Surface Heating from Remote Sensing of the Hypervelocity Entry of the NASA GENESIS Sample Return Capsule

Jenniskens, Peter; Wercinski, Paul; Olejniczak, Joseph; Wright, Michael J.; Raiche, George A.; Kontinos, Dean; Desai, Prasun N.; Va, Hampton; Spalding, R. E.; Sandquist, K.; Rossano, G. S.; Russell, R. W.; Revelle, D. O.; Hladiuk, D.; Hildebrand, A. R.

doi:10.2514/6.2006-381

Cited by 18 publications

(13 citation statements)

References 8 publications

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“…The entry velocity of Hayabusa's SRC was the second fastest into Earth's atmosphere. Building upon previous re-entry observation missions (Genesis, Stardust and ATV) [3][4][5] , the Hayabusa Observation Mission team successfully executed the airborne observation campaign. 6 This paper presents an overview of the calculated Hayabusa SRC trajectory and methods utilized to design the observation flight track.…”

Section: Introductionmentioning

confidence: 99%

Hayabusa Re-entry: Trajectory Analysis and Observation Mission Design

Cassell

Winter

Grinstead

et al. 2011

42nd AIAA Thermophysics Conference

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On June 13th , 2010, the Hayabusa sample return capsule successfully re-entered Earth's atmosphere over the Woomera Prohibited Area in southern Australia in its quest to return fragments from the asteroid 1998 SF36 "Itokawa". The sample return capsule entered at a super-orbital velocity of 12.04 km/sec (inertial), making it the second fastest human-made object to traverse the atmosphere. The NASA DC-8 airborne observatory was utilized as an instrument platform to record the luminous portion of the sample return capsule re-entry (~60 sec) with a variety of on-board spectroscopic imaging instruments. The predicted sample return capsule's entry state information at ~200 km altitude was propagated through the atmosphere to generate aerothermodynamic and trajectory data used for initial observation flight path design and planning. The DC-8 flight path was designed by considering safety, optimal sample return capsule viewing geometry and aircraft capabilities in concert with key aerothermodynamic events along the predicted trajectory.

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Section: Introductionmentioning

confidence: 99%

Hayabusa Re-entry: Trajectory Analysis and Observation Mission Design

Cassell

Winter

Grinstead

et al. 2011

42nd AIAA Thermophysics Conference

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“…The data are interpreted to reveal quantities of importance to atmospheric entry aerothermodynamics: apparent temperatures, shock radiation spectra, ablation species spectra (if present), and their temporal evolution during entry. The first of these collaborations was for NASA's Genesis reentry in 2004 33,34 followed by NASA's Stardust in 2006 [35][36][37][38][39][40][41][42][43][44][45][46][47] and JAXA's Hayabusa in 2010.…”

Section: Current Quantitative Imaging Applicationsmentioning

confidence: 99%

A Vision of Quantitative Imaging Technology for the Validation of Advanced Flight Technologies

Horvath

Kerns

Jones

et al. 2011

42nd AIAA Thermophysics Conference

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Flight-testing is traditionally an expensive but critical element in the development and ultimate validation and certification of technologies destined for future operational capabilities. Measurements obtained in relevant flight environments also provide unique opportunities to observe flow phenomenon that are often beyond the capabilities of ground testing facilities and computational tools to simulate or duplicate. However, the challenges of minimizing vehicle weight and internal complexity as well as instrumentation bandwidth limitations often restrict the ability to make high-density, in-situ measurements with discrete sensors. Remote imaging offers a potential opportunity to noninvasively obtain such flight data in a complementary fashion. The NASA Hypersonic Thermodynamic Infrared Measurements Project has demonstrated such a capability to obtain calibrated thermal imagery on a hypersonic vehicle in flight. Through the application of existing and accessible technologies, the acreage surface temperature of the Shuttle lower surface was measured during reentry. Future hypersonic cruise vehicles, launcher configurations and reentry vehicles will, however, challenge current remote imaging capability. As NASA embarks on the design and deployment of a new Space Launch System architecture for access beyond earth orbit (and the commercial sector focused on low earth orbit), an opportunity exists to implement an imagery system and its supporting infrastructure that provides sufficient flexibility to incorporate changing technology to address the future needs of the flight test community. A long term vision is offered that supports the application of advanced multi-waveband sensing technology to aid in the development of future aerospace systems and critical technologies to enable highly responsive vehicle operations across the aerospace continuum, spanning launch, reusable space access and global reach. Motivations for development of an Agency level imagery-based measurement capability to support cross cutting applications that span the Agency mission directorates as well as meeting potential needs of the commercial sector and national interests of the Intelligence, Surveillance and Reconnaissance community are explored. A recommendation is made for an assessment study to baseline current imaging technology including the identification of future mission requirements. Development of requirements fostered by the applications suggested in this paper would be used to identify technology gaps and direct roadmapping for implementation of an affordable and sustainable next generation sensor/platform system.

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“…Following the reentries of the Genesis in (ReVelle et al, 2005Jenniskens et al, 2006) and the Stardust in 2006 (Edwards et al, 2007), the return of the Hayabusa Sample Return Capsule (H-SRC) was the third direct reentry event from the interplanetary transfer orbit to the Earth at a velocity of over 11.2 km/s. In addition, it was the world's rst case of a direct reentry of the spacecraft (H-S/C) itself from the interplanetary transfer orbit.…”

Section: Introductionmentioning

confidence: 99%

Infrasound/seismic observation of the Hayabusa reentry: Observations and preliminary results

et al. 2012

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The Hayabusa, the world's rst sample-return minor body explorer, returned to the Earth, and reentered the Earth's atmosphere on June 13, 2010. Multi-site ground observations of the Hayabusa reentry were carried out in the Woomera Prohibited Area (WPA), Australia. The ground observations were con gured with optical imaging with still and video recordings, spectroscopies, and shockwave detection with infrasound and seismic sensors. At three main stations, we installed small aperture infrasound/seismic arrays, as well as three single component seismic sub stations. The infrasound and seismic sensors clearly recorded sonic-boom-type shockwaves from the Hayabusa Sample Return Capsule (H-SRC) and the disrupted fragments of the Hayabusa Spacecraft (H-S/C) itself. Positive overpressure values of shockwaves (corresponding to the H-SRC) recorded at the three main stations were 1.3 Pa, 1.0 Pa, and 0.7 Pa with slant distances of 36.9 km, 54.9 km, and 67.8 km, respectively. Incident vectors of the shockwave from the H-SRC at all three arrays are estimated by an F-K spectrum and agree well with those predicted. Particle motions of ground motions excited by the shockwave show characteristics of a typical Rayleigh wave.

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Surface Heating from Remote Sensing of the Hypervelocity Entry of the NASA GENESIS Sample Return Capsule

Cited by 18 publications

References 8 publications

Hayabusa Re-entry: Trajectory Analysis and Observation Mission Design

Hayabusa Re-entry: Trajectory Analysis and Observation Mission Design

A Vision of Quantitative Imaging Technology for the Validation of Advanced Flight Technologies

Infrasound/seismic observation of the Hayabusa reentry: Observations and preliminary results

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