航天器多普勒测速平均误差的分析与修正

对航天器多普勒测速平均误差进行了分析,详细推导了圆轨道和椭圆轨道时该误差的计算公式,计算了不同采样周期和轨道高度时的误差大小。经过分析指出,该项误差对于高轨航天器影响较小,对于低轨航天器可以通过缩短采样周期或利用3个点或多个点的连续测量数据进行修正。     

基于杆臂补偿的多MIMU六方位倍速率标定方法

误差建模、标定与补偿是提高微惯性测量单元(MIMU)精度的关键,而杆臂效应是影响低成本微机电系统(MEMS)惯导精度进一步提升的瓶颈。针对杆臂效应引起的多MIMU标定误差问题,提出了一种基于杆臂补偿的多MIMU六方位倍速率标定方法。分析了杆臂效应影响多MIMU标定的误差机理,设计了一种六方位倍速率标定方案,建立了基于杆臂补偿的误差系数标定解算模型,补偿了杆臂效应引起的标定误差,并应用加权最小二乘法对MIMU加速度通道和角速度通道的非对称性误差进行了抑制。试验结果表明,与现有六方位正反速率标定方法相比,采用该方法的MIMU加速度通道补偿误差降低了84%,角速度通道补偿误差降低了68%。     

光学压力敏感涂料测量技术及其在内流场应用

本文介绍了应用基于发光强度的全域压力测量方法进行叶片表面压力分布的一系列实验结果。在自主建立光学压力测量系统和自主研发国产压力敏感涂料的基础上，对高亚音速叶栅风洞出口处大弯度孤立叶片吸力面和对转压气机实验平台出口整流叶片吸力面的压力分布进行了测量，并采用传统电子静压扫描装置在高亚音速叶栅风洞中进行了同步测量。光学压力测量与电子压力扫描结果的对比表明所建立的光学压力测量系统可用于内流场测量，其精度达到了工程应用水平。     

A learning-based approach for solving shear stress vector distribution from shear-sensitive liquid crystal coating images

A learning-based approach for solving wall shear stresses from Shear-Sensitive Liquid Crystal Coating(SSLCC) color images is presented in this paper. The approach is able to learn and establish the mapping relationship between the SSLCC color-change responses in different observation directions and the shear stress vectors, and then uses the mapping relationship to solve wall shear stress vectors from SSLCC color images. Experimental results show that the proposed approach can solve wall shear s...     

一种基于模观测法的离心机加速度计组合标定方法研究

为了实现惯性组合中加速度计误差模型系数的整体标定,提高惯性导航系统的导航精度,应用模观测法重点实现了对加速度计二次项系数的标定.应用Tylor级数对加速度模型的解进行多项式展开,利用最小二乘法求得含误差模型系数的中间变量,并给出了加速度计的二次项系数、标度因数以及零偏的计算公式.设计了20位置法对加速度计组合进行标定,通过仿真验证了该方法的有效性,并分析了安装误差角和杆臂误差对系数标定精度的影响.结果 表明,安装误差角与杆臂误差对系数标定的影响小于10-8,在实际标定过程中可以忽略.     

IABC: An iteratively automatic machine learning boosted hand-eye calibration method for laser displacement sensor

An on-machine measuring (OMM) system with a laser displacement sensor (LDS) is designed for measuring free-form surfaces of hypersonic aircraft’s radomes. To improve the measurement accuracy of the OMM system, a novel Iteratively Automatic machine learning Boosted hand-eye Calibration (IABC) method is proposed. Both the hand-eye relationship and LDS measurement errors can be calibrated in one calibration process without any hardware changes via IABC. Firstly, a new objective function is derived, containing analytical parameters of the hand-eye relationship and LDS errors. Then, a hybrid calibration model composed of two kernels is proposed to solve the objective function. One kernel is the analytical kernel designed for solving analytical parameters. Another kernel is the automatic machine learning (AutoML) kernel designed to model LDS errors. The two kernels are connected with stepwise iterations to find the best calibration results. Compared with traditional methods, hand-eye experiments show that IABC reduces the calibration RMSE by about 50%. Verification experiments show that IABC reduces the measurement deviations by about 25%-50% and RMSEs within 40%. Even when the training data are obviously less than the test data, IABC performs well. Experiments demonstrate that IABC is more accurate than traditional hand-eye methods.     

Installation error calibration for MEMS angular measurement system in hypersonic wind tunnel

The accuracy of model attitude measurement has an important impact on wind tunnel test results. Microelectromechanical System Inertial Measurement Unit (MEMS IMU) provides a feasible way to measure model attitudes with high accuracy. However, the installation error between MEMS IMU coordinate system and the body coordinate system of test models can make the accuracy of the model attitude measurement decrease. In wind tunnel tests, the installation error depends on the relationship between the IMU and the model mechanism before tests. Therefore, in-field calibration in wind tunnel tests is necessary to reduce installation errors. To improve attitude measurement accuracy, the least squares quaternion calibration method based on MEMS IMU and six-position calibration procedure are proposed. High-precision three-axis turntable tests are performed. The pitch accuracy after calibration is higher than that before calibration in the angle of attack sweeping tests. The Root-Mean-Square Errors (RMSE) in the roll and yaw are within 0.01°, which are smaller than those before calibration. In the roll sweeping tests, RMSE of three attitude angles decrease significantly. In hypersonic wind tunnel tests, the pitch errors before and after calibration are within 0.05° and 0.02° in the angle of attack sweeping tests without wind. In five angle of attack sweeping tests with wind, the deviation between the mean of the pitch and the pitch after the elastic angle correction is within 0.03° and the standard deviation of five tests is within 0.01°. The proposed method is confirmed to enhance the accuracy of attitude measurement effectively, which is convenient for engineering applications.     

地面放射性测量模型γ剂量率值空间分布规律研究

地面模型是根据IAEA174号报告研建的用于校准便携式γ能谱仪、γ辐射仪的计量标准装置，最初主要用于地质勘查。2016年至2018年，新研建了钾含量30 %（YK3）和铀含量1 %（YU4）的两个模型，并确定了模型量值。远离模型表面中心位置的剂量率较低，随着中心点的接近，剂量率逐渐上升，YK3和YU4的剂量率坪区分别为模型中心点及周围半径约40 cm和50 cm范围内，在坪区内剂量率变化均不大于0.6 %；在参考点3.0 cm上的剂量率分别为320.8 nGy·h^-1和4.3×10⁴ nGy·h^-1；超过3.0 cm时，剂量率随高度呈非线性变化；根据不同高度上的理论计算和实测结果比对，在40 cm高度实测范围以内，YK3实测结果与理论计算结果相对偏差在3 %范围以内，120 cm高度实测范围内，YU4实测结果与理论计算结果相对偏差在2 %范围以内。     

标定脉宽对冲击传感器标定结果的影响

不同冲击脉宽在标定压电式冲击传感器过程产生不同的结果，主要原因是脉宽冲击频率处于传感器安 装频响的放大区，不同的脉宽作用于传感器后放大效应不同，导致标定结果差异。冲击传感器使用空气炮和霍普金 生杆进行单独标定，对标定结果进行了差异分析。对传感器安装频响曲线进行了定性分析，符合冲击脉宽差导致不 同标定结果的事实。对标定过程中标定脉宽控制提出了具体的措施，对于正确标定冲击传感器具有指导意义。