A Method of Determining the Equivalent Static Load of Shock Load
An impact load and static load technology, applied in the direction of elasticity test, machine/structural component test, force/torque/work measuring instrument, etc., can solve the problems of excessive safety factor, lack of theoretical basis, conservative design, etc. The theoretical basis is sufficient, the application scope is wide, and the effect of improving the authenticity
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Embodiment 1
[0094] Taking a beam structure as an example, the implementation process of determining the equivalent static load of impact load based on this method is explained.
[0095] 1. Establish the finite element model of the beam structure
[0096] Figure 6 A schematic diagram of a beam structure is shown. The beam is 2m long and forms an included angle of 45o with the negative direction of the OY axis. The cross section is a straight ring with an outer diameter of 0.05m and an inner diameter of 0.04m. The material is alloy steel, the elastic modulus of the material is 200GPa, the Poisson's ratio is 0.3, and the density is 7800kg / m 3 . A linear spring is arranged at 1 / 10 of the end of the beam close to the origin O, which only provides stiffness in the Y direction and is used to adjust the bending frequency of the beam around the OZ axis. The finite element model of the structure is established by MSC.PATRAN.
[0097] 2. Calculate the natural frequency of the finite element mo...
Embodiment 2
[0115] Taking the water load measurement test of ditching on a scale model of a certain type of aircraft as an example, the process of determining the equivalent static pressure of ditching based on this method is illustrated.
[0116] 1. Determine P and T D
[0117] Figure 8 The pressure time history of a certain place on the fuselage obtained from the test side is shown. It can be seen that the first impact pressure peak value P=900kPa. according to Figure 5 The method shown to determine T E = 0.006s, therefore, the duration T D =2.5T E = 0.015s.
[0118] 2. Determine f n
[0119] According to the aircraft ground resonance test, the first-order natural frequency of the fuselage can be obtained as 9Hz, so f n = 9Hz.
[0120] 3. Calculate the dynamic scaling factor λ
[0121] dimensionless parameter f n T D =0.848, the dynamic scaling coefficient λ=0.415 obtained according to formula (20).
[0122] 4. Calculation of equivalent static pressure
[0123] Equival...
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