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公开(公告)号：US08567716B2
公开(公告)日：2013-10-29
申请号：US12809885
申请日：2008-12-19
Applicant: R. Kyle Schmidt , Michael Sinclair , Edward Chun Kei Chan
Inventor： R. Kyle Schmidt , Michael Sinclair , Edward Chun Kei Chan
IPC: B64C25/10
Abstract: An uplock assembly for retaining and releasing landing gear systems, said uplock assembly comprising: a thermal actuator comprising: a chamber configured to contain expansible material therein; a heating mechanism coupled to said chamber for heating said expansible material and causing volumetric expansion thereof; a piston slidably coupled to said chamber and adapted to extend in response to said volumetric expansion; and an uplock release mechanism releasably engaged by said piston when extended such that said engaged uplock release mechanism causes the release of said landing gear.
Abstract translation: 一种用于保持和释放起落架系统的上锁组件，所述上锁组件包括：热致动器，其包括：被配置为在其中容纳可膨胀材料的腔室; 耦合到所述室的加热机构，用于加热所述可膨胀材料并引起体积膨胀; 活塞可滑动地联接到所述腔室并且适于响应于所述体积膨胀而延伸; 以及当所述活塞伸长时可释放地与所述活塞接合的上锁释放机构，使得所述接合的上锁释放机构引起所述起落架的释放。
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公开(公告)号：US20110056197A1
公开(公告)日：2011-03-10
申请号：US12809885
申请日：2008-12-19
Applicant: R. Kyle Schmidt , Michael Sinclair , Edward Chun Kei Chan
Inventor： R. Kyle Schmidt , Michael Sinclair , Edward Chun Kei Chan
Abstract: An uplock assembly for retaining and releasing landing gear systems, said uplock assembly comprising: a thermal actuator comprising: a chamber configured to contain expansible material therein; a heating mechanism coupled to said chamber for heating said expansible material and causing volumetric expansion thereof; a piston slidably coupled to said chamber and adapted to extend in response to said volumetric expansion; and an uplock release mechanism releasably engaged by said piston when extended such that said engaged uplock release mechanism causes the release of said landing gear.
Abstract translation: 一种用于保持和释放起落架系统的上锁组件，所述上锁组件包括：热致动器，其包括：被配置为在其中容纳可膨胀材料的腔室; 耦合到所述室的加热机构，用于加热所述可膨胀材料并引起体积膨胀; 活塞可滑动地联接到所述腔室并且适于响应于所述体积膨胀而延伸; 以及当所述活塞伸长时可释放地与所述活塞接合的上锁释放机构，使得所述接合的上锁释放机构引起所述起落架的释放。
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3.发明授权System and method for determining aircraft hard landing events from inertial and aircraft reference frame data 有权用于从惯性和飞机参考帧数据确定飞机硬着陆事件的系统和方法公开(公告)号：US07589645B2
公开(公告)日：2009-09-15
申请号：US11423529
申请日：2006-06-12
Applicant: R. Kyle Schmidt
Inventor： R. Kyle Schmidt
IPC: G08B21/00
CPC classification number: G05D1/0066 , B64C25/001 , B64D2045/008
Abstract: This invention allows for the precise determination of an aircraft's landing conditions and whether an aircraft has experienced a hard landing that exceeds the allowable design loads of the aircraft's landing gear. The system comprises a computer that measures signals from an inertial measurement unit (IMU) at high data rates (e.g. 100 Hz) and also records signals from the aircraft avionics data bus. The computer compares the output from the inertial measurement unit's accelerometers against at least one predetermined threshold parameter to determine whether the aircraft's three dimensional landing deceleration is safely within the design allowances or other regulatory limitations, or whether the landing event needs further investigation.
Abstract translation: 本发明允许精确地确定飞机的着陆条件以及飞机是否经历超过飞机起落架的允许设计载荷的硬着陆。 该系统包括以高数据速率（例如100Hz）测量来自惯性测量单元（IMU）的信号并且还记录来自飞行器航空电子数据总线的信号的计算机。 计算机将惯性测量单元的加速度计的输出与至少一个预定的阈值参数进行比较，以确定飞机的三维着陆减速度是否安全地在设计允许范围内或其他监管限制之内，还是着陆事件是否需要进一步调查。
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公开(公告)号：US20120053784A1
公开(公告)日：2012-03-01
申请号：US13271468
申请日：2011-10-12
Applicant: R. Kyle Schmidt , Steven A. Gedeon
Inventor： R. Kyle Schmidt , Steven A. Gedeon
CPC classification number: G07C5/0808 , B64D2045/008 , B64F5/60 , G01G19/07
Abstract: The invention relates to a new method and system for health monitoring of aircraft landing gear. The system includes sensors that are attached to the landing gear structure and equipment (e.g., one or more of brakes, tires, hydraulics, electrical systems and switches) and analyzed to report and alert personnel such as pilots, maintenance personnel, airline operators, ground crew and regulatory authorities of the health of the landing gear and the potential need for service, maintenance or replacement. The system monitors and reports critical health issues as real-time information which can be analyzed in conjunction with an extensive database of information and used to alert pilots or other relevant personnel to the condition of the landing gear and actions that may be required as a result.
Abstract translation: 本发明涉及一种用于飞机起落架健康监测的新方法和系统。 该系统包括附接到起落架结构和设备（例如，制动器，轮胎，液压装置，电气系统和开关中的一个或多个）的传感器，并且被分析以报告和警告诸如飞行员，维护人员，航空公司操作员，地面 船员和监管机构对起落架的健康以及潜在的服务，维护或更换需求。 该系统监测和报告关键的健康问题作为实时信息，可以结合广泛的信息数据库进行分析，并用于向飞行员或其他相关人员提供起落架状况和可能需要的行动。 。
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公开(公告)号：US20100239361A1
公开(公告)日：2010-09-23
申请号：US12793128
申请日：2010-06-03
Applicant: R. KYLE SCHMIDT
Inventor： R. KYLE SCHMIDT
IPC: F16C11/04
CPC classification number: B64C25/18 , Y10T403/255
Abstract: This invention provides a pin assembly that is self-lubricating and includes a pin, a pin insert that is received within the pin and a quantity of lubricating agent. The present invention also provides an insert for a pin that may be used in a pin joint that contains an automatic lubrication dispensing mechanism.
Abstract translation: 本发明提供一种销组件，该销组件是自润滑的，并且包括销，销插入件，其被容纳在销内和一定量的润滑剂。 本发明还提供一种用于销钉的插入件，其可以用在包含自动润滑分配机构的销接头中。
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Patent Agency Ranking
6.发明申请SYSTEM AND METHOD FOR DETERMINING AIRCRAFT HARD LANDING EVENTS FROM INERTIAL AND AIRCRAFT REFERENCE FRAME DATA 有权用于从惯性和航空器参考框架数据确定飞机硬起落事件的系统和方法公开(公告)号：US20100114411A1
公开(公告)日：2010-05-06
申请号：US12539162
申请日：2009-08-11
Applicant: R. KYLE SCHMIDT
Inventor： R. KYLE SCHMIDT
CPC classification number: G05D1/0066 , B64C25/001 , B64D2045/008
Abstract: This invention allows for the precise determination of an aircraft's landing conditions and whether an aircraft has experienced a hard landing that exceeds the allowable design loads of the aircraft's landing gear. The system comprises a computer that measures signals from an inertial measurement unit (IMU) at high data rates (e.g. 100 Hz) and also records signals from the aircraft avionics data bus. The computer compares the output from the inertial measurement unit's accelerometers against at least one predetermined threshold parameter to determine whether the aircraft's three dimensional landing deceleration is safely within the design allowances or other regulatory limitations, or whether the landing event needs further investigation.
Abstract translation: 本发明允许精确地确定飞机的着陆条件以及飞机是否经历超过飞机起落架的允许设计载荷的硬着陆。 该系统包括以高数据速率（例如100Hz）测量来自惯性测量单元（IMU）的信号并且还记录来自飞行器航空电子数据总线的信号的计算机。 计算机将惯性测量单元的加速度计的输出与至少一个预定的阈值参数进行比较，以确定飞机的三维着陆减速度是否安全地在设计允许范围内或其他监管限制之内，还是着陆事件是否需要进一步调查。
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7.发明申请METHOD AND SYSTEM FOR DETERMINING FRICTION COEFFICIENT μ FOR AN AIRCRAFT LANDING EVENT 有权用于确定飞机登陆事件的摩擦系数μ的方法和系统公开(公告)号：US20140107990A1
公开(公告)日：2014-04-17
申请号：US14005500
申请日：2012-03-16
Applicant: Laura Collett , R. Kyle Schmidt , Pia Sartor
Inventor： Laura Collett , R. Kyle Schmidt , Pia Sartor
IPC: G06F17/50
CPC classification number: G06F17/5009 , B64C25/00 , B64D2045/008 , G05B17/02 , G05B23/0243
Abstract: Method and system of determining ground-to-tyre friction coefficient for an aircraft landing event. The method uses an aircraft computational model to repeatedly model the landing event, varying one or more initial conditions of the aircraft model until a best match between a modelled value and a provided value of aircraft vertical acceleration is determined. The method uses initial conditions associated with the best match of modelled and provided vertical acceleration values and a strain value from a sensor on the aircraft landing gear, with the ground-to-tyre friction coefficient is a variable. The method models the landing gear to generate a modelled strain value and compares this with the measured strain value, and repeats the landing gear modelling step with a different value for the ground-to-tyre friction coefficient until a best match between the modelled strain value and the measured strain value is determined and outputting the respective friction coefficient value.
Abstract translation: 确定飞机着陆事件的地面与轮胎摩擦系数的方法和系统。 该方法使用飞行器计算模型来重复模拟着陆事件，改变飞行器模型的一个或多个初始条件，直到确定了建模值和所提供的飞机垂直加速度值之间的最佳匹配。 该方法使用与建模和提供的垂直加速度值的最佳匹配的初始条件和来自飞机起落架上的传感器的应变值，其中地对轮胎摩擦系数是变量。 该方法对起落架进行建模以产生建模应变值，并将其与测量的应变值进行比较，并重复起落架建模步骤，其具有不同的地对轮胎摩擦系数值，直到建模的应变值之间的最佳匹配 并且确定测量的应变值并输出相应的摩擦系数值。
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公开(公告)号：US07845220B2
公开(公告)日：2010-12-07
申请号：US11844900
申请日：2007-08-24
Applicant: R. Kyle Schmidt , Simon Hou
Inventor： R. Kyle Schmidt , Simon Hou
CPC classification number: F17C13/04 , F16F9/3264 , F16F9/3292 , F16F9/43 , F16F2230/0047 , F16F2230/06 , F16F2230/08 , F16F2230/24 , F17C2250/043 , F17C2270/0189 , Y10T29/49716
Abstract: The present invention is a device that allows the pressure inside an aircraft landing gear shock strut to be measured. A charging valve is modified by integrating a small pressure sensing device into the stem of the part such that the active diaphragm is subjected to the pressure within the charged vessel. The wires from the pressure sensing device are connected to a receptacle or connector in the bore of the stem such that a corresponding electrical receptacle may be mated for the purposes of making a measurement. The internal receptacle is designed such that the flow of air or oil is not excessively impeded and normal servicing tools do not interfere with the receptacle.
Abstract translation: 本发明是允许测量飞行器起落架冲击支柱内的压力的装置。 通过将小的压力感测装置集成到部件的杆中来改变充气阀，使得活动隔膜受到带电容器内的压力。 来自压力感测装置的电线连接到杆的孔中的插座或连接器，使得相应的电插座可以配合用于进行测量。 内部容器被设计成使得空气或油的流动不被过大的阻碍，并且正常的维修工具不会妨碍容器。
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9.发明申请公开(公告)号：US20090293624A1
公开(公告)日：2009-12-03
申请号：US11844900
申请日：2007-08-24
Applicant: R. Kyle SCHMIDT , Simon Hou
Inventor： R. Kyle SCHMIDT , Simon Hou
CPC classification number: F17C13/04 , F16F9/3264 , F16F9/3292 , F16F9/43 , F16F2230/0047 , F16F2230/06 , F16F2230/08 , F16F2230/24 , F17C2250/043 , F17C2270/0189 , Y10T29/49716
Abstract: The present invention is a device that allows the pressure inside an aircraft landing gear shock strut to be measured. A charging valve is modified by integrating a small pressure sensing device into the stem of the part such that the active diaphragm is subjected to the pressure within the charged vessel. The wires from the pressure sensing device are connected to a receptacle or connector in the bore of the stem such that a corresponding electrical receptacle may be mated for the purposes of making a measurement. The internal receptacle is designed such that the flow of air or oil is not excessively impeded and normal servicing tools do not interfere with the receptacle.
Abstract translation: 本发明是允许测量飞行器起落架冲击支柱内的压力的装置。 通过将小的压力感测装置集成到部件的杆中来改变充气阀，使得活动隔膜受到带电容器内的压力。 来自压力感测装置的电线连接到杆的孔中的插座或连接器，使得相应的电插座可以配合用于进行测量。 内部容器被设计成使得空气或油的流动不被过大的阻碍，并且正常的维修工具不会妨碍容器。
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公开(公告)号：US20080217107A1
公开(公告)日：2008-09-11
申请号：US12024631
申请日：2008-02-01
Applicant: R. Kyle SCHMIDT
Inventor： R. Kyle SCHMIDT
CPC classification number: B64C25/18 , Y10T403/255
Abstract: This invention provides a pin assembly that is self-lubricating and includes a pin, a pin insert that is received within the pin and a quantity of lubricating agent. The present invention also provides an insert for a pin that may be used in a pin joint that contains an automatic lubrication dispensing mechanism.
Abstract translation: 本发明提供一种销组件，该销组件是自润滑的，并且包括销，销插入件，其被容纳在销内和一定量的润滑剂。 本发明还提供一种用于销钉的插入件，其可以用在包含自动润滑分配机构的销接头中。
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