Air Turbo-Rocket solid propellant development and testing

Working Fluid modeling Based on Air Turbine Rocket Engine and Propellant Comparative Analysis

“…The thermodynamic properties of the primary gas produced by propellant combustion have an important impact on the secondary combustion in the combustion chamber. Combined domestic and foreign related research on the characteristics of ATR engine propellants [6,9], This paper mainly makes the following four requirements for the propellant, as shown in Table 3.…”

Combustion Characteristics Experimental Study of Solid Hydrocarbon Propellant for Air-Turbo Rocket

“…For secondary combustion, the fuel gas should have a high energy density, be easily ignitable, and have good combustion stability. However, high-energy-density propellants often contain large amounts of solid/condensed particles that could severely erode the turbine blades or clog the flow-path [8]. Because of the limitations of a turbine, it is difficult for SP-ATRs to achieve the specific impulse performance level of boron-based solid-propellant ramjets.…”

“…Regarding the evaluation of propellants, Ostrander and Thomas [8] conducted a feasibility analysis of ammonium perchlorate (AP)based and boron-based solid propellants used in SP-ATRs. The results showed that the advantages of AP-based propellants are their low molecular weight and fewer solid particles, but the calorific value of the gas is low, which reduces the engine performance.…”

Adaptive Pressure Control for Use in Variable-Thrust Rocket Development

“…1), introducing secondary injection to the GG chamber to control burning rate and utilizing a vortex valve which introduces a swirl to the flow in order to control the effective throat area [2,3]. Among these methods of regulating the fuel mass flow rate, changing the throat area using a mechanical valve is the most commonly used approach [3][4][5][6][7][8][9][10]. A typical thrust/speed control loop has a hierarchical structure where an outer loop is driven by the error between the desired and the measured thrust/speed and determines the required GG pressure to minimize this error.…”