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.