Finite element load application method – Eureka

[0022] The present invention will be described in further detail below through specific embodiments and in conjunction with the accompanying drawings.

[0023] 1. Taking the load application of an aircraft as the research object, find out the concentrated load among all the loads of the aircraft, including engine load, missile load, and radar load, and divide the distributed load into fuselage, wing, horizontal tail, and vertical tail Four partitions, see attached figure 1.

[0024] 2. Select the nodes that can be loaded in the finite element model, and press the selected finite element nodes according to the attached figure 1 Partitioned.

[0025] 3. Add the engine load to the joint between the engine and the airframe, add the missile load to the joint between the missile and the airframe, and add the radar load to the fixed point of the radar on the airframe.

[0026] 4. Divide the section of the wing according to the ribs to calculate the section, integrally calculate the total distributed load P between two adjacent ribs and the load action point m, and distribute P to the adjacent calculation section according to the principle of leverage, and the loads are respectively Pa and Pb, the load action points are ma and mb respectively, see appendix figure 2 shown.

[0027] 5. Apply loads Pa and Pb at ma and mb, and establish MPC units between ma and mb and the finite element nodes on the calculation section. In this way, the load application of all airfoil partition calculation sections is completed.

[0028] 6. The application scheme of the distributed load of the fuselage, horizontal tail and vertical tail is the same as that of the wing, and the calculation section of the fuselage is a frame section.