information, which is lacked in the traditional model. The traditional method presents an impressive estimation of RCS, as depicted in Figure 12. It does not demonstrate the good performance of the traditional method. The reason is that when the target is high flying, ground wave attenuation is close to the atmospheric propagation attenuation gradually. The attenuation arising from seawater gets vanished, which leads to lower resolution of attenuation at high altitude.In the following section, a practical example is used to make further evaluations of the proposed model. A scenario of international airplane is presented in Figure13, in which the airplane is an uncooperative target. The radar frequency of operation is 8.9 MHz; the range between T/R and R station is 54.3 km.Figure 13
Flight trajectory of an unknown civil airplane inT/R-R HFSWR.The altitude and RCS estimation results are depicted from Figures14, 15, and 16.Figure 14
The estimated altitude of an international flight.Figure 15
The estimated RCS corresponding toT/R station.Figure 16
The estimated RCS corresponding toR station.From Figures14 to 16, it is shown that the proposed model provides considerable altitude and RCS estimation. The altitude is estimated to be 9.5 km. Although the ground truth is unknown, this estimation result is acceptable for an international airplane, which flies approximately at 10 km of altitude, and the effectiveness of the presented model is verified.The simulations and practical examples demonstrate that the new method provides significant improvements compared with the traditional method. It results from the complete observability of the proposed model. The altitude and RCS information of the target can be estimated with high accuracy. Even the errors of initial target state are large; the results of the fusion model converge quickly within a few measurements. Although the proposed method presents an impressive performance, the flaw is that it demands that the airplane should be detected by theT/R and R stations simultaneously. When the target is detected by only one receiver, the fusion approach could not be performed. Under such circumstances, an accurate estimation result could not be guaranteed.


## 5. Conclusions

A simultaneous altitude and RCS estimator is proposed with the propagation attenuation in bistatic HFSWR. It utilizes the variation property of propagation attenuation at different altitudes. In order to improve the accuracy of estimation, four measurement vectors are constructed with range, azimuth, and echo amplitude; centralized optimal fusion is adopted to fuse the measurements. Simulations and a practical example show that the proposed model provides preferable results of estimation with small RMSE, which demonstrates the benefits from using this altitude and RCS estimator.



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