## 1 Introduction  
At present, most of the UAV honeycomb sandwich body structures are bonded by two layers of carbon fiber (or 7075 aluminum skin) and a single layer of NOMEX honeycomb core. In the face of damaged elements such as shock waves and high-speed fragments, the stacking energy consumption of the core layer is relatively weak, and the longitudinal tensile effect of the skin cannot be reflected. The impact speed of 10 m/s can completely damage the structure, so the impact resistance of the structure is not strong, which only meets the needs of lightweight [1]. Therefore, the study of honeycomb sandwich structure should focus on the failure mode and energy absorption after failure, so as to reduce the damage effect on the whole structure [2, 3]. Although the honeycomb sandwich structure composed of NOMEX honeycomb core and carbon fiber skin reduces the weight of the fuselage, it is not suitable for the structure of anti-fragment impact. At present, the research work on the structural design of UAV honeycomb sandwich bodies is rarely reported. Therefore, in order to seize air superiority, the design of a comprehensive, effective, and impact-resistant new honeycomb sandwich body structure becomes very important. Honeycomb sandwich structure has a series of characteristics such as high specific strength, high specific stiffness, and excellent thermal insulation/noise reduction performance, which makes its application on UAVs inevitable [4]. In recent years, the research of UAVs has made great progress in the direction of lightweight design. At present, many structural parts of military UAVs, including parts, basically adopt a lightweight honeycomb sandwich structure and composite material. More than 90% of the body structure of X-45 UAV developed by Boeing Company uses low-temperature curing prepreg and a foam sandwich structure. By adding beams and ribs made of carbon fiber-embedded composite materials, new hybrid fiber prepregs, epoxy resin structural skins, low-temperature curing prepregs, and other improved materials, the performance of UAVs has been greatly improved [5; 6; 7; 8; 9; 10; 11]. Although the light weight of the fuselage structure is basically realized, the existing impact mode is sufficient to fully damage the fuselage structure. Therefore, the UAV protection measures need to be improved, and the impact resistance of the fuselage still needs to be further strengthened. The structural design of the UAV fuselage still needs more scientific research work. The shape of the traditional honeycomb structure is relatively regular, mainly including quadrilateral, hexagonal, circular, foam, corrugated, etc. [12; 13; 14; 15; 16; 17]. Based on the traditional honeycomb sandwich structure, new structures such as chirality and anti-chirality [18; 19; 20; 21] have emerged, followed by structural composite, stepped, and mixed honeycomb sandwich structures of different materials in the above research [22; 23; 24]. In addition to the new design carried out by many scholars, there are a large number of impact experiments on composite honeycomb structures, including the relationship between impact energy and residual strength. The influence of structural free vibration on the dynamic performance of sandwich beams under different magnetic field intensities; there is an energy absorption effect of series multilayer honeycomb structure after crushing. At the same time, with the progress of the finite element method, a large number of scholars have carried out numerical simulation and static compression test research on honeycomb structure [25; 26; 27]. [PERSON] et al. [28]. studied the effect of high-speed impact on carbon fiber epoxy resin quasi-isotropic laminates. The residual velocity and damage area under impact angle and large-scale velocity were tested to evaluate the effect of projectile kinetic energy on the dynamic response of laminates. [PERSON] et al. [29].