Research on modeling and dynamic characteristics of floating-poppet thrust vector control valve

The floating-poppet valve is primarily utilized in solid-propellant attitude and orbit control rocket engines that require rapid response capabilities, offering advantages such as fast actuation and stable, reliable operational performance. Consequently, reducing the dynamic response time of the floating-poppet valve represents a critical research objective for enhancing its overall performance. This study established a mathematical model and an experimental system to investigate the dynamic characteristics of the floating-poppet valve. Numerical simulations of the valve were conducted and validated through experimental comparisons. The simulations captured the poppet displacement, velocity, and pressure variations in the upper and lower chambers. Key factors influencing the valve’s response time were analyzed, including the size ratio of the poppet stem to head, stem dimensions, jet-to-pilot orifice area ratio, and lower chamber volume. Optimal design criteria were derived and generalized for practical applications. The results indicate that the dynamic mathematical model of the floating-poppet valve aligns well with experimental observations, and the working mechanism of the valve is clarified. The generalized design parameters for the floating-poppet valve are determined as follows: the area ratio between the poppet stem and head is 1, the stem dimensions match the nozzle throat size of the valve, the jet-to-pilot orifice area ratio ranges from 0.5 to 0.6, and the initial lower chamber volume is set to zero.