Atmospheric Cruise Flight Challenges for Hypersonic Vehicles Under the Ajax Concept

Hong

et al. 2015

AMM

The magnetohydrodynamic (MHD) flow control techniques for inlet based on “AJAX” vehicle concept have attracted many researchers’ attention for its potential wide applications in the supersonic flights or the hypersonic ones. In this paper, a preliminary discussion for basic problems that are ionization and magnetic field in the MHD applications is presented. And three major MHD techniques for enhancing inlet aerodynamic performance and operability, which are large scale flow control for enlarging flight scope in Mach/angle-of-attack, near surface flow control for shock wave/boundary layer interaction and leading edge heating-transfer control for enormous thermal load on leading edge of the compression ramp, are briefly explained and reviewed.

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Progress in Hypersonic Inlet Flow Controls by Magnetohydrodynamic

Hong

et al. 2015

AMM

Proceedings of the 2014 International Conference on Mechanics and Civil Engineering

“…MHD presents a tantalizing opportunity to control hypersonic flows without the need for strong shock waves, low combustion efficiency, and thrust decreases sharply, which has broad potential application prospect in hypersonic aircraft [1][2][3][4]. MHD involves the interaction of supersonic field, magnetic field and electric field, currently, the research on MHD mainly depends on computational and theoretical analysis due to complex techniques and strict experimental demands of MHD, relevant ground experimental researches are carried out only in a few countries [5].…”

Section: Introductionmentioning

confidence: 99%

Preliminary Experimental Investigation on CCRF Barrier Discharge in Supersonic Flow

Fan¹,

Zhang²,

Li³

et al. 2014

Producing large-scale and uniform plasma in supersonic field is the foundation of researching cold Magnetohydrodynamic (MHD). The experimental system of capacitively coupled radio-frequency (CCRF) barrier discharge based on Ma3.5 double-throat tunnel is established, and the discharges in the condition of static and supersonic flow are investigating respectively. Main conclusions are as follows. Firstly, a stable and continuous supersonic field is generated by wind tunnel, which could guarantee the discharge experiments working reliably. Secondly, the space distribution of plasma changes and the discharge area reduces in the supersonic flow. Thirdly, the diffusion of plasma is restrained by the magnetic field, which leads to the increase of the degree of ionization.

Proceedings of the Institution of Mechanical Engineers, Part G:

“…The most innovative and principal issue about the AJAX program is how to utilize the MHD system to develop an MHD bypass scramjet technology and control the inlet of the propulsion system. Kuranov and Korabelnikov [7] discussed the challenges of atmospheric cruise flight of a hydrocarbon-fuelled hypersonic flight vehicle under the AJAX concept. The results indicated that the MHD effects on the flow make it possible to enhance the specific impulse of the engine and create a controlled inlet under an offdesign flight condition.…”

Section: Introductionmentioning

confidence: 99%

Three-dimensional design and numerical simulation of magnetohydrodynamic controlled hypersonic inlets

Cao

2011

The purpose of this study is to perform numerical simulation for the design and optimization of three-dimensional magnetohydrodynamic (MHD) controlled hypersonic inlets. An airframe/propulsion integrated module was first established for a waverider-based hypersonic vehicle at design Mach number of 6. Using this generic configuration, an MHDbased technique for large-scale inlet flow control is studied at the off-designed Mach value of 8.5. The results indicate that the inlet mass flowrate can act as an optimization criterion. Using a proper value of mass flowrate, an MHD generator possessing reasonable design parameters can effectively restore the flow field shock structure, i.e. shock-on-lip condition and improves the flow field characteristics at the combustor entrance at higher Mach number than the design value. The results further reveal that the MHD effect on the flow with higher load factor helps to extract more electric power from the external MHD generator and also helps in improving the performance of the combustor entrance.