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1. 发明公开

EP0320543A1 Landing gear mechanism including bypass valve assembly for reducing damping loads during taxiing 失效
标题翻译：底盘与旁通阀系统，以减少滑行在地面上时的阻尼载荷。
公开(公告)号：EP0320543A1
公开(公告)日：1989-06-21
申请号：EP87311055.5
申请日：1987-12-15
申请人： Pneumo Abex Corporation
发明人： Hrusch, Louis C.
IPC分类号： B64C25/60
CPC分类号： F16F9/06 , B64C25/60 , F16F9/48
摘要： Landing gear mechanism includes a restrictor assembly (6) containing a main orifice (15) for controlling the rate of instroke of the landing gear mechanism during landing and a taxi instroke bypass valve assembly (20) which provides for increased flow of hydraulic fluid within the landing gear mechanism whenever the landing gear mechanism engages a bump during taxiing to reduce the damping loads that would otherwise occur if all of the hydraulic fluid were required to flow through the main orifice (15). The taxi instroke bypass valve assembly (20) includes a slide member (22) axially movable relative to the restrictor assembly (6) for opening and closing one or more bypass orifices (21) in the restrictor assembly (6). The slide member (22) is held in the closed position whenever the landing gear mechanism is in a specified stroke range from fully extended by a secondary piston (28) which is acted upon by the pressure in a precharged secondary chamber (30) urging the secondary piston (22) into engagement with a probe (23) connected to the slide member (22). At some point in the strut stroke, the pressure within the upper piston chamber (19) of the landing gear mechanism will rise to that of the precharged secondary chamber (30), whereby the secondary piston (28) will be stroked along with the main strut piston (5) and the slide member (22) will move to the open position allowing fluid to bypass the main orifice (15), thereby reducing the damping loads as the landing gear mechanism negotiates bumps during taxiing.
摘要翻译：起落架机构包括一个限流器组件（6）包含一个主孔（15），用于控制所述起落架机构的内向行程的着陆过程中的速率和出租车内向行程旁通阀组件（20），其用于内的液压流体的流动增加提供登陆每当起落架机构滑行以减少阻尼载荷那样，如果所有的液压流体被要求通过主孔（15）中流动否则将会发生期间接合凸块齿轮机构。出租车内向行程旁通阀组件（20）包括用于打开滑动部件（22）相对于所述限流器组件（6）可轴向移动和关闭在所述限流器组件的一个或多个旁通孔（21）（6）。所述滑动部件（22）在关闭位置保持每当起落架机构是在规定行程范围内从由次级活塞（28），所有这些是在由压力在预置次级室（30）作用完全延伸催促副活塞（22）与连接到所述滑动部件（22）的探针（23）接合。将在支柱行程的某个时刻，起落架机构的上活塞腔室（19）内的压力将上升到没有预充电的次级室（30），由此，副活塞（28）地连同主抚摸的支柱活塞（5）和滑动部件（22）将移动到打开位置允许流体绕过主孔（15），由此降低了阻尼载荷作为起落架机构滑行期间协商的凸块。

2. 发明公开

EP0299588A2 Landing gear mechanism for use on rough runways 失效
标题翻译： Fahrwerkfürunebene Rollbahn。
公开(公告)号：EP0299588A2
公开(公告)日：1989-01-18
申请号：EP88201744.5
申请日：1985-08-19
申请人： Pneumo Abex Corporation
发明人： Hrusch, Louis C.
IPC分类号： B64C25/60 , F16F9/46
CPC分类号： F16F9/49 , B64C25/60
摘要： Landing gear mechanism includes a built-in hydraulic actuator (30) which may be actuated to provide a heavy load range, soft spring rate during take-off with a heavy take-off weight and a lower load range, softer spring rate after take-off and prior to landing with a lighter landing weight to yield more shock strut stroke for a given range of vertical load during landing. A special taxi valve (45) allows for some fluid to bypass the main orifice (15) more freely to and from the lower piston damping chamber (54) to the shock strut air-oil chamber (20) as soon as the landing energy stroke is complete to greatly reduce or eliminate high damping loads that might otherwise take place as the gear negotiates bumps. Such a valve may automatically be set to close for landing by the action of the gear extension during a subsequent take-off, thus reactivating the main orifice. For normal bounce, air in the primary chamber (20) drives oil through an orifice (69) in a rebound damper valve (65) to the lower piston chamber (54) in order to lift the supported weight of the aircraft as part of the return stroke. However, when riding over a hole, the air acts freely on the differential or net piston area of the gear which is too small to lift the supported weight of the aircraft, but is large enough to accelerate the unsprung mass of the gear quickly into the hole. An anti-cavitation bypass valve (62) assures oil refill in the lower portion of the piston chamber as the gear extends. Also, a pressure actuated valve (71) may be provided in the metering pin (10) which, upon sensing cavitation in the lower piston chamber (54) during extension, will open a series of holes (72, 73) both above and below the main orifice (15), providing a flow path for oil around the main orifice, to eliminate the aforementioned cavitation. The metering pin is part of this flow path. A check valve (95) may be provided at the top of the metering pin to keep the metering pin full of oil by allowing free flow of oil upward but not allowing downward flow, thus preventing the intake and down flow of shock strut air during the anti-cavitation re-fill of the lower piston chamber. An extension snubber valve (116) may also be provided to develop piston rebound damping during the last portion of stroke of the landing gear before full extension thereof during take-off.
摘要翻译：起落架机构包括一个内置的液压执行器（30），其可以被致动以提供重的载荷范围，在起飞时的软弹簧速率具有较大的起飞重量和较低的载荷范围，在降落之前和降落之前，在着陆期间给定的垂直载荷范围内产生更多的冲击支柱行程。特殊的出水阀（45）允许一些流体在着陆能量冲程一旦更靠近或从下活塞阻尼室（54）向冲击支柱空气 - 油室（20）绕过主孔（15）是完全的，以大大减少或消除高阻尼负载，否则当齿轮协商碰撞时可能会发生。这样的阀可以在随后的起飞期间通过齿轮延伸的作用自动地设定为关闭，从而重新激活主孔。对于正常的反弹，主室（20）中的空气通过位于下活塞室（54）的回弹阻尼器阀（65）中的孔口（69）驱动油，以便提升飞机的支撑重量，作为回程。然而，当骑在一个孔上时，空气在齿轮的差速或净活塞区域上自由地作用，该区域太小而不能提升飞机的支撑重量，但是足够大以将齿轮的簧下质量快速地加速到孔。防气蚀旁通阀（62）在齿轮延伸时确保活塞室下部的补油。此外，压力致动阀（71）可以设置在计量销（10）中，其在延伸期间在感测下活塞室（54）中的气蚀时将在上下方向打开一系列孔（72,73）主孔口（15），为主孔口周围的油提供流动路径，以消除上述空化现象。计量销是该流路的一部分。可以在计量销的顶部设置止回阀（95），以通过允许向上自由流动但不允许向下流动而使计量销保持在油位上，从而防止在该期间的冲击支柱空气的进入和下流下部活塞室的反气蚀再填充。还可以设置延伸缓冲阀（116），以在起落架的全部延伸期间在起落架的行程的最后部分期间形成活塞回弹阻尼。

3. 发明公开

EP0212022A1 Landing gear mechanism for use on rough runways 失效
标题翻译：飞机起落架不均匀的跑道。
公开(公告)号：EP0212022A1
公开(公告)日：1987-03-04
申请号：EP85305889.9
申请日：1985-08-19
申请人： Pneumo Abex Corporation
发明人： Hrusch, Louis C.
IPC分类号： B64C25/60 , F16F9/46
CPC分类号： F16F9/06 , B64C25/60 , F16F9/512
摘要： Landing gear mechanism includes a built-in hydraulic actuator (30) which may be actuated to provide a heavy load range, soft spring rate during take-off with a heavy take-off weight and a lower load range, softer spring rate after take-off and prior to landing with a lighter landing weight to yield more shock strut stroke for a given range of vertical load during landing. A special taxi valve (45) allows for some fluid to bypass the main orifice (15) more freely to and from the lower piston damping chamber (54) to the shock strut air-oil chamber (20) as soon as the landing energy stroke is complete to greatly reduce or eliminate high damping loads that might otherwise take place as the gear negotiates bumps. Such a valve may automatically be set to close for landing by the action of the gear extension during a subsequent take-off, thus reactivating the main orifice. For normal bounce, air in the primary chamber (20) drives oil through an orifice (69) in a rebound damper valve (65) to the lower piston chamber (54) in order to lift the supported weight of the aircraft as part of the return stroke. However, when riding over a hole, the air acts freely on the differential or net piston area of the gear which area is too small to lift the supported weight of the aircraft, but is large enough to accelerate the unsprung mass of the gear quickly into the hole. An anti-cavitation bypass valve (62) assures oil refill in the lower portion of the piston chamber as the gear extends. Also, a pressure actuated valve (71) may be provided in the metering pin (10) which, upon sensing cavitation in the lower piston chamber (54) during extension, will open a series of holes (72, 73) both above and below the main orifice (15), providing a flow path for oil around the main orifice, to eliminate the aforementioned cavitation. The metering pin is part of this flow path. A check valve (95) may be provided at the top of the metering pin to keep the metering pin full of oil by allowing free flow of oil upward but not allowing downward flow, thus preventing the intake and down flow of shock strut air during the anti-cavitation re-fill of the lower piston chamber. An extension snubber valve (116) may also be provided to develop piston rebound damping during the last portion of stroke of the landing gear before full extension thereof during take-off.

4. 发明公开

EP0298579A2 Landing gear mechanism for use on rough runways 失效
标题翻译： Fahrwerkfürunebene Rollbahn。
公开(公告)号：EP0298579A2
公开(公告)日：1989-01-11
申请号：EP88201750.2
申请日：1985-08-19
申请人： Pneumo Abex Corporation
发明人： Hrusch, Louis C.
IPC分类号： B64C25/60 , F16F9/46
CPC分类号： F16F9/512 , B64C25/60 , F16F9/06
摘要： Landing gear mechanism includes a built-in hydraulic actuator (30) which may be actuated to provide a heavy load range, soft spring rate during take-off with a heavy take-off weight and a lower load range, softer spring rate after take-off and prior to landing with a lighter landing weight to yield more shock strut stroke for a given range of vertical load during landing. A special taxi valve (45) allows for some fluid to bypass the main orifice (15) more freely to and from the lower piston damping chamber (54) to the shock strut air-oil chamber (20) as soon as the landing energy stroke is complete to greatly reduce or eliminate high damping loads that might otherwise take place as the gear negotiates bumps. Such a valve may automatically be set to close for landing by the action of the gear extension during a subsequent take-off, thus reactivating the main orifice. For normal bounce, air in the primary chamber (20) drives oil through an orifice (69) in a rebound damper valve (65) to the lower piston chamber (54) in order to lift the supported weight of the aircraft as part of the return stroke. However, when riding over a hole, the air acts freely on the differential or net piston area of the gear which area is too small to lift the supported weight of the aircraft, but is large enough to accelerate the unsprung mass of the gear quickly into the hole. An anti-cavitation bypass valve (62) assures oil refill in the lower portion of the piston chamber as the gear extends. Also, a pressure actuated valve (71) may be provided in the metering pin (10) which, upon sensing cavitation in the lower piston chamber (54) during extension, will open a series of holes (72, 73) both above and below the main orifice (15), providing a flow path for oil around the main orifice, to eliminate the aforementioned cavitation. The metering pin is part of this flow path. A check valve (95) may be provided at the top of the metering pin to keep the metering pin full of oil by allowing free flow of oil upward but not allowing downward flow, thus preventing the intake and down flow of shock strut air during the anti-cavitation re-fill of the lower piston chamber. An extension snubber valve (116) may also be provided to develop piston rebound damping during the last portion of stroke of the landing gear before full extension thereof during take-off.
摘要翻译：起落架机构包括一个内置的液压执行器（30），其可以被致动以提供重的载荷范围，在起飞时的软弹簧速率具有较大的起飞重量和较低的载荷范围，在降落之前和降落之前，在着陆期间给定的垂直载荷范围内产生更多的冲击支柱行程。特殊的出水阀（45）允许一些流体在着陆能量冲程一旦更靠近或从下活塞阻尼室（54）向冲击支柱空气 - 油室（20）绕过主孔（15）是完全的，以大大减少或消除高阻尼负载，否则当齿轮协商碰撞时可能会发生。这样的阀可以在随后的起飞期间通过齿轮延伸的作用自动地设定为关闭，从而重新激活主孔。对于正常的反弹，主室（20）中的空气通过位于下活塞室（54）的回弹阻尼器阀（65）中的孔口（69）驱动油，以便提升飞机的支撑重量，作为回程。然而，当骑在一个洞上时，空气在齿轮的差速器或净活塞区域上自由地起作用，该区域太小而不能提升飞机的支撑重量，但是足够大以将齿轮的非弹簧质量快速加速那个洞。防气蚀旁通阀（62）在齿轮延伸时确保活塞室下部的补油。此外，压力致动阀（71）可以设置在计量销（10）中，其在延伸期间在感测下活塞室（54）中的气蚀时将在上下方向打开一系列孔（72,73）主孔口（15），为主孔口周围的油提供流动路径，以消除上述空化现象。计量销是该流路的一部分。可以在计量销的顶部设置止回阀（95），以通过允许向上自由流动但不允许向下流动而使计量销保持在油位上，从而防止在该期间的冲击支柱空气的进入和下流下部活塞室的反气蚀再填充。还可以设置延伸缓冲阀（116），以在起落架的全部延伸期间在起落架的行程的最后部分期间形成活塞回弹阻尼。

5. 发明授权

EP0212022B1 Landing gear mechanism for use on rough runways 失效
标题翻译：用于粗糙运行的起落架齿轮机构
公开(公告)号：EP0212022B1
公开(公告)日：1990-07-25
申请号：EP85305889.9
申请日：1985-08-19
申请人： Pneumo Abex Corporation
发明人： Hrusch, Louis C.
IPC分类号： B64C25/60 , F16F9/46
CPC分类号： F16F9/06 , B64C25/60 , F16F9/512

6. 发明公开

EP0358820A1 Landing gear mechanism including controlled instroke and rebound damping & stroke overload protection 失效
标题翻译： Fahrwerk mit geregelterDämpfungin beiden Richtungen undÜberlastsicherung。
公开(公告)号：EP0358820A1
公开(公告)日：1990-03-21
申请号：EP88308451.9
申请日：1988-09-13
申请人： Pneumo Abex Corporation
发明人： Hrusch, Louis C. , Winn, Richard J.
IPC分类号： B64C25/60 , F16F9/50 , F16F9/46
CPC分类号： B64C25/60
摘要： Landing gear mechanism (1) includes a variable area orifice (18) to obtain the desired rebound damping of the landing gear mechanism during landing, and one or more check valve assemblies (20) that operate in conjunction with the variable area orifice (18) to provide the desired controlled instroke of the landing gear mechanism during landing. Also, the landing gear mechanism (1) is provided with a relief valve assembly (40) that permits bypass flow at a pre-set pressure drop only during an intermediate portion of the instroke of the landing gear mechanism (1) to attenuate severe bumps and the like without adversely affecting the controlled instroke and rebound damping of the landing gear mechanism (1) during landing.
摘要翻译：起落架机构（1）包括可变区域孔口（18），以在着陆期间获得起落架机构的期望的回弹阻尼，以及与可变面积孔口（18）一起操作的一个或多个止回阀组件（20）以在着陆期间提供起落架机构所期望的受控制的启动。此外，起落架机构（1）设置有安全阀组件（40），其仅在起落架机构（1）的行程的中间部分期间允许在预设压降下的旁路流动，以衰减严重的颠簸而不会对着陆齿轮机构（1）在着陆期间的受控起搏和回弹阻尼产生不利影响。

7. 发明公开

EP0298579A3 Landing gear mechanism for use on rough runways 失效
标题翻译：在粗略跑道上使用的起落架机构
公开(公告)号：EP0298579A3
公开(公告)日：1989-04-05
申请号：EP88201750.2
申请日：1985-08-19
申请人： Pneumo Abex Corporation
发明人： Hrusch, Louis C.
IPC分类号： B64C25/60 , F16F9/46
CPC分类号： F16F9/512 , B64C25/60 , F16F9/06
摘要： Landing gear mechanism includes a built-in hydraulic actuator (30) which may be actuated to provide a heavy load range, soft spring rate during take-off with a heavy take-off weight and a lower load range, softer spring rate after take-off and prior to landing with a lighter landing weight to yield more shock strut stroke for a given range of vertical load during landing. A special taxi valve (45) allows for some fluid to bypass the main orifice (15) more freely to and from the lower piston damping chamber (54) to the shock strut air-oil chamber (20) as soon as the landing energy stroke is complete to greatly reduce or eliminate high damping loads that might otherwise take place as the gear negotiates bumps. Such a valve may automatically be set to close for landing by the action of the gear extension during a subsequent take-off, thus reactivating the main orifice. For normal bounce, air in the primary chamber (20) drives oil through an orifice (69) in a rebound damper valve (65) to the lower piston chamber (54) in order to lift the supported weight of the aircraft as part of the return stroke. However, when riding over a hole, the air acts freely on the differential or net piston area of the gear which area is too small to lift the supported weight of the aircraft, but is large enough to accelerate the unsprung mass of the gear quickly into the hole. An anti-cavitation bypass valve (62) assures oil refill in the lower portion of the piston chamber as the gear extends. Also, a pressure actuated valve (71) may be provided in the metering pin (10) which, upon sensing cavitation in the lower piston chamber (54) during extension, will open a series of holes (72, 73) both above and below the main orifice (15), providing a flow path for oil around the main orifice, to eliminate the aforementioned cavitation. The metering pin is part of this flow path. A check valve (95) may be provided at the top of the metering pin to keep the metering pin full of oil by allowing free flow of oil upward but not allowing downward flow, thus preventing the intake and down flow of shock strut air during the anti-cavitation re-fill of the lower piston chamber. An extension snubber valve (116) may also be provided to develop piston rebound damping during the last portion of stroke of the landing gear before full extension thereof during take-off.
摘要翻译：起落架机构包括内置式液压致动器（30），其可以被致动以提供重负荷范围，在起飞期间具有较大的起飞重量和较低的负荷范围时的软弹簧比率，在起飞后较软的弹簧比率，在登陆前以较轻的着陆重量着陆，以在给定的垂直载荷范围内产生更多的冲击支柱行程。一旦着陆能量冲程（45）允许某些流体更自由地绕过主孔口（15）到达下部活塞阻尼室（54）并且从下部活塞阻尼室（54）绕过冲击支柱空气油室（20）是完全可以大大减少或消除高速阻尼负荷，否则可能会发生齿轮协商颠簸。在随后的起飞期间，这样的阀可以通过齿轮延伸的作用自动地设定为关闭着陆，从而重新激活主孔。为了正常弹跳，主腔室（20）中的空气将油通过回弹阻尼阀（65）中的孔口（69）驱动到下活塞腔室（54）以提升飞机的支撑重量作为回程。然而，当骑在一个孔上时，空气自由地作用在齿轮的差速器或净活塞区域上，该区域太小而不能提升飞机的支撑重量，但是足够大以将齿轮的非悬挂质量快速加速到洞。当齿轮延伸时，防气蚀旁通阀（62）确保活塞室下部的再充油。而且，可以在计量销（10）中设置压力致动阀（71），该压力致动阀（71）在延伸期间感测到下活塞腔室（54）中的气蚀时将打开上方和下方的一系列孔（72,73）主孔（15）为主孔周围的油提供流动路径，以消除前述的气穴。计量销是该流路的一部分。在计量销的顶部可设置止回阀（95），以通过允许油向上自由流动但不允许向下流动来保持计量销充满油，从而防止冲击支撑空气在下部活塞腔的防空穴重新填充。延伸缓冲阀（116）也可以设置成在起落架的行程的最后部分期间在起飞期间完全伸出之前产生活塞回弹阻尼。

8. 发明公开

EP0299588A3 Landing gear mechanism for use on rough runways 失效
标题翻译：用于粗糙运行的起落架齿轮机构
公开(公告)号：EP0299588A3
公开(公告)日：1989-03-29
申请号：EP88201744.5
申请日：1985-08-19
申请人： Pneumo Abex Corporation
发明人： Hrusch, Louis C.
IPC分类号： B64C25/60 , F16F9/46
CPC分类号： F16F9/49 , B64C25/60
摘要： Landing gear mechanism includes a built-in hydraulic actuator (30) which may be actuated to provide a heavy load range, soft spring rate during take-off with a heavy take-off weight and a lower load range, softer spring rate after take-off and prior to landing with a lighter landing weight to yield more shock strut stroke for a given range of vertical load during landing. A special taxi valve (45) allows for some fluid to bypass the main orifice (15) more freely to and from the lower piston damping chamber (54) to the shock strut air-oil chamber (20) as soon as the landing energy stroke is complete to greatly reduce or eliminate high damping loads that might otherwise take place as the gear negotiates bumps. Such a valve may automatically be set to close for landing by the action of the gear extension during a subsequent take-off, thus reactivating the main orifice. For normal bounce, air in the primary chamber (20) drives oil through an orifice (69) in a rebound damper valve (65) to the lower piston chamber (54) in order to lift the supported weight of the aircraft as part of the return stroke. However, when riding over a hole, the air acts freely on the differential or net piston area of the gear which is too small to lift the supported weight of the aircraft, but is large enough to accelerate the unsprung mass of the gear quickly into the hole. An anti-cavitation bypass valve (62) assures oil refill in the lower portion of the piston chamber as the gear extends. Also, a pressure actuated valve (71) may be provided in the metering pin (10) which, upon sensing cavitation in the lower piston chamber (54) during extension, will open a series of holes (72, 73) both above and below the main orifice (15), providing a flow path for oil around the main orifice, to eliminate the aforementioned cavitation. The metering pin is part of this flow path. A check valve (95) may be provided at the top of the metering pin to keep the metering pin full of oil by allowing free flow of oil upward but not allowing downward flow, thus preventing the intake and down flow of shock strut air during the anti-cavitation re-fill of the lower piston chamber. An extension snubber valve (116) may also be provided to develop piston rebound damping during the last portion of stroke of the landing gear before full extension thereof during take-off.

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