Abstract
This research adopts a shock tube 16 meters long and with a 9 cm bore to create a supersonic, high-temperature, and high-pressure flowfield to observe the gasification and ignition of HTPB solid fuel under different environments. Also, full-scale 3D numerical simulation is executed to enhance the comprehension of this complex phenomenon. The CFD (Computational Fluid Dynamics) code is based on the control volume method and the pre-conditioning method for solving the Navier-Stokes equations to simulate the compressible and incompressible coupling problem. In the tests, a HTPB slab is placed in the windowed-test section. Various test conditions generate different supersonic Mach numbers and environmental temperatures. In addition, the incident angles of the HTPB slab were changed relative to the incoming shock wave. Results show that as the Mach number around the slab section exceeded 1.25, the flowfield temperature achieved 1100 K, which is higher than the HTPB gasification temperature (930 K~1090 K). Then, gasification occurred and a short-period ignition could be observed. In particular, when the slab angle was7∘, the phenomenon became more visible. This is due to the flow field temperature increase when the slab angle was at7∘.
Highlights
With the development of the space shuttle and solar system exploration, hypersonic high technology in aviation will play an important role in the next-generation frontier [1]
Marxman and Gilbert [3] considered that the optimal position of the flame should be at the top of the fuel surface, and the regression rate is the minimum in the turbulence layer at about 10–20%
Using Computational Fluid Dynamics (CFD) simulates the supersonic flow through the HTPB slab, and its results are compared with the experimental data
Summary
With the development of the space shuttle and solar system exploration, hypersonic high technology in aviation will play an important role in the next-generation frontier [1]. In the 1960s, researchers indicated that the regression ratio is the key in mixer-rocket studies. For this reason, many test models have been developed in different combustion conditions. Greiner and Grederick [6] expressed the fuel regression ratio as proportional to the oxidizer flow rate, and the pressure fluctuation decreased when raising the mixed region length. When the diaphragm in the high pressure driver section ruptured, a series of compression waves coalesced into a single shock front which compressed and heated to a high pressure the gas in the low pressure region, and created the supersonic gas flow condition. Computational Fluid Dynamics (CFD) is a good tool to deal with the problems In this study, both of these two methods are used. Using CFD simulates the supersonic flow through the HTPB slab, and its results are compared with the experimental data
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