This work is the next stage of the project of the aerial target presented before, this time related to the structural integrity of the composite-made structure of the airframe. According to aircraft design regulations, the aircraft structure must be able to support limit loads without any permanent deformation. The paper contains: the methodology of determination of external loads (critical loads) of a flight envelope acting on the airframe during the flight, then the numerical analysis of the strength and integrity of the airframe structure, and finally ground statics tests on the measurement so-called the proof of compliance strength tests under load. The research and investigation presented are in accordance with the airworthiness regulations (CS-VLA standards) required by the European Union Aviation Safety Agency (EASA), which are prerequisite of the qualification tests of the aircraft, leading to the certification of the aircraft (type certificate). The aerial system was positively verified during the qualification tests of the system at the Polish Air Force training range and finally received the type certificate and introduced into the service.