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公开(公告)号：US11416871B2
公开(公告)日：2022-08-16
申请号：US16552383
申请日：2019-08-27
申请人： C Kirk Nance
发明人： C Kirk Nance
摘要： An aircraft operation method of providing weight and center of gravity information is used to dispatch the aircraft. The aircraft has telescoping landing gear struts and strut seals that interfere with the free movement of the strut. An event trigger signaling departure is detected from aircraft operations at a loading area. Internal strut pressure is measured and recorded upon detection for a period of time as the aircraft moves away. The recorded pressure measurements are transmitted to a first off-aircraft computer, which determines the total weight and center of gravity of the aircraft and provides the information to an operator of the aircraft.
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公开(公告)号：US20210319455A1
公开(公告)日：2021-10-14
申请号：US15917149
申请日：2018-03-09
申请人： C Kirk Nance
发明人： C Kirk Nance
摘要： A method of establishing a justification basis to Aircraft Regulatory Authorities, to allow a regulated aircraft to operate at increased maximum weight limitations, through the statistical identification of non-recognized weight errors being allowed in today's aircraft weight determination methods, with the recovery and utilization of the non-recognized weight errors to increase weight limitations through a Regulatory Authority finding of an Equivalent Level of Safety. A system for use in measuring aircraft weight and center of gravity, providing a method to reveal non-recognized weight errors. Sensors are attached to the landing gear struts, so to periodically and randomly measure and monitor aircraft weight and center of gravity.
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公开(公告)号：US10082420B2
公开(公告)日：2018-09-25
申请号：US14910376
申请日：2014-08-04
申请人： LACSOP LIMITED
发明人： Gordon A. Morris
CPC分类号： G01G19/07 , G01G9/00 , G01G19/086
摘要： A method for determining the mass of a body is described. The method comprises the application and measurement of a first motive force to the body to move the body in a first state of motion. The acceleration of the body is also measured at this time. This methodology is repeated for a second state of motion. The measured motive forces and accelerations are then used to calculate the mass, and hence the weight of the body. An accelerometer may be employed to measure the accelerations. The methods may be adapted so as to correct for the angle θ of the ground across which the body is moved and or the tilt angle α of the accelerometer relative to the ground. The methods may employ a novel surface angle measuring device that does not require contact with the ground and which does not require the body to be stationary.
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公开(公告)号：US20180224321A1
公开(公告)日：2018-08-09
申请号：US15887859
申请日：2018-02-02
申请人： Philippe Henrion , Olivier Collet
发明人： Philippe Henrion , Olivier Collet
CPC分类号： G01G19/12 , B64C25/001 , B64C25/36 , B64D45/00 , G01B7/24 , G01G3/15 , G01G7/02 , G01G19/07 , G01M1/125
摘要： An aircraft undercarriage has an axle for carrying at least one wheel. The undercarriage further includes a magnetic measurement target and at least one magnetic movement sensor cooperating with the magnetic measurement target to measure bending of the axle. The magnetic measurement target has a body that extends inside the axle and includes a fastener end fastened to one end of the axle. The body also include a target surface that extends over an inside surface of the body. The magnetic movement sensor is positioned inside the axle to measure movement of the target surface.
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公开(公告)号：US20180209837A1
公开(公告)日：2018-07-26
申请号：US15415585
申请日：2017-01-25
申请人： THE BOEING COMPANY
发明人： Sina S. Golshany , Gnanulan Canagaratna , Matthew W. Orr , Andrew W. Fassmann , Daniel Wajerski
CPC分类号： G01G19/07 , B64F5/60 , G05D1/0055 , G06Q10/04 , G06Q10/06312 , G06Q10/083 , G06Q50/30 , G07C5/0841 , G08G5/0034 , G08G5/0039
摘要： In a particular implementation, a method includes generating an initial weight estimate associated with an aircraft based on a reference operational empty weight (OEW) and at least one of a latitude or an altitude of the aircraft at a first location. The reference OEW is predetermined at a second location that is distinct from the first location. The method includes determining an additional load capability of the aircraft based on a difference between the initial weight estimate and the reference OEW. The method further includes generating an output that indicates the additional load capability.
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6.发明申请公开(公告)号：US20180188102A1
公开(公告)日：2018-07-05
申请号：US15388440
申请日：2016-12-22
申请人： C KIRK NANCE
发明人： C KIRK NANCE
IPC分类号： G01G19/07
CPC分类号： G01G19/07
摘要： A method for validating or invalidating the computed weight of an aircraft, where the computed weight of the aircraft is determined by compiling various weight assumptions added to a known empty weight of the aircraft. The method measures the aircraft center of gravity, determines the percentage of computed weight supported by the combined main landing gear struts, and using a database such as a look-up table to validate if the percentage of computed weight is determined within a reasonable range to the measured load on the combined main landing gear struts. Sensors are attached to the landing gear struts, so to measure and monitor aircraft loads and center of gravity without measuring the aircraft weight.
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7.发明授权公开(公告)号：US09550561B1
公开(公告)日：2017-01-24
申请号：US14491201
申请日：2014-09-19
发明人： Brian C. Beckman , Brandon William Porter , Gur Kimchi , Daniel Buchmueller , Jeffrey P. Bezos , Frederik Schaffalitzky , Amir Navot
摘要： This disclosure describes a system and method for determining the center of gravity of a payload engaged by an automated aerial vehicle and adjusting components of the automated aerial vehicle and/or the engagement location with the payload so that the center of gravity of the payload is within a defined position with respect to the center of gravity of the automated aerial vehicle. Adjusting the center of gravity to be within a defined position improves the efficiency, maneuverability and safety of the automated aerial vehicle. In some implementations, the stability of the payload may also be determined to ensure that the center of gravity does not change or shift during transport due to movement of an item of the payload.
摘要翻译： 本公开描述了一种用于确定由自动航空器接合的有效载荷的重心的系统和方法，并且调整自动航空器的组件和/或与有效载荷的接合位置，使得有效载荷的重心在 相对于自动航空器的重心定义的位置。 将重心调整在一个确定的位置提高了自动航空器的效率，机动性和安全性。 在一些实施方式中，还可以确定有效载荷的稳定性，以确保由于有效载荷物品的移动而在运输过程中重心不改变或移动。
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公开(公告)号：US20160349103A1
公开(公告)日：2016-12-01
申请号：US15111776
申请日：2014-01-15
申请人： Chet R. CREACY , Anthony Samy JAYAPAL , Matthew COLEGROVE , Hao CUI , John Martin EVANS , David Brook BANNING , Don MCHODGKINS , Rammohan THANIKACH-ALAM , Carrie RANGEEN , Laura C. TRUITT , David Woodman GOULD , David PEREZ , Mark J. SCRIFFINY , Michelle Lynn Hill DAUM , HEWLETT-PACKARD DEVELOPMENT COMPANY, L.P.
发明人： Chet R. Creacy , Antony Samy Jayapal , Matthew Colegrove , Hao CUI , John Martin Evans , David Brook Banning , Don McHodgkins , Rammohan Thanikachalam , Carrie Rangeen , Laura C. Truitt , David Woodman Gould , David Perez , Mark J. Scriffiny , Michelle Lynn Hill Daum
IPC分类号： G01G19/07
CPC分类号： G01G19/07
摘要： Managing a payload distribution for a flight includes specifying a flight with a payload distribution to be managed, obtaining, based on a flight timed event, historical payload data to determine a maximum takeoff weight limit for the flight, retrieving, based on the flight timed event, all planned payload values to determine an estimated takeoff weight for the flight, and obtaining, based on the flight timed event, actual payload values to manage the distribution of the payload for the flight.
摘要翻译： 管理航班的有效载荷分配包括指定具有要管理的有效载荷分布的飞行，基于飞行定时事件获得历史有效载荷数据，以确定飞行的最大起飞重量限制，基于飞行定时事件检索 ，所有计划的有效载荷值以确定飞行的估计起飞重量，并且基于飞行时间事件获得实际有效载荷值以管理飞行的有效载荷的分布。
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9.发明授权Inclination detection device for aircraft, and method for loading and unloading cargo using same 有权飞机倾角检测装置及使用该装置的货物装卸货物的方法公开(公告)号：US09205930B2
公开(公告)日：2015-12-08
申请号：US14122762
申请日：2011-06-01
申请人： Hiroki Yanagawa
发明人： Hiroki Yanagawa
摘要： An inclination detection device 11 for an aircraft includes a gravity sensor 13 that detects an inclination angle in a pitch direction at a parking time of a fuselage 1, an alarm device 16, and a control unit 17 that causes the device 16 to issue an alarm when the inclination angle detected by the sensor 13 approaches allowable limit inclination angles F4 and R4 in a forward inclination direction and a backward inclination direction of the fuselage 1. The control unit 17 has gravity center management information peculiar to the fuselage 1 inputted therein by a USB memory 20 or the like, and corrects a movable range in the forward and—backward inclination directions until the inclination angle reaches the angles F4 and R4 based on the gravity center management inclination information, before a loading and unloading operation of cargo into and from the fuselage 1.
摘要翻译： 用于飞行器的倾斜检测装置11包括重力传感器13，其在机身1的停车时检测俯仰方向的倾斜角度，报警装置16以及使装置16发出报警的控制单元17 当传感器13检测到的倾斜角度接近机身1的向前倾斜方向和后倾方向上的容许极限倾斜角度F4和R4时。控制单元17具有通过输入的机身1特有的重心管理信息 USB存储器20等，并且在货物进出货物的装载和卸载操作之前，基于重力中心管理倾斜信息来校正前后倾斜方向上的可移动范围，直到倾斜角度达到角度F4和R4 机身1。
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10.发明授权公开(公告)号：US07683274B2
公开(公告)日：2010-03-23
申请号：US11440044
申请日：2006-05-25
申请人： Stéphane Dellac , Emmanuel Lafaye
发明人： Stéphane Dellac , Emmanuel Lafaye
CPC分类号： G01L5/0004
摘要： The invention relates to a force-measurement cell for insertion in a bore of a pin, the cell comprising a bushing: having a generally cylindrical tubular wall with an outside surface adapted to extend against an inside surface of the bore in the pin; and within which there extends at least one sensor suitable for measuring at least one parameter representative of the stresses to which the wall is subjected. The invention also relates to a pin provided with such a force-measurement cell.
摘要翻译： 本发明涉及一种用于插入销的孔中的力测量单元，该单元包括衬套：具有大致圆柱形的管状壁，其外表面适于抵靠销中的孔的内表面延伸; 并且其中延伸有至少一个适于测量表示壁受到的应力的至少一个参数的传感器。 本发明还涉及一种设置有这种力测量单元的销。
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