An exciter device is configured to apply both a vibrational force and an impact force to a device-under-test. A first end of a piston is couplable to the device-under-test and a second end of the piston is aligned with a position of an impact hammer tip. The impact hammer tip and an electromagnet are both coupled to a moveable housing that is positioned around the piston. The exciter device applies a vibrational force to the device-under-test when an alternating magnetic field is applied by the electromagnet to the permanent magnet causing a linear reciprocating movement of the moveable housing relative to the piston. The exciter device applies an impact force to the device-under-test when a magnet field is applied by the electromagnet to the permanent magnet causing a linear movement of the moveable housing that is sufficient to cause the impact hammer to contact the second end of the piston.

A shock testing machine including: a carriage for holding a component to be tested, the carriage being configured to be movable in a linear direction along one or more elongated rails; a drum rotatable on a shaft, the drum having a circumferential surface; a cable having one end connected to the carriage and an other end connected to the drum; a motor having an output connected to the shaft to rotate the drum under the motive power of the motor to wind the cable on the circumferential surface of the drum; and a clutch disposed in a power train operatively connecting the motor to the drum, the clutch having a disengaged state and an engaged state. Where the motor is controlled to disengage the clutch while the motor reaches a predetermined rotational speed or predetermined rotational torque and to engage the clutch when the motor reaches the predetermined rotational speed or predetermined rotational torque to accelerate the carriage and component to be tested in the linear direction.

An apparatus and a method for simulating a mechanical stress applied to a sealant from a lightning strike upon an aircraft is provided. The apparatus comprises a specimen, a test fixture, and a capacitor. The specimen comprises an electrically non-conductive sealant for an aircraft fuel tank having a cylindrical shape, and an electrically conductive wire centered axially within the sealant. The test fixture secures the specimen during testing. The capacitor is electrically coupled to the test fixture, and simulates a lightning strike upon the aircraft by vaporizing the wire with a current to generate a mechanical shock to the sealant.

An apparatus and a method for simulating a mechanical stress applied to a sealant from a lightning strike upon an aircraft is provided. The apparatus comprises a specimen, a test fixture, and a capacitor. The specimen comprises an electrically non-conductive sealant for an aircraft fuel tank having a cylindrical shape, and an electrically conductive wire centered axially within the sealant. The test fixture secures the specimen during testing. The capacitor is electrically coupled to the test fixture, and simulates a lightning strike upon the aircraft by vaporizing the wire with a current to generate a mechanical shock to the sealant.

Embodiments described herein provide apparatus and a method for simulating a mechanical stress applied to a sealant from a lightning strike upon an aircraft. One embodiment comprises a specimen, a test fixture, and a capacitor. The specimen comprises an electrically non-conductive sealant for an aircraft fuel tank having a cylindrical shape, and an electrically conductive wire centered axially within the sealant. The test fixture secures the specimen during testing. The capacitor is electrically coupled to the test fixture, and simulates a lightning strike upon the aircraft by vaporizing the wire with a current to generate a mechanical shock to the sealant.

The present invention relates generally to a system and method for measuring the structural characteristics of an object. The object is subjected to an energy application processes and provides an objective, quantitative measurement of structural characteristics of an object. The system may include a device, for example, a percussion instrument, capable of being reproducibly placed against the object undergoing such measurement for reproducible positioning. The system includes features for adjusting the energy applied to an energy application tool to compensate for the physical characteristics or type of the object, and/or for orientation of the device relative to the horizontal during measurement. The system also includes a disposable feature or assembly for minimizing cross-contamination between tests. The structural characteristics as defined herein may include vibration damping capacities, acoustic damping capacities, structural integrity or structural stability.

The present invention discloses a rapid dot matrix micro-nano impact indentation testing system. The rapid dot matrix micro-nano impact indentation testing system comprises a three-dimensional electric positioning module, wherein the three-dimensional electric positioning module comprises an XY translation stage and a Z-axis lifting stage; a dot matrix impact indentation module, wherein the dot matrix impact indentation module comprises a three-degree-of-freedom piezoelectric platform arranged on the Z-axis lifting stage, one surface of the three-degree-of-freedom piezoelectric platform is provided with a piezoelectric ceramic actuator, and one end of the piezoelectric ceramic actuator is connected to an indenter; a clamp, wherein the clamp clamps a test piece, and the test piece faces the indenter; and an imaging module, wherein the imaging module comprises a microscope lens. The system can achieve in-situ micro-nano impact indentation test and rapid dot matrix indentation, and has higher indentation precision.

The present invention discloses a rapid dot matrix micro-nano impact indentation testing system. The rapid dot matrix micro-nano impact indentation testing system comprises a three-dimensional electric positioning module, wherein the three-dimensional electric positioning module comprises an XY translation stage and a Z-axis lifting stage; a dot matrix impact indentation module, wherein the dot matrix impact indentation module comprises a three-degree-of-freedom piezoelectric platform arranged on the Z-axis lifting stage, one surface of the three-degree-of-freedom piezoelectric platform is provided with a piezoelectric ceramic actuator, and one end of the piezoelectric ceramic actuator is connected to an indenter; a clamp, wherein the clamp clamps a test piece, and the test piece faces the indenter; and an imaging module, wherein the imaging module comprises a microscope lens. The system can achieve in-situ micro-nano impact indentation test and rapid dot matrix indentation, and has higher indentation precision.

Disclosed is a synchronous and dynamic loading method in electro-magneto-thermo-mechanical multi-field coupling conditions. The method comprises the following steps: applying maximum pulse current to a test object by a pulse power supply to realize loading in extreme electric field and magnetic field conditions; meanwhile, generating a large amount of friction heat by the high-speed rotation of a rotating body and the friction of the test object to realize loading in an extreme-temperature field combined with a large amount of Joule heat and arc heat; synchronously applying pressure to the rotating body by a pressure device to realize loading of extreme force combined with the gravity of the rotating body and the friction force between the rotating body and the test object.

Disclosed is a synchronous and dynamic loading method in electro-magneto-thermo-mechanical multi-field coupling conditions. The method comprises the following steps: applying maximum pulse current to a test object by a pulse power supply to realize loading in extreme electric field and magnetic field conditions; meanwhile, generating a large amount of friction heat by the high-speed rotation of a rotating body and the friction of the test object to realize loading in an extreme-temperature field combined with a large amount of Joule heat and arc heat; synchronously applying pressure to the rotating body by a pressure device to realize loading of extreme force combined with the gravity of the rotating body and the friction force between the rotating body and the test object.