Combined line-of-sight error and angular position to generate feedforward control for a charge-coupled device–based tracking loop

Abstract. A feedforward control based on data fusion is proposed to enhance closed-loop performance. The target trajectory as the observed value of a Kalman filter is recovered by synthesizing line-of-sight error and angular position from the encoder. A Kalman filter based on a Singer acceleration model is employed to estimate the target velocity. In this control scheme, the control stability is influenced by the bandwidth of the Kalman filter and time misalignment. The transfer function of the Kalman filter in the frequency domain is built for analyzing the closed loop stability, which shows that the Kalman filter is the major factor that affects the control stability. The feedforward control proposed here is verified through simulations and experiments.


Introduction
Two-axis (azimuth and elevation) gimbals with a chargecoupled device (CCD)-based control system can be used for monitoring and positioning as well as tracking an interesting target. [1][2][3] The basic mechanism and configuration is a two-axis gimbal equipped mainly with motor, encoder, CCD, and other components. 2,3 Unlike the previous control problem, the tracker of CCD cannot provide the target trajectory or the target velocity, but only line-of-sight (LOS) error. A direct feedback loop is usually utilized to control LOS. High control bandwidth (BW) facilitates good closed loop performance. However, the time delay is the major reason to restrict the BW in a CCD-based tracking loop. In general, there are three factors causing the time delay to the closed loop system: exposure time of the CCD, image process time, and transmit time. The time delay cannot be cut to zero, which results in an ineffectiveness of a high BW. A feedforward control, such as a rate-aided control, is introduced into a CCD-based tracking system to reduce the LOS error. 4,5 The target trajectory either can be recovered through sensor fusion, including a rangefinder, the CCD, encoder, and rate sensor, or can be given. Experiments verify rate the feedforward control to be effective for improving the tracking performance, especially for a maneuvering target tracking. Motivated by pervious research, 6,7 an improved feedforward control is proposed in this paper. This method only combines the CCD and encoder for data fusion to recover the target trajectory as an observed value of the Kalman filter, which can produce the target velocity to implement the feedforward control. The previous researches usually focused on how to optimize the Kalman filter or how to make precise models for better estimation of the target rate. [8][9][10] However, if the target trajectory is unknown, it is necessary to consider the closed loop stability when a Kalman filter is used to estimate the target velocity. To analyze the closed loop stability, the transfer function of a Kalman filter in the frequency domain is built.
Section 2 presents a detailed introduction to a feedforward control, mainly describing the CCD-based control structure and the implementation of the feedforward control. Section 3 focuses on parameters' design, specifically in terms of the proportional-integral (PI) controller and the Kalman filter. Section 4 discusses and analyzes the system stability. Section 5 sets up experiments to verify this method. Concluding remarks are presented in Sec. 6.

Feedforward Control
A classical feedforward control is shown in Fig. 1, where QðsÞ is the feedforward controller, CðsÞ is the position controller, and PðsÞ is the control plant. The time delay e −T 0 s characterizes the CCD in the control system, although it may be rough.
The feedforward control not only has little influence on the closed loop stability, but also contributes a lot to the control performance. However, the tracking sensor cannot provide the target trajectory or target speed, but only an LOS error in a CCD-based servo control system. Considering R ¼ E þ Y, the equivalent control structure of Fig. 1 is depicted in Fig. 2.
This control structure in Fig. 2 is practical. The target trajectory can be recovered by combining the LOS error and the angular position of the gimbals. The sensitivity function is E Q -T A R G E T ; t e m p : i n t r a l i n k -; e 0 0 1 ; 3 2 6 ; 1 1 6 The improvement of the feedforward control is mainly subject to 1 − e −T 0 s if this feedforward controller QðsÞ is designed to be the inverse PðsÞ. It is obvious that the term 1 − e −T 1 s is close to T 1 s in low frequencies. In this situation, the smaller the time parameter is set, the more the feedforward control contributes to the closed-loop performance. However, it is impractical to implement QðsÞ ¼ P −1 ðsÞ, because the term PðsÞ includes not only the non-nominal part, but also the high-frequency characteristics.
PðsÞ is depicted in Fig. 3, where GðsÞ is the control plant and C v ðsÞ is the velocity controller designed according to the classical control theorem. A tachometer providing the angular velocity of the gimbals usually has a high BW, resulting only in a minor influence on the closed-loop control system.
We can easily get the transfer function from O to V in Fig. 3: E Q -T A R G E T ; t e m p : i n t r a l i n k -; e 0 0 2 ; 6 3 ; 3 5 7 PðsÞ ¼ As a matter of fact, this term C v ðsÞGðsÞ∕1 þ C v ðsÞGðsÞ is very close to constant 1 in low frequencies because the velocity closed loop has a much higher BW than that of the position closed loop. Thus, PðsÞ ≈ 1∕s is true to some extent. In this case, the feedforward controller can be described as E Q -T A R G E T ; t e m p : i n t r a l i n k -; e 0 0 3 ; 6 3 ; 2 4 6 QðsÞ ¼ The phase lag term 1∕1 þ T f s indicates the main feature of a filter. It is impossible to obtain the velocity by directly differentiating the synthesizing signal E þ Y, because noise can pollute the differential signal, resulting in ineffectiveness.
From Eqs. (1) and (4), the difference between the two parameters and the filter QðsÞ may affect the stability or even lead to control instability.

Parameters Design
The sampling frequency of the CCD is 50 Hz. The time delay T 0 is 0.06 s, which is about three times more than the sam- Combining the two equations to remove the integral parameter K I yields Eq. (9): E Q -T A R G E T ; t e m p : i n t r a l i n k -; e 0 0 7 ; 3 2 6 ; 4 0 2 Let ∂K p ∕∂w ¼ 0, then the maximum gain can be obtained and w c T 0 ≈ 0.5275 is resolved. Substituting this into Eqs. (6) and (7), the PI controller parameters can be resolved as K p ¼ 0.
The requirements of the closed-loop system with feedforward control need to meet a phase margin larger than 35 deg of the open-loop transfer function, we have E Q -T A R G E T ; t e m p : i n t r a l i n k -; e 0 0 9 ; 3 2 6 ; 1 2 6 arg½S open ðsÞj s¼jw 0 c þ 180 deg ≥ 35: The feedforward control is expected to have little influence on the closed-loop BW, resulting in w 0 c ≈ w c . Substituting the results of the PI controller parameters into Eq. (8), we get T f ≥ 1.893T 0 , from which it can be deduced  that the BW of the filter must be limited to less than 1∕ð1.893T 0 Þ ¼ 1.221 Hz.
The Kalman filter is an optimal linear mean minimum square filter to suppress noise. The target velocity can be estimated by the Kalman filter and be fed into the control system. The standard Kalman equations are depicted as follows: E Q -T A R G E T ; t e m p : i n t r a l i n k -; e 0 1 0 ; 6 3 ; 4 5 6 The observed signal is the target trajectory recovered by LOS error and the angular position. A simple mode called the Singer acceleration model, nicknamed the zero-mean first-order Markov model, 9 is used to estimate the target speed. Then we can easily know the Kalman filter parameters as follows: The solution of the Kalman filter is given below: E Q -T A R G E T ; t e m p : i n t r a l i n k -; e 0 1 2 ; 6 3 ; 2 3 4x kþ1 ¼ ðA − K kþ1 CAÞx k þ K kþ1 y k : The gain K kþ1 of the Kalman filter can be obtained from the Ricatti equation if the matrices A, B, and C are time invariant. Using the "dare" function can help to quickly solve the Ricatti equation. The reconstructive characteristics of the Kalman filter in the frequency domain can be described in Eq. (13): E Q -T A R G E T ; t e m p : i n t r a l i n k -; e 0 1 3 ; 6 3 ; 1 3 7 φ ¼ ðZI − A þ K kþ1 CAÞ −1 K kþ1 : The bode plot indicates that the target speed is pretty efficient in low frequencies in Fig. 4, where the phase lags a little. The bigger the process variance is, the higher the BW of the Kalman filter. A high BW probably leads to control system instability, although it has enough margin to adapt to a maneuvering target.
The BW of the Kalman filter needs to be smaller than 1.2 Hz according to the analysis above. The green line in Fig. 4 illustrates the Kalman filter response for which the BW is about 0.99 Hz.

Stability and Improvement Analysis
Based on these considerations and design, the responses in the sensitivity function [Eqs. (1) and (14)] are shown in Fig. 6. A large attenuation, about one-tenth less than that with only a feedback loop control, is achieved in the low-frequency region with a feedforward controller in Fig. 6. However, the attenuation in the middle-frequency range is magnified from 0.2 Hz to about 0.4 Hz, a little larger than that with only the feedback control. This is due to the amplification by the Kalman filter.
It is natural that the misalignment error inevitably occurs, although the sample frequency of the encoder can reach several thousand hertz or more while the CCD has usually a few dozens of hertz. In comparison with the Kalman filter, we can see from Fig. 7 that the deviations of the misalignment between the two parameters have little effect on the stability.

Experimental Setup
The trajectory of a moving target is provided by dynamic moving target simulators. A two-axis gimbal with a 50-Hz CCD as a tracker is used to track the moving target, for which the angular speed differentiated by a position angular from encoder is about 11.8 deg ∕s for the azimuth axis and 5 deg ∕s for the elevation axis in Figs. 8 and 9.
The target acceleration is obtained by further differentiating the speed, about 4 deg ∕s 2 for the azimuth axis and 2 deg ∕s 2 for the elevation axis in Fig. 10.
Comparing the target velocity estimated with the Kalman filter with the target velocity by the differentiating encoder, the noise is suppressed by the Kalman filter.
In Fig. 11, A stands for the azimuth axis, whereas E represents the elevation axis. The LOS error with the feedforward control is shown in Fig. 11, and is much less than that without a feedforward control whose error curve is not drawn because the field of view of this CCD is too narrow to accommodate the 0.2-deg range.

Conclusions
This paper-focusing on the implementation of the feedforward control, the optimization of the control parameters, and the detailed stability analysis-proposes a feedforward control mechanism and configuration based on data fusion in a CCD-based tracking system. Experiments verify that this technique effectively enhances the closed-loop performance in comparison with the classical control mode. Related topics not covered in this paper are how to optimize the control parameters in an all-around manner rather than in an independent way and what kind of filters must be used to estimate target speeds and their effects on control stability. Furthermore, it is very challenging to investigate acceleration feedforward 12 to improve performance further.