公开(公告)号：US20240425172A1

公开(公告)日：2024-12-26

申请号：US18338463

申请日：2023-06-21

Applicant: The Boeing Company

Inventor： Steven F. Griffin ,  Zackary L. Endsley

IPC: B64C9/02 ,  F16F1/36

Abstract: An apparatus and method for suppressing free play chatter of a control surface of an aircraft. The free play chatter suppression apparatus includes a containment vessel connected to a control surface of an aircraft. A lossy material is contained within the containment vessel. A body is positioned within the lossy material. The deceleration of the body by the lossy fluid is transmitted to the control surface to dampen vibrations of the control surface.

公开(公告)号：US11595759B2

公开(公告)日：2023-02-28

申请号：US16849237

申请日：2020-04-15

Applicant: The Boeing Company

Inventor： Steven F. Griffin ,  Daryn D. Kono ,  Timothy John Paulitz ,  James Benjamin Turner

IPC: H02N2/18 ,  H04R9/02 ,  H01L41/04 ,  H02M7/217

Abstract: An energy harvesting circuit is disclosed and comprises one or more electrical loads that consume direct current (DC) power, a rectifier, and a hybrid acoustic absorber. The rectifier comprises one or more active switching elements that are driven by a gate drive voltage. The hybrid acoustic absorber comprises a diaphragm and a voice coil. The diaphragm is constructed at least in part of a piezoelectric material. The piezoelectric material is configured to generate a diaphragm voltage in response to sound waves deforming the diaphragm. The diaphragm voltage is at least equal to the gate drive voltage to drive the one or more active switching elements of the rectifier. The voice coil is attached to the diaphragm and configured to generate a voice coil voltage that is less than the gate drive voltage of the one or more active switching elements.

公开(公告)号：US10364860B2

公开(公告)日：2019-07-30

申请号：US15836131

申请日：2017-12-08

Applicant: The Boeing Company

Inventor： Steven F. Griffin ,  Richard W. Aston ,  Jazzmin P. Martinez ,  Michael John Langmack ,  Christopher R. Shurilla

IPC: F16F15/03 ,  F16F6/00 ,  B60G99/00 ,  F16F15/121 ,  F16F15/00

Abstract: Systems and methods for dampening dynamic loading between two bodies are described. An example dampening system includes a non-ferrous metal body attached to a second body and a stack of magnets attached to a third body. The stack of magnets is movably disposed within or around the non-ferrous metal body, and adjacent magnets are arranged in an opposed polar relationship, whereby relative movement of said second and third bodies is damped. An example method of dampening dynamic loading includes arranging a plurality of magnets along an axis to form at least one pair of magnets having an opposed polar relationship along the axis. The method further includes axially moving the at least one pair of magnets relative to a non-ferrous metal body, so as to dampen dynamic loading of a payload attached to a vehicle.

公开(公告)号：US20190145481A1

公开(公告)日：2019-05-16

申请号：US15810793

申请日：2017-11-13

Applicant: The Boeing Company

Inventor： Steven F. Griffin ,  Stefan P. Hovik

IPC: F16F7/10 ,  F16F15/02 ,  F16F7/104 ,  B64C17/00 ,  G01M9/04

Abstract: Methods of damping vibrations in a host structure are described. In one embodiment, the vibrations can be damped using a tuned mass damper. The tuned mass damper can include a suspended mass with magnets which is configured to move in response to current being applied to a voice coil. The tuned mass damper can damp vibrations resulting from an external load applied to the host structure, such as an external aerodynamic load. In one embodiment, the tuned mass damper can be mounted within a wind tunnel model undergoing transonic testing. The tuned mass damper can be operated to limit potentially destructive vibrations which can occur during testing.

公开(公告)号：US20190024608A1

公开(公告)日：2019-01-24

申请号：US15654554

申请日：2017-07-19

Applicant: The Boeing Company

Inventor： Steven F. Griffin

IPC: F02K1/34 ,  F02K1/30 ,  F15D1/00 ,  F15D1/08 ,  B64C21/08 ,  B64G1/26 ,  B64G1/40

Abstract: An acoustic cavity tailored synthetic jet employs a body having a cavity with a wall including a taper from a first extent to an aperture. The cavity is configured to produce a matched acoustic resonance. A drive system has a piston engaged to the cavity at the first extent. The drive system and piston are configured for oscillatory motion inducing a synthetic jet at the aperture.

公开(公告)号：US20170056913A1

公开(公告)日：2017-03-02

申请号：US15222913

申请日：2016-07-28

Applicant: The Boeing Company

Inventor： Steven F. Griffin

IPC: B05B17/06 ,  F04B35/04 ,  B64C21/08 ,  F04B39/00 ,  F04B39/12 ,  F04B51/00 ,  F04B37/00 ,  F04B49/06

CPC classification number: B05B17/0653 ,  B64C21/04 ,  B64C21/08 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/18 ,  F04B35/04 ,  F04B37/00 ,  F04B49/06 ,  F04B51/00 ,  F04F7/00 ,  F15D1/0095 ,  Y02T50/166

Abstract: An active flow control drag-induced damping reduction apparatus. The apparatus includes a variable frequency signal power supply; a jet generator defining an internal cavity and having pump member, and coupled to the variable frequency signal power supply to receive a control signal; a feedback sensor coupled to the pump member to generate a feedback signal measuring the reciprocating motion of the pump member; a detection circuit that receives the feedback signal and measures a difference compared to the variable frequency generator; and an adjustment circuit that receives the measured difference and tunes the variable frequency signal of the variable frequency signal power supply to maintain the jet generator at an optimum flow.

Abstract translation: 一种主动流量控制拖曳减振装置。 该装置包括可变频率信号电源; 限定内腔并具有泵构件的射流发生器，并且耦合到所述可变频率信号电源以接收控制信号; 耦合到所述泵构件以产生测量所述泵构件的往复运动的反馈信号的反馈传感器; 检测电路，其接收所述反馈信号并测量与所述可变频率发生器相比的差; 以及调节电路，其接收所测量的差并调谐所述可变频率信号电源的可变频率信号，以将所述喷射发生器保持在最佳流量。

公开(公告)号：US20160319895A1

公开(公告)日：2016-11-03

申请号：US14699283

申请日：2015-04-29

Applicant: The Boeing Company

Inventor： Steven F. Griffin ,  Guy D. Granger

IPC: F16F7/104 ,  B64C7/00 ,  F16F15/02

CPC classification number: F16F7/104 ,  B64D7/00 ,  F16F7/1011

Abstract: A vibration damping system employs a component having a directionally sensitive element thereon, mounted to an aircraft, which experiences dynamic excitation that induces bending deflection in the component that will reorient the directionally sensitive element. At least one tuned mass damper is mounted on the component in an orientation in which an internal mass of the tuned mass damper is moveable such that the tuned massed damper absorbs and attenuates at least a portion of the deflective motion, to thereby suppress bending deflection of the component in the particular axial direction and generally maintain the linearity of the directionally sensitive element.

Abstract translation: 振动阻尼系统采用安装在飞行器上的具有定向敏感元件的部件，该飞行器经历动态激励，其引起部件中的弯曲偏转，该方向敏感元件将重新定向定向敏感元件。 至少一个调谐质量阻尼器以调整质量阻尼器的内部质量可移动的方向安装在部件上，使得调谐的质量阻尼器吸收和衰减至少一部分偏转运动，从而抑制弯曲偏转 该组件在特定轴向方向上并且通常保持定向敏感元件的线性。

公开(公告)号：US20150097467A1

公开(公告)日：2015-04-09

申请号：US14569464

申请日：2014-12-12

Applicant: The Boeing Company

Inventor： Steven F. Griffin ,  Shawn Haar

IPC: H01L41/09 ,  H01L41/25 ,  H01L41/053

CPC classification number: H01L41/09 ,  B64C21/04 ,  B64C21/08 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/18 ,  H01L41/053 ,  H01L41/25 ,  H02N2/043 ,  Y02T50/166 ,  Y10T29/42

Abstract: A strain amplification structure has a frame with a hexagonal structure incorporating a plurality of rigid beams that are connected to opposing end beams by a plurality of flexible joints. A piezoceramic actuator assembly is connected to the opposing end beams having a collar including an opening. A shaft providing an output is connected to the plurality of rigid beams with flexible joints and passes through the opening in the collar for non-interfering motion orthogonal to the actuator assembly.

Abstract translation: 应变放大结构具有六边形结构的框架，其结合有多个刚性梁，其通过多个柔性接头连接到相对的端部梁。 压电陶瓷致动器组件连接到具有包括开口的套环的相对端梁。 提供输出的轴连接到具有柔性接头的多个刚性梁，并且穿过轴环中的开口，用于与致动器组件正交的非干涉运动。

公开(公告)号：US12234015B2

公开(公告)日：2025-02-25

申请号：US18338463

申请日：2023-06-21

Applicant: The Boeing Company

Inventor： Steven F. Griffin ,  Zackary L. Endsley

IPC: F16F1/36 ,  B64C9/02

Abstract: An apparatus and method for suppressing free play chatter of a control surface of an aircraft. The free play chatter suppression apparatus includes a containment vessel connected to a control surface of an aircraft. A lossy material is contained within the containment vessel. A body is positioned within the lossy material. The deceleration of the body by the lossy fluid is transmitted to the control surface to dampen vibrations of the control surface.

公开(公告)号：US20240410165A1

公开(公告)日：2024-12-12

申请号：US18810741

申请日：2024-08-21

Applicant: The Boeing Company

Inventor： Naval Kishore Agarwal ,  Steven F. Griffin

IPC: E04B1/84 ,  G10K11/172 ,  G10K11/178

Abstract: Methods, systems, and apparatuses are disclosed for reducing sound level, by providing enclosures comprising enclosure walls having integral tunable resonator cavities, and reducing sound levels within the enclosure in response to detected sound levels outside of the enclosure.