The paper proposes an algorithm for designing a power set of the low-aspect lifting plane for the air-to-air short-range unmanned aerial vehicle. The work objective was to reduce the lifting plane mass and to increase its strength characteristics taking into account the operational loads. The algorithm was based on introduction of the topological optimization method in terms of calculating the structure maximum static stiffness under constraints in volume. Calculations of the stress-strain state and topological optimization were carried out using the ANSYS Workbench 19.2 software package. Boundary conditions were determined; load acting on the wing was set. Material suitable for manufacturing the structure using additive technologies was selected for optimization. Topological optimization resulted in obtaining a structural power diagram of the wing power frame. Taking into account the actual operating conditions, a skin of constant thickness was added to the resulting load-bearing frame. To verify the study, comparative analysis of the optimized wing model and its possible analogue made by traditional methods was carried out. Results of this analysis showed that the mass of the optimized lifting plane was by 12.7% less compared to the mass of a typical stamped structure. At the same time, the maximum equivalent stress values for the optimized wing were 755.7 MPa, which was by 10.3% less than for the standard design. Recommendations were given for further stages of designing the resulting lifting plane.
Currently, materials with shape memory effect (SME) are widely utilized in the field of joining thin-walled shells. The application of SME materials in the joining of unmanned aerial vehicle (UAV) compartments makes it possible to increase the accuracy, high assembly manufacturability to perform multiple joint assembly-disassembly work and ensures the forces transfer from UAV different surfaces in compliance with the specified strength conditions. The paper considers a design technique for a detachable clamp (tape) joint, made up of SME material, of UAV small-diameter compartments. The clamp is an open shell made up of SME material. Before installation, the clamp is cooled, and the required shape is given to it. When heated, its diameter reduces to the specified to ensure tightness and absence of clearances in the design. The critical parameters were specified. They are required to solve the problem of parametric optimization of the clamp joint, whereby the joint will meet the strength requirements and have the minimum mass. Based on the calculation of a clamped joint, the calculation algorithm, that allows the calculation of tape connections for various diameters UAV compartments, was obtained. A computer model of joining in CAD Solid Works with the parameters that comply with the structural strength requirements was created. Based on geometry of the model and the properties of the stated materials, the calculation of structural mass under various values of the inclination angle of the clamp surface was carried out. The method of designing a clamp joint, made up of titanium nickel, is represented. The dependences of compartments joints strength on the clamp parameters and a set of parameters, allowing us to design the working structure of the clamp joint with the lowest mass, are found.
The paper proposes an algorithm to prepare a design technological solution for the aerodynamic rudder of an unmanned aerial vehicle. The formation process of the rudder design technological solution includes the refinement stage taking into account the technological limitations. The algorithm is based on application of the topological optimization method for the case of maximizing the rudder structure static rigidity with the volume limitation. The structure of the finite element model for optimization was proposed, and the boundary conditions and parameters of the design flight mode were determined. Topological optimization resulted in obtaining a rudder power frame with minimum mass for the given design case. To verify the research, parameters of the stress-strain state were determined, and flutter for typical and optimized rudder design was calculated. Based on the optimization results, a structure was designed that met technological limitations and requirements in strength and aeroelastic stability.
scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.
customersupport@researchsolutions.com
10624 S. Eastern Ave., Ste. A-614
Henderson, NV 89052, USA
Copyright © 2024 scite LLC. All rights reserved.
Made with 💙 for researchers
Part of the Research Solutions Family.