Propeller aircraft rack-mounted electronics testing
RTCA/DO-160D Environmental Conditions and Test Procedures for Airborne Equipment （http://www.rtca.org), 8.7 Robust Vibration Test Procedure-Fixed-Wing Aircraft: Curve M）
80 mm × 220 mm × H150 mm, 6 kg
■ Critical vibration frequency *1 survey
Curve M, 1oct/min, 1 round trip (13min), 3 axes, monitoring changes in EUT operation during shaking.
■ Critical vibration frequencies
Two points in the X-axis, two points in the Y-axis and three points in the Z-axis were detected.
*1 Resonance frequency at which the vibration response exceeds 2 times, or the frequency at which a change in EUT operation occurs.
■ Critical frequency endurance test
The EUT was subjected to 30 min of excitation at each critical frequency, in sequence, in three axes.
■ Sweep endurance test
Curve M, 1oct/min, recording the response during shaking, investigating changes in resonance frequency and monitoring changes in EUT operation.
X-axis (3h-1 min-2 × 30min)=1h 47min Y-axis (3h-13min-2 × 30min) = 1h 47min
Z-axis (3h-13min-3 × 30min)=1h 17min
RTCA/DO-160D, Curve M Sine wave test conditions
Vertical vibration Z / Horizontal vibration X
Vibration test system with slip table: i220/SA1M/H6
Vibration controller: K2 software Sine
Dedicated fixture: 15 kg
8 hours/2 days