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    • 1. 发明授权
    • Bi-stable magnetic latch assembly
    • 双稳磁锁组件
    • US07468646B2
    • 2008-12-23
    • US11448382
    • 2006-06-06
    • David A. Osterberg
    • David A. Osterberg
    • H01H9/00
    • G02B6/358G02B6/3526G02B6/3572G02B26/00
    • A bi-stable magnetic switch assembly is provided that comprises a stator and a rotor, which is configured for rotation with respect to the stator between a first latched position and a second latched position. The stator and the rotor cooperate to form a first magnetic path and a magnetic path having a shared portion. A spring, which is coupled to the rotor, biases the rotor toward the first and second latched positions when the rotor is in the second and first latched positions, respectively. At least one magnet is fixedly coupled to either the stator or the rotor. The magnet is included within the first magnetic path and configured to produce a magnetic latching force that biases the rotor toward first latched position when the rotor is closer to the first latched position than to the second latched position, and toward the second latched position when the rotor is closer to the second latched position than to the first latched position. At least one coil is fixedly coupled to either the stator or the rotor and, when energized, alters the flux in the second magnetic path to reduce the magnetic latching force.
    • 提供了一种双稳态磁开关组件,其包括定子和转子,其被配置为相对于定子在第一锁定位置和第二锁定位置之间旋转。 定子和转子协作形成具有共享部分的第一磁路和磁路。 当转子处于第二和第一锁定位置时,联接到转子的弹簧分别将转子朝向第一和第二锁定位置偏压。 至少一个磁体固定地联接到定子或转子上。 所述磁体包括在所述第一磁路内,并被配置为产生磁力锁定力,当所述转子比所述第二锁定位置更靠近所述第一锁定位置时,所述磁性锁定力将所述转子朝向所述第一锁定位置偏压,并且当所述转子位于所述第一锁定位置时, 转子比第一锁定位置更靠近第二锁定位置。 至少一个线圈固定地耦合到定子或转子上,并且当被激励时,改变第二磁路中的磁通以减小磁性锁定力。
    • 3. 发明申请
    • Bi-stable magnetic latch assembly
    • 双稳磁锁组件
    • US20070279168A1
    • 2007-12-06
    • US11448382
    • 2006-06-06
    • David A. Osterberg
    • David A. Osterberg
    • H01F7/14
    • G02B6/358G02B6/3526G02B6/3572G02B26/00
    • A bi-stable magnetic switch assembly is provided that comprises a stator and a rotor, which is configured for rotation with respect to the stator between a first latched position and a second latched position. The stator and the rotor cooperate to form a first magnetic path and a magnetic path having a shared portion. A spring, which is coupled to the rotor, biases the rotor toward the first and second latched positions when the rotor is in the second and first latched positions, respectively. At least one magnet is fixedly coupled to either the stator or the rotor. The magnet is included within the first magnetic path and configured to produce a magnetic latching force that biases the rotor toward first latched position when the rotor is closer to the first latched position than to the second latched position, and toward the second latched position when the rotor is closer to the second latched position than to the first latched position. At least one coil is fixedly coupled to either the stator or the rotor and, when energized, alters the flux in the second magnetic path to reduce the magnetic latching force.
    • 提供了一种双稳态磁开关组件,其包括定子和转子,其被配置为相对于定子在第一锁定位置和第二锁定位置之间旋转。 定子和转子协作形成具有共享部分的第一磁路和磁路。 当转子处于第二和第一锁定位置时,联接到转子的弹簧分别将转子朝向第一和第二锁定位置偏压。 至少一个磁体固定地联接到定子或转子上。 所述磁体包括在所述第一磁路内,并被配置为产生磁力锁定力,当所述转子比所述第二锁定位置更靠近所述第一锁定位置时,所述磁性锁定力将所述转子朝向所述第一锁定位置偏压,并且当 转子比第一锁定位置更靠近第二锁定位置。 至少一个线圈固定地耦合到定子或转子上,并且当被激励时,改变第二磁路中的磁通以减小磁性锁定力。
    • 4. 发明授权
    • High speed optical element switching mechanism
    • 高速光学元件切换机构
    • US07013057B2
    • 2006-03-14
    • US10103534
    • 2002-03-20
    • David A. Osterberg
    • David A. Osterberg
    • G02B6/26
    • G02B6/3566G02B6/351G02B6/358G02B7/182G02B26/007G02B26/02
    • The present invention provides an optical element switching mechanism that overcomes many of the disadvantages found in the prior art. The switching mechanism uses a balanced arm, with an optical element attached at one end of the arm. The arm is suspended on a axis that allows it to rotate from a first position to a second position. The arm is balanced to provide low force disturbance during this movement. A spring is coupled to the arm that provides the rotational energy to move the arm. The spring is coupled such that its neutral position is between the first and second positions, and thus the spring provides the energy to move the arm from the first position to the second position and vice versa. A latch mechanism is also provided for selectively holding the arm in the first position or second position. Additionally, the latch mechanism can provide additional energy needed to catch and move the arm into final position.
    • 本发明提供了克服现有技术中存在的许多缺点的光学元件切换机构。 切换机构使用平衡臂,其中一个光学元件安装在臂的一端。 臂悬挂在允许其从第一位置旋转到第二位置的轴上。 平衡臂在此运动期间提供较低的力量扰动。 弹簧联接到臂,其提供旋转能量以移动臂。 弹簧联接成使得其中性位置在第一和第二位置之间,因此弹簧提供能量以将臂从第一位置移动到第二位置,反之亦然。 还设置有用于将臂保持在第一位置或第二位置的闩锁机构。 此外,闩锁机构可以提供将臂移动到最终位置所需的额外的能量。
    • 6. 发明授权
    • Method and system for decoupling structural modes to provide consistent control system performance
    • 解耦结构模式的方法和系统,以提供一致的控制系统性能
    • US06834841B2
    • 2004-12-28
    • US10189860
    • 2002-07-03
    • David A. Osterberg
    • David A. Osterberg
    • F16M100
    • F16F15/022B64G1/641B64G1/645B64G2001/228F16C32/044F16C2326/47
    • A method and system for calculating a control function for a structural system (10) that can be used to determine an appropriate control force to apply to an active member (18) within a stationary member (12) on the structural system (10). An active member (18) and a stationary member (12) are defined as a two-mass system in which the active member (18) and the stationary member (12) move in opposite directions. The stationary member (12) is mounted to an isolation subsystem (14) that is composed of six isolators (28) at multiple degrees of freedom. The isolation subsystem (14) is softer than the stationary member (12), active member (18) and a spacecraft surface (16) due to a damping element (32) of the isolation subsystem (16). The isolation subsystem (16) is mounted to the spacecraft (16) and decouples the spacecraft (16) from the stationary member (12) and thus the active member (18). An accurate control force for the active member (18) can be determined based upon the above structure (10).
    • 一种用于计算结构系统(10)的控制功能的方法和系统,所述结构系统(10)可用于确定施加到结构系统(10)上的固定构件(12)内的有效构件(18)的适当控制力。 活动构件(18)和固定构件(12)被定义为活动构件(18)和固定构件(12)沿相反方向移动的双质量系统。 固定构件(12)安装到由多个自由度的六个隔离器(28)组成的隔离子系统(14)。 隔离子系统(14)由于隔离子系统(16)的阻尼元件(32)而比固定构件(12),有源构件(18)和航天器表面(16)软。 隔离子系统(16)被安装到航天器(16)并且将航天器(16)与固定构件(12)和所述有源构件(18)分离。 可以基于上述结构(10)来确定活动构件(18)的精确控制力。
    • 10. 发明授权
    • Method and system for decoupling structural modes to provide consistent control system performance
    • 解耦结构模式的方法和系统,以提供一致的控制系统性能
    • US07093806B2
    • 2006-08-22
    • US10851975
    • 2004-05-20
    • David A. Osterberg
    • David A. Osterberg
    • F16M1/00
    • F16F15/022B64G1/641B64G1/645B64G2001/228F16C32/044F16C2326/47
    • A method and system for calculating a control function for a structural system (10) that can be used to determine an appropriate control force to apply to an active member (18) within a stationary member (12) on the structural system (10). An active member (18) and a stationary member (12) are defined as a two-mass system in which the active member (18) and the stationary member (12) move in opposite directions. The stationary member (12) is mounted to an isolation subsystem (14) that is composed of six isolators (28) at multiple degrees of freedom. The isolation subsystem (14) is softer than the stationary member (12), active member (18) and a spacecraft surface (16) due to a damping element (32) of the isolation subsystem (16). The isolation subsystem (16) is mounted to the spacecraft (16) and decouples the spacecraft (16) from the stationary member (12) and thus the active member (18). An accurate control force for the active member (18) can be determined based upon the above structure (10).
    • 一种用于计算结构系统(10)的控制功能的方法和系统,所述结构系统(10)可用于确定施加到所述结构系统(10)上的固定构件(12)内的有效构件(18)的适当控制力。 活动构件(18)和固定构件(12)被定义为活动构件(18)和固定构件(12)沿相反方向移动的双质量系统。 固定构件(12)安装到由多个自由度的六个隔离器(28)组成的隔离子系统(14)。 隔离子系统(14)由于隔离子系统(16)的阻尼元件(32)而比固定构件(12),有源构件(18)和航天器表面(16)软。 隔离子系统(16)被安装到航天器(16)并且将航天器(16)与固定构件(12)和所述有源构件(18)分离。 可以基于上述结构(10)来确定活动构件(18)的精确控制力。