Orbital debris hazard for nuclear electric propulsion earth-escape trajectories

Details Orbital debris hazard for nuclear electric propulsion earth-escape trajectories Orbital debris hazard for nuclear electric propulsion earth-escape trajectories

Aug 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992aiaa.conf..165v&link_type=abstract

IN: 1992 AIAA/AAS Astrodynamics Conference, Hilton Head Island, SC, Aug. 10-12, 1992, Technical Papers (A92-52051 22-13). Washin

Astronomy and Astrophysics

Astronomy

Earth-Mars Trajectories, Earth-Moon Trajectories, Flight Hazards, Nuclear Electric Propulsion, Particle Collisions, Space Debris, Collision Avoidance, Geosynchronous Orbits, Monte Carlo Method, Statistical Analysis, Thrust-Weight Ratio

Scientific paper

A quantitative method for estimating the debris collision hazard for NEP vehicles is described. The method is capable of estimating, over extended time intervals, the statistical distribution of the distances from the potential target to the nearest debris object as a function of the target's trajectory and the spatial configuration of the debris population. The collision probabilities obtained for a nuclear electric propulsion (NEP) target passing through such a large spatial configuration of debris are then scaled for the projected growth in the debris population, and for the larger population of untracked, but still hazardous, debris. Data obtained indicate that the debris hazard may be significant for a large NEP vehicle in the 2015 era, particularly if its spiral trajectory is initialized below an altitude of 1100 km.

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