Abstract
The flexible behaviors in the aerospace structures can lead to undesired performance and degradation of their control and guidance system. The aims of the current work are to analyze the bending vibration of a Two Stage to Orbit (TSTO) Launch Vehicle (LV) with propulsion force modeled as a free–free jointed bipartite beam under a follower force, study its effects on oscillation of the actuators, and finally develop a solution to reduce these oscillations. The vibration analysis of the beam model is carried out using Ritz method. The rigid dynamics of a TSTO LV in the pitch channel was then modeled and modified using the vibrational model of the device for the same channel. A new dynamic model with an adaptive control system for a TSTO LV has been developed, allowing the aerospace structure to run on its maximum bearable propulsion force with the optimum effects on the oscillation of its actuators. Simulation results show that such a control model provides an effective way to reduce the undesirable oscillations of the actuators.
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