esa-sceva/satcom-chunk-collection huggingface dataset:
## 2 The Model of Incident Elastic Wave Scattering by a Two-Ring Borehole
\begin{array}{ll}\varphi_{2}^{(s)}=\sum\limits_{n=-\infty}^{\infty}A_{n}^{ 2}H_{n}(k_{12}r)e^{in(\theta-\alpha)}e^{-i\omega t}+B_{n}^{2}H_{n}(k_{12}r)e^{ in(\theta-\alpha)}e^{-i\omega t}\\ \psi_{2}^{(s)}=\sum\limits_{n=-\infty}^{\infty}C_{n}^{2}H_{n}(k_{22}r)e^{in( \theta-\alpha)}e^{-i\omega t}+D_{n}^{2}H_{n}(k_{22}r)e^{in(\theta-\alpha)}e^{ -i\omega t}\end{array} \Bigg{\}},\text{ for the grout layer} \tag{7}\]  
\[ \begin{array}{ll}\varphi_{3}^{(s)}=\sum\limits_{n=-\infty}^{\infty}A_{n}^{ 3}H_{n}(k_{13}r)e^{in(\theta-\alpha)}e^{-i\omega t}+B_{n}^{3}H_{n}(k_{13}r)e^{ in(\theta-\alpha)}e^{-i\omega t}\\ \psi_{3}^{(s)}=\sum\limits_{n=-\infty}^{\infty}C_{n}^{3}H_{n}(k_{23}r)e^{in( \theta-\alpha)}e^{-i\omega t}+D_{n}^{3}H_{n}(k_{23}r)e^{in(\theta-\alpha)}e^{- i\omega t}\end{array} \Bigg{\}},\text{ for the instrument casing} \tag{8}\]  
where \(k_{1\star}=\omega/c_{sp}\) and \(k_{2\star}=\omega/c_{\ast s}\) are wave numbers of scattering P and S waves in the corresponding layers, respectively. Substituting total wave fields, including the incident wave fields and the scattering wave fields, into the traction-free boundary conditions at the inner wall of the instrument casing and the continuity of stress and displacement at the borehole-grout and grout-instrument casing interfaces obtains the unknown constants, and then radial displacement at the inner wall of the instrument casing \(u_{r}|_{r=a}\). The diameter change of the inner wall of the instrument casing, measured by the first gauge at azimuth angle \(\theta_{1}\) in borehole tensor strainmeters, can be expressed by  
\[U_{r}(\theta_{1})=\frac{u_{r}(\theta_{1})|_{r=a}+u_{r}(\theta_{1}+180^{\circ})| _{r=a}}{2a} \tag{9}\]Similar to the scattering model of the incident elastic waves by an empty model, theoretical frequency responses \(FV_{2}\), \(FV_{4}\), \(TV\), \(FS\) and \(TS\) of borehole tensor strainometers are introduced as follows,  
\[ \begin{array}{l}FV_{2}=\frac{U_{r}(\theta_{1})+U_{r}(\theta_{1}+90^{o})}{U_{r} (\theta_{1})+\frac{\lambda}{U_{r}(\theta_{1}+45^{o})}+U_{r}(\theta_{1}+90^{o})+ U_{r}(\theta_{1}+135^{o})}\\ TV=\frac{U_{r}(\theta_{1})+U_{r}(\theta_{1}+60^{o})+U_{r}(\theta_{1}+120^{o})}{ \lambda}\\ FS=\frac{U_{r}(\theta_{1})-U_{r}(\theta_{1}+90^{o})}{\lambda}\\ TS=\frac{U_{r}(\theta_{1}+60^{o})-U_{r}(\theta_{1}+120^{o})}{\lambda}\end{array}  \Bigg{\}}, \tag{10}\]  
where \(\Delta=\left\{ \begin{array}{l}\varepsilon_{\chi^{\prime}}^{(i)}=-\varphi_{0} k_{1}^{2}e^{-i\omega t}\quad\text{ for the incident P wave}\\ \varepsilon_{\chi^{\prime}\psi^{\prime}}^{(i)}=\frac{1}{2}\psi_{0}k_{2}^{2}e^{-i \omega t}\quad\text{ for the incident S wave}\end{array} \right..\) Zero-frequency responses for \(FV_{2}\), \(FS\), and \(TV\) reflect the far-field areal strain representing a strain invariant. Zero-frequency responses for \(FS\) and \(TS\) reflect the maximum far-field shear strain not representing a strain invariant.
# 3-D Printed Fabry-Perot Resonator Antenna with Paraboloid-Shape Superstrate for Wide Gain Bandwidth  
[PERSON]  
School of Electrical and Information Engineering, Sichuan University, Chengdu 610064, China; [EMAIL_ADDRESS] (Q.C.); [EMAIL_ADDRESS] (K.X.)  
[PERSON]L_ADDRESS]; Tel.: +86-134-5856-4058  
[PERSON]  
School of Electrical and Information Engineering, Sichuan University, Chengdu 610064, China; demnie_chen@163.  
Many technologies have been proposed to enhance the FPRAs' gain bandwidth [6; 7; 8; 12; 13; 14; 15; 16; 17; 18] and most of them can be divided into three categories. The first is adopting non-uniform superstrate or non-uniform ground plane, such as superstrate with tapered-sized FSS (frequency selective surface) or ground plane with tapered-sized HIS (high impedance surface) [7; 12; 13]. The second is designing superstrates with positive phase gradient, i.e., the superstrates' reflection phase increasing with frequency [8; 14; 15; 16; 17]. The third is employing an antenna array instead of a single antenna as the excitation antenna to feed a FPRA [6; 18].  
Quite differently from the aforementioned technologies, this work explores enhancing the FPRAs' gain bandwidth by designing a paraboloid-shape superstrate. Unlike planar superstrates used in most FPRAs, the cambered superstrate adopted by the proposed FPRA is able to create various resonant heights which satisfy the resonant conditions of the FPRA at a wide range of frequencies. To the best of our knowledge, this technology has never been investigated in previous studies.  
To validate the proposed technology, a sample FPRA working at 6 GHz will be presented. Considering its complex structure, especially the paraboloid-shape superstrate, the prototype antenna will be fabricated by using the three-dimensional (3-D) printing technology. The 3-D printing technology also identified as additive manufacturing or rapid prototyping has been gradually used for fabricating microwave and millimeter components--such as antennas, filters, waveguides, 3-D metamaterials, etc. [19; 20; 21; 22]--as it has the advantage of fabricating complex structures at a low cost. The 3-D printing technology enables designers have more freedom in their designs. The research work in [23] demonstrates the 3-D printed and surface metallized microwave components have nearly identical performances with solid metal structures if their skin depths of metal operate identically. Nowadays, by adopting some technologies such as using a beam of laser to solidify liquid photopolymer resin layer, a 3-D printing operation can achieve a very high printing precision of \(\pm 50\) um, while also guaranteeing good surface quality [24].
###### Abstract  
Antennas with quasi-hemispherical radiation patterns are preferred in many wide\(-\)area wireless communication systems which require the signals to uniformly cover a wide two\(-\)dimensional region. In this work, a simple but effective beamwidth broadening technique based on an antipodal linearly tapered slot antenna (ALTSA) is first proposed and then experimentally verified. Compared with most of the reported designs, the proposed antenna can significantly widen beamwidth and achieve a quasi-hemispherical radiation pattern without increasing the overall size and structural complexity. Only two rows of subwavelength metallic elements (eight elements in total) are simply and skillfully printed at specified positions on the dielectric substrate (relative permittivity \(\epsilon_{t}=2.94\) and thickness h = 1.5 mm) of a general ALTSA whose peak gain is 11.7 dBi, approximately 200% half-power beamwidth (HPBW) enlargement can be obtained in all cut-planes containing the end-fire direction at the central frequency of 15 GHz, and the HPBW extensions in different cut-planes have good consistency. Thus, a quasi-hemispherical beam pattern can be acquired. Thanks to the simplicity of this method, the antenna size and structural complexity do not increase, resulting in the characteristics of easy fabrication and integration, being lightweight, and high reliability. This proposed method provides a good choice for wide\(-\)beam antenna design and will have a positive effect on the potential applications of wide-area wireless communication systems.  
Keywords: antipodal linearly tapered slot antenna; wide beam; subwavelength elements; HPBW +
Footnote †: journal: Electronics Letters
## 1 Introduction
Therefore, these models only demonstrated that satellite signal tracking performance could be enhanced with INS aiding, but could not be used for quantitative analysis to guide IMU selection, parameter optimization and quantitative analysis of INS-aided PLLs. In addition, since developing a deeply-coupled system requires the adjustment of the receiver internal structures, there were only limited cases of real-time hardware systems achieved by the co-operation of companies [14,15]. However, most research institutions use software platforms [16, 17, 18], resulting in literature being scant on the deeply-coupled system performance verification on embedded hardware platforms. Figure 2: INS-aided GNSS receiver tracking loop model in previous work [9,10]. (**a**) Proposed by [PERSON] _et al._; (**b**) proposed by [PERSON]. To provide a theoretical tool for IMU selection, parameter optimization and quantitative analysis of INS-aided PLLs, this paper builds the error transfer function of INS-aided PLLs based on a scalar-based architecture in Section 2, which reflect the relationships between all known error sources (including thermal noise, oscillator noise, INS errors and the delay of INS aiding information) and carrier phase tracking error. What needs to be emphasized is that INS errors are modeled in detail in this paper, which is proposed for the first time, compared to previous works. Based on that, it derives and analyzes the PLL steady-state error model before and after INS information assistance in Section 3, which can be used for the parameter design of INS-aided PLLs, IMU selection and hardware system development. Moreover, an integrated real-time deeply-coupled hardware prototype is developed in Section 4, in which the real-time running and the INS information delay are optimized. The proposed hardware prototype design is also unique compared to software systems in previous works. In Section 5, tests and analysis of PLL tracking performance in dynamic conditions are carried out based on a GPS/INS simulator and vehicle. Finally, the INS-aided PLLs on a deeply-coupled hardware prototype are summarized and concluded.
## 1 Introduction
The extraction efficiency during UAE is dependent on several factors, like the physical parameters during ultrasonication (power, power intensity, frequency, duty cycle, time and transducer efficiency), medium characteristics (solvent type, substrate properties and solvent-to-solid ratio) and environment parameters (temperature and air pressure) [14]. Regarding the solvents, besides their capacity to solubilize the desired compounds, they must possess several physical properties that promote acoustic cavitation [15]. The extraction of phenolic compounds from BC is commonly performed by maceration and mechanical rubbing in solvents like dichloromethane, methanol, ethanol or acetone/water [16]. However, combining alcohol with water demonstrated superior efficiency in extracting the antioxidants than using a single solvent [17]. Thus, compared with conventional technologies, UAE has emerged as an efficient and economic extraction technology [14]. Several studies have been performed on the application of UAE for the identification of the optimum extraction conditions for the phenolic compounds from BC pomace [7; 13]. However, most of them provide a chromatographic profile of the major anthocyanins and focus less on the non-anthocyanin phenolic compounds. Taking into consideration that many of the phenolic compounds from BC pomace have a strong antimicrobial effect [10], their identification and quantification is essential and would maximize their valorization in a sustainable manner. Therefore, the aim of this study was to valorize BC byproducts by applying an environmentally friendly technique based on UAE that would generate BC extracts with increased functionality in terms of antioxidant and antimicrobial properties. First, the effects of the ultrasound amplitude and time on the total polyphenols and antioxidant activity in water and 70% ethanol were investigated using spectrophotometric assays. The extract with the highest concentration of phenolic compounds was chromatographically characterized and tested for antibacterial activity. In addition, in silico investigations elucidated the mechanisms involved in the antibacterial activity exerted by the main phenolic com-pounds from the BC extract against _Escherichia coli_ and _Staphylococcus aureus_.
# Identification of Water Hammering for Centrifugal Pump Drive Systems
## 3 Real-Time Simulation Results
Due to pressure changes, the pressure-head drops rapidly, i.e., from 3.998 m to 1.336 m when two valves are suddenly closed and opened, and from 1.580 m to 0.5099 m, 2.243 m to 0.928 m, and 2.029 m to 0.928 m when three valves are suddenly closed and opened; in this case, flow rate also changes rapidly. Thus, sudden change of pressure head, velocity, and flow rate leads to both cavitation and water hammering in the system (Table 1). In this work, at different times, i.e., starting from 0 to 50 s time, data are collected. For the sudden closing and opening of valve pressure drops, flow rate changes and velocity changes. When the pressure goes below the vapor pressure head, water hammering occurs as the sudden hydraulic shock is created in the fluid. At every 5-s gap, a fault has been created, i.e., 25 to 30-s change, 15 to 20-s change, 30 to 35-s change, and 45 to 50-s change. Figure 6: Pressure head processes behind the pump of complete-time series in different positions of the valve. Figure 7: The velocity of pump processes behind the pump of a complete-time series in different positions of the valve. \begin{table}
\begin{tabular}{c c c c c c c c c c c c} \hline \hline  & \multicolumn{3}{c}{**Pressure Head When**} & \multicolumn{3}{c}{**Pressure Head When**} & \multicolumn{3}{c}{**Pressure Head When**} \\
**Time (Sec)** & **Set Pressure (Jan)** & **One Valley Sudan** & **Flow Rate** & **Velocity** & **Two Valices Sudden** & **Flow Rate** & **Velocity** & **Three Valices Sudden** & **Flow Rate** & **Velocity** \\  & & **Open and Close** & **(plan)** & **(m/h)** & **Open and Close** & **(plan)** & **(m/h)** & **Open and Close** & **(plan)** & **(m/h)** & **Open and Close** & **(plan)** & **(m/h)** \\  & & **(Method)** & & & & & & & & & \\ \hline
0 & 1 & 2.243 & 5150 & 0.1771 & 2.029 & 2700 & 0.0925 & 2.243 & 1900 & 0.0650 \\
5 & 1.1 & 1.805 & 5250 & 0.1802 & 3.121 & 2700 & 0.1019 & 2.458 & 1890 & 0.0648 \\
10 & 1.2 & 2.243 & 5300 & 0.1877 & 4.661 & 2500 & 0.0857 & 1.805 & 1755 & 0.0802 \\
15 & 1.3 & 1.805 & 5200 & 0.1783 & 2.029 & 2700 & 0.0926 & 1.580 & 1900 & 0.0546 \\
20 & 1.4 & 1.805 & 500 & 0.1732 & 2.243 & 2885 & 0.0989 & 0.5099 & 1422 & 0.0900 \\
25 & 1.5 & 3.345 & 5100 & 0.1748 & 3.998 & 2810 & 0.0964 & 2.029 & 1998 & 0.0685 \\
30 & 1.6 & 3.549 & 5150 & 0.1767 & 1.366 & 2779 & 0.0953 & 2.243 & 1953 & 0.06697 \\
35 & 1.7 & 2.029 & 5300 & 0.1817 & 2.662 & 2762 & 0.0947 & 0.928 & 1521 & 0.0216 \\
40 & 1.8 & 1.805 & 5300 & 0.1817 & 2.906 & 2605 & 0.0893 & 2.029 & 1834 & 0.0629 \\
45 & 1.9 & 1.80 & 5200 & 0.1783 & 5.009 & 2550 & 0.08068 & 0.928 & 1559 & 0.0528 \\
50 & 2 & 2.243 & 5150 & 0.1771 & 4.447 & 2564 & 0.00570 & 2.029 & 1834 & 0.0628 \\ \hline \hline \end{tabular}
\end{table} 
Table 1: Real-time data from the pump.
# Energy Efficiency and Coverage Trade-Off in 5G for Eco-Friendly and Sustainable Cellular Networks
## 4 Optimization Programming and Simulation Setup
### Simulation Setup  
The simulation parameters used in this study are given in Table 1. MATLAB software is used in this study. During a period of off-peak traffic load demand, 5G BSs are switched off, and LTE BSs will guarantee both the service and the coverage. The execution and implementation of PSO algorithm are aimed at maximizing the cell coverage area (LTE) during a switched-off session, under the constraints of P\({}_{\text{tx}}\), BW, G, SINR, and \(\sigma\). More details of the simulation parameters are given in Table 1.  
\begin{table}
\begin{tabular}{c c c c c} \hline \hline
**Item** & **Parameter** & **Acronym** & **LTE** & **Unit** \\ \hline Network & Frequency & \(f\) & 2.6 & GHz \\ parameters & Bandwidth & \(BW\) & 1.4–20 & MHz \\  & Cell radius & \(R\) & 0.5 & km \\  & Transmission power & \(p_{tx}^{\text{min}}\)–\(p_{tx}^{\text{max}}\) & 10–40 & W \\ Base station & Antenna height & \(h_{BS}\) & 20 & m \\  & Antenna gain & \(G_{\text{min}}\)–\(G_{\text{max}}\) & 5–10 & dB \\  & Number of antennas & \(N_{Ant.}\) & 2 & \# \\  & Number of sectors & \(N_{Sect.}\) & 3 & \# \\  & Number of carriers & \(N_{Carr}\) & 1 & \# \\ \hline \hline \end{tabular}
\end{table}
Table 1: List of simulation parameters.  
Figure 6: Pseudocode of the considered PSO algorithm.
# An Efficient Mobility Model for Improving Transmissions in Multi-UAVs Enabled WSNs
## 6 Conclusions and Future Work  
Efficient topological formations and coordinated movements help to achieve effective and sustainable UAV-coordinated WSNs. In this article, a novel mobility scheme based on the transmission density of the WSN nodes is proposed for moving UAVs in a coordinated manner for improved coverage and better performance. The proposed approach is evaluated against Random way-point, Random Walk, Gauss-Markov and Fixed Maneuver UAV movements. The random models produce close but considerably fewer performance levels as long as the WSN nodes lie in their movement corridor. The Gaussian model gives results on average performance when applied to the UAV movements. The fixed maneuvering scheme produces less delay but with a huge compromise on throughput, coverage, and latency. The proposed approach shows significant gains in coverage, throughput, jitter, and data transfer ratios. The packet drop rate is decreased exponentially and massive gains are observed for packet delivery ratio.  
The proposed approach presents a generalized model for UAV traversals according to the transmission statistics of the underlying geography. The model can be extended to include multi-path traversals that will effectively result in better coverage, throughput and data transfer results in less time. The proposed approach can also be incorporated into Software Defined Networks as a controller component and thus increase its applicability towards various system models and approaches.  
M.A.S. and R.K. have equal contributions towards Conceptualization, Methodology, Validation, Formal Analysis and Editing. The Software Components, Simulations and Initial Writing was completed by M.A.S.  
This research received no external funding  
A part of this paper in the form of a security variant is submitted to the workshop associated with the 12 th International Conference on Provable Security to be held on 25-28 October 2018, Jeju, South Korea.  
The guest editor shared a similar affiliation with the authors during his earlier employment and has previously published articles with the authors. However, this study is the sole contribution of the two authors and the review works of this article were handled by the academic editor of Drones MDPI.
## 2 Materials and Methods  
### Principle of Two-Color Pyrometry  
The most basic principle of the two-color thermometry method is [PERSON]'s law of radiation [33], where the spectral radiance emitted by an object is related to wavelength and temperature as in Equation (1):  
\[M(\lambda,T)=\frac{1}{\pi}\varepsilon(\lambda)\frac{C_{1}}{\lambda^{5}}\exp(1 -\frac{C_{2}}{\lambda T}), \tag{1}\]  
\(M(\lambda,T)\) is the monochromatic radiant exitance at a given wavelength \(\lambda\) and temperature \(T\), \(\varepsilon(\lambda)\) is the monochromatic emissivity for a given wavelength, \(T\) is absolute temperature, \(K\); the first radiation constant \(C_{1}=2\pi hc^{2}\), the second radiation constant \(C_{2}=hc/k\), \(h\) is the [PERSON] constant, \(k\) is the Boltzmann constant, \(c\) is the speed of light, \(C_{1}=3.7415\times 10^{8}W\cdot\mu m^{4}\cdot m^{-2}\), \(C_{2}=1.4388\times 10^{4}\mu m\cdot\text{K}\).  
When the condition \(\lambda T\leq 2000\)\(\mu m\cdot K\) is satisfied, \(M_{b}(\lambda,T)\) is a monochromatic blackbody radiant exitance, [PERSON]'s law can be replaced by Wien's law:  
\[\begin{array}{l}M(\lambda,T)\approx\frac{1}{\pi}\varepsilon(\lambda)\frac{C _{1}}{\lambda^{5}}\exp(-\frac{C_{2}}{\lambda T})=\varepsilon(\lambda)M_{b}( \lambda,T)\\ M_{b}(\lambda,T)=\frac{1}{\pi}\frac{C_{1}}{\lambda^{5}}\exp(-\frac{C_{2}}{ \lambda T})\end{array}, \tag{2}\]  
If the monochromatic radiant exitance \(M(\lambda_{1},T),M(\lambda_{2},T)\) of the two spectral lines \(\lambda_{1},\lambda_{2}\) can be obtained, their division provides the following two-color ratio Equation (3):  
\[\frac{M(\lambda_{1},T)}{M(\lambda_{2},T)}=\bigg{(}\frac{\varepsilon_{\lambda_ {1}}}{\varepsilon_{\lambda_{2}}}\bigg{)}\frac{\lambda_{2}^{5}}{\lambda_{1}^{5} }\times\exp\biggl{[}-\frac{C_{2}}{T}\bigg{(}\frac{1}{\lambda_{1}}-\frac{1}{ \lambda_{2}}\bigg{)}\biggr{]}, \tag{3}\]Finally, we obtain the two-color thermometry Equation (4):  
\[T=-C_{2}(\frac{1}{\lambda_{1}}-\frac{1}{\lambda_{2}})/\ln(\frac{M_{\rm b}(\lambda_ {1},T)}{M_{\rm b}(\lambda_{2},T)}\frac{\varepsilon_{\lambda 2}}{\varepsilon_{ \lambda_{1}}}\frac{\lambda_{1}^{5}}{\lambda_{2}^{5}}), \tag{4}\]  
The selected wavelength range for calculating temperature was based on the following principles [34]: First, spectral lines that exhibit significant variations in intensity within the flame should be avoided. Second, it is essential to ensure high signal-to-noise ratios for the spectral measurement data by excluding the beginning and end of the spectral measurement range. If the spectral emissivity varies with wavelength and the relationship between them is unknown, the two-color method is not applicable for temperature measurements. Therefore, when employing the two-color temperature measurement technique, it is crucial to ensure that the flame adheres to the gray body property, which means that the emissivities are approximately equal within the chosen spectral range.
## 4 Results and Discussion  
### Simulation of Control System  
#### 4.1.1 Initial PID Coefficients  
The initial PID coefficients were selected using the delay time and time constant based on Equations (16)-(18). The delay time and time constant of the shuttle shifting actuator were 0.137 and 0.410 s, respectively, when gear-shifting from neutral to forward, and were 0.145 and 0.380 s, respectively, when gear-shifting from neutral to reverse. The delay time and time constant showed similar ranges in both cases. In this study, the initial PID coefficients for the shuttle shifting actuator were selected as K\({}_{\text{P}}\) = 3.43, K\({}_{\text{I}}\) = 12.25, and K\({}_{\text{D}}\) = 0.24, using average values (delay time: 0.140 s, time constant: 0.400 s). The response characteristics of the potentiometer were measured assuming the Z-N step-response to move from disengagement to engagement, in order to select the initial PID control coefficients of the clutch actuator. As the delay time and time constant were 0.190 and 0.310 s, the initial coefficients K\({}_{\text{P}}\) = 1.96, K\({}_{\text{I}}\) = 5.16, and K\({}_{\text{D}}\) = 0.18 were selected.