The recent development of the Structural Health Monitoring (SHM) framework has required the simultaneous development of the tools fundamentals for its realization. The shape sensing methods and the loads identification ones have established themselves as crucial tools for the monitoring of aerospace structures. The two families of methods have been developed separately, although the possibility to achieve the knowledge of the displacement field and of the external loads together can enable a further progress in the SHM. In this paper, an integrated approach to simultaneously preform loads identification and shape sensing from discrete strain measurements is proposed. The methods is based on a two-steps process. The first step involves the identification of continuously distributed and concentrated external loads from discrete strain measurements. This step is achieved by discretizing the loads with Finite Elements (FE) and by computing the coefficients of influence between the nodal values of the loads and the discrete strain measurements. The second step reduces the shape sensing inverse problem to a simple direct Finite Element Analysis. The loads identified in the previous step are applied to a refined FE model of the structure and the displacement field is easily obtained through a direct FE analysis. This investigation proves that the two-steps method can accurately identify the loads and the displacement field of a wing box subject to an aerodynamic pressure distribution and a set of concentrated forces, when a sufficient number of strain information is available. When the number of discrete strain measurements decreases or the strains are affected by measurement error, the loads are poorly predicted but the method is still capable of an extremely accurate displacements reconstruction.

结构健康监测（SHM）框架的最新开发要求同时开发用于实现它的工具基础。形状感测方法和载荷识别方法已经成为监视航空航天结构的重要工具。尽管可以同时获得有关位移场和外部载荷的知识，但可以在SHM中取得进一步的进展，但分别开发了这两种方法。在本文中，提出了一种从离散应变测量中同时进行瓶坯载荷识别和形状感测的集成方法。该方法基于两步过程。第一步涉及从离散应变测量中识别连续分布和集中的外部载荷。通过用有限元（FE）离散载荷并计算载荷的节点值与离散应变测量之间的影响系数，可以实现这一步骤。第二步将形状感测反问题简化为简单的直接有限元分析。将上一步中确定的载荷应用于结构的有限元模型，并且可以通过直接有限元分析轻松获得位移场。该研究证明，当有足够数量的应变信息时，两步法可以准确地识别受到空气动力压力分布和集中力作用的机翼箱的载荷和位移场。当离散应变测量的数量减少或应变受到测量误差的影响时，