A cantilever beam-type active-passive integrated orthogonal six-degree-of-freedom vibration isolation device

Abstract

A cantilever beam type active and passive integrated orthogonal six-degree-of-freedom vibration isolation device of the present invention comprises: an upper platform (1), three three-joint quasi-zero rotational stiffness hinges (2), six carbon fiber rods (3), six two Joint quasi-zero rotational stiffness hinge (4), 6 active and passive integrated linear vibration isolation mechanisms (5); each active and passive integrated linear vibration isolation mechanism (5) is fixedly connected to the external spacecraft, and the upper platform (1 ) is connected with the external load; the low-frequency and high-frequency micro-vibrations generated when the external spacecraft moves along the direction of six degrees of freedom are passed through 3 three-joint quasi-zero rotational stiffness hinges (2), 6 carbon fiber rods (3), 6 Two quasi-zero rotational stiffness hinges (4) with two joints cooperate together to convert the axial vibration along the active-passive integrated linear vibration isolation mechanism (5) in a decoupled form, and the active-passive integrated linear vibration isolation mechanism (5) 5) Perform isolation of high-frequency micro-vibrations and suppression of low-frequency micro-vibrations to reduce the impact of external spacecraft micro-vibrations on the stability and pointing accuracy of the external load connected to the upper platform (1).

Description

A cantilever beam-type active-passive integrated orthogonal six-degree-of-freedom vibration isolation device technical field The present invention relates to a kind of cantilever beam type active-passive integrated orthogonal six-degree-of-freedom vibration isolation device, belonging to aerospace high-resolution The field of multi-degree-of-freedom micro-vibration control including rate earth observation, spaceborne precision optical instruments, etc. Background technique [0002] With the spacecraft missions of large space-based astronomical observation spacecraft and extremely high-resolution earth observation satellites, optical Ultra-agile maneuvering search of academic load and laser load, ultra-high-precision pointing, ultra-high stability control and other "three-super" control requirements. In-orbit medium and high frequency micro-vibration induced by moving parts such as spacecraft body flywheel, control torque gyroscope, refrigerator and drive mechanism Dyna...

AI Technical Summary

Problems solved by technology

[0005] In view of the large optical load active vibration isolation requirements for large output of the actuator, the weight of the voice coil motor actuator is too heavy, and the voice coil motor has no guiding device, so it is necessary to configure a linear guide rail, which further increases the weight of the single-leg actuator. Large, which limits the practical application on spacecraft

[0006] 2. Actuator backup is difficult

[0007] The voice coil motor actuator is the core actuator of active control. Due to its large size and heavy weight, it is difficult to carry out backup design for it. There is a plan to realize the actuator by changing the six-rod type of the Stewart configuration into an eight-rod type. Backup, but this undoubtedly increases the weight and complexity of the control system

[0008] 3. The elastic hinge does not achieve zero rotational stiffness

[0009] Whether it is a six-rod vibration isolation device or an eight-rod vibration isolation device, the movement of the external load relative to the spacecraft is accompanied by the extension and rotation of the rod. The vibration transmission path includes the telescopic movement of the rod and three rotations and four routes. The telescopic movement is mainly controlled by the actuator. When the rotation stiffness of the elastic hinge is not zero, the two paths of expansion and rotation are coupled. Only when the rotation stiffness is zero can decoupling be realized. Although the hinges seen so far have been elastically designed to reduce the Rotational stiffness but there is still a large gap

[0010] 4. The distance between the rotation centers of the elastic hinges on the upper platform is large, making it difficult to achieve decoupling

[0011] According to the decoupling design of the six-bar vibration isolation platform in the Stewart configuration, the six bars are divided into three groups, and the two bars in each group are perpendicular to each other and are connected to the same point as the upper platform through elastic hinges. Asana, the two poles in each group can be perpendicular to each other, but the common point connection with the upper platform cannot be achieved alone, and the entire six-pole platform cannot be decoupled

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