Hayabusa Re-entry: Trajectory Analysis and Observation Mission Design

Cassell, Alan M.; Winter, Michael; Grinstead, Jay H.; Antimisiaris, Manny E.; Jenniskens, Peter; June, On

doi:10.2514/6.2011-3330

Cited by 29 publications

(17 citation statements)

References 4 publications

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“…Apart from the Apollo command module and the Orion crew module, the known cases of hypervelocity reentry of man-made objects include the Genesis (ReVelle et al, 2005;Jenniskens et al, 2006;Tang and Wright, 2007) and Stardust (Desai et al, 2000;ReVelle and Edwards, 2007) capsules, and Hayabusa (Cassel et al, 2011;Fujita et al, 2011;Ueda et al, 2011). These events, together with the NASA FIRE 2 flight experiment (Cauchon, 1967), have been of paramount importance to study mechanical and thermal states, which cannot be reproduced at a ground facility all at the same time.…”

Section: Hypervelocity Earth's Reentriesmentioning

confidence: 97%

The reentry to Earth as a valuable option at the end-of-life of Libration Point Orbit missions

Alessi

2015

Advances in Space Research

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Section: Hypervelocity Earth's Reentriesmentioning

confidence: 97%

The reentry to Earth as a valuable option at the end-of-life of Libration Point Orbit missions

Alessi

2015

Advances in Space Research

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“…The data were analyzed to reveal quantities of importance to atmospheric reentry aerothermodynamics: apparent temperatures, shock radiation spectra from high temperature gases, ablation species spectra (if present), and their temporal evolution during reentry. The first successful collaboration was for NASA's Stardust in 2006 [48][49][50][51][52][53][54][55][56][57][58][59][60] followed by JAXA's Hayabusa in 2010 [61,62]. These reentry observation campaigns used aerial based imaging systems.…”

Section: Emission Spectroscopy Imaging (Entry Vehicles)mentioning

confidence: 99%

Remote observations of reentering spacecraft including the space shuttle orbiter

Horvath

Cagle

Grinstead

et al. 2013

2013 IEEE Aerospace Conference

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Abstract-Flight measurement is a critical phase in development, validation and certification processes of technologies destined for future civilian and military operational capabilities. This paper focuses on several recent NASA-sponsored remote observations that have provided unique engineering and scientific insights of reentry vehicle flight phenomenology and performance that could not necessarily be obtained with more traditional instrumentation methods such as onboard discrete surface sensors. The missions highlighted include multiple spatially-resolved infrared observations of the NASA Space Shuttle Orbiter during hypersonic reentry from 2009 to 2011, and emission spectroscopy of comparatively small-sized sample return capsules returning from exploration missions. Emphasis has been placed upon identifying the challenges associated with these remote sensing missions with focus on end-to-end aspects that include the initial science objective, selection of the appropriate imaging platform and instrumentation suite, target flight path analysis and acquisition strategy, pre-mission simulations to optimize sensor configuration, logistics and communications during the actual observation. Explored are collaborative opportunities and technology investments required to develop a next-generation quantitative imaging system (i.e., an intelligent sensor and platform) with greater capability, which could more affordably support cross cutting civilian and military flight test needs.

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“…12,13 From these data, first estimates of stagnation point heat flux and velocity profiles were extracted to construct the heat pulse and then select appropriate time points on the pulse for "high-fidelity" computational fluid dynamics (CFD) simulations. In addition to three CFD solutions at radiative, convective, and total peak heating, four points on each side of total peak heating were selected to cover the range where experimental data were available.…”

Section: Selection Of Trajectory Pointsmentioning

confidence: 99%

Radiation Modeling for the Reentry of the Hayabusa Sample Return Capsule

Winter

McDaniel

Chen

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Predicted shock-layer emission signatures of the Japanese Hayabusa capsule during its reentry are presented for comparison with flight measurements made during an airborne observation mission using NASA's DC-8 Airborne Laboratory. For each altitude, lines of sight were extracted from flow field solutions computed using an inhouse high-fidelity CFD code, DPLR, at 11 points along the flight trajectory of the capsule. These lines of sight were used as inputs for the line-by-line radiation code NEQAIR, and emission spectra of the air plasma were computed in the wavelength range from 300 nm to 1600 nm, a range which covers all of the different experiments onboard the DC-8. In addition, the computed flow field solutions were post-processed with the material thermal response code FIAT, and the resulting surface temperatures of the heat shield were used to generate thermal emission spectra based on Planck radiation. Both spectra were summed and integrated over the flow field. The resulting emission at each trajectory point was propagated to the DC-8 position and transformed into incident irradiance. Comparisons with experimental data are shown.

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Hayabusa Re-entry: Trajectory Analysis and Observation Mission Design

Cited by 29 publications

References 4 publications

The reentry to Earth as a valuable option at the end-of-life of Libration Point Orbit missions

The reentry to Earth as a valuable option at the end-of-life of Libration Point Orbit missions

Remote observations of reentering spacecraft including the space shuttle orbiter

Radiation Modeling for the Reentry of the Hayabusa Sample Return Capsule

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