Differential air-floating vertical control dual-supersatellite platform ground simulation equipment

Abstract

The invention provides a ground simulation device for a double supersatellite platform based on differential air-floating vertical control, which belongs to the field of spacecraft physical simulation. The air bearing realizes the X and Y degrees of freedom movement of the air bearing platform in the load compartment and the air bearing platform in the platform cabin. The supporting column forms an air floating structure through the throttle hole set on the supporting column and the air supply of the horizontal moving platform, and realizes the support column. Air suspension support, vertical guidance and vertical upward pressure control drive; through the throttle hole set on the air bearing guide thrust plate, the vertical guidance of the support column and the vertical downward pressure control drive are realized, thereby realizing the The differential air bearing vertical motion control of the support column has the advantages of non-contact support drive with six degrees of freedom, high stability and fast response, and can be used for attitude simulation, large swing angle maneuvering characteristics and dynamic imaging of dual super satellite platforms Ground verification, etc.

Description

technical field [0001] The invention relates to the field of spacecraft physical simulation, in particular to a ground simulation device for a dual supersatellite platform with differential air-floating vertical 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 document 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 is seriously serious. The response frequency and stability of the platform system are weakened; 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 swing degree of freedom devices realizes the transportation and installation of six degrees of freedom for heavy equipment, but the vertical movement, front and rear flip, and left and right swing mechanisms in the air floatation vehicle all use direct contact motion guide rails, which in turn bring greater friction. Unable to 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 is realized by means of a spherical air bearing, three planar air bearings and a lifting column assembly The six-degree-of-freedom movement of the platform, but 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 will be caused by the elastic deformation of the steel wire. Low accuracy, long settling time

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