Non-momentum wheel satellite platform based on magnetic buoyancy device control system

Abstract

The invention discloses a non-momentum wheel satellite platform based on a magnetic buoyancy device control system. The non-momentum wheel satellite platform comprises a static cabin, a movable cabin and magnetic buoyancy devices, wherein a permanent magnet is arranged on each magnetic buoyancy device; the static cabin is connected with the magnetic buoyancy devices through the movable cabin; the static cabin comprises a load cabin body, a payload base, an attitude sensor, two gyroscopic sensors and a platform electronics sensor, wherein the load cabin body is fixed to the bottom of the static cabin; the platform electronics sensor is fixed to the static cabin; the two gyroscopic sensors are fixed to the surface of the load cabin body; and the attitude sensor is fixed to the right side of the load cabin body. The non-momentum wheel satellite platform based on the magnetic buoyancy device control system disclosed by the invention has the advantages of being low in cost, high in accuracy, long in life, and high in reliability; and the requirements of subsequent development of astronautical missions of comprehensive remote sensing to ground, communication, navigation, space science and the like can be better met.

Description

technical field

[0001] The invention relates to a satellite platform and relates to a momentum wheel-free satellite platform based on a magnetic buoyancy device control system. Background technique

[0002] In the future, high-performance aerospace equipment requires attitude pointing accuracy and stability to be two orders of magnitude higher than the current level. The vibration of flexible accessories such as large solar panels of traditional satellites and the micro-vibration of actuators such as flywheels and gyroscopes are important reasons for reducing the accuracy and stability of attitude pointing.

[0003] Traditionally, there are mainly three suppression methods for the vibration of satellite flexible accessories and movable parts: passive vibration isolation, active vibration isolation and active-passive hybrid vibration isolation, but these methods cannot meet the requirements of ultra-high precision control of future spacecraft. A master-slave non-contact ultr...

Examples

Embodiment Construction

[0016] The preferred embodiments of the present invention are given below in conjunction with the accompanying drawings to describe the technical solution of the present invention in detail.

[0017] Such as figure 1 As shown, the present invention is based on the non-momentum wheel satellite platform of magnetic buoyancy device control system and comprises static cabin 1, dynamic cabin 2 and magnetic buoyancy device 3, and magnetic buoyancy device 3 is provided with a permanent magnet 9, static cabin 1 and magnetic buoyancy device 3 are connected through the dynamic cabin 2. The static cabin 1 includes the load cabin body 4, the payload base 5, the attitude sensor 6, the gyro sensor 7, and the platform electronics sensor 8. The load cabin body 4 is fixed at the bottom of the static cabin 1. A platform electronics sensor 8 is fixed on the cabin 1, two gyro sensors 7 are fixed on the surface of the load cabin body 4, an attitude sensor 6 is fixed on the right side of the load c...

technical field

[0001] The invention relates to a satellite platform and relates to a momentum wheel-free satellite platform based on a magnetic buoyancy device control system. Background technique

[0002] In the future, high-performance aerospace equipment requires attitude pointing accuracy and stability to be two orders of magnitude higher than the current level. The vibration of flexible accessories such as large solar panels of traditional satellites and the micro-vibration of actuators such as flywheels and gyroscopes are important reasons for reducing the accuracy and stability of attitude pointing.

[0003] Traditionally, there are mainly three suppression methods for the vibration of satellite flexible accessories and movable parts: passive vibration isolation, active vibration isolation and active-passive hybrid vibration isolation, but these methods cannot meet the requirements of ultra-high precision control of future spacecraft. A master-slave non-contact ultr...

Examples

Embodiment Construction

[0016] The preferred embodiments of the present invention are given below in conjunction with the accompanying drawings to describe the technical solution of the present invention in detail.

[0017] Such as figure 1 As shown, the present invention is based on the non-momentum wheel satellite platform of magnetic buoyancy device control system and comprises static cabin 1, dynamic cabin 2 and magnetic buoyancy device 3, and magnetic buoyancy device 3 is provided with a permanent magnet 9, static cabin 1 and magnetic buoyancy device 3 are connected through the dynamic cabin 2. The static cabin 1 includes the load cabin body 4, the payload base 5, the attitude sensor 6, the gyro sensor 7, and the platform electronics sensor 8. The load cabin body 4 is fixed at the bottom of the static cabin 1. A platform electronics sensor 8 is fixed on the cabin 1, two gyro sensors 7 are fixed on the surface of the load cabin body 4, an attitude sensor 6 is fixed on the right side of the load c...

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