Transfer Matrix Method for the Determination of the Natural Vibration Characteristics of Realistic Thrusting Launch Vehicle—Part I

Figure 10

Variation of (a) flexural stiffness, (b) axial force due to constant nominal thrust = 1×10⁶N, and (c) mass per unit length of a typical rocket distributed along the vehicle length for two selected times of flight (—𝑡=0 and - - - 𝑡=50sec).

(a)

(b)

(c)