Acoustic node calibration using a moving source

Acoustic nodes, each containing an array of microphones, can track targets in x-y space from their received acoustic signals, if the node positions and orientations are known exactly. However, it is not always possible to deploy the nodes precisely, so a calibration phase is needed to estimate the position and the orientation of each node before doing any tracking or localization. An acoustic node can be calibrated from sources of opportunity such as beacons or a moving source. We derive and compare several calibration methods for the case where the node can hear a moving source whose position can be reported back to the node. Since calibration from a moving source is, in effect, the dual of a tracking problem; methods derived for acoustic target trackers are used to obtain robust and high resolution acoustic calibration processes. For example, two direction-of-arrival-based calibration methods can be formulated based on combining angle estimates, geometry, and the motion dynamics of the moving source. In addition, a maximum likelihood (ML) solution is presented using a narrowband acoustic observation model, along with a Newton-based search algorithm that speeds up the calculation the likelihood surface. The Cramer-Rao lower bound (CRLB) on the node position estimates is also derived to show that the effect of position errors for the moving source on the estimated node position is much less severe than the variance in angle estimates from the microphone array. The performance of the calibration algorithms is demonstrated on synthetic and field data.     

CS-01高空台推力测量和校准装置研制

推力是涡喷涡扇发动机高空模拟试验的重要测量参数之一。CS－01高空台原推力测量采用杠杆、砝码、测力秤系统，现采用原位校准，液压加载、应变式推力传感器来测量和校准，从而消除了“高度差”的影响，降低了稳态推力测量系统的测量不确定度。     

Altitude Estimation Using Asynchronous ? - ? Tracking Filters

In the analysis of the ?-? tracking filter it is usually assumed that the tracking filter and data source operate in synchronism at a constant data rate. However, in a multisensor environment in which the tracking algorithm operates at fixed intervals, the tracking filter cannot be synchronized with the sensors. An analytical solution is obtained for the case in which the tracking filter and data source operate asynchronously with a ?time-correction? process used to approximate the synchronous operation of the tracking filter. An example is given in which the effects of data quantization on the performance of an altitude tracking filter for air traffic control are examined. It is shown that the asynchronous operation of the tracking filter in the example without the time-correction process will result in significant errors in the predicted altitude.     

AD598的RVDT数据采集系统校准方法研究及分析

RVDT(Rotary Variable Differential Transformer)数据采集系统广泛应用于民用航空领域飞行控制系统功能的研究及测试。RVDT将机械位移信号转换成电信号。数据采集系统接收RVDT输出的差分信号,将信号调理、转化并计算后显示。分析了基于AD598的RVDT数据采集系统的校准方法,并对系统的不确定度来源及分析方法进行了介绍。     

The Far Ultra-Violet Imager on the Icon Mission

ICON Far UltraViolet (FUV) imager contributes to the ICON science objectives by providing remote sensing measurements of the daytime and nighttime atmosphere/ionosphere. During sunlit atmospheric conditions, ICON FUV images the limb altitude profile in the shortwave (SW) band at 135.6 nm and the longwave (LW) band at 157 nm perpendicular to the satellite motion to retrieve the atmospheric O/N₂ ratio. In conditions of atmospheric darkness, ICON FUV measures the 135.6 nm recombination emission of \(\mathrm{O}^{+}\) ions used to compute the nighttime ionospheric altitude distribution. ICON Far UltraViolet (FUV) imager is a Czerny–Turner design Spectrographic Imager with two exit slits and corresponding back imager cameras that produce two independent images in separate wavelength bands on two detectors. All observations will be processed as limb altitude profiles. In addition, the ionospheric 135.6 nm data will be processed as longitude and latitude spatial maps to obtain images of ion distributions around regions of equatorial spread F. The ICON FUV optic axis is pointed 20 degrees below local horizontal and has a steering mirror that allows the field of view to be steered up to 30 degrees forward and aft, to keep the local magnetic meridian in the field of view. The detectors are micro channel plate (MCP) intensified FUV tubes with the phosphor fiber-optically coupled to Charge Coupled Devices (CCDs). The dual stack MCP-s amplify the photoelectron signals to overcome the CCD noise and the rapidly scanned frames are co-added to digitally create 12-second integrated images. Digital on-board signal processing is used to compensate for geometric distortion and satellite motion and to achieve data compression. The instrument was originally aligned in visible light by using a special grating and visible cameras. Final alignment, functional and environmental testing and calibration were performed in a large vacuum chamber with a UV source. The test and calibration program showed that ICON FUV meets its design requirements and is ready to be launched on the ICON spacecraft.     

Geolocation of a known altitude object from TDOA and FDOA measurements

Most satellite systems for locating an object on Earth use only time difference of arrival (TDOA) measurements. When there are relative motions between an emitter and receivers, frequency difference of arrival (FDOA) measurements can be used as well. Often, the altitude of an object is known (it is zero, for example) or can be measured with an altimeter. Two sets of geolocation solutions are proposed which exploit the altitude constraint to improve the localization accuracy. One is for TDOAs alone and the other for the combination of TDOA and FDOA measurements. The additional complexity by imposing the constraint is a one-dimensional Newton's search and the rooting of a polynomial. The covariance matrices of the new estimators are derived under a small measurement noise assumption and shown to attain the constrained Cramer-Rao lower bound (CRLB). When there is a bias error in the assumed altitude, using the altitude constraint will introduce a bias to the solution. Since applying the constraint decreases the variance, there is a tradeoff between variance and bias in the mean square error (MSE). The maximum allowable altitude error such that the constraint solution will remain superior to the unconstraint is given. Simulation results are included to corroborate the theoretical development.     

一种联合估计的有源校正高精度测向算法

针对存在系统误差的阵列模型,提出了一种有源标校下的联合估计测向算法。该算法把误差矩阵估计转化为误差系数估计,并采用到达角精确已知的源信号进行标校,在此基础上使用最小二乘法联合估计幅相不一致误差系数和互耦误差系数,最后使用结合误差矩阵的MUSIC算法测量信号的到达角。仿真表明,该算法仅需要3个标校源,其精度相比于无阵列误差情况下降0.05°,具有较好的工程可实现性。     

用大面积源检定核应急机载/车载伽玛能谱仪

人工核素大面积源标准是核工业航测遥感中心等单位经过十余年研究建立的新型计量保障标准,使用该标准,可对监测核应急伽玛辐射环境的机载/车载伽玛能谱仪进行检定.使用大面积源标准检定,可以有效地弥补因机载/车载伽玛能谱仪系统的角响应影响因素复杂而难于模拟计算的缺陷,为监测核应急伽玛辐射环境的机载/车载伽玛能谱仪提供了量值传递的保障.本文介绍了大面积源检定的原理和技术方法.     

空速的GPS试飞校准方法

通过“往返试飞”消除风速影响从而由 GPS测得的地速求得真空速,运用近似理想气体理论,建立Ma数真值与真空速、大气总温的关系,解算出 Ma数真值,得到“GPS速度法”;或者考虑真实大气与标准大气的差异,在水平航线上引入气压高度常值偏差及航路气压修正系数,建立 GPS几何高度与气压高度的关系,结合“速度法”求得的任一 Ma数点的校准量,解算出气压高度真值,得到“GPS高度法”。通过对某型飞机的飞行试验,验证了这些方法的可靠性与实用性。     

冲击响应谱绝对校准研究中冲击响应谱的计算方法

介绍了应用于冲击响应谱绝对校准中的冲击响应谱的计算方法,该方法的实现基于MATLAB编程语言,即通过MATLAB中的仿真直接求解单自由度二阶微分方程的数值解以获得冲击响应谱的绝对复现.     

Minimax Approach to Trajectory Optimization of Multistage Launch Vehicles

An optimum pitch steering program is developed, using a minimax technique, for a multistage launch vehicle in the presence of large parameter uncertainties. The uncertainties are characterized by deterministic bounds on the respective parameters. The pitch steering program is obtained by maximizing two independent scalar performance ance indexes. 1) the coast apogee velocity for a specified altitude; 2) the perigee of the satellite orbit. The product of dynamic pressure and angle of attack is constrained so as to minimize the structural loads during the atmospheric flight. The values of the uncertain parameters are determined by minimizing the same performance indexes in order to achieve a worst case design. The existence of saddle point solution to this class of problems is shown using the techniques of differential game theory. The conjugate gradient algorithm has been used for computer er aided design of the minimax technique.     

航空发动机试车台附加阻力修正方法

附加阻力(进气冲量阻力和外部冲量阻力)是航空发动机试车台架推力的重要组成部分,准确地确定附加阻力对提高发动机试车台推力测量的准确性有十分重要的意义。本文对发动机总推力和试车台的对比标定进行了介绍,对发动机在露天试车台、室内地面台和高空台上附加阻力的确定方法和修正方法进行了详细地研究,给出了高空台与高空台、高空台与地面台的对比标定试验结果。      

Microscope Instrument Development,Lessons for GOCE

Two space missions are presently under development with payload based on ultra-sensitive electrostatic accelerometers. The GOCE mission takes advantage of a three axis gradiometer accommodated in a very stable thermal case on board a drag-free satellite orbiting at a very low altitude of 250 km. This ESA mission will perform the very highly accurate mapping of the Earth gravity field with a geographical resolution of 100 km. The MICROSCOPE mission is devoted to the test of the “Universality of free fall” in view of the verification of the Einstein Equivalence Principle (EP) and of the search of a new interaction. The MICROSCOPE instrument is composed of two pairs of differential electrostatic accelerometers and the accelerometer proof-masses are the bodies of the EP test. The satellite is also a drag-free satellite exhibiting a fine attitude control and in a certain way, each differential accelerometer is a one axis gradiometer with an arm of quite null length. The development of this instrument much interests the definition and the evaluation of the sensor cores of the gradiometer. The in flight calibration process of both instruments is also very similar. Lessons form these parallel developments are presented. This revised version was published online in August 2006 with corrections to the Cover Date.     

惯性平台误差标定仿真数据源建模研究

为满足平台导航方式自标定算法对仿真数据源的需求,归纳总结了标定算法对仿真数据源的要求,提出了用于产生标定仿真数据的平台运动学模型.该模型在反映误差作用的同时回避了平台复杂控制系统和动力学特性,采用运动学微分方程描述台体在指令角速度激励下相对惯性空间的运动,通过代数方程描述加速度计的输出和框架角输出.在典型轨迹下,对仿真...     

时空守恒元和解元方法的爆震波一维数值模拟

运用基元化学反应模型和流体力学的基本原理，建立了脉冲爆震发动机一维非定常反应流数学模型。应用一种改进的时空守恒元和解元(CESE)方法建立控制方程的差分格式，针对化学反应源项的刚性问题，在对非线性源项进行线性化处理的基础上，应用隐式梯形方法实现源项的积分。对氢氧爆震波的形成和传播过程进行数值计算，结果表明，应用CESE方法和基元化学反应模型能够成功地模拟氢氧爆震波的精细结构。     

扭矩扳子检定装置量值传递相关问题探讨

通过对扭矩量值传递中有关器具工作原理及工作时受力的分析,指出了用扭矩扳子检定装置检定扭矩扳子时检定结果难以一致的原因,给出了解决办法,并进行了验证。     

一种低空声源分布式定位系统及其算法与实验研究

低空声源目标具有较强的隐身性,为了实现对此类目标的定位,构建基于TMS320C6713平台的分布式麦克风阵列低空声源定位系统.麦克风阵列节点以DSP为核心处理器,通过A/D芯片采样麦克风阵列接收到的信号,通过到达时间差(TDOA)计算声源的角度,利用测向交叉法,融合多个节点的角度信息,计算出声源的位置.结果表明:在时延估计精确的情况下,对低空目标具有较好地估计;系统具有较高的精度和稳定性,能够满足对低空声源目标进行定位的实际需求.     

大气系统校准的基准空速管法

针对国际适航认证（FAR25）及300m垂直间距空中交通管制（RVSM）等对大气系统校准提出的高精度参考基准要求,提出了直观的标准空速管法,通过对初步试验结果的分析,发现了直接校准的缺陷和偏差根源。提出了“飞行检定”观点,改进了校准原理、观测模型和数据处理方法,建立了基准空速管法。实际飞行试验及误差分析讨论,表明该方法可满足相关领域的严格要求。     

底层隔板法流体壁面剪切力的测量研究

针对流体壁面剪切力测量难度较大的问题,研制了一种流体壁面剪切力测量元件的底层隔板法,并采用理论推导、数值计算和实验相结合的方法对其性能进行研究。通过公式推导,分析了元件用于流体壁面剪切力测量的原理,找出壁面剪切力和隔板前后压力差的函数关系。实验结果表明：元件隔板前后差压与测得的流体剪切力的幂次方成正比。数值计算结果表明：测量元件的敏感尺寸是迎风薄片高度,高度越大,校准曲线斜率越小,幂次系数越小,而正比例系数越大。对底层隔板法壁面剪切力系数特性的研究,为探索其免标定应用方法奠定了基础。     

基于高度控制的拖靶定高飞行分析

超低空飞行的航空拖靶需要高精度的高度控制,而作为试验和训练的消耗性装备,其低成本设计要求使得航空拖靶不能采用常规飞行器的高度控制方法。针对以拖曳力为飞行动力的航空拖靶,研究其基于非姿态控制的定高飞行的运动特性。定高飞行航空拖靶采用高稳定性的气动布局,并基于准直接力控制的升降舵面进行高度调整操纵。通过建立拖靶的纵向运动数学模型,设计非姿态控制定高飞行控制方法,详细分析拖靶气动特性,并进行定高飞行控制的仿真计算。计算结果给出拖靶的高度控制能力及飞行状态,结果表明拖靶具有一定的高度调整能力,可以实现定高飞行。