Reentry Demonstration of Flare-type Membrane Aeroshell for Atmospheric Entry Vehicle using a Sounding Rocket

Yamada, Kazuhiko; Nagata, Yasunori; Abe, Takashi; Suzuki, Kojiro; Imamura, Osamu; Akita, Daisuke

doi:10.2514/6.2013-1388

Cited by 14 publications

(16 citation statements)

References 4 publications

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“…The reentry trajectory of the SMAAC was evaluated by Yamada et al [18] and the measured orbit was confirmed to be in agreement with the preliminary predicted profile. The SMAAC vehicle was launched by the S-310-41 sounding rocket in August 8, 2012, at the Uchinoura space center, Kagaoshima, Japan.…”

Section: Flight Sequence and Reentry Trajectorymentioning

confidence: 50%

“…These parameters are tuned so that the stretch of the aeroshell because of the membrane deformation corresponds to the flight experimental results which were constructed based on the images taken by onboard JPEG cameras mounted on the backside of the SMAAC [18]. Thus, the textile properties of the aeroshell are assumed to be isotropic.…”

Section: Membrane Deformationmentioning

confidence: 99%

“…At the inflow, the freestream parameters are given following the orbit data [18]. As outflow conditions, all the flow properties are determined by the zeroth extrapolation, because the flow was supersonic in most regions.…”

Section: Boundary and Calculation Conditionsmentioning

confidence: 99%

“…This mission was a demonstration to clarify the low-ballistic-coefficient flight of a kind of inflatable vehicle during reentry. On August 8, 2012, a suborbital reentry demonstration of the SMAAC inflatable vehicle was successfully performed using a JAXA/ISAS S-310-41 sounding rocket [17][18][19][20]. Figure 1 shows a photograph of the SMAAC before the flight experiment.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Aerodynamic Heating Around Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry Demonstration Flight

Takahashi

Yamada

Abe

et al. 2015

Journal of Spacecraft and Rockets

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A demonstration flight of an advanced reentry vehicle was carried out using a sounding rocket. The vehicle was equipped with a flexible (membrane) aeroshell deployed by an inflatable torus structure. Its most remarkable feature was the low ballistic coefficient that enables reduction in aerodynamic heating and deceleration at a high altitude. During the suborbital reentry, temperatures at several locations on a backside of the flexible aeroshell and inside the capsule were measured by means of embedded thermocouples. The aerodynamic heating behavior of the vehicle was investigated using the measured temperature history, in combination with a numerical prediction in which a flow-field simulation of the heating was conducted. In this flow-field simulation, both laminar flow and turbulent flow were assumed, and the deformation of the flexible aeroshell was considered. A thermal model of the capsule and membrane aeroshell was developed, and the heat flux profiles of the vehicle surface during aerodynamic heating were constructed based on the measured temperatures. The measured temperature data were found to be in reasonable agreement with the predicted data if the flow field near the capsule of the vehicle was assumed to be laminar, with a transition to turbulent flow near the membrane aeroshell.

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Section: Flight Sequence and Reentry Trajectorymentioning

confidence: 50%

Section: Membrane Deformationmentioning

confidence: 99%

Section: Boundary and Calculation Conditionsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Aerodynamic Heating Around Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry Demonstration Flight

Takahashi

Yamada

Abe

et al. 2015

Journal of Spacecraft and Rockets

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“…As an important milestone in the MAAC project, a reentry demonstration using an S-310-41 sounding rocket (SMAAC: Sounding Rocket Experiment of Membrane Aeroshell for Atmospheric-Entry Capsule) was conducted on August 7, 2012, at the Uchinoura Space Center, Kagoshima, Japan [15][16][17][18][19][20]. This mission was a demonstration to clarify the low-ballisticcoefficient flight of a kind of inflatable vehicle during reentry.…”

Section: Introductionmentioning

confidence: 99%

Aerodecelerator Performance of Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry

Takahashi¹,

Ha²,

Oshima³

et al. 2017

Journal of Spacecraft and Rockets

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A flight experiment of an inflatable reentry vehicle, equipped with a thin-membrane aeroshell deployed by an inflatable torus structure, was performed using a JAXA S-310-41 sounding rocket. The drag coefficient history was evaluated by analyzing the acceleration of the vehicle with atmospheric density and temperature using a global reference atmospheric model. The vehicle successfully demonstrated deceleration. During the reentry flight, the position, velocity, and acceleration of the vehicle were obtained by using the Global Positioning System. The experimental drag coefficient had an almost constant value of 1.5 in the supersonic region but decreased to 1.0 in the subsonic region. In the transonic region, a steep decrease of the drag coefficient was confirmed. To study the detailed aerodynamics for the reentry vehicle, flow-field simulations were conducted with computational fluid dynamics techniques. The aerodynamic force acting on the vehicle was investigated with the measured data throughout the supersonic and subsonic regions. In the flow-field simulation, the computed result for the drag coefficient shows reasonable agreement with the experimental one. In addition, a compressible effect in front of the vehicle was seen to appear in the supersonic region and a vortex ring at the rear of the vehicle was formed in the subsonic region.

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Aero-thermo-dynamic analysis of a low ballistic coefficient deployable capsule in Earth re-entry

2016

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Reentry Demonstration of Flare-type Membrane Aeroshell for Atmospheric Entry Vehicle using a Sounding Rocket

Cited by 14 publications

References 4 publications

Aerodynamic Heating Around Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry Demonstration Flight

Aerodynamic Heating Around Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry Demonstration Flight

Aerodecelerator Performance of Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry

Aero-thermo-dynamic analysis of a low ballistic coefficient deployable capsule in Earth re-entry

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