CFD and FEM coupling analysis of OREX aerothermodynamic flight data

Yamamoto, Yukimitsu; Yoshioka, Minako

doi:10.2514/6.1995-2087

Cited by 31 publications

(20 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…For an ExB layer simulation in a hypersonic flow, we use the OREX vehicle, which was launched by the H-II rocket from Japan to conduct an earth reentry experiment. 18 OREX is a blunt body reentry vehicle and it has a nearly zero angle of attack in the reentry experiment. Figure 14 shows the simulation domain with a simplified OREX geometry that is composed of a spherical nose with a 1.35 m radius and a 50-deg sphere cone.…”

Section: B An Exb Layer In a Hypersonic Flowmentioning

confidence: 99%

Two-dimensional Model of an Electromagnetic Layer for the Mitigation of Communications Blackout

Kim

Keidar

Boyd

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

During hypersonic, the shock heated air generates a weakly ionized plasma layer around a vehicle. Since the created plasma layer has a high plasma number density, the vehicle has a communication problem known as radio blackout. Solving radio blackout is an important issue for safety of the vehicle, catastrophe analysis, and mission success. In order to solve radio blackout, we propose to manipulate a plasma number density. This paper describes studies of manipulating a flowing plasma with electric and magnetic fields. We suggest a two-dimensional model of an ExB layer which helps to determine the optimal configuration of the ExB layer and location of an antenna. The suggested numerical model uses a hydrodynamic MHD approximation and it is solved using a finite volume method with a Riemann solver. In this paper, we demonstrate that an applied ExB layer can manipulate plasma density in a specific region. The manipulated plasma reduces radio wave attenuation in a plasma layer and provides the possibility for communication during radio blackout.

show abstract

Section: B An Exb Layer In a Hypersonic Flowmentioning

confidence: 99%

Two-dimensional Model of an Electromagnetic Layer for the Mitigation of Communications Blackout

Kim

Keidar

Boyd

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

show abstract

“…28 Table 2 shows the inflow conditions and wall temperature of OREX at several altitudes. 29 The chemical composition of free stream air is assumed to be 79% N 2 and 21% O 2 in terms of mole fraction at all altitudes. Since OREX experienced a radio blackout at approximately 80 km, 30 this study chose the 79.9 km inflow condition of OREX for the simulation.…”

Section: Gps Navigation Data During Re-entry and In Orbitmentioning

confidence: 99%

“…Freestream conditions and wall temperature of OREX for several altitude conditions29 The required plasma density reduction for OREX at 79.9 km reentry condition…”

mentioning

confidence: 99%

Numerical Modeling of Plasma Manipulation Using an ExB Layer in the Hypersonic Boundary Layer

Kim

Boyd²,

Keidar

2009

40th AIAA Plasmadynamics and Lasers Conference

View full text Add to dashboard Cite

When a vehicle flies with hypersonic velocity or re-enters the atmosphere, a weakly ionized plasma layer is generated around the vehicle due to the shock heated air. Since the created plasma layer has a high plasma number density, the vehicle has a communication problem known as radio blackout. In this study, we illustrate that an applied ExB layer can manipulate the plasma density in a specific region. The manipulated plasma reduces radio wave attenuation in the plasma layer and provides the possibility for communication during radio blackout. The possibility of the ExB layer mitigation scheme is evaluated in a realistic operating condition for a hypersonic flow in terms of signal attenuation.

show abstract

“…Aerodynamic analyses of the COMmercial Experiment Transport (COMET) reentry capsule have been carried out by Wood et al [10] solving the thin layer laminar Navier-Stokes at high speeds. Yamamoto and Yoshioka [11] have performed flowfield computation over the Orbital Reentry EXperiments (OREX) using CFD method in conjunction with flight aerodynamic data. Ivanov [12] cataloged different shapes for non-winged reentry vehicles.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Base Pressure and Drag of Space Reentry Capsules at High Speed

Mehta¹

2019

Hypersonic Vehicles - Past, Present and Future Developments

View full text Add to dashboard Cite

The numerical simulations over several reentry vehicles are carried out by solving time-dependent compressible laminar axisymmetric Navier-Stokes equations for Mach 1.2-6.0. The fluid dynamics equations are discretized in spatial coordinates using integral formulation in conjunction with a finite volume method which reduce to semi-discretized ordinary differential equations. A local time-step is used to achieve steady-state solution. The numerical computation is carried out on a single-block structured computational grid. The flowfield features over the reentry vehicle such as formation of a bow shock wave ahead of the fore-body, expansion fan on the shoulder, and recirculation zone in the base region are well captured in the numerical simulations. Lower pressure acting on the base of the reentry capsule acts as base drag. The base drag coefficient based on maximum cross-section of the reentry capsule must satisfy inequality. The base drag coefficient is a function of several geometrical parameters of the fore-body and back-shell of reentry capsule, boundary layer, formation of free-shear layer in the wake region and freestream Mach number. The purpose of this chapter is to numerically evaluate and tabulate the base pressure and the base drag coefficients of various reentry space capsules at zero angle of incidence.Keywords: aerodynamic, base drag, CFD, high speed flow, viscous flow, reentry vehicle, shock wave Present and Future Developments Numerical Simulation of Base Pressure and Drag of Space Reentry Capsules at High Speed DOI: http://dx.doi.org/10.5772/intechopen.83651 the axisymmetric laminar compressible Navier-Stokes equations on a single-block structured grid, i.e., the number of grid points in the radial direction in each zone of the computational region is same. Surface pressure variations over the vehicles are computed which reveal a systematic understanding of the flow features over the capsule at high speeds. It also reveals the effect of geometrical parameters on aerodynamic base drag coefficient. The unsteady flow characteristics of the OREX and the Beagle-2 are analyzed in Ref. [28].

show abstract

CFD and FEM coupling analysis of OREX aerothermodynamic flight data

Cited by 31 publications

References 1 publication

Two-dimensional Model of an Electromagnetic Layer for the Mitigation of Communications Blackout

Two-dimensional Model of an Electromagnetic Layer for the Mitigation of Communications Blackout

Numerical Modeling of Plasma Manipulation Using an ExB Layer in the Hypersonic Boundary Layer

Numerical Simulation of Base Pressure and Drag of Space Reentry Capsules at High Speed

Contact Info

Product

Resources

About