Structural design and analysis of low-disturbance performance for a deployable ribbed mechanism in missle-borne antenna

For high-speed aircraft, the space deployment mechanism is evolving towards higher speed, greater precision, and reduced interference. This paper presents the design of a low-disturbance ribbed development mechanism by considering the inherent balance condition and extended configuration of the Fischer-mechanism, as well as the characteristics of the mechanism's development angle. The design is based on evaluation indexes comprising weight, fundamental frequency, and reflector area. Furthermore, an analysis of vibration force and moment for the low-disturbance ribbed developing mechanism is conducted using the mass-radius product and momentum formula. A balanced performance model is established to achieve equilibrium from the initial stages of design. The performance evaluation of this low-disturbance ribbed deployable mechanism combines static stiffness and dynamic stiffness performance indexes along with a mathematical model for static stiffness and finite element fundamental frequency simulation. Finally, an example simulation verifies the reliability of the theoretical analysis. The feasibility of the developable ribbed mechanism in confined spaces under conditions of high speed and low-disturbance has been validated.