Control system design and experiment of needle-type gas regulating system for ducted rocket

Abstract

The control system design and experimental investigation of the gas regulating system for a ducted rocket are studied in this article. First, the dynamic model of the gas regulating system for the ducted rocket was established, and comparison of the two regulating modes regarding non-linearity and uncertainty was done. In contrast with the area-regulated mode, the non-linearity of the pressure-balanced mode is smaller and the robustness is stronger. Then, the study of the the gas control system is performed based on the model established in this article. The introduction of high-gain feedback suppresses the effects of non-linearity and uncertainty in the pneumatic servo system. Also, a proportional-integral controller for the gas regulating system based on linear matrix inequality is designed. Lastly, an experimental investigation of the gas flow control system is done to verify the validity of the gas control system. The experimental result shows that the gas flow control system has good performance. The turndown ratio of mass flow through the control valve was up to 3.7:1.

High-Performance Adaptive Pressure Control in the Presence of Time Delays: Pressure Control for Use in Variable-Thrust Rocket Development

“…The discussion in this article on the employment of advanced control methodologies should benefit practitioners whose goal is to obtain a fast system response in safety-critical applications where nonlinear dynamics, time-varying parameters, and time delays pose significant challenges. One of the most common approaches to control GG pressure is utilizing linear controllers that are designed based on a model of the system obtained by linearizing the nonlinear dynamics around a certain operating point [14], [16], [17]. Although this method is simple to implement, it may limit the performance when the operating point changes, as shown in the simulations and experimental studies presented in this article.…”

Supersonic inlet buzz margin control of ducted rockets

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“…During the movement, the needle valve is subjected to several forces. The force equation of the valve head is given as [30] b…”

2 loop Nonlinear Dynamic Inversion Fuel Flow Controller Design for Air to Air Ducted Ramjet Rocket

“…In 7 , author has proposed FFC design using variable throttle valve and using variable gas generator pressure through pneumatic pressure (pressure balance mode) with help of PID. However, this needs extra hardware which lead to complexities in small rocket design.…”