Jay H. Grinstead Aerothermodynamics Branch, NASA Ames Research Center Airborne Observation of NEO/Asteroid Entries – Rapid Response Capability Airborne observation: capabilities and heritage Long endurance aircraft with global reach Instrumentation with spectral, hyperspectral, thermal, and documentary imaging capabilities Mission planning methodologies Applications: Re-entering spacecraft, expended launch vehicles, atmospheric flight vehicles, meteors Characterization of NEO entry events with airborne observations Objective: Obtain hyperspectral imagery of NEO entry events with the best possible spatial resolution Approach: Extend proven atmospheric entry airborne observation techniques to NEOs Initial activity: Determine if approach is viable from a technical, logistical, and programmatic perspective Breakup characteristics are of vital importance for engineering and high- fidelity simulation validation -Fragmentation altitudes -Fragment sizes, shapes, trajectories -Spectral properties (surface, gas, ablation products) Fragmentation simulation (CFD) Challenges for optical instrumentation used to capture NEO entries (requires development) -Transient with rapid fluctuations -Wide dynamic range -Spatial and spectral resolution demands Challenges for airborne mission preparation and execution to capture NEO entries -Short notification (~24-48 h) of confirmed NEO entry -Aircraft and mission crew availability -Logistical needs to place aircraft, instrumentation, and crew on station in less than 24 h Chelyabinsk 2013 Filtering and image processing reveal plume features ATV ~4.5 X 10 m Rapid response airborne observation capability: assessment study Develop analytic model from end-to- end concept formulation. Use model to conduct system trades Compare results against mission requirements Identify gaps, optimize parameters to meet programmatic objectives Assess viability and utility of airborne observation Simulation Input TECHNICAL Impactor entry physics Flight path determination Instrument response TECHNICAL Impactor entry physics Flight path determination Instrument response LOGISTIC NEO notification Asset deployment LOGISTIC NEO notification Asset deployment PARAMETERS AND CONSTRAINTS Notification time Data requirements Deployment schedule Aircraft and mission crew availability Aircraft performance specifications Instrument specifications PARAMETERS AND CONSTRAINTS Notification time Data requirements Deployment schedule Aircraft and mission crew availability Aircraft performance specifications Instrument specifications VARIABLES NEO characteristics, orbit, and entry time/date VARIABLES NEO characteristics, orbit, and entry time/date Program decisions Airborne observation of ESA’s ATV-1 destructive re-entry (Sept. 29, 2008) -NASA Ames and the SETI Institute -South Pacific Ocean, 2300 mi south of Tahiti -Time-resolved imaging of fragment spectra Spectra of a rotating fragment Titanium on one side Al/Mg on other side Next steps Conduct study to assess viability and identify capability gaps Develop interfaces with aircraft providers and operators Establish requirements for critical instrumentation Acknowledgments: NASA Planetary Defense Integrated Product Team, M. Nemec (STC/NASA Ames); P. Jenniskens (SETI Institute) International partnerships with ESA and JAXA Participation of NASA and non- NASA researchers from the US, Europe, Japan, and Australia Hayabusa sample return capsule and spacecraft (JAXA) – June 13, NASA Ames and the SETI Institute -Woomera Prohibited Area (Australia) -Time-resolved imaging and spectra of SRC and spacecraft fragments Stardust sample return capsule (NASA) – January 15, NASA Ames and the SETI Institute -Utah Test and Training Range -Time-resolved imaging and spectra of SRC