Aerothermoelastic Analysis of a Hypersonic Vehicle Based on Thermal Modal Reconstruction

Figure 8

The first six vibration modes and frequencies of the wing, (1) case 1: without the thermal effects, (2) case 2: with the thermal effects.

(a) Case 1: mode 1,

(b) Case 2: mode 1,

(c) Case 1: mode 2,

(d) Case 2: mode 2,

(e) Case 1: mode 3,

(f) Case 2: mode 3,

(g) Case 1: mode 4,

(h) Case 2: mode 4,

(i) Case 1: mode 5,

(j) Case 2: mode 5,