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TOC Alert for Publication# 7 2018April 26<![CDATA[Table of Contents]]>542C1C4101<![CDATA[IEEE Aerospace and Electronic Systems Society]]>542C2C2135<![CDATA[From the Editor-in-Chief]]>54251951979<![CDATA[Optical Beam Position Tracking in Free-Space Optical Communication Systems]]>5425205361380<![CDATA[Censoring-Based Cooperative Spectrum Sensing with Improved Energy Detectors and Multiple Antennas in Fading Channels]]>5425375531987<![CDATA[Statically Fused Converted Measurement Kalman Filters for Phased-Array Radars]]>5425545681183<![CDATA[Circulation Retrieval of Simulated Wake Vortices Under Rainy Condition With a Side-Looking Scanning Radar]]>$Gamma$. At the same time, two other important parameters (vortex spacing $b_0$ and vortex-core height $y_0$) can be retrieved as well. Numerical simulation results verify good performance of the retrieval method.]]>5425695842036<![CDATA[Three-Dimensional Tracking of an Aircraft Using Two-Dimensional Radars]]>5425856001547<![CDATA[Optimizing Communication and Computation for Multi-UAV Information Gathering Applications]]>542601615938<![CDATA[Multihop Broadcast Protocol in Intermittently Connected Vehicular Networks]]>5426166281073<![CDATA[Social Sensing With Minimal Resources: Profiling Agents by Simply Knowing How to Count]]>type by aggregating actions that are believed to be taken under the same state of nature. The time-varying state of nature is unknown and must be inferred, and the effect of such uncertainty on the otherwise classical-type estimator is of central interest here. It is shown that a simple counting procedure leads to an asymptotically strong consistent profiling estimator in the limit of large number of agents and large number of per-agent observations. Analytical formulas are provided for finite values of both of these two parameters, and simulations are presented.]]>542629641870<![CDATA[Distributed Attitude Control for Multispacecraft via Takagi–Sugeno Fuzzy Approach]]>$H_infty$ controller is designed. It is proven that the attitude of multispacecraft can synchronously reach zero by using the designed controller. Numerical examples are provided to illustrate the effectiveness of the proposed controller and comparisons with the existing results.]]>5426426541341<![CDATA[Sparsity-Driven Micro-Doppler Feature Extraction for Dynamic Hand Gesture Recognition]]>542655665947<![CDATA[Novel Multichain-Based Loran Positioning Algorithm for Resilient Navigation]]>542666679978<![CDATA[<inline-formula><tex-math notation="LaTeX">$mathcal{L}_1$</tex-math></inline-formula> Adaptive Output Feedback Augmentation for Missile Systems]]>$mathcal{L}_1$ adaptive output feedback controller for a class of underactuated multi-input multi-output (MIMO) systems. The proposed approach is applied as an augmentation of an existing three-loop autopilot. The adaptive scheme is introduced to compensate for the uncertainties and to recover the nominal performance. Stability and performance, both in transient and steady state, are analyzed. Nonlinear simulation results demonstrate the performance of the augmented control system.]]>542680692546<![CDATA[Zero-Effort-Miss Shaping Guidance Laws]]>5426937052689<![CDATA[Cooperative Missile Guidance for Active Defense of Air Vehicles]]>5427067211576<![CDATA[A Semi-Open Loop GNSS Carrier Tracking Algorithm for Monitoring Strong Equatorial Scintillation]]>5427227381920<![CDATA[GNSS Signal Authentication Via Power and Distortion Monitoring]]>$<$0.6% single-channel false alarm rate.]]>5427397541122<![CDATA[Optimal Design of the Adaptive Normalized Matched Filter Detector Using Regularized Tyler Estimators]]>$rho$. This makes them more suitable for high-dimensional problems with a limited number of secondary data samples than traditional sample covariance estimates. The motivation behind this paper is to understand the effect and properly set the value of $rho$ that improves estimate conditioning while maintaining a low-estimation bias. More specifically, we consider the design of the ANMF detector for two kinds of regularized estimators, namely the regularized sample covariance matrix, the regularized Tyler estimator (RTE). The rationale behind this choice is that the RTE is efficient in mitigating the degradation caused by the presence of impulsive noises while inducing little loss when the noise is Gaussian. Based on asymptotic results brought by recent tools from random matrix theory, we propose a design for the regularization parameter that maximizes the asymptotic detection probability under constant asymptotic false alarm rates. Provided simulations support the efficiency of the proposed method, illustrating its gain over conventional settings of the regularization parameter.]]>542755769736<![CDATA[Altitude Estimation Using Multipath With a Two-Dimensional Radar Over Spherical Earth]]> $sigma _e=0.5^{circ }$) and the 2-D radar has very low indirect path PD (PD = 0.1).]]>542770782802<![CDATA[Conservative Term Constrained Kalman Filter for Autonomous Orbit Determination]]>5427837931135<![CDATA[Tracking Initially Unresolved Thrusting Objects Using an Optical Sensor]]>single fixed optical sensor. Since the initial separations in the FP are smaller than the resolution of the sensor, there are merged FP measurements, compounding the usual false-alarm and missed-detection uncertainty. We present a two-step methodology. First, we assume a Wiener process acceleration model for the motion of the images of the objects in the optical sensor's FPA. We model the merged measurements with increased variance, and thence employ a multi-Bernoulli (MB) filter using the 2-D measurements in the FPA. Second, using the set of associated measurements for each confirmed MB track, we formulate a parameter estimation problem, whose maximum likelihood solution can be obtained via numerical search and can be used for impact point prediction. Simulation results illustrate the performance of the proposed method.]]>5427948071005<![CDATA[Height Measurement of Low-Angle Target Using MIMO Radar Under Multipath Interference]]>542808818749<![CDATA[A Novel Uplink Scheduling Algorithm for the Galileo System]]>5428198331512<![CDATA[Optimal Rendezvous Trajectory for Unmanned Aerial-Ground Vehicles]]>5428348472601<![CDATA[On the Estimation of LFM Signal Parameters: Analytical Formulation]]>5428488601368<![CDATA[Modeling Three-Dimensional Passive STAP With Heterogeneous Clutter and Pulse Diversity Waveform Effects]]>5428618724404<![CDATA[Characterization of Received Signal Strength Perturbations Using Allan Variance]]>5428738891794<![CDATA[Statistical Modeling of Wireless Communications Interference and Its Effects on Adaptive-Threshold Radar Detection]]>$-6$ to $-text{2 dB}$ mean INR at the output of the matched filter).]]>5428909111384<![CDATA[Pilot Control Modeling With Stochastic Periodical Discrete Movement]]>542912922889<![CDATA[Attitude Correction Using Corner Landmarks in 3-D SLAM]]>5429239311024<![CDATA[Clutter Suppression and High-Resolution Imaging of Noncooperative Ground Targets for Bistatic Airborne Radar]]>5429329491727<![CDATA[Compressive Sensing of Sparse Signals in the Hermite Transform Basis]]>5429509671545<![CDATA[Distributed RZF Precoding for Multiple-Beam MSC Downlink]]>542968977966<![CDATA[Coherent Airborne MIMO Detection of Multiscatter Targets]]>542978991820<![CDATA[Optimal Collaborative Mapping of Terrestrial Transmitters: Receiver Placement and Performance Characterization]]>54299210071340<![CDATA[A Thrust Model Aided Fault Diagnosis Method for the Altitude Estimation of a Quadrotor]]>z-axis accelerometer and the barometer. The knowledge of the thrust model is used to generate an analytical redundancy based fault diagnosis approach for altitude estimation. The filter design, fault detection, isolation, and recovery problems are addressed. An improved chi-test method is used for fault detection. Real-flight data is used to validate the proposed approaches, showing that the faults of the z-axis accelerometer and the barometer can both be detected and the thrust model of a quadrotor can be used to replace the faulty z-axis accelerometer.]]>542100810191355<![CDATA[Robust Attitude Tracking Control for Spacecraft with Quantized Torques]]>54210201028850<![CDATA[Minimum Residual Vibrations for Flexible Satellites With Frequency Uncertainty]]>542102910381320<![CDATA[Technical Areas and Editors: AESS IEEE Aerospace & Electronic Systems Society]]>54210391044140<![CDATA[Information for Authors]]>54210451046102