4 results about "Aeroelasticity" patented technology

The application discloses a method for suppressing transonic buffeting load and response based on agent cooperation, and relates to the technical field of aeroelasticity, and aims at solving the problem of transonic buffeting of a wing of an aircraft. The method comprises the following steps: firstly, calculating the elastic wing tip acceleration response based on a one-way fluid-solid coupling method; secondly, configuring a multi-target reinforcement learning agent, taking the variable-camber trailing edge and the telescopic micro-bulge as control mechanisms, taking the maintenance of the aerodynamic lift-drag ratio and the suppression of the vibration response of the structure as targets, and letting the agent adopt a proximal policy optimization algorithm to be trained to obtain an optimal control law capable of cooperatively driving the telescopic micro-bulge and the variable-camber trailing edge; and thirdly, deploying the trained cooperative control law on the target wing, and observing the suppression effect of the wing buffeting through quantitative evaluation of the slowing rate. The application trains the agent through a deep reinforcement learning method, so that the agent can guide the telescopic micro-bulge to suppress the diffusion in the separation zone, reduce the shock motion amplitude, drive the variable-camber trailing edge to regulate the flow at the trailing edge and compensate the overall lift fluctuation, and cooperatively suppress the buffeting load and response.

This invention discloses a method for analyzing the coupled influence of structural deformation and detection performance on sensor aircraft, belonging to the fields of aircraft design and aeroelasticity. The specific steps of the method are as follows: establishing an aerodynamic and structural model of the aircraft; establishing state-space aerodynamic equations; defining a flight dynamics model; obtaining rigid-elastic coupled dynamic equations based on the Lagrange equations; performing aeroelastic dynamic response calculations through coupled solution to obtain the physical deformation of the wing structure; and calculating antenna performance based on this deformation to analyze the impact of structural deformation on detection performance. This invention, by establishing a rigid-elastic coupled aeroelastic model, achieves a full-process coupled analysis from aeroelastic excitation to structural response and then to antenna performance changes. It solves the problem that traditional methods cannot accurately consider the impact of structural deformation on detection performance under actual flight conditions, providing a more accurate analytical means for the integrated design of sensor aircraft.

This invention discloses an intelligent optimization algorithm for curved fiber wing that integrates physical information buckling proxy, relating to the field of aircraft design technology. The method includes: equivalently planarizing the spatially twisted quadrilateral; deriving the Jacobian matrix through a double-triangle affine mapping to construct a variable stiffness total potential energy functional; embedding the mechanical control equations using a physical information neural network (PINN) to quickly solve for the buckling critical load factor and modes, replacing traditional finite element calculations; parameterizing the fiber path and thickness to construct design variables; and employing a multi-stage adaptive differential evolution algorithm for global optimization, integrating process, static / dynamic aeroelasticity, and strength constraints. This invention achieves a closed-loop modeling-evaluation-optimization process, significantly reducing computational costs while maintaining mechanical consistency, solving the convergence problem of high-dimensional variable coupling, and greatly improving the automation and engineering efficiency of curved fiber wing design.

This invention belongs to the field of aircraft aeroelasticity, and specifically discloses a method for analyzing the spiral flutter of multirotor aircraft. It is designed for the configuration characteristics (hingedless small-diameter propeller) and flight modes (vertical takeoff and landing, large pitch angles in forward flight) of multirotor aircraft. The 2-DOF model in the preliminary design stage does not require complex modeling and software operation, supports rapid adjustment of structural, overall, and aerodynamic parameters, and can complete the analysis of multiple sets of parameters in a short time, meeting the needs of rapid iteration in the preliminary design. The 2-DOF (rapid analysis) and 4-DOF (precise verification) models can be flexibly switched according to the design stage, taking into account both analysis efficiency and calculation accuracy, and adapting to the needs of the entire process from preliminary design to detailed design.