VIBRATION ABSORBER FOR AIRCRAFT
    1.
    发明专利

    公开(公告)号:JPH1172138A

    公开(公告)日:1999-03-16

    申请号:JP10782598

    申请日:1998-04-17

    Abstract: PROBLEM TO BE SOLVED: To absorb energy of time cycle vibration of a structural member by hanging a mass body from a mount base between rods to constitute a flexible body type spring assembly and changing the stiffness of a spring by a tuning mechanism by the adjustment of tensile force in the rods and compression. SOLUTION: A durable mass body 32 is positioned in a cavity 34 in an external housing 31 and is arranged at a fixed interval from a closed end part of the housing by a first flexible body assembly 36. The first flexible body assembly 36 has a rod 40 and circular rings 37, 38 which are parallel each other. A second flexible body 55 is formed by a flexible rod 59 having a circular cross section and circular rings 57 and 58 which are in parallel. By changing the compression force which acts on the rods 40 and 59 of the flexible body assembly, the stiffness of a spring is changed to change resonance frequency and maintain the optimum adjustment of a vibration absorber. Consequently, it is possible to absorb vibration energy due to the vibration of the durable mass body 32 in the optimum condition.

    VIBRATION ABSORPTION DEVICE
    2.
    发明专利

    公开(公告)号:JPH1172137A

    公开(公告)日:1999-03-16

    申请号:JP10782498

    申请日:1998-04-17

    Abstract: PROBLEM TO BE SOLVED: To absorb energy of time cycle vibration of a structural member by providing a first spring and a second spring which include rings provided with rods connected between the rings and have the stiffness which determines resonance frequency at which a first barrel part and a second barrel part vibrate. SOLUTION: A first deflection body 36 has circular rings 37 and 38. A rod 40 is thin between the rings 37 and 38 and a diameter of a cross section thereof is small at a central position thereof so that the first deflection body 36 plays the role of a spring. A second deflection body 55 is formed by a rod 59 having a circular cross section and rings 57 and 58. A retaining ring 51 enters an end part of a housing and comes in contact with the ring 58 of the second deflecting body 55. By changing the stress which acts on the rods 40 and 59 of a deflecting body assembly, the stiffness of the spring is changed to change resonance frequency and to adjust a vibration absorbing device. Consequently, the vibration energy can be absorbed by the vibration of a durable mass body 32 and a motor assembly 50 in the optimum condition.

    ADAPTIVELY TUNED VIBRATION ABSORBER WITH DUAL FLEXURES

    公开(公告)号:CA2232767C

    公开(公告)日:2007-01-30

    申请号:CA2232767

    申请日:1998-03-20

    Abstract: An apparatus for counteracting vibrations includes a housing for attachment to a vibrating member. First and second bodies are connected to the housing by first and second springs, respectively, with a combined stiffness which defines a resonant frequency at which the first and second bodies oscillate with respect to the housing. Each of the first and second springs include a plurality of rods fixedly connected between a pair of rings. A lever engages the first and second bodies to vary a spacing between those bodies when force from an actuator is applied to the lever. The lever action alters the stiffness of the first and second springs which varies the resonant frequency of the vibration absorber.

    ADAPTIVELY TUNED VIBRATION ABSORBER FOR REDUCTION OF AIRCRAFT CABIN NOISE

    公开(公告)号:CA2233495C

    公开(公告)日:2006-10-03

    申请号:CA2233495

    申请日:1998-03-27

    Abstract: An aircraft engine is attached to the fuselage by a mounting structure that has a vibration absorbing system which includes first and second sensors to produce signals indicating vibration along two orthogonal axes. A third sensor, such as an accelerometer, is coupled to the mounting structure for sensing vibration of the engine. A tachometer circuit, connected to the third sensor, produces first and second speed signals that indicate the speeds of two rotating spools in the engine. Four vibration absorbers are attached to the engine mounting structure and controllers are provided to dynamically tune the resonant frequency of each vibration absorber in response to a unique combination of one of the two vibration signals and one of the two speed signals. Thus the vibration absorbers reduce the engine spool vibrations that are transmitted through the mounting structure along the two orthogonal axes. The resonant frequency of each absorber is altered to track variation of the vibrations due to changes in engine speed.

    ADAPTIVELY TUNED VIBRATION ABSORBER WITH DUAL FLEXURES

    公开(公告)号:CA2232767A1

    公开(公告)日:1998-10-17

    申请号:CA2232767

    申请日:1998-03-20

    Abstract: An apparatus for counteracting vibrations includes a housing for attachment to a vibrating member. First and second bodies are connected to the housing by first and second springs, respectively, with a combined stiffness which defines a resonant frequency at which the first and second bodies oscillate with respect to the housing. Each of the first and second springs include a plurality of rods fixedly connected between a pair of rings. A lever engages the first and second bodies to vary a spacing between those bodies when force from an actuator is applied to the lever. The lever action alters the stiffness of the first and second springs which varies the resonant frequency of the vibration absorber.

    ADAPTIVELY TUNED VIBRATION ABSORBER FOR REDUCTION OF AIRCRAFT CABIN NOISE

    公开(公告)号:CA2233495A1

    公开(公告)日:1998-10-17

    申请号:CA2233495

    申请日:1998-03-27

    Abstract: An aircraft engine is attached to the fuselage by a mounting structure that has a vibration absorbing system which includes first and second sensors to produce signals indicating vibration along two orthogonal axes. A third sensor, such as an accelerometer, is coupled to the mounting structure for sensing vibration of the engine. A tachometer circuit, connected to the third sensor, produces first and second speed signals that indicate the speeds of two rotating spools in the engine. Four vibration absorbers are attached to the engine mounting structure and controllers are provided to dynamically tune the resonant frequency of each vibration absorber in response to a unique combination of one of the two vibration signals and one of the two speed signals. Thus the vibration absorbers reduce the engine spool vibrations that are transmitted through the mounting structure along the two orthogonal axes The resonant frequency of each absorber is altered to track variation of the vibrations due to changes in engine speed.

    9.
    发明专利
    未知

    公开(公告)号:DE69821818D1

    公开(公告)日:2004-04-01

    申请号:DE69821818

    申请日:1998-04-16

    Abstract: An aircraft engine is attached to the fuselage by a mounting structure (20) that has a vibration absorbing system which includes first and second sensors (61,62), to produce signals indicating vibration along two orthogonal axes. A third sensor, such as an accelerometer (64), is coupled to the mounting structure for sensing vibration of the engine. A tachometer circuit (67), connected to the third sensor, produces first and second speed signals that indicate the speeds of two rotating spools (N1,N2) in the engine. Four vibration absorbers (26-29) are attached to the engine mounting structure and controllers (60) are provided to dynamically tune the resonant frequency of each vibration absorber in response to a unique combination of one of the two vibration signals and one of the two speed signals. Thus the vibration absorbers reduce the engine spool vibrations that are transmitted through the mounting structure along the two orthogonal axes. The resonant frequency of each absorber is altered to track variation of the vibrations due to changes in engine speed.

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