Long-duration spacecraft in low Earth orbit such as the International Space Station (ISS) are exposed to high-speed impacts by pieces of debris from past Earth-orbiting missions. Among the hazards that accompany the perforation of a pressurized manned spacecraft are critical crack propagation in the inner wall of a multi-panel module wall system, crew hypoxia, and uncontrolled thrust due to air rushing out of the module inner wall hole. These phenomena are directly related to the hole diameter and crack lengths in a spacecraft inner wall following a performation. A new empirical model of hole diameter and maximum tip-to-tip crack length for some of the multi-wall systems being developed for the ISS is presented and discussed. The model is used to show that 1) hole diameters and crack lengths are directly related to the momentum of the impacting projectile, and 2) properly constructed hole size and crack length models based on data obtained at moderate impact velocities (i.e., approximately 6 to 7 km/s) can be used successfully to predict hole size and crack lengths at impact velocities exceeding 11 km/s.
Modeling Damage in Spacecraft Impacted by Orbital Debris Particles
J of Astronaut Sci
The Journal of the Astronautical Sciences ; 47 , 1-2 ; 103-115
1999-03-01
13 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Modeling Damage in Spacecraft Impacted by Orbital Debris Particles
Online Contents | 1999
|Modeling Damage in Spacecraft Impacted by Orbital Debris Particles
Online Contents | 1999
|Reliability Analysis of Spacecraft Impacted by Space Debris
British Library Conference Proceedings | 1998
|Protecting spacecraft against orbital debris impact damage using composite materials
Tema Archiv | 2000
|Spacecraft Orbital Debris Reentry Aerothermal Analysis
British Library Conference Proceedings | 1997
|