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公开(公告)号：US08104711B2
公开(公告)日：2012-01-31
申请号：US11997720
申请日：2006-08-04
Applicant: Ian Bennett , Richard C. Lang , Robert A. Menezes
Inventor： Ian Bennett , Richard C. Lang , Robert A. Menezes
Abstract: An auxiliary actuator (49) comprises a two stage telescopic hydraulic unit comprising first (59, 63) and second (56, 50) stage piston and cylinder actuators operating coaxially within an outer casing (50). A respective actuator is connected to a respective one of the strut (1) and bogie beam (4). The second stage actuator (56, 60) serves to control the tilt position of the bogie beam (4) relative to the strut (1). The second stage actuator (56. 60), when in the retracted position with the first stage actuator (59, 63) in the extended position, limits the length ol the auxiliary actuator (9) between its connections (62,67) to the strut (1) and bogie beam (4), so as to assume a predetermined intermediate length in which the bogie beam (4) is restrained to tilt about the auxiliary pivot (14) and thereby lengthens the landing gear during take-off.
Abstract translation: 辅助致动器（49）包括两级伸缩液压单元，其包括在外壳（50）内同轴运行的第一（59,63）和第二（56,50）级的活塞和气缸致动器。 相应的致动器连接到支柱（1）和转向架梁（4）中的相应的一个。 第二级致动器（56,60）用于控制转向架（4）相对于支柱（1）的倾斜位置。 当处于处于延伸位置的第一级致动器（59,63）的缩回位置时，第二级致动器（56.60）将辅助致动器（9）在其连接（62,67）之间的长度限制到 支柱（1）和转向架梁（4），以便呈现预定的中间长度，其中转向架梁（4）被限制在辅助枢轴（14）周围倾斜，从而在起飞期间延长起落架。
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Patent Agency Ranking
公开(公告)号：US20120091271A1
公开(公告)日：2012-04-19
申请号：US13333249
申请日：2011-12-21
Applicant: Ian BENNETT , Richard C. LANG , Robert A. MENEZES
Inventor： Ian BENNETT , Richard C. LANG , Robert A. MENEZES
IPC: B64C25/20
Abstract: A semi-levered landing gear for an aircraft includes a main shock absorber strut, a bogie beam and an auxiliary actuator mechanism. The bogie beam extends fore and aft of an airframe of the aircraft with forward and aft axles for respective forward and aft wheels, and a main pivot between the forward and aft axle pivotally connected to the lower portion of the main shock absorber strut. The auxiliary actuator mechanism includes a spring unit pivotally connected at a lower end to an auxiliary pivot on the bogie forward of the main pivot, and at an upper end to an anchor point offset from the pivot connection of the upper portion to the aircraft fuselage. During stowing the strut and spring unit pivot together about different pivot points, causing a relative longitudinal movement between the main pivot and auxiliary pivot that further tilts the bogie beam to a stowing position.
Abstract translation: 用于飞行器的半起落架起落架包括主减震器支柱，转向架梁和辅助致动器机构。 转向架梁用于相应的前轮和后轮的前轮和后轴的飞机机身的前后延伸，并且前后轴之间的主枢轴枢转地连接到主减震器支柱的下部。 辅助致动器机构包括弹簧单元，该弹簧单元在下端处枢转地连接到主枢轴前方的转向架上的辅助枢轴上，并且在上端处于从上部的枢转连接偏离飞行器机身的锚定点。 在收起期间，支柱和弹簧单元围绕不同的枢转点枢转在一起，导致主枢轴和辅助枢轴之间的相对纵向运动，其进一步将转向架梁倾斜到收起位置。
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公开(公告)号：US20090050736A1
公开(公告)日：2009-02-26
申请号：US11997720
申请日：2006-08-04
Applicant: Ian Bennett , Richard C. Lang , Robert A. Menezes
Inventor： Ian Bennett , Richard C. Lang , Robert A. Menezes
Abstract: A semi-levered landing gear for an aircraft comprises a main shock absorber strut (1) connected to the airframe; a bogie beam (4) extending fore and aft of the airframe with forward and aft wheels (J, T) and a main pivot connection (5) to the strut (1) between the forward and aft wheels (7, T) and an auxiliary actuator (49) connected between the strut (1) and the front of the bogie beam (4) at an auxiliary pivot (14). The auxiliary actuator (49) comprises a two stage telescopic hydraulic unit comprising a first stage piston and cylinder actuator (59, 63) and a second stage piston and cylinder actuator (56, 50) operating coaxially within an outer casing (50). A respective piston rod (65, 60) each extends from each end of the casing (50) and is connected to a respective one of said (strut 1) and bogie beam (4). The first stage actuator (59, 63) is operable to an extended position, and the second stage actuator (56, 60) is operable between a retracted position (FIG. 11) and an extended position (FIG. 12) defined by respective end stops (75, 77) within the outer casing (50) and serves to control the tilt position of the bogie beam (4) relative to the strut (1). The second stage actuator (56, 60), when in the retracted position with the first stage actuator (59, 63) in the extended position, limits the length of the auxiliary actuator (9) between its connections (62, 67) to the strut (1) and bogie beam (4), so as to assume a predetermined intermediate length in which the bogie beam (4) is restrained to tilt about the auxiliary pivot (14) and thereby lengthens the landing gear during take-off. The second stage actuator (56, 60), when in the extended position with the first stage actuator (59, 63) in the extended position, allows the length of the auxiliary actuator (49) to assume a predetermined maximum length in which the bogie beam (4) is tilted about the main pivot (5) to a stowing position for stowing the landing gear in the aircraft.
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公开(公告)号：US20120119025A1
公开(公告)日：2012-05-17
申请号：US13333138
申请日：2011-12-21
Applicant: Ian Bennett , Richard C. Lang , Robert A. Menezes
Inventor： Ian Bennett , Richard C. Lang , Robert A. Menezes
IPC: B64C25/10
Abstract: An auxiliary actuator mechanism includes a lever, a spring unit and a control linkage. The lever is pivotally connected to the upper portion of a main shock absorber strut, and pivotable between an upper position for take-off, and a lower position. The spring unit is pivotally connected at an upper end to the lever and at a lower end to the bogie at an auxiliary pivot forward of the main pivot. The control linkage is connected between the lever and the upper portion of the main shock absorber strut to define the upper predetermined position of the lever. The control linkage is connectable to an anchor point that moves relative to the upper portion of the main shock absorber strut during stowing, and is operated by initial stowing movement of the stowing mechanism to lower the lever from the upper position to a stowing position.
Abstract translation: 辅助致动器机构包括杆，弹簧单元和控制连杆。 杠杆枢转地连接到主减震器支柱的上部，并且可以在用于起飞的上部位置和下部位置之间枢转。 弹簧单元在上端枢转地连接到杠杆，并且在下端处以主枢轴前方的辅助枢轴枢转地连接到转向架。 控制联动装置连接在杠杆和主减震器支柱的上部之间，以限定杠杆的上部预定位置。 控制联动装置可连接到在收起期间相对于主减震器支柱的上部移动的锚点，并且通过收起机构的初始收起运动来操作以将杠杆从上部位置降低到收起位置。
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公开(公告)号：US5285456A
公开(公告)日：1994-02-08
申请号：US700737
申请日：1991-05-15
Applicant: Dennis P. Cheney , Richard C. Lang , Andrew E. Petruski , Mark J. Wolski , Robert J. Yagley
Inventor： Dennis P. Cheney , Richard C. Lang , Andrew E. Petruski , Mark J. Wolski , Robert J. Yagley
Abstract: A system and method for verifying the integrity of control information and informational data. One embodiment of the present invention verifies the integrity of control information received from a host computer, and verifies the integrity of this information as it is transmitted throughout the present invention. Another embodiment of the present invention contemplates verifying the integrity of informational data sent from a host computer, verifying the integrity of informational data as it is transmitted throughout the present invention, generating a CRC based upon the informational data and control information, and transmitting the informational data, control information and corresponding CRC to a storage device.
Abstract translation: 一种用于验证控制信息和信息数据完整性的系统和方法。 本发明的一个实施例验证从主计算机接收的控制信息的完整性，并且在贯穿本发明时验证该信息的完整性。 本发明的另一实施例考虑了验证从主计算机发送的信息数据的完整性，验证了在整个本发明中传输的信息数据的完整性，基于信息数据和控制信息生成CRC，并且发送信息 数据，控制信息和相应的CRC存储到存储设备。
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公开(公告)号：US20120112001A1
公开(公告)日：2012-05-10
申请号：US13332680
申请日：2011-12-21
Applicant: Ian Bennett , Richard C. Lang , Robert A. Menezes
Inventor： Ian Bennett , Richard C. Lang , Robert A. Menezes
Abstract: An auxiliary mechanism includes a lever unit, a spring unit and a positioning unit. One of the units pivotally connects to the upper portion of a main shock absorber strut so as to pivot between a predetermined lower position for take-off and landing and an upper position. Another unit pivotally connects at an upper end to the upper portion of the main shock absorber strut and pivotally connects at a lower end to the first unit. A third unit pivotally connects at a lower end to the bogie beam at an auxiliary pivot and connects at an upper end to the lever. The positioning unit assumes either a contracted state or extended state for taxiing, take-off and landing, and assumes the other state for stowing the landing gear after take-off. The spring unit provides spring resistance to pivotal movements of the bogie beam about the main pivot during taxiing.
Abstract translation: 辅助机构包括杠杆单元，弹簧单元和定位单元。 其中一个单元枢转地连接到主减震器支柱的上部，以便在用于起飞和着陆的预定下部位置和上部位置之间枢转。 另一个单元在上端枢转地连接到主减震器支柱的上部，并且在下端枢转地连接到第一单元。 第三单元在下端处以辅助枢轴枢转地连接到转向架梁，并且在上端连接到杠杆。 定位单元承担滑行，起飞和着陆的承包状态或延长状态，并在起飞后采取起落架的另一种状态。 弹簧单元在滑行期间提供弹簧抵抗转向架梁绕主枢轴的枢转运动。
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