An MTI Technique for Processing Radar Measurements of a Waking Reentry Body

A processing technique based on pulse-cancellation techniques familiar in moving target indicator (MTI) radar is proposed for separating (in Doppler) echoes of a reentry body traveling at hypersonic velocities from those of its lower velocity turbulent wake appearing in the same range cell. The cancellation technique is implemented by forming the sum of the products of binomial weighting coefficients of alternating sign with the complex echoes of a small number of closely spaced transmitted coherent pulses; thereby, in effect, synthesizing a digital canceler. The ability of the two-and three-pulse canceler to estimate body RCS in the presence of attached wake is demonstrated by employing coherent burst data collected by the AMRAD radar for a mission flown at the White Sands Missile Range. Estimates of body RCS obtained from the two-and three-pulse canceler compare favorably to the corresponding estimates obtained from a 30-pulse Doppler periodogram for this mission. Expressions for both the achievable wake rejection ratio and the mean and standard deviation of the body power estimate of the N-pulse canceler are derived as a function of the wake parameters, assuming Gaussian wake statistics.     

Wake-vortex characteristics of military-type aircraft measured at airport oberpfaffenhofen using the DLR laser doppler anemometer

The DLR ground-based cw Doppler lidar was used for experimental investigations of wake vortices generated by military-type aircraft, including fixed-wing as well as rotor-wing aircraft. The measurements were mainly focused on the roll-up phase of the vortices. The experimental data has been analysed regarding vortex structure and circulation, partly also regarding their temporal development. The influence of flight parameters was measured during consecutive aircraft fly-bys. Small variations in the velocity profiles could be observed which were overlayed by the signatures of the variable wind and turbulence field. This problem can be solved on a statistical basis by measuring many cases under the same atmospheric conditions. The influence of aircraft design could be demonstrated by comparison of the vortex signatures of two B707-type aircraft showing pronounced design differences, namely a standard B707 and a AWACS E3A.     

Frequency-Agile Radar Signal Processing

Modern radars may incorporate pulse-to-pulse carrier frequency modulation to increase probability of detection, to reduce Vulnerability to jamming, and to reduce probability of interception. However, if coherent processing is used for clutter rejection, the frequency of N consecutive pulses must be held constant for N-pulse clutter cancellation or Doppler filtering. If M pulses are transmitted during the time the antenna illuminates a target, there are M/N coherently integrated echoes available for noncoherent integration in the computer or the operator's display to further improve the signal-to-noise ratio (SNR). In this paper, analytical and simulation methods are employed to determine the balance between coherent and noncoherent integration that yields the greatest SNR improvement. Attention is focused upon a model using peak selection of fast Fourier transform (FFT) Doppler channels and is compared to a reference model involving only a single Doppler channel. Curves of detectable SNR as a function of M and N are presented for both models.     

Wingtip generated wake vortices as radar target

Previous radar wake vortex detection experiments have resulted in measured beam averaged values of radar reflectivity from wake vortices in clear air. We have employed average wind and thermodynamic variable output from a two dimensional wake vortex model in clear air and fog to predict radar reflectivity in a wake vortex on a one meter grid. The results agree well, compared to data in the literature. In the clear air case, scales of turbulence were analyzed at each grid point to determine the appropriate maximum radar frequency for detection, initial wake structure, transport, and vortex persistence are related to atmospheric winds, atmospheric stability, and generating aircraft characteristics     

侧向风速对飞机尾流运动的影响

为了使机场雷达能实时探测和定位飞机尾流,对飞机飞行环境进行合理假设后提出了一个仿真尾流的保守被动模型,该模型能很好地描述尾流中水蒸气等物质的运动演化规律。综合考虑大气环境中风速对尾流的影响,利用该仿真模型对尾流进行了实时仿真,得到了不同侧向风速情况下,不同时刻尾流的状态分布等重要特性。通过分析侧向风速对飞机尾流运动过程的影响,证明了当侧向风速为1.0~3.0 m/s时是最危险的,所得结论可为飞机飞行过程中避免尾流的影响提供理论依据。     

飞机尾流的快速建模方法

尾流的强度主要由飞机的飞机重量、飞行速度和机翼形状所决定和仿真尾流的保守被动模型可很好的描述尾流系统中水蒸汽、位温等保守被动量的运动演化规律,但这种参数仿真时间长、对计算机要求高,不能实时预测任一机型所产生的尾流的状态分布特性.为此提出了一种尾流的快速建模方法,很好的解决了以往尾流实时仿真时的缺点,为飞机飞行过程中实时预测前机尾流的影响区域提供理论依据,从而减少尾流事故的发生.      

Electromagnetic Effects of Aircraft Wake-Active Feuillet Interaction

A mechanism by which an aircraft wake can interact strongly with the electromagnetic radiation present in an active elevated anomalous refractivity region (active feuillet) is analyzed. The aircraft wake structure, assumed to consist of twin contrarotating vortices plus entrained irrotational gas, trailing behind the wings of typical large aircraft is shown to be capable of descending a distance of approximately 3 wing span distances and attaining a length of the order of 10 km, prior to instability-induced disruption. The parcel of air such a descending coherent wake structure can convey into an active feuillet is demonstrated to alter significantly the local refractive index of the duct and induce substantial radiation spillage. The general characteristics of the electromagnetic radiation produced by this interaction process (i.e., scattering by diaphanous objects) is described.     

高信噪比、高分辨宽测绘带成像

针对传统高分辨和宽测绘带以及高信噪比和宽测绘带之间的矛盾,提出一种基于脉内扫描面阵合成孔径雷达(SAR)系统的二维空域联合处理算法实现高信噪比、高分辨宽测绘带成像。文中首先建立脉内扫描面阵SAR系统模型,该系统采用低脉冲重复频率(PRF)获得宽测绘带信息,同时利用脉内扫描方式获得高信噪比的回波信号。对于低PRF采样宽多普勒谱(对应方位高分辨)引起的多普勒模糊以及脉内扫描引起的距离模糊,提出一种二维空域联合处理算法解距离和多普勒模糊,并且详细地分析了地形高度变化对解模糊算法的影响。最后,通过仿真实验验证了本文算法的有效性。     

Adaptive polarimetric target detection with coherent radar. I.Detection against Gaussian background

The derivation of a completely adaptive polarimetric coherent scheme to detect a radar target against a Gaussian background is presented. A previously proposed Generalized Likelihood Ratio Test (GLRT) polarimetric detector is extended to the case of a general number of channels; this exploits the polarimetric characteristics of the received radar echoes to improve the detection performance. Together with the fully adaptive scheme, a model-based detector is derived that has a lower estimation loss. A complete theoretical expression is derived for the detection performance of both proposed polarimetric detectors. They are shown to have Constant False Alarm Rate (CFAR) when operating against Gaussian clutter, but to be sensitive to deviations from the Gaussian statistic. The application to recorded radar data demonstrates the performance improvement achievable in practice     

Probablity of Detection for ICW Radars

Eclipsing of received signals is analyzed for Interrupted Continuous Wave (ICW) radars. A probability density for the Signal to Noise Ratio (SNR) at the Doppler filter output is derived which incorporates eclipsing effects and a fluctuating target cross section model. The probability of detection as a function of SNR is calculated for typical ICW parameters and the magnitude of the detection loss due to eclipsing is assessed     

The turbulent decay of trailing vortex pairs in stably stratified environments

The decay of trailing vortex pairs in thermally stably stratified environments is investigated by means of large eddy simulations. Results of in-situ measurements in the wakes of different aircraft are used to find appropriate intitializations for the simulation of wake turbulence in the quiescent atmosphere. Furthermore, cases with weak atmospheric turbulence are investigated. It is shown that the early development of the vortices is not affected by turbulence and develops almost identically as in 2D simulations of wake vortices in stably stratified environments. In a quiescent atmosphere the subsequent vortex decay is controlled by the interaction of short-wave disturbances, owing to the aircraft induced turbulence, and baroclinic vorticity, owing to stable stratification. As a consequence, vertical vorticity streaks between the vortices are induced which are substantially intensified by vortex stretching and finally lead to rapid turbulent wake-vortex decay. When in addition atmospheric turbulence is also present, the long-wave instability is dominantly promoted. For very strong stratification (Fr<1) it is observed that wake vortices may rebound but lose most of their strength before reaching the flight level. Finally, the simulation results are compared to the predictive capabilities of Greene's approximate model.     

Two-dimensional wake vortex physics in the stably stratified atmosphere

The effects of stable stratification on aircraft wake vortices are investigated by means of high-resolution two-dimensional simulations. The simulations elucidate that the vortices first decelerate and then accelerate their descent, where they largely conserve their circulation. However, for very stable stratification the tip vortices may rise again to the flight path. The underlying physical mechanisms are revealed by means of a point vortex method and are examined complementarily by balancing the impulse of the wake vortices. It is shown that the prominant effects, deceleration, detrainment and acceleration, are caused by the kinematic interaction of the vorticity generated by baroclinity and the primary vorticity. Furthermore, it is found that the impulse of the ‘whole’ system, including the detrained secondary vorticity, is oscillating with the Brunt-Väisälä frequency which implies that the wingtip vortices themselves do not. Finally, a local shear-number is proposed which takes into account the interaction of primary and secondary vorticity and can describe the instantaneous tendency of wake vortices to accelerate or to decelerate.     

喷流对飞机尾流涡影响的试验研究

飞机产生的尾流涡,特别是大尺度的翼尖涡,对尾随其后的飞行器是非常有害的,本文旨在探索利用飞机发动机产生的喷流加速尾流涡消亡的方法。试验采用简化的飞机模型(有尾翼),建立了包含一对翼尖涡及一对反向旋转的尾翼涡(通过以负迎角安装尾翼得到)的4涡尾流系统。在无外来扰动的情况下,不同的尾翼设置下得到的尾翼涡对翼尖涡的作用效果不同,有的能导致翼尖涡提前消亡,有的则不能。考察了不同强度的喷流对不同4涡尾流系统的影响,且作为对比,对无尾翼(2涡系统)及无喷流下的各种情况也分别作了观测。试验在拖曳水槽中进行,运用体视粒子图像测速(SPIV)技术,观测了与模型拖曳方向垂直的、从机翼后缘到下游约45翼展间均布的一系列切面。结果表明:当喷流直接作用于涡时,其效果主要取决于两者之间的初始距离及相对强度;而当喷流作用于整个4涡尾流系统时,其引入的扰动对不同的系统均能起到一定程度的改善作用,这种作用的关键在于利用喷流优化对翼尖涡进行扰动的机制,而不仅仅取决于喷流的强度。     

Signal-to-Noise Ratio Calculations in Pulse and Pulse Doppler Radars

In low pulse-repetition frequency (PRF) pulse radars, signal-to-noise ratio (SNR) is usually calculated on a per pulse basis and this value is then multiplied by the number of pulses integrated to obtain the SNR for a given duration of target illumination. In high PRF pulse Doppler radars, SNR is usually calculated by using the centerline power of the transmitted signal spectrum as the target return power because the centerline is kept in the receiver and returns of the PRF lines are notched out [1]. We show here that both methods of SNR calculations are entirely equivalent for matched transmit-receive radar systems.     

Wake vortex control - a challenge for large transport aircraft

One of the most promising routes to increase capacity at over-crowded European airports is to reduce the separation distances between aircraft on landing and take-off, or vertical separations in densely flown en-route sectors. Separations are necessary to avoid the risk of encountering a wake from a preceding aircraft - and hence are vital for flight safety. This is becoming even more critical with the advent of very-large transport aircraft. This article explains the characterisation of wave vortices, and explores the European Projects looking at the problem.     

扫描模式航管监视雷达风电场杂波检测与抑制

近年来,全球风力发电装机容量呈指数增长。研究表明,风轮机对其附近的航管(ATC)监视雷达会产生严重影响。风轮机杂波的有效检测及抑制,对于保证空中交通安全具有重要意义。首先提出了基于回波谱宽特征的航管监视雷达的风轮机杂波检测方法。针对扫描模式下航管监视雷达频谱分辨率较低的问题,将基于自回归(AR)模型的超分辨率方法和质量中心的概念应用于雷达回波的快速谱宽和谱中心估计算法中,提高谱宽估计的精度。其次针对扫描模式下的风轮机回波数据不是一个完整周期数据的问题,基于缺省数据幅度和相位估计(GAPES)算法实现了扫描模式下风轮机雷达回波缺省数据的估计,而后利用风轮机杂波的周期性抑制风轮机杂波。该算法实现了风轮机杂波的有效检测和抑制,并且其不受限于风轮机与飞机目标在同一个距离单元的情况。仿真结果验证了所提方法的有效性。     

翼尖涡流场特性及其控制

大型运输飞机的尾涡系是诱发后继小型飞机空难的重要原因,需要有效的涡控制装置来削弱其强度.通过风洞实验,研究了翼型为NACA23016的矩形半机翼模型翼尖尾涡流动结构和控制方法.应用七孔探针空间流场定量测试技术研究了翼尖涡的流动结构,给出了翼尖尾涡在下游两倍弦长距离内的速度和压力场分布随迎角变化的规律.在机翼翼梢布置不同组合方式的翼梢涡扩散器,来控制翼尖涡.研究结果表明,正负90°和60°安装角的双翼梢涡扩散器可将翼尖涡涡核的静压增加60%以上.其旋涡强度削弱机理为:翼梢涡扩散器将集中的翼尖涡破碎分成两个或多个强度更弱的旋涡.在流体粘性的作用下,旋涡能量耗散更快,可有效地削弱翼尖尾涡的强度.     

Radiometric detection of spread-spectrum signals in noise ofuncertain power

The standard analysis of the radiometric detectability of a spread-spectrum signal assumes a background of stationary, white Gaussian noise whose power spectral density can be measured very accurately. This assumption yields a fairly high probability of interception, even for signals of short duration. By explicitly considering the effect of uncertain knowledge of the noise power density, it is demonstrated that detection of these signals by a wideband radiometer can be considerably more difficult in practice than is indicated by the standard result. Worst-case performance bounds are provided as a function of input signal-to-noise ratio (SNR), time-bandwidth (TW) product and peak-to-peak noise uncertainty. The results are illustrated graphically for a number of situations of interest. It is also shown that asymptotically, as the TW product becomes large, the SNR required for detection becomes a function of noise uncertainty only and is independent of the detection parameters and the observation interval     

Closed-Form Expressions for Noncoherent Radar Integration Gain and Collapsing Loss

Closed-form formulas allow rapid determination of noncoherent integration gain and integration loss when the single-sample IF signal-to-noise ratio (SNR) is known. In addition, if the required SNR is known for any number of integrated pulses, the required SNR for any other number is easily determined. A closed-form expression is given for radar collapsing loss, expressed in terms of the equivalent integrated signal-to-noise ratio required to produce a given combination of false-alarm and detection probabilities. Alternatively, the single-sample signal-to-noise ratio of a set of samples may be used together with the closed-form expression for integration gain to get the equivalent integrated signal-to-noise ratio.