A Performance Measure for Evaluating Aircraft Landing Trajectories

A general performance index is developed for evaluating aircraft landing trajectories. The primary term in the index is the effect of noise on people residing near the air terminal. Other terms included are passenger comfort, fuel consumed, and the time spent in the near-terminal area. Models are developed for aircraft engine noise, passenger comfort, the population distribution about a specific airport, and the aircraft flight behavior. While this performance index may be used in computing optimal trajectories, it is also useful for comparing nonoptimal trajectories which, for one reason or another, may be worthy of consideration. Some examples of such comparisons are included through simulations of landing. The aircraft considered is a Boeing 737.     

Tracking of conventional beamforming with hydrophone array ofvarying geometry

In conventional beamformers of a large towed hydrophone array of fixed linear array geometry the sensors may be displaced from their nominal positions due to various kinds of force on the array. The displacements are usually time varying and can severely degrade the performance of the beamformer. This problem is approached by restoring the sensor output signals before beamforming by adaptively tracking and compensating for the displacements. This approach does not require modifications of the conventional shipboard beamformer and hence can be used cost-effectively to upgrade existing conventional systems. Two adaptive algorithms are used for two different cases: known sensor moving trajectories and unknown trajectories with relatively small displacements compared with the intersensor spacing. Tracking performance of the algorithms is analyzed. Simulation results show that for known sensor trajectories the algorithm significantly improves the performance of the conventional shipboard beamformer whereas only limited improvement can be achieved when the trajectories are unknown     

某民用机场航空噪声影响计算分析

根据《机场周围飞机噪声环境标准（GB9660—88）》，以计权等效连续感觉噪声级￡删为评价量，同时参照ICAO（国际民航组织）和SAE（汽车工程师协会）的计算方法，借助FAA（美国联邦航空局）的INM（综合噪声模型）对某机场的航空噪声影响进行了详细分析，比较详细地考虑了机型组合、飞行架次、起降方向、时间分布和飞行程序等因素对机场噪声的强度、分布区域形状和分布区域面积的影响。提出一套先进的机场航空噪声影响计算与分析方法，可为今后机场作航空噪声环境影响评价提供借鉴。     

击中月球的转移轨道研究

对击中月球的转移轨道进行了全局性的研究,对这种转移轨道的要求是,近地点高度及飞行时间都是预先确定的,采用一种十分有效的算法,可以方便地找出所有满足要示转移轨道,这种方法的关键是利用初始状态终极状态的状态转移矩阵进行迭代,给出了这些转移轨道和近地点和着月点的轨迹,并讨论了轨迹随飞行时间变化的特性,研究结果表明,对于任意的轨道倾角都可以到两条满足要求的转移轨道。     

Limiter Intermodulation Improvement Due to Selective Carrier Spacing

In many space communications applications, the intermodulation between carriers, due to limiting in a common amplifier, reduces the overall signal-to-noise ratio of the signal received at the ground station. By selectively spacing the carriers, one is often able to avoid the strong or low-order intermodulation. The question arises how much improvement is gained in carrier-to-interference ratio and signal-to-interference ratio by selectively spacing carriers such that low-order cross products are avoided or their impact is effectively reduced. The following analysis investigates interference improvement due to selective carrier spacing for several spacing sequences relative to equal carrier spacing. It is shown that the intermodulation noise reduction depends on the carrier packing density of the selected spacing sequence. The carrier-to-intermodulation noise ratio increases with the number of participating carriers, while the bandwidth efficiency decreases. The signal-to-intermodulation noise ratio improves not only because of the improved carrier-to-intermodulation noise ratio, but also because the remaining interference components have spectra with larger frequency spreading.     

Infrared Systems: I. Accuracy of Angle Measurement

In this paper expressions are derived for the error in position measurement for the problem of estimating the position of an infrared target in a random background and the combined prob lem when white detector noise is also affecting the estimation. Space filters performing linear scanning, nutation, and rotation are considered. A linear scanning infrared system is then considered in greater detail. The noise on the error signal is calculated, taking into account both the estimation error, as discussed in the first part, and "false alarms" occurring in the scan area far from the target.     

Sliding mode control based guidance law with impact angle constraint

The terminal guidance problem for an unpowered lifting reentry vehicle against a sta- tionary target is considered. In addition to attacking the target with high accuracy, the vehicle is also expected to achieve a desired impact angle. In this paper, a sliding mode control （SMC）-based guidance law is developed to satisfy the terminal angle constraint. Firstly, a specific sliding mode function is designed, and the terminal requirements can be achieved by enforcing both the sliding mode function and its derivative to zero at the end of the flight. Then, a backstepping approach is used to ensure the finite-time reaching phase of the sliding mode and the analytic expression of the control effort can be obtained. The trajectories generated by this method only depend on the initial and terminal conditions of the terminal phase and the instantaneous states of the vehicle. In order to test the performance of the proposed guidance law in practical application, numerical simulations are carried out by taking all the aerodynamic parameters into consideration. The effec- tiveness of the proposed guidance law is verified by the simulation results in various scenarios.     

Hectometric and kilometric solar radio emission observed from satellites in August 1972

Type II, III, and continuum solar radio events, as well as intense terrestrial magnetospheric radio emissions, were observed at low frequencies (10 MHz to 30 kHz) by the IMP-6 satellite during the period of high solar activity in August 1972. This review covers briefly the unique direction finding capability of the experiment, as well as a detailed chronology of the low frequency radio events, and, where possible, their association with both groundbased radio observations and solar flares. The attempted observation of solar bursts in the presence of intense magnetospheric noise may, as illustrated, lead to erroneous results in the absence of directional information. The problem of assigning an electron density scale and its influence on determining burst trajectories is reviewed. However, for the disturbed conditions existing during the period in question, we feel that such trajectories cannot be determined accurately by this method. In conclusion, the capabilities, limitations, and observing programs of present and future satellite experiments are briefly discussed.     

高超声速典型弹道下的壁板热气动弹性动力学分析

对高超声速流中带有热防护系统（TPS）的二维壁板进行了热气动弹性的双向耦合建模与分析,采用三阶活塞理论计算气动力,通过参考焓法获得气动热流,在有限差分法的基础上进行结构热传导计算,拟合了结构材料特性随温度退化的曲线,最后将气动热模块、气动弹性模块进行双向耦合以考虑气动热与结构形变之间的相互反馈,并在2种典型弹道状态下进行热气动弹性响应分析。结果表明,在X-34A的设计弹道下,双向耦合分析会引起更加剧烈的热应力与热弯矩的变化与较长的瞬态混沌过程。在FALCON弹道下,双向耦合得到的结果加热更为剧烈,而温度下降的过程也更快。对比2种弹道发现,长时间的高超声速飞行更容易引发颤振,而机动性较强的弹道面临的主要问题则是屈曲,需要考虑材料的应力及强度特性。同时说明了双向耦合策略对于现代飞行器在弹道状态下工作的热气弹响应分析的必要性。     

Angle Estimation in Amplitude Comparison Monopulse Systems

The problem of estimation of angle of arrival in amplitude comparison monopulse (ACM) radars in the presence of internally generated thermal noise is considered. A pulse-type radar is assumed and angular noise is postulated to be absent. In the treatment of the problem, explicit inclusion of various simple models for the pulse returns is made to draw a relationship between the a priori statistics of the echo signals and the ability to estimate the angle of arrival in ACM radars. A maximum likelihood analysis is made to determine the form of the estimates of angle of arrival for the various cases and the accuracy of these estimates is evaluated as a function of the signal-to-noise ratio per hit and of the number of hits. Although most of the estimates considered have already received attention, many of the results are believed to be new.     

利用恢复系数预报梁结构弹性正碰载荷的两种有效近似法

对于小球撞击欧拉－贝努利梁问题,应用撞击力模型,给出预报撞击力的两种方法。方法1基于位移协调方程,分别考虑碰撞发生阶段结束和恢复阶段结束两个时刻的位移协调方程。方法2基于梁的动力微分方程,利用撞击系统的动量守恒原理和恢复系数概念。两种方法均得到撞击过程中撞击力随时间变化的曲线。分析结果与已有结果进行比较,结果符合较好。其中方法1大幅简化计算量,可推广到小球与板撞击问题中去;方法2能够较好地描述撞击力,同时可分析各种因素对接触撞击力的影响。     

Specification and Performance of Passive Sonar Spectral Estimators

The application of existing estimation theory to the problem of specification and performance of passive sonar spectral estimators is considered. The classification function is addressed, so that the signal is assumed to be present, and so that the energy arrival angle is known. The spatial filter considered is a line array of M equally spaced omnidirectional hydrophones. Signal and ambient noise are both zero-mean, wide-sense, stationary Gaussian random processes that differ in their spatial correlation across the face of the array. The signal is a plane wave that can be made totally spacially corrected between array elements by inserting delays between sensors to invert the signal propagation delay. The noise correlation is a function of frequency, bandwidth, element separation, and the relative time delay between sensors. Under these assumptions, the Cramer-Rao lower bound is derived for the class of unbiased estimates of signal power in a narrow frequency band at the hydrophone in the presence of correlated ambient noise of known power. The bound is examined numerically, resulting in a threshold phenomenon with M that constitutes a new design consideration. In addition, there is a striking insensitivity to realistic values of ambient noise correlation, and there are ranges in signal-to-noise ratio for which one gains more by increasing M than by increasing the bandwidth-time product. Specific processors, including a new unbiased estimator when noise power is unknown, are developed.     

基于带有事件触发机制的集员滤波的RSSI室内移动定位

在室内移动定位系统中,由于待定位节点易受统计特性未知的噪声干扰影响,采用Kalman滤波和粒子滤波等经典的噪声抑制方法,已无法有效满足室内定位精度不断提升的要求.针对这一问题,提出了一种基于事件触发的集员滤波室内移动定位算法.首先,针对基于接收信号强度指数(RSSI)测距误差导致传统三边定位算法无法获取可行解的问题,提...     

Estimating the number of signals using reference noise samples

Criteria for estimating the number of signals in the case of small-sample populations are considered. The criteria introduced by M. Wax and T. Kailath (1985) do not work well in this case. Two new criteria based on information theoretic and eigenmode composition-based criteria are proposed, assuming a known noise covariance. Simulation results show a significant improvement in the performance of estimating the number of signals in the small-sample case, by the use of the new criteria combined with an estimate of the noise covariance obtained from reference noise samples     

Orbital rendezvous using two-step sliding mode control

The problem of spacecraft rendezvous is studied, using sliding mode control in the presence of the earth's gravitational perturbation. The impulsive solution of Lambert's problem is obtained using the combined equations method to minimize total ΔV via an iterative method, and it is used as the desired trajectory for the rendezvous. In this paper, a two-step sliding mode control method is introduced for solving the rendezvous problem with finite-thrust including unmodeled dynamics.The thrust-coast-thrust type control laws for the system to follow the desired trajectories are represented and resultant trajectories are close enough to the Lambert's orbit with comparable amount of ΔV to the Lambert's impulsive solution. All state variables matched the final boundary conditions reasonably well at the end of maneuver.     

In-Flight Alignment and Calibration of Inertial Measurement Units?Part II: Experimental Results

This is the second part of a two-part paper which summarizes work pursued by the author in 1967 [2]. The paper describes the application of minimum-variance estimation techniques for in-flight alignment and calibration of an inertial measurement unit (IMU) relative to another IMU and/or some other reference. The first paper [1] formulates the problem, and this paper reports numerical results and analyses. The approach taken is to cast the problem into the framework of Kalman-Bucy estimation theory, where velocity and position differences between the two IMU's are used as observations and the IMU parameters of interest become part of the state vector. Instrument quantization and computer roundoff errors are considered as measurement noise, and environmental induced random accelerations are considered as state noise. In this paper, numerical results for three important IMU error parameter configurations are presented and discussed. The main results of the paper determine the effects of state and observation noise levels and the nominal trajectory on the identifications of the errors for these configurations. A discussion of the minimum number of trajectory maneuvers and of the optimal trajectory maneuvering is given.     

Noise subspace techniques in non-gaussian noise using cumulants

We consider noise subspace methods for narrowband direction-of-arrival or harmonic retrieval in colored linear non-gaussian noise of unknown covariance and unknown distribution. The non-gaussian noise covariance is estimated via higher order cumulants and combined with correlation information to solve a generalized eigenvalue problem. The estimated eigenvectors are used in a variety of noise subspace methods such as multiple signal classification (MUSIC), MVDR and eigenvector. The noise covariance estimates are obtained in the presence of the harmonic signals, obviating the need for noise-only training records. The covariance estimates may be obtained nonparametrically via cumulant projections, or parametrically using autoregressive moving average (ARMA) models. An information theoretic criterion using higher order cumulants is presented which may be used to simultaneously estimate the ARMA model order and parameters. Third- and fourth-order cumulants are employed for asymmetric and symmetric probability density function (pdf) cases, respectively. Simulation results show considerable improvement over conventional methods with no prewhitening. The effects of prewhitening are particularly evident in the dominant eigenvalues, as revealed by singular value decomposition (SVD) analysis     

飞机性能参数预测的不确定性处理

 利用飞机的性能参数对飞机进行故障预报和状态监控是非常重要的。飞机的性能参数不仅具有非线性而且往往包含噪声,使得故障预测结果具有不确定性。针对这些问题,研究了利用非线性支持向量机处理飞机性能参数的预测问题,通过增加线性约束的方式解决了噪声带来的不确定性问题。此种方法不仅提高了预测的精度,而且模型可以利用适用于处理大规模二次规划的序列最小最优化算法进行求解,使得其可以解决大数据量的预测问题。利用仿真数据以及实际飞机性能参数对该方法进行了实验分析,实验结果表明此方法在精度上较不考虑噪声影响的模型有所提高,对于进一步提高飞机故障预测的精度,从而提高飞机的安全性具有重要意义。     

Distributed state estimation for heterogeneous mobile sensor networks with stochastic observation loss

The problem of distributed fusion and random observation loss for mobile sensor networks is investigated herein. In view of the fact that the measured values, sampling frequency and noise of various sensors are different, the observation model of a heterogeneous network is constructed. A binary random variable is introduced to describe the drop of observation component and the topology switching problem caused by complete observation loss is also considered. A cubature information filtering algo...     

飞机壁板辐射声的有源控制

利用一块飞机壁板讨论有源消声技术降低飞机舱内噪声。首先从理论上说明了利用有源消声抵消壁板辐射声的可行性;介绍了可用于工程的自适应有源消声器;最后在实验室对振动激励的壁板输射声、声激励时壁板的透射声进行了消声实验,取得了良好的效果。