![]() To sum up, it is seriously important to establish a complete set of aircraft static aeroelastic model designs, wind tunnel tests and numerical simulation technologies to explore the correction measures of wind tunnel and flight data. With the increasing complexity and costs of aircraft, the danger of flight tests and the progress of wind tunnel test technology, researchers gradually began to use the similarity principle to reproduce the aeroelastic phenomenon of aircraft in the wind tunnel. This was the first experiment to use the static aeroelastic effect of the wing. In 1899, the Wright brothers improved the designed wing by controlling the bending/torsion of the wing tip to achieve the purpose of enhancing roll control. Therefore, it is increasingly important to focus on static aeroelastic effects in aircraft design.Īs early as the development of aircraft, aerodynamicists and aircraft designers have been engaged in experimental research related to static aeroelasticity. For example, the efficiency of the rudder surface maybe decreased, slightly deformed and even cause the rudder surface to stop working. Secondly, the structural deformation of the wing has a great impact on the efficiency of the control surface. This leads to variation in the lift characteristics, drag characteristics, torque characteristics, and static/dynamic stability of the whole aircraft. Firstly, the pressure distribution of the wing and its adjacent components are changed by the wing elastic deformation, and even trigger the flow separation of the lift surface. In general, there are two typical static aeroelastic problems in conventional aircraft. Static aeroelastic deformation has a significant impact on the load distribution, control efficiency, static and dynamic stability of aircraft. The static aeroelasticity investigation is interdisciplinary, combining aerodynamic, elastic, and inertial forces. Therein, the prediction and correction of static aeroelasticity are very important for the safe flight of aircraft. At present, the development trend of aircraft includes high cruise speed, low fuel consumption, and high-performance flight quality. With the rapidly growing demand for aircraft in military and civil domains, the requirements for aircraft performance are constantly improving. Additionally, this paper briefly introduces the static aeroelastic prediction and correction method, especially the widely practiced K-value method. The research status and key technologies of aeroelastic numerical simulation of aircraft are introduced in detail. ![]() It is worth noting that computational fluid dynamics (CFD) and computational structure dynamics (CSD) have attracted increasing attention from researchers for application in aeroelastic analysis of the flow field. Furthermore, the wind tunnel and test technique also play an important role in static aeroelastic experiments. The structural layout of the static aeroelastic model, including plate type, beam type, bearing skin type, and full structural similarity type, are described in detail. Meanwhile, similar stiffness distribution, manufacturing materials, and processing technology are strongly associated with the simulation of aircraft structural dynamics. ![]() It is significantly important to determine the similarity conditions and static aeroelastic scaling modeling in wind tunnel experiments to obtain accurate aerodynamic characteristics. This paper comprehensively reviews the progress of static aeroelastic effect prediction and correction methods for aircraft, including the damage and protection of aeroelastic.
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