The Development of an Intelligent Health Monitoring System for Micrometeoroid and Space Debris Protection Systems and Spacecraft Structural Components

RESUME Le debut des activites humaines dans l’espace, en 1957, a marque aussi le debut de la pollution graduelle de cet environnement avec des debris orbitaux (DO). Aujourd'hui, ce probleme cree ce qui est appele «l’impact a de tres haute vitesse», un des principaux dangers pouvant se produire (impact a hyper vitesse) entre des debris orbitaux et un vehicule spatial ou satellite en cours de vol atour de l'orbite terrestre. A la suite de ces collisions plus de debris sont formes en basse orbite (region inferieure a 2000 km d'altitude) et un phenomene dit «collision potentielle en cascade» (egalement connu sous le nom de «syndrome de Kessler») peut survenir. La collision en cascade est mentionnee par plusieurs etudes de modelisation de l'environnement spatial effectuees par des agences spatiales comme la NASA ou l'ESA. Un autre type de danger qui peut conduire au meme risque d'impact a une tres grande vitesse dans l’espace sont les micrometeorites. Les micrometeorites et les debris spatiaux voyagent en orbite terrestre basse a des vitesses allant de 17 a 20 Km/s et 70 a 80 Km/s respectivement, et leur impact sur les vehicules spatiaux peut varier d'une degradation des performances jusqu’a la perte totale de l’engin. Actuellement, il y a plus de 22000 morceaux de debris orbitaux qui sont suivis et repertories, et cela pour des objets avec des dimensions superieures a 5 cm, pour lesquels la prevention des collisions est la seule option, et pour lesquelles aussi des dizaines de conjonctions d’avertissements sont emises quotidiennement par les centres d'operations satellitaires. En revanche, Il y a plus de 500000 morceaux de debris orbitaux avec des dimensions inferieures a 5 cm representant aussi un haut risque de collision pour les satellites qui sont en orbite basse. Le cas de l'impact de DO ayant des dimensions allant jusqu'a 5 mm pourrait creer une degradation des fonctions operationnelles d'un vehicule spatial. Les DO ayant des dimensions de 0,5 a 1 cm sont la principale menace pour les vehicules spatiaux en orbite basse et pour lesquels les solutions actuelles sont juste representees par des systemes de protection. Le maintien d'une structure sure et saine de satellites ou de vehicules spatiaux et une meilleure comprehension de l'interaction des MMOD avec les systemes spatiaux motive en effet la creation d'un systeme de surveillance (Health Monitoring System) integre afin de surveiller en temps reel ou en temps quasi reel la degradation de la structure ou du systeme de protection.----------ABSTRACT Human activity in the space environment began in 1957. From this moment forward, these activities have created another phenomena; the gradual pollution of space with orbital debris (OD). Today this accumulated debris is one of the main hazards in the near–Earth space environment. More specifically, hypervelocity impact between OD and every satellite and space vehicle that is launched or is currently orbiting the Earth. As each collision occurs more OD is created and, in the Low Earth Orbit (LEO) zone (the region below 2000 km altitude), a potential ongoing collision cascade effect (also known as the “Kessler Syndrome”) can occur. This potential for collision cascade has been identified during space environment modeling studies performed by space agencies such as NASA or ESA. Increased space activity combined with poor standardization of space activity and the limited options for cleaning the space environment will lead to an increased frequency of collisions. Within the next few decades we will not be able to use the LEO for practical purposes. Another type of particle that creates the same primary risk of hypervelocity impact in the space environment is micrometeoroids. Micrometeoroids and space debris travel in low earth orbit at velocities up to 17-20 Km/s (OD) and 70-80 Km/s respectively, and their impact on space assets can vary from degraded performance to catastrophic loss. More than 22000 pieces of OD are currently tracked. These are objects with dimensions larger than 5 cm for which collision prevention is the only option, and for which tens of conjunction warnings are issued daily by satellite operations centers. In addition, there are more than 500,000 pieces of OD with dimensions less than 5 cm that present a high risk for collisions with satellites that are orbiting in the LEO. Solutions for debris in this dimensional range still have to be developed and include concepts capable of preventing and blocking the huge energy of hypervelocity impact and/or concepts for OD removal. Impact between OD with dimensions up to 5 mm and spacecraft is a special case because it could create a degradation of operational functions. OD in the 0.5 to 1 cm dimensional range, which represents 80 % of debris larger than 0.5 cm, is the main threat to spacecraft in the LEO. The only current solutions are protection systems or shields. To evaluate the risks associated with spacecraft impact with micrometeoroids and orbital debris (MMOD) we have to analyze factors such as: environment (the fluxes of particles), damage prediction (number of impacts) and damage tolerance (how much damage the structure can stand).

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