Shock isolation system for spacecraft fairing

A launch vehicle assembly comprising:

• a launch vehicle body having a lip therearound, said lip having a first upper surface, a first lower surface and a first side surface extending between said first upper surface and said first lower surface, said first upper surface having a first slot therein, said first side surface having a second slot therein and said first lower surface having a third slot therein;
• a first magnet disposed within said first slot;
• a second magnet disposed within said second slot;
• a third magnet disposed within said third slot;
• a fairing assembly having a ring positioned adjacent to the lip, said ring having an second upper surface adjacent to said first upper surface, a second lower surface adjacent to said first lower surface and a second side surface adjacent to first side surface, said second upper surface having a fourth slot therein, said second side surface having a fifth slot therein and said second lower surface having a sixth slot therein;
• a fourth magnet disposed within said fourth slot;
• a fifth magnet disposed within said fifth slot;
• a sixth magnet disposed within said sixth slot;
• so that said first magnet repels said fourth magnet, said second magnet repels said fifth magnet and said third magnet repels said sixth magnet.

A method of operating a launch vehicle comprising;

• positioning a payload fairing adjacent to a launch vehicle body;
• contacting the payload fairing with the launch vehicle body above a predetermined force on the payload fairing;
• levitating the payload fairing relative to the launch vehicle body below a predetermined force on the payload fairing;
• and
• after levitating the payload fairing, releasing the payload fairing from the lunch vehicle.