This work focuses on a novel pseudomeasurement-aided estimation scheme for angle of attack (AOA) in a mini unmanned aerial vehicle with a 1.61 m wingspan. A scale-reduced model of the same is used in a wind tunnel, and the necessary measurements are recorded. Wind-tunnel measurements are used to write down the $C_L$ and $C_D$ equations of the flight vehicle. A pseudomeasurement-aided scheme for estimation of AOA is established using an aerodynamic model extracted from wind-tunnel experiments. Computational analysis of the estimation scheme is performed, followed by flight tests and postflight analysis. The flight vehicle is instrumented with all the necessary sensors, along with a commercially available AOA vane probe (Swiss Air data smart miniature vane SMV-1) for direct measurements of AOA. Using flight recorded data in a MATLAB program, the estimated AOA is compared with actual measurements of Alpha $\alpha$, and estimation schemes performances are evaluated.

这项工作的重点是一种新颖的伪测量辅助估计方案，用于翼展为1.61 m的微型无人机中的迎角（AOA）。在风洞中使用相同比例的缩小模型，并记录必要的测量值。风洞测量用于记下$C_{\mathrm{大号}}$ 和 $C_d$飞行器方程。使用从风洞实验中提取的空气动力学模型，建立了一种伪测量辅助的AOA估计方案。对估计方案进行计算分析，然后进行飞行测试和飞行后分析。该飞行器配备了所有必需的传感器，以及用于直接测量AOA的市售AOA叶片探头（瑞士航空数据智能微型叶片SMV-1）。使用MATLAB程序中的飞行记录数据，将估算的AOA与Alpha的实际测量值进行比较$\alpha$，并对评估方案的性能进行评估。