Provided is a damper wherein viscous fluid which fills a circular cylinder chamber is more reliably prevented from leaking. A rotary damper (1) includes: a first seal ring (8a) of an elastic body, arranged between a through-hole (23) of a circular cylinder chamber (21) in a case (2) and a lower end of a rotor body of a rotor (3); and a second seal ring (8b) of an elastic body, arranged between a through-hole (60) in a lid (6) and an upper end of the rotor body. The first seal ring (8a) has: an outer peripheral surface with a width in a direction of a center axis of the circular cylinder chamber (21), which is pressed against an inner peripheral surface of the through-hole (23); and an inner peripheral surface with a width in the direction of the center axis of the circular cylinder chamber (21), which is pressed against an outer peripheral surface of the lower end of the rotor body, and also a second seal ring (8b) has: an outer peripheral surface with a width in the direction of the center axis of the circular cylinder chamber (21), which is pressed against an inner peripheral surface of the through-hole (60); and an inner peripheral surface with a width in the direction of the center axis of the circular cylinder chamber (21), which pressed against an outer peripheral surface of the upper end of the rotor body.

Aircraft landing gear strut breakout friction values are used to correct measured strut pressure as related to the amount of weight supported; with the ability to generate and refine the breakout friction value database, and a further ability to predict a future breakout friction correction value by trending historical measurements, as compared to recent measurements, as further compared to real-time breakout friction values. The system is used in monitoring, measuring, computing and displaying the weight and center of gravity for aircraft utilizing telescopic oleo landing gear struts. Pressure sensors, temperature sensors, humidity sensors, axle deflection sensors, accelerometers, inclinometers are mounted in relation to landing gear struts to monitor, measure and record strut pressure as related to strut telescopic movement, rates of strut telescopic movement, axle deflection, current temperature, current relative humidity, vertical acceleration; experienced by landing gear struts, as the aircraft proceeds through typical ground and flight operations.

A compact testing module (1) for use in dynamic characteristics experiments of hydraulic damper valve under extreme high or low temperature conditions, an automated system and approach based on the compact testing module (1). The compact testing module (1) comprises an outer cylinder assembly (2), a guide seat assembly (3), a foam/air separator for guide seat (4), an inner cylinder (5), a piston-and-rod assembly (6), fluids (7), a foot valve assembly (8), a washer for inner cylinder (9), a washer for foot valve assembly (10), a fluid-guiding structure (11), a magnet (12), a fluid-returning assembly (13), a framework oil seal (14), a screw cover (15) and a dust wiper (16). Based on the integrated design principle, the compact testing module (1) allows the fluids (7), the pressure fluid supplier, the hydraulic damper valve being tested (32), the pressure sensors be all integrated in one component.

A telescopic arrangement (10) having a hollow cylinder (12) and a part (14) which is telescopically engaged with the cylinder. The arrangement is provided with at least one coil (22) constituting a first form of pulse-induction device, and at least one target (28) constituting a second form of pulse-induction device, to monitor the position of the said part (14) relative to the cylinder (12). A plurality of devices (22) each of one of the said first and second forms of device are positioned on the outside of the cylinder (12), at different respective positions therealong. At least one (28) of the other of the said first and second forms of device is fixed relative to the said part (14) of the arrangement (10) in a position such that it is moved over the said plurality of devices (22) in succession as the said part (14) is telescopically moved relative to the cylinder (12) of the arrangement (10).

A dual-stage, separated gas/fluid shock strut arrangement includes a dual-stage, separated gas/fluid shock strut, a pressure/temperature sensor mounted to the primary gas chamber, a stroke sensor, and a monitoring system, comprising a recorder configured to receive a plurality of sensor readings from at least one of the pressure/temperature sensor and the stroke sensor, a landing detector configured to detect a landing event based upon a stroke sensor reading received from the stroke sensor, and a health monitor configured to determine a volume of oil in the oil chamber, a volume of gas in the primary gas chamber, and a volume of gas in the secondary gas chamber.

An energy-supply rotary inertia driver system for an offshore platform includes an annular fixed plate, an active control module, a wind power generation module and a solar power generation module. The system can monitor a motion state of the offshore platform in real time, and can generate a force through the active control module if necessary to apply a force torque of the offshore platform to further achieve the vibration suppression. Moreover, when the offshore platform is under normal operation, the system can act as an energy supply device via wind and solar power generation to feed electric energy to the active control module and other electrical equipment on the offshore platform when needed.

A dual-stage, separated gas/fluid shock strut arrangement includes a dual-stage, separated gas/fluid shock strut and a monitoring system. The shock strut includes a strut cylinder, a strut piston operatively coupled to the strut cylinder, an oil chamber, a primary gas chamber, and a secondary gas chamber. The monitoring system includes a first pressure/temperature sensor, a second pressure/temperature sensor, a stroke sensor, a recorder configured to receive a plurality of sensor readings from the first pressure/temperature sensor, the second pressure/temperature sensor, and/or the stroke sensor, a landing detector configured to detect a landing event based upon a stroke sensor reading received from the stroke sensor, and a health monitor configured to determine a volume of oil in the oil chamber, a primary chamber gas volume in the primary gas chamber, and a secondary chamber gas volume in the secondary gas chamber.

A damping arrangement for dampening rotational irregularities in a drive train of a motor vehicle, having a slip arrangement providing slip between an input and output region of a torque-transmitting arrangement. The slip arrangement has a closed-loop control device that performs closed-loop control of the slip dependent on a measured signal for a rotational irregularity. The closed-loop control device performs closed-loop control of the slip dependent on at least one characteristic variable of a periodic oscillation component of an alternating component of a rotational speed proceeding from an average rotational speed. A sensor device is connected to the closed-loop control device and is designed to ascertain the average rotational speed in the torque-transmitting path downstream of the slip arrangement and to ascertain a frequency of the alternating component in the torque-transmitting path upstream of the slip arrangement.

A cargo-carrying apparatus is provided. The cargo-carrying apparatus includes: an upper deck and a vibration-isolation section. The upper deck is configured to carry cargo. The vibration-isolation section is disposed beneath the upper deck. The vibration-isolation section includes an elastic vibration-isolation layer and one or more indicator components, and the one or more indicator components are disposed on one or more side surfaces of the elastic vibration-isolation layer, and height of the one or more indicator components varies depending on thickness of the elastic vibration-isolation layer. It is determined whether the elastic vibration-isolation layer of the cargo-carrying apparatus is invalid according to a compression ratio of the elastic vibration-isolation layer obtained from an indicator-component image of one of the one or more indicator components.

An electromagnetic damper 100 according to an embodiment of the present invention includes a first tubular member 111, a second tubular member 121, a rod 123, a plurality of electromagnetic coils 113, permanent magnets 125, and a short circuit 130. The second tubular member 121 is mounted on the first tubular member 111 and is configured to be capable of being relatively displaced in one axis direction with respect to the first tubular member 111. The rod 123 extends in the one axis direction and is, at one end, fixed to the second tubular member 121. The plurality of electromagnetic coils 113 are disposed in either one of an inside of the first tubular member 111 or the rod 123. The permanent magnet generates induced electromotive force in the plurality of electromagnetic coils 113 by relative displacement with respect to the plurality of electromagnetic coils 113 and are disposed in the other of the inside of the first tubular member 111 or the rod 123. The short circuit 130 is connected to the plurality of electromagnetic coils 113 and shorts the terminals of the plurality of electromagnetic coils 113 to each other.