Low-Density Aerodynamics for the Inflatable Reentry Vehicle Experiment

Moss, James N.; Glass, Christopher E.; Hollis, Brian R.; Norman, John W. Van

doi:10.2514/1.22707

Cited by 15 publications

(3 citation statements)

References 11 publications

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“…In the area where the Knudsen number is under 0.01, the drag coefficient of 60 half taper angle is about 1.4. This result is coincided with the result of IRVE and Stardust which have the same half taper angle and the similar shape 6 . Finally, when the Mach number become larger than 15, the drag coefficient start separate and become nearly constant at the end.…”

Section: A CD Resultssupporting

confidence: 92%

The optimal design and analysis of the IRDT system based on two-dimensional ballistic trajectory in atmosphere reentry

Wang¹,

Hou²,

Niu³

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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The modeling of two-dimensional reentry trajectory for the IRDT system is presented in this paper. The CFD simulation and theoretical formula is employed to compute the drag coefficient, and the final precise drag coefficient and trajectory of the IRDT system during the reentry is calculated through iteration process. With the result of final drag coefficient and trajectory data, the optimal design and analysis of the IRDT system is carried out. The heat flux on stagnation point, the maximum heat absorption on stagnation point and the maximum drag acceleration are chosen as optimizing restrictions to optimize the half taper angle and initial reentry angle of the IRDT system. The influences of different half taper angle and initial reentry angle under the same reentry height and velocity are investigated in this study. The results show that under the current technological level, the optimal half taper angle of the IRDT system is above 55°and the optimal initial reentry angle is between -2° and -2.7°. The investigation also provide the principle for the design of the IRDT system and long term goals for the IRDT subsystem development. Nomenclature βe= flight range angle ρ = local density Θ = flight path angle Θ0 = initial reentry angle θc = the half taper angle CD = drag coefficient g = local gravity g0 = gravity at earth surface h = spacecraft height IRDT = Inflatable Reentry and Descent Technology m = mass of spacecraft r = distance between spacecraft and earth center rN = radius of blunt rp = radius of edge rg = radius of the IRDT system t = reentry time S = front projection area of the IRDT system TPS = thermal protection system v = spacecraft velocity

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Section: A CD Resultssupporting

confidence: 92%

The optimal design and analysis of the IRDT system based on two-dimensional ballistic trajectory in atmosphere reentry

Wang¹,

Hou²,

Niu³

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…According to Ref. [27], the Knudsen number (Kn) is less than 0.01 when the height is below 91 km, which indicates that it can be regarded as continuous fluid. In the hypersonic CFD simulation, the velocity, pressure, and temperature boundary conditions are set to the inlet, while no boundary condition is set for the outlet.…”

Section: Boundary Conditionsmentioning

confidence: 99%

Thermal Aeroelastic Characteristics of Inflatable Reentry Vehicle Experiment (IRVE) in Hypersonic Flow

Wu¹,

Zhang²,

Hou³

et al. 2021

International Journal of Aerospace Engineering

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The inflatable reentry vehicle provides a new technical way in aerospace entry, descent, and landing. The structural failure of inflatable reentry vehicle experiment caused by thermal aeroelastic effect is serious, which needs to be further studied. A traditional numerical method about flexible vehicles separates the aeroheating and aeroelastic problems, resulting in poor matching with the actual test. In this paper, a thermal-fluid-solid coupling model considering inflation gas effect was established, which associates the aeroheating and aeroelastic modules and adopts the LES to improve the depicting ability of hypersonic flow. The model was used to solve the thermal aeroelastic characteristics under extreme aeroheating load. From aeroheating results, the large-scale vortex on windward generated by the interaction of the shock layer and boundary layer has great influence on aeroheating due to the heat dissipation, and the skin deformation also increases the surface friction and local heating near depressions. From aeroelastic analysis, the flexible structure performs violent forced vibration induced by the unsteady large-scale vortex on windward, and the aeroheating effect will significantly increase the thermal stress and natural vibration properties. The thermal-fluid-solid coupling method for the flexible structure proposed in this paper provides a reasonable reference for engineering.

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“…14(3), 215-221 (2013) The difficulty in the development of a hypersonic vehicle is caused by quite a number of problems of modeling fullscale flight conditions in wind tunnels. The analysis of the aerodynamics and aerothermodynamic characteristics of a hypersonic vehicle at high-altitude requires numerous numerical calculations [3][4][5].…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Investigation for Prospective Aerospace Vehicle in the Transitional Regime

Ivanovich¹,

Myint²,

Yurievich³

2013

International Journal of Aeronautical and Space Sciences

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The basic quantitative tool for the study of hypersonic rarefied flows is the direct simulation Monte Carlo method (DSMC). The DSMC method requires a large amount of computer memory and performance and is unreasonably expensive at the first stage of spacecraft design and trajectory analysis. A possible solution to this problem is approximate engineering methods. However, the Monte Carlo method remains the most reliable approach to compare to the engineering methods that provide good results for the global aerodynamic coefficients of various geometry designs. This paper presents the calculation results of aerodynamic characteristics for spacecraft vehicles in the free molecular, the transitional and the continuum regimes using the local engineering method. Results and methods would be useful to calculate aerodynamics for new-generation hypersonic vehicle designs.

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Low-Density Aerodynamics for the Inflatable Reentry Vehicle Experiment

Cited by 15 publications

References 11 publications

The optimal design and analysis of the IRDT system based on two-dimensional ballistic trajectory in atmosphere reentry

The optimal design and analysis of the IRDT system based on two-dimensional ballistic trajectory in atmosphere reentry

Thermal Aeroelastic Characteristics of Inflatable Reentry Vehicle Experiment (IRVE) in Hypersonic Flow

Aerodynamic Investigation for Prospective Aerospace Vehicle in the Transitional Regime

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