A method for stabilizing transversal oscillations of a rotor including the steps of acquiring a first signal representing a value of transversal oscillations of a rotor; estimating a value of a thermal gradient from the first signal; computing a value of an actuation parameter from the value of thermal gradient; emitting an actuation signal representing the value of the actuation parameter.

An easy-to-maintain frame-type energy-absorption structure, including: a fixing frame, anti-climder which are arranged at the front of the bottom of the fixing frame, energy absorption block which are detachably connected with the fixing frame and the anti-climder respectively, a connecting device for hinging the anti-climder and the fixing frame, and shear pins which are respectively arranged at a junction of the connecting device and the fixing frame, and a junction of the connecting device and the anti-climder. So that changing the traditional whole welded frame type energy absorbing device into an easy-to-maintain frame-type energy-absorption structure, and when a collision occurs, protecting the fixing frame from being damaged, and the energy absorption block can be replaced to achieve reuse it.

In a shock-absorbing member in which a wood member is embedded in a resin covering member so as to be integrated therewith and in which the wood member is collapsed when subjected to an impact load, thereby absorbing a portion of the impact load, sealing members are disposed between both end surfaces of the wood member in an axis direction of annual rings and an inner surface of the covering member, so as to hermetically cover both end surfaces of the wood member.

To increase a compactness of damping systems intended to operate in the event of a dynamic landing of an aircraft, a damping system comprises a primary damper device and a secondary damper device. The primary damper device comprises at least one beam, each beam extending along a direction of a longitudinal axis. The damping system is configured so that at rest, the primary damper device has a stiffness greater than a stiffness of the secondary damper device in the direction of the longitudinal axis. When a force is applied to the damping system along the direction of the longitudinal axis, with a value less than a limit value, each beam remains in a compression state. When the force applied has a value greater than or equal to the limit value, each beam undergoes buckling and the secondary damper device undergoes elastic deformation.

A friction damped insert for highly stressed engineering components is disclosed. The disclosed inventive concept provides a method and system for increasing the damping capacity of an engineering system by adding a non-flat solid, highly damped insert to a system component that contributes most to the system's dynamic response. The insert can either be embedded into a system component during casting or be fastened to the system component outer surface. The insert is made of the single layer of flexible material by forming it into a rigid elongated body. The layer of material can be turned over on itself without folding to create a cylinder or can be folded over a number of times to create a prismatic bar. The layer of material may be shaped into a corrugated panel. The layer of flexible material may have a number of relatively small openings or perforations with a uniform spatial distribution.

A friction damped insert for highly stressed engineering components is disclosed. The disclosed inventive concept provides a method and system for increasing the damping capacity of an engineering system by adding a non-flat solid, highly damped insert to a system component that contributes most to the system's dynamic response. The insert can either be embedded into a system component during casting or be fastened to the system component outer surface. The insert is made of the single layer of flexible material by forming it into a rigid elongated body. The layer of material can be turned over on itself without folding to create a cylinder or can be folded over a number of times to create a prismatic bar. The layer of material may be shaped into a corrugated panel. The layer of flexible material may have a number of relatively small openings or perforations with a uniform spatial distribution.

A supporting structure for supporting a device includes: a base portion configured to support the device; and a plurality of leg portions configured to support the base portion. At least one of the plurality of leg portions includes a height adjusting mechanism whose length is adjustable in a height direction of the base portion, and a ground contact member configured to make contact with a ground. The ground contact member is fixed to the base portion with the height adjusting mechanism sandwiched between the ground contact member and the base portion so as to fix the height adjusting mechanism, and the ground contact member has a ground contact surface formed in the shape of a convex-shaped curved surface.

A supporting structure for supporting a device includes: a base portion configured to support the device; and a plurality of leg portions configured to support the base portion. At least one of the plurality of leg portions includes a height adjusting mechanism whose length is adjustable in a height direction of the base portion, and a ground contact member configured to make contact with a ground. The ground contact member is fixed to the base portion with the height adjusting mechanism sandwiched between the ground contact member and the base portion so as to fix the height adjusting mechanism, and the ground contact member has a ground contact surface formed in the shape of a convex-shaped curved surface.

Exemplary embodiments of a decorative hard flooring system for an aircraft are disclosed herein. The hard flooring system includes a plurality of decorative hard floor assemblies at least some of which include a decorative hard flooring layer and a metallic substrate layer having at least one aperture formed therein to receive a warming element. The flooring system further includes, a power supply coupled to the warming element and a controller coupled to the power supply to control the power supplied to the warming element. An ambient temperature sensor coupled to the controller to provide an indication of ambient temperature so that the controller controls the power supply to power the warming elements to warm the decorative hard floor assemblies to be substantially at the ambient temperature.

Exemplary embodiments of a decorative hard flooring system for an aircraft are disclosed herein. The hard flooring system includes a plurality of decorative hard floor assemblies at least some of which include a decorative hard flooring layer and a metallic substrate layer having at least one aperture formed therein to receive a warming element. The flooring system further includes, a power supply coupled to the warming element and a controller coupled to the power supply to control the power supplied to the warming element. An ambient temperature sensor coupled to the controller to provide an indication of ambient temperature so that the controller controls the power supply to power the warming elements to warm the decorative hard floor assemblies to be substantially at the ambient temperature.