[go: up one dir, main page]

CN101808902A - 载荷指示器 - Google Patents

载荷指示器 Download PDF

Info

Publication number
CN101808902A
CN101808902A CN200880107790A CN200880107790A CN101808902A CN 101808902 A CN101808902 A CN 101808902A CN 200880107790 A CN200880107790 A CN 200880107790A CN 200880107790 A CN200880107790 A CN 200880107790A CN 101808902 A CN101808902 A CN 101808902A
Authority
CN
China
Prior art keywords
load
indicator
carrying member
load carrying
parts
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN200880107790A
Other languages
English (en)
Other versions
CN101808902B (zh
Inventor
马提恩·因斯
史蒂夫·史密斯
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Landing Systems UK Ltd
Original Assignee
Messier Dowty Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Messier Dowty Ltd filed Critical Messier Dowty Ltd
Publication of CN101808902A publication Critical patent/CN101808902A/zh
Application granted granted Critical
Publication of CN101808902B publication Critical patent/CN101808902B/zh
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C23/00—Bearings for exclusively rotary movement adjustable for aligning or positioning
    • F16C23/02—Sliding-contact bearings
    • F16C23/04—Sliding-contact bearings self-adjusting
    • F16C23/043—Sliding-contact bearings self-adjusting with spherical surfaces, e.g. spherical plain bearings
    • F16C23/045—Sliding-contact bearings self-adjusting with spherical surfaces, e.g. spherical plain bearings for radial load mainly, e.g. radial spherical plain bearings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C11/00—Pivots; Pivotal connections
    • F16C11/04—Pivotal connections
    • F16C11/045—Pivotal connections with at least a pair of arms pivoting relatively to at least one other arm, all arms being mounted on one pin
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/12—Sliding-contact bearings for exclusively rotary movement characterised by features not related to the direction of the load
    • F16C17/24—Sliding-contact bearings for exclusively rotary movement characterised by features not related to the direction of the load with devices affected by abnormal or undesired positions, e.g. for preventing overheating, for safety
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C23/00—Bearings for exclusively rotary movement adjustable for aligning or positioning
    • F16C23/02—Sliding-contact bearings
    • F16C23/04—Sliding-contact bearings self-adjusting
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
    • G01L5/0061—Force sensors associated with industrial machines or actuators
    • G01L5/0071—Specific indicating arrangements, e.g. of overload
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N19/00—Investigating materials by mechanical methods
    • G01N19/08—Detecting presence of flaws or irregularities
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N21/00—Investigating or analysing materials by the use of optical means, i.e. using sub-millimetre waves, infrared, visible or ultraviolet light
    • G01N21/84—Systems specially adapted for particular applications
    • G01N21/88—Investigating the presence of flaws or contamination
    • G01N21/8803—Visual inspection
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P15/00—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration
    • G01P15/02—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses
    • G01P15/04—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses for indicating maximum value
    • G01P15/06—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses for indicating maximum value using members subjected to a permanent deformation
    • G—PHYSICS
    • G08—SIGNALLING
    • G08B—SIGNALLING OR CALLING SYSTEMS; ORDER TELEGRAPHS; ALARM SYSTEMS
    • G08B23/00—Alarms responsive to unspecified undesired or abnormal conditions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D2045/008—Devices for detecting or indicating hard landing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2326/00—Articles relating to transporting
    • F16C2326/43—Aeroplanes; Helicopters

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Health & Medical Sciences (AREA)
  • Pathology (AREA)
  • Immunology (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Biochemistry (AREA)
  • General Health & Medical Sciences (AREA)
  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Force Measurement Appropriate To Specific Purposes (AREA)
  • Thermally Insulated Containers For Foods (AREA)
  • Glass Compositions (AREA)
  • Water Treatment By Sorption (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
  • Vibration Dampers (AREA)
  • Measurement Of Force In General (AREA)

Abstract

本发明的载荷指示器包括由彼此连接的第一和第二载荷承载构件(23，22)构成的载荷承载组件，该载荷承载组件承载施加到第一构件(23)上的横向载荷，第一载荷承载构件(23)与第二载荷承载构件(22)共同限定腔室(25)，其中第一载荷承载构件在超过一指示器载荷时是脆弱的，并且该腔室(25)包含指示器液体，一旦第一载荷承载构件由所述载荷导致破裂则该指示器液体从该腔室漏出。载荷承载构件(23，22)包括同心布置的圆柱形构件，并且外部构件(23)具有厚度减小的部分，使得该部分脆弱，并限定腔室(25)。该腔室(25)包括在第二载荷承载构件(22)内的内部容积。该载荷指示器可以构造成为连接两个部件的载荷承载销。

Description

载荷指示器
技术领域
本发明涉及一种载荷指示器。该指示器的应用包括但不限于：指示飞机的硬着陆；以及指示施加到飞机上的牵引力过度。本发明还涉及用于检测飞机的方法和检测飞机牵引设备的方法。
背景技术
无论何种原因，飞机停飞(AOG)的成本是很大的，并且航空公司希望制造商可以通过如下方式尽可能减小停飞的冲击：即进行计划的维修和/或故障排除，用于进一步的飞行，直到达到下一次的预定维修时间。然而，有些事件是计划无法帮助的。其中之一就是“硬着陆”。
无论何种原因，超过认证的着陆参数时会发生“硬着陆”。这种情况通常会由飞机驾驶员报告并随后通过检测机身结构和从数字飞行数据记录仪(DFDR)获取的信息而确认。问题在于，需要花费时间来分析数据，以确定该事件是否真是“硬着陆”。这种分析通常需要3周才能得出结论，而航空公司经常不能容忍这个时间。
US4392623描述了一种适于在作用在不同方向的不同的过载下而失效的熔断连接。其目的是保护油箱(主机翼结构)不会由于起落架在竖直或水平方向上的过载而导致破裂。
US5927646描述了一种包括用于指示冲击载荷的大小的装置的吸能起落架/尾撬。冲击载荷导致设备的塑性变形，并且细长杆伸出参考平面从而提供视觉上的指示，指示冲击载荷的大小已经到达阀值。
发明内容
本发明涉及一种载荷指示器，该载荷指示器包括由彼此连接的第一和第二载荷承载构件构成的载荷承载组件，该载荷承载组件承载施加到第一构件上的载荷，其中，第一载荷承载构件与第二载荷承载构件一起限定一腔室，使得第一承载构件在超过一指示器载荷时是脆弱的，并且所述腔室包含指示器液体，一旦第一载荷承载构件由所述载荷导致破裂则该指示器液体从所述腔室漏出。
两个部件可以包括飞机起落架的部件，该起落架的部件包括侧撑杆或阻力杆或铰接接头或牵引连接件的部件。
附图说明
现在通过参照附图以举例的方式来描述本发明，其中：
图1示出了摇臂式起落架；
图2示出了图1中起落架的铰接连杆；
图3是图2的铰接连杆的关节的截面图；
图4是示出了本发明的其他可能应用的另一起落架；和
图5示出了飞机牵引设备。
具体实施方式
图1示出了飞机的包括减震器支柱1的起落架，该减震器支柱1具有可伸缩的上部2和下部3，该上部2与机身连接，该下部3通过附连到枢转式转向架梁5上而承载有一个或多个轴4。铰接的柱组件6连接在减震器的上部和机身之间，并且用于使起落架稳定，该柱组件6可以在“下部”位置反抗载荷，还能够折叠以允许起落架可以收回。
铰接连杆7、8连接在转向架梁5的前部和减震器的上部2之间，以抵抗产生张力，并由此在着陆早期形成用于转向架梁的支点。下部连杆8附连在转向架梁5的前部和上部连杆7之间，并且上部连杆7附连于下部连杆8和减震器的上部2之间。调螺距器9安装在减震器的上部2和上部铰接连杆7上的靠近附连到下部铰接连杆8的位置的点10之间，并用作液压弹簧/减震器，以将铰接连杆保持在适当的位置。最终结果是形成一连杆机构，该连杆机构抵抗下部连杆8的张力，但是当施加压缩载荷时允许该张力升高。
图3中更加详细地示出了通过枢轴关节13连接的上部连杆7和下部连杆8。上部连杆7的分叉端部具有一对凸耳11，在该对凸耳11之间在下部连杆8的端点收纳有单个凸耳12。所有这三个凸耳具有装有轴承的对准的孔，以收纳枢轴销13。在下部连杆的凸耳和销之间的是球面轴承，该球面轴承是劈开的从而使得该球面轴承可以组装在该凸耳内的球形腔室15中。球面轴承的内表面16是圆柱形的以接收销。在外部凸耳内的轴承包括成对的圆柱形衬套17。枢轴销在一端具有头部18，在另一端具有螺纹部19，并且该枢轴销穿过对准的轴承插入直到头部18在一端抵靠外部凸耳11。然后锁紧螺母20拧紧到销的从第二外部凸耳11伸出的螺纹部上。枢轴销的头部18具有径向延伸的凸缘19，借助该凸缘19，头部18通过销钉21连接到相邻的凸耳上，从而防止销旋转。
枢轴销13包括内部圆柱形构件22和脆弱轴套23，该构件在一端携带头部18，在另一端携带螺纹部19，该轴套23在头部和螺纹部之间配合在内部构件22上。轴套23的每个端部紧密配合在内部构件上，并且形成台部31，轴套的台部之间的部分24具有减小的厚度，从而该部分24的内表面与内部构件22隔开从而形成腔室25。厚度减小的中央部分与中央凸耳12和球面轴承14对准，从而该中央部分暴露在施加在上部连杆和下部连杆之间的载荷下。中央部分24的外端形成有附加的内部通道26，从而进一步降低轴套的厚度，使得脆弱轴套23在载荷的作用下更可能在这些点发生破裂。
内部构件22形成有盲孔27，该盲孔27通过径向通道28与内部构件和外部脆弱轴套之间的腔室25连接。盲孔27、腔室25和连接通道28的整体体积充有红色染料，盲孔的开口端通过塞子29密封。在内部构件22和外部轴套23之间在两端都设置环形密封件30，以防止红色染料从内部构件22和外部轴套23之间纵向漏出。
在飞机着陆时，枢轴销13承受着陆作用力。具体地，铰接连杆经受箭头100指示的拉伸载荷(指示施加在凸耳11上的向上的力)和施加到凸耳12上的向下的力101。这导致向下的力102通过凸耳12和轴承14施加到枢轴销的中央部分24上，向上的力103通过凸耳11施加到枢轴销的外端上。
当力102超出一定水平时，枢轴销13在沟槽26的区域中发生破裂。这导致红色染料从腔室25中释放出来，并在两个连杆的端点之间从铰接连杆流出。
因此，枢轴销用作剪切销并且提供简单、快速并且准确的检测报告的“硬着陆”情况的手段。此外，由于即使当枢轴销13已经破裂时，该枢轴销仍然可以继续支撑着陆载荷，因此对硬着陆的指示并不会损害飞机的安全或操作。检测也不需要专用工具。应该可以在常规的飞机周转时间(通常为4小时)内进行检测。
在机组人员报告事故之后通过简单地检测关节可以迅速地识别超出了限制载荷。该检测可以在飞机正常停在地面上时进行，不需要附加的或者特殊的设备。关节的任何自由度的缺乏都可以指示枢轴销的变形，因此隔离主起落架MLG，以进行进一步检测或排除。
剪切销在上面的示例中示出为铰接连杆中的枢轴销，但是可以在起落架的其他部分设置类似的剪切销，例如如图4和5所示，剪切销可以用作侧撑枢轴销40或阻力杆枢轴销(未示出)，以指示在主枢轴销在设计的载荷上限处失效之前是否超出载荷下限。此外，不必将销限制用作枢轴构件。例如，销还可以用作隔膜销60，来将减震器的内部保持在外部壳体内，以与内部压力成比例地抵抗载荷，并在预定的载荷极限剪断。
替代定位在起落架中，剪切销可以定位在飞机上的其他承受着陆力的部分，如尾撬。
此外，该剪切销组件可以用在飞机的牵引设备中，如图5中的70所示。在这种情况下，该剪切销承受飞机牵引力，并且可以被检测来确定牵引力是否已经超出预定水平，该预定水平可以是低于较高失效水平的较低警告水平，在该较高失效水平，其他剪切销设计成失效并释放载荷。
尽管已经示例描述了剪切销用在有翼飞机上，同样该剪切销还可以用在其他飞机上，如直升机。
在所示的实例中，腔室25充有红色染料。在替代实施方式中，红色染料可以替换为其他液体指示物、替换为其他可流动的指示物，如粉末或可膨胀泡沫。

Claims (11)

1.一种载荷指示器，所述载荷指示器包括由彼此连接在一起的第一载荷承载构件和第二载荷承载构件(23，22)构成的载荷承载组件，所述载荷承载组件承受施加到所述第一载荷承载构件上的横向载荷，所述载荷指示器的特征在于，所述第一载荷承载构件(23)与所述第二载荷承载构件(22)共同限定腔室(25)，其中所述第一载荷承载构件在超过一指示器载荷时是脆弱的，并且所述腔室(25)包含指示器液体，一旦所述第一载荷承载构件由所述指示器载荷导致破裂，则所述指示器液体从所述腔室漏出。
2.如权利要求1所述的载荷指示器，其中，所述第一载荷承载构件(23)是管状的，并且将所述第二载荷承载构件(22)接收在所述第一载荷承载构件中，其中所述第一载荷承载构件和所述第二载荷承载构件在相对的端部经由台部(31)接合，并在中央区域(24)分隔开，以形成所述腔室(25)。
3.如权利要求2所述的载荷指示器，其中，所述第一载荷承载构件(23)的一部分具有减小的厚度，以使得所述部分脆弱，并且限定所述腔室(25)。
4.如权利要求3所述的载荷指示器，其中，所述第一载荷承载构件和所述第二载荷承载构件(23，22)包括同心布置的圆柱形构件。
5.如权利要求2至4中任一项所述的载荷指示器，其中，所述腔室(25)包括在所述第二载荷承载构件(22)内的内部容积(27)。
6.如前述权利要求中任一项所述的载荷指示器，其中，所述载荷指示器构造成载荷承载销，以连接两个部件(7，8)并且承受施加在所述两个部件之间的载荷。
7.一种组件，所述组件由两个部件和如权利要求2至5中任一项所述的载荷指示器组成，所述载荷指示器构造成载荷承载销，所述销接合在所述两个部件中的一个部件(7)上的与所述台部(31)对准的一对凸耳(11)和在所述两个部件中的另一部件上的位于所述一对凸耳(11)之间的凸耳(12)，以便当所述两个部件被加载在压缩或张紧状态时，所述销承载横向载荷。
8.如权利要求7所述的组件，其中，所述两个部件(7，8)包括飞机起落架的部件。
9.如权利要求8所述的组件，其中，所述两个部件(7，8)包括侧撑杆或铰接连杆或牵引连接件的构件。
10.一种利用如权利要求1至6中任一项所述的载荷指示器检测飞机的硬着陆的方法。
11.一种利用如权利要求1至6中任一项所述的载荷指示器检测在牵引飞机过程中的过载力的方法。
CN2008801077906A 2007-09-19 2008-09-19 载荷指示器 Active CN101808902B (zh)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GB0718296.7 2007-09-19
GB0718296A GB2452938B (en) 2007-09-19 2007-09-19 Load indicator
PCT/GB2008/003187 WO2009037475A1 (en) 2007-09-19 2008-09-19 Load indicator

Publications (2)

Publication Number Publication Date
CN101808902A true CN101808902A (zh) 2010-08-18
CN101808902B CN101808902B (zh) 2013-04-24

Family

ID=38670176

Family Applications (1)

Application Number Title Priority Date Filing Date
CN2008801077906A Active CN101808902B (zh) 2007-09-19 2008-09-19 载荷指示器

Country Status (11)

Country Link
US (1) US8539843B2 (zh)
EP (1) EP2190744B1 (zh)
JP (1) JP4873391B2 (zh)
CN (1) CN101808902B (zh)
AT (1) ATE554003T1 (zh)
BR (1) BRPI0816415A2 (zh)
CA (1) CA2699705C (zh)
ES (1) ES2386570T3 (zh)
GB (1) GB2452938B (zh)
RU (1) RU2478921C2 (zh)
WO (1) WO2009037475A1 (zh)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104918852A (zh) * 2013-01-10 2015-09-16 梅西耶-布加蒂-道提公司 用于连结两个轭以形成铰链的易熔构件
CN109979037A (zh) * 2019-03-19 2019-07-05 四川函钛科技有限公司 Qar参数综合可视化分析方法及系统
CN110182373A (zh) * 2015-01-07 2019-08-30 洛德公司 飞行器发动机安装架
CN111152916A (zh) * 2018-11-07 2020-05-15 庞巴迪公司 用于飞机起落架的硬着陆指示器
CN112429253A (zh) * 2020-12-14 2021-03-02 江西洪都航空工业集团有限责任公司 一种加速度重着陆指示器
CN113062934A (zh) * 2021-04-23 2021-07-02 中铁工程装备集团有限公司 一种盾构机主驱动减速机过载保护器及盾构机
CN114674550A (zh) * 2022-03-29 2022-06-28 中航飞机起落架有限责任公司 一种飞机主支柱磨合试验装置及试验方法

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0723506D0 (en) * 2007-12-03 2008-01-09 Airbus Uk Ltd Apparatus for indicating loading in a structure having exceeded a predetermined threshold
EP2993128B1 (en) * 2010-03-05 2017-06-21 Goodrich Corporation System for indicating an airplane hard landing
GB2478579A (en) 2010-03-11 2011-09-14 Messier Dowty Ltd Aircraft landing gear stop pad
GB2485803B (en) 2010-11-24 2013-02-06 Messier Dowty Ltd Mechanical position indicator
WO2012170252A2 (en) * 2011-06-10 2012-12-13 Shockwatch, Inc. Impact indicator
US9499257B2 (en) 2013-06-17 2016-11-22 Goodrich Corporation Weight reducing landing gear features
CN103983463B (zh) * 2014-04-17 2016-08-24 中国航空工业集团公司沈阳飞机设计研究所 一种飞机机体与起落架联合加载的验证试验方法
EP3159260B1 (en) * 2015-10-23 2019-11-27 Safran Landing Systems UK Limited Aircraft landing gear assembly including a health and usage monitoring system (hums) and method
US10272991B2 (en) * 2016-06-23 2019-04-30 Goodrich Corporation Metallic composite joint
EP3336485B1 (en) 2016-12-15 2020-09-23 Safran Landing Systems UK Limited Aircraft assembly including deflection sensor
JP6728089B2 (ja) * 2017-02-27 2020-07-22 三菱重工業株式会社 位置決定装置、それを備えた位置決定システム、及び位置決定方法並びに位置決定プログラム
EP3379222B1 (en) 2017-03-22 2020-12-30 Methode Electronics Malta Ltd. Magnetoelastic based sensor assembly
US11135882B2 (en) 2018-02-27 2021-10-05 Methode Electronics, Inc. Towing systems and methods using magnetic field sensing
EP3758959B1 (en) 2018-02-27 2025-11-05 Methode Electronics, Inc. Towing systems and methods using magnetic field sensing
US11491832B2 (en) 2018-02-27 2022-11-08 Methode Electronics, Inc. Towing systems and methods using magnetic field sensing
US11084342B2 (en) 2018-02-27 2021-08-10 Methode Electronics, Inc. Towing systems and methods using magnetic field sensing
US11221262B2 (en) 2018-02-27 2022-01-11 Methode Electronics, Inc. Towing systems and methods using magnetic field sensing
US11014417B2 (en) 2018-02-27 2021-05-25 Methode Electronics, Inc. Towing systems and methods using magnetic field sensing
US11130563B2 (en) * 2018-11-07 2021-09-28 The Boeing Company Monolithic outboard gear beam support fitting
US11124293B2 (en) * 2019-04-23 2021-09-21 Goodrich Corporation Integral bracket manifold for landing gear assemblies
KR102325331B1 (ko) 2019-12-20 2021-11-10 한화토탈 주식회사 터트-부탄올로부터 이소부틸렌의 제조방법
FR3136264B1 (fr) * 2022-06-03 2024-07-05 Safran Landing Systems Dispositif de blocage d’une broche d’arrêt
EP4428031A1 (en) 2023-03-06 2024-09-11 Lilium GmbH Landing gear for a vertical take-off and landing aircraft

Family Cites Families (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2960289A (en) * 1958-07-07 1960-11-15 Cleveland Pneumatic Ind Inc Aircraft landing gear
GB1027395A (en) * 1962-02-16 1966-04-27 Nat Res Dev Controlled fluid lubricated bearings
US3237590A (en) * 1963-09-13 1966-03-01 Bendix Corp Strain gauge means
SU467246A1 (ru) 1973-02-14 1975-04-15 Краснодарский Филиал Вниимонтаж Спецстрой Всесоюзного Научно-Исследовательского Института По Монтажным И Специальным Строительным Работам Устройство дл контрол усилий зат жки резьбовых соединений
US3845919A (en) * 1974-01-07 1974-11-05 Boeing Co Landing gear truck pitch damping
US3948141A (en) * 1974-08-20 1976-04-06 Katsumi Shinjo Load indicating washer
JPS5746842A (en) * 1980-08-15 1982-03-17 Teijin Ltd High frequency welding method
US4392623A (en) * 1980-12-22 1983-07-12 The Boeing Company Fused connection adapted to fail under different overloads acting in different directions
FR2511103A1 (fr) * 1981-08-10 1983-02-11 Aerospatiale Composants munis d'un dispositif d'absorption d'energie par deformation plastique et/ou de limitation d'effort, et trains d'atterrissage d'aerodynes equipes de tels composants
US4373862A (en) * 1981-10-26 1983-02-15 United Technologies Corporation Rotor blade shaft integrity monitoring system
US4447388A (en) * 1981-11-30 1984-05-08 The United States Of America As Represented By The United States Department Of Energy Bolt failure detection
DE3343495A1 (de) * 1983-12-01 1985-07-18 Paul 7936 Allmendingen Friese Dehnbruch-anzeiger
JPS60209137A (ja) * 1984-04-03 1985-10-21 Topy Ind Ltd 疲労損傷予知法
US4698623A (en) * 1984-11-07 1987-10-06 Smith Richard G Overload detection apparatus
JPS6261898A (ja) * 1985-09-10 1987-03-18 ニユ−モ・コ−ポレ−シヨン 着陸装置
US4869444A (en) * 1986-09-30 1989-09-26 The Boeing Company Adjustable two-stage aircraft landing gear system
GB8815826D0 (en) * 1988-07-04 1988-08-10 Westland Helicopters Method & apparatus for detecting cracks
SU1658186A1 (ru) * 1989-03-20 1991-06-23 Киевский Политехнический Институт Им.50-Летия Великой Октябрьской Социалистической Революции Индикатор виброперегрузок
JP3037370B2 (ja) * 1990-07-11 2000-04-24 東芝エンジニアリング株式会社 ピン形ロードセル
WO1997010145A1 (en) 1995-09-14 1997-03-20 Sikorsky Aircraft Corporation Energy absorbing landing gear/tail skid including means for indicating the magnitude of impact loads
GB9828475D0 (en) * 1998-12-24 1999-02-17 British Aerospace Load measurement
AUPR001800A0 (en) 2000-09-08 2000-10-05 Structural Monitoring Systems Ltd Method and apparatus for monitoring the integrity of structures
GB0428378D0 (en) * 2004-12-24 2005-02-02 Airbus Uk Ltd Apparatus and method for measuring loads sustained by a bearing pin
US7193530B2 (en) * 2005-03-29 2007-03-20 Nance C Kirk Aircraft landing gear automated inspection and life limitation escalation system and method
GB2452939B (en) * 2007-09-19 2011-09-07 Messier Dowty Ltd Overload detection
GB2453554B (en) * 2007-10-09 2012-03-14 Messier Dowty Ltd Load detection in an aircraft landing gear
GB0723506D0 (en) * 2007-12-03 2008-01-09 Airbus Uk Ltd Apparatus for indicating loading in a structure having exceeded a predetermined threshold

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104918852A (zh) * 2013-01-10 2015-09-16 梅西耶-布加蒂-道提公司 用于连结两个轭以形成铰链的易熔构件
CN104918852B (zh) * 2013-01-10 2017-05-31 梅西耶-布加蒂-道提公司 用于连结两个轭以形成铰链的易熔构件
CN110182373A (zh) * 2015-01-07 2019-08-30 洛德公司 飞行器发动机安装架
CN110182373B (zh) * 2015-01-07 2023-01-10 洛德公司 用于飞行器发动机安装架的轴承组件
CN111152916A (zh) * 2018-11-07 2020-05-15 庞巴迪公司 用于飞机起落架的硬着陆指示器
CN111152916B (zh) * 2018-11-07 2024-03-15 庞巴迪公司 用于飞机起落架的硬着陆指示器
CN109979037A (zh) * 2019-03-19 2019-07-05 四川函钛科技有限公司 Qar参数综合可视化分析方法及系统
CN112429253A (zh) * 2020-12-14 2021-03-02 江西洪都航空工业集团有限责任公司 一种加速度重着陆指示器
CN113062934A (zh) * 2021-04-23 2021-07-02 中铁工程装备集团有限公司 一种盾构机主驱动减速机过载保护器及盾构机
CN114674550A (zh) * 2022-03-29 2022-06-28 中航飞机起落架有限责任公司 一种飞机主支柱磨合试验装置及试验方法
CN114674550B (zh) * 2022-03-29 2024-05-07 中航飞机起落架有限责任公司 一种飞机主支柱磨合试验装置及试验方法

Also Published As

Publication number Publication date
US8539843B2 (en) 2013-09-24
ES2386570T3 (es) 2012-08-23
ATE554003T1 (de) 2012-05-15
GB0718296D0 (en) 2007-10-31
WO2009037475A1 (en) 2009-03-26
GB2452938A (en) 2009-03-25
CA2699705A1 (en) 2009-03-26
GB2452938B (en) 2011-08-10
JP2010539509A (ja) 2010-12-16
CA2699705C (en) 2014-11-18
EP2190744A1 (en) 2010-06-02
RU2478921C2 (ru) 2013-04-10
RU2010115338A (ru) 2011-10-27
BRPI0816415A2 (pt) 2015-03-03
JP4873391B2 (ja) 2012-02-08
CN101808902B (zh) 2013-04-24
EP2190744B1 (en) 2012-04-18
US20100257946A1 (en) 2010-10-14

Similar Documents

Publication Publication Date Title
CN101808902B (zh) 载荷指示器
US7193530B2 (en) Aircraft landing gear automated inspection and life limitation escalation system and method
EP2993128B1 (en) System for indicating an airplane hard landing
CA2620188C (en) Landing load monitor for aircraft landing gear
CA2699268C (en) Overload detection
EP2350590B1 (en) Load indicator
US4087062A (en) Aircraft undercarriage including a safety device having a predetermined breaking load
GB2108065A (en) Rotor blade shaft integrity monitoring system
US8955799B2 (en) Aircraft landing gear stop pad
CN103630346A (zh) 一种起落架应急断离销试验台及其试验方法
CN109506908B (zh) 尾段试验件疲劳试验平尾载荷加载装置
Brot Developing strategies to combat threats against the structural integrity of aircraft
US20250100678A1 (en) Landing gear assemblies, rotorcraft and rotorcraft methods
Phillips Technology Innovations for Aircraft'Hard Landing'Events.
CA3273338A1 (en) A swivel device for connecting human and/or non-human cargo to a rotorcraft
BR102023024189A2 (pt) Conjuntos de indicador de pouso duro e de trem de pouso, e, indicador de pouso duro
CN119394556A (zh) 动态冲击能量测量装置、飞机襟翼组件以及动态冲击能量测量的方法
Janssen Modular approach to development and substantiation of highly dynamic integrated systems-Simple units build a complex system!
Schmid Pilatus Pc-21–A Damage Tolerant Aircraft
Reddy et al. DESIGN and PROCESS GUIDELINES FOR HELICOPTER STRUCTURAL MODIFICATIONS
GB2490282A (en) Load indicator

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
C14 Grant of patent or utility model
GR01 Patent grant