The invention relates to an
impact testing device for a parachute landing unmanned aerial vehicle
damper and a method thereof. The
impact testing device comprises a displacement sensor, an electric discharging loop, an electric discharging coil, an
induction coil, a conical driving head, a guiding shaft and a
pressure sensor. The electric discharging loop performs instantaneous electric discharging on the electric discharging coil.
Strong pulse current is generated in the discharging coil and furthermore an alternated high-strength
magnetic field is formed at the periphery of the discharging coil. The
induction coil closely abuts against the electric discharging coil. Because
electromagnetic induction generates strong
eddy current, the directions of the magnetic fields generated by the electric discharging coil and the
induction coil are opposite, thereby generating an electromagnetic
repulsion force, namely an electromagnetic
impact force. The electromagnetic impact force performs
impact loading on a to-be-tested
damper through the conical driving head and the guiding shaft.
Impact force data are acquired through a
pressure sensor. Compression amount of the
damper is acquired through the displacement sensor. The
impact testing device and the method have advantages of accurate controllable impact force, high stability, simple operation and small
land occupation. The
impact testing device and the method thereof overcome defects of large
land occupation, tedious operation and limited
impact energy in a landing vibration testing platform for damper
impact testing.