Attitude Ground Simulation Simulator for Double Super Satellite Platform Based on Aeromagnetic Composite Control

Abstract

The invention provides a double supersatellite platform attitude ground simulation simulator based on aeromagnetic composite control, which belongs to the field of spacecraft physics simulation. The floating bearing realizes the X and Y degrees of freedom movement of the air-floating platform in the load compartment and the air-floating platform in the platform cabin. The supporting column is realized by the magnetic levitation supporting the floating magnetic steel set on the supporting column and the magnetic levitating fixed magnetic steel set on the horizontal moving platform. The non-contact gravity compensation support with the horizontal mobile platform realizes the non-contact force control and Z freedom movement between the support column and the horizontal mobile platform through the Lorentz motor composed of the Lorentz motor magnet and the Lorentz motor coil, and then The six-degree-of-freedom motion of the rotating platform is obtained, which has the advantages of six-degree-of-freedom non-contact support, high stability, and fast response. It can be used for attitude simulation of dual supersatellite platforms, maneuvering characteristics at large swing angles, and ground verification of in-motion imaging.

Description

technical field [0001] The invention relates to the field of spacecraft physical simulation, in particular to a dual supersatellite platform attitude ground simulation simulator based on aeromagnetic composite control. Background technique [0002] With the rapid development of science and technology, space-to-earth observation remote sensing tasks are gradually developing towards high spatial resolution and high efficiency, and the high spatial resolution and high efficiency of observation remote sensing mainly depend on the pointing accuracy, stability and agile maneuvering of satellite loads performance. In traditional satellite platforms, flexible accessories such as large solar panels and movable parts such as flywheels, gyroscopes, and drive mechanisms are the main reasons that affect the satellite load attitude pointing accuracy, stability, and agile maneuverability. [0003] In traditional satellite design, the load cabin is fixedly connected to the platform cabin, ...

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Problems solved by technology

However, the hydraulic drive structure used in this patent has a large viscous damping interference due to the high viscosity of the hydraulic oil. At the same time, it adopts an open control method in which the one-way hydraulic cylinder propulsion is balanced with the gravity of the air-floating motion platform, which seriously weakens the The response frequency and stability of the platform system are improved; the patent document CN104875907A mentions a six-degree-of-freedom air suspension vehicle for transporting and installing heavy equipment in a narrow space. The combination of degree-of-freedom devices realizes the six-degree-of-freedom transportation and installation of heavy equipment, but the vertical movement, front and rear flipping, and left and right swing mechanisms in the air float vehicle all use direct contact motion guide rails, which in turn bring greater friction and cannot Meet the ground simulation requirements of the micro-disturbance moment environment of the spacecraft; a six-degree-of-freedom air-floating motion simulator in the patent document CN105321398A realizes the platform by means of a spherical air bearing, three planar air bearings and a lifting column assembly However, the lifting column assembly in this patent connects the outer support column and the balance weight in the form of a steel wire rope and a pulley block, which will cause large friction interference, and the vertical motion control accuracy will be caused by the elastic deformation of the steel wire. low, stable time

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