The separation shock test facility is used to measure and analyze the shock levels applied to spacecraft when the spacecraft separates from the final stage rocket and when the antenna is deployed by the reaction of pyrotechnics.
  The facility consists of a pyrotechnic controller, analyzing units, analog processing units, digital processing units, and a data recording system.
  The pyrotechnic controller sends the electric ignition current to the spacecraft pyrotechnics and controls the digital processing units and drives the high-speed camera. The response data attained from the on-Board accelerometer sensor are read into the data recording system and uploaded onto analyzing units for Fourier transform, shock response spectrum analysis, and other data processing. The photographic image of separation is recorded with a high-speed camera.











  Applicable shock sourcesCompatible with pyrotechniques (band clamp, rod cutter, etc.), while capable of measureing and data processing for other shock sources.
  Measurement Time  Max : 1 hour
  Measurable Frequency Range  ∼10kHz(Sampling Frequency 100kHz)
  Number of Measuring Channels  Accelerometer 400ch, Ignition current 1ch