摘要
介绍了嵌入式大气数据传感(FADS)系统的测压孔布局和压力模型;分析了超定线性方程组的解法,并用广义逆矩阵A+计算其最小二乘解;建立了形压系数ε与马赫数M∞、迎角α和侧滑角β的确切的函数模型;提出了故障点的处理方法;并用神经网络实现对动压、静压的求解。计算结果表明:飞翼飞行器的FADS系统的算法能够满足设计要求。
Structures of pressure points and the pressure model of the flush airdata sensing（FADS） system are introduced,the algorithm of linear equations of the overdetermined system is analyzed, and the pseudo-inverse matrix A^＋ is developed to work out the least-square solution. The definite function model between the calibration factor ε and M∞ ,α ,β is developed. An idea of dealing with failure points is showed. Solutions of the dynamic pressure and static pressure are worked out by means of the neural network. The result of validation indicates that the algorithm in FADS system of flying wing vehicle can meet the requirement of designing.
出处
《传感器与微系统》
CSCD
北大核心
2008年第4期12-14,17,共4页
Transducer and Microsystem Technologies
关键词
嵌入式大气数据传感系统
超定线性方程组
广义逆A^+
故障点
神经网络
flush airdata sensing system
overdetermined system of linear equations
pseudo-inverse A^＋
failure points
neural network
