Hoisting device and method for satellite
A lifting device and satellite technology, applied in the field of mechanical structure, can solve the problems of inability to meet the requirements of use, excessive weight of the connection point of the spreader, etc., and achieve the effects of optimizing the layout, improving the bearing capacity, and relieving the bearing pressure.
Active Publication Date: 2020-09-08
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology
However, for satellites up to 9000kg and above, in order to be able to adapt to large lifting loads and ensure sufficient lifting strength, it is also necessary to ensure that the spacecraft structure using honeycomb sandwich panels does not have excessive weight at the connection point of the hanger that cannot be separated, ensuring that the lifting point is high. Bearing-to-mass ratio, the existing lifting joints can no longer meet the use requirements
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[0045] A heavy-duty lightweight lifting device, such as figure 1 As shown, the hoisting device used for satellites includes hoisting points 1-8 and adapter brackets 9-12. Suspension points 1-8 are pre-buried laterally on the upper edge of the north and south decks of the satellite, and 4 are arranged respectively, such as figure 2 shown. One side of the transfer brackets 9-12 is connected with the satellite universal cross hanger, and the other side is connected with two suspension points 1-8. By increasing the number of lifting points 1 to 8, the load capacity of a single lifting point can be reduced to less than 1500kg. And combine it into the final four-point lifting state through the one-to-two adapter bracket 9-12, such as image 3 shown. It realizes that the traditional cross hanger adapts to the 1-8 interfaces of the eight hoisting points of the whole satellite, and solves the problem of lifting large-mass satellites with multiple hoisting points 1-8.
[0046] Lif...
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The invention discloses a hoisting device and method for a satellite and belongs to the technical field of mechanical structures. An eight-point hoisting mode is adopted, a four-point hoisting state is achieved finally through combination by means of a two-in-one adapter-connection support, and the effect that a universal satellite cross-shaped hosting frame adapts to eight hoisting points of thewhole satellite is achieved. The hoisting points are uniformly distributed on a structural plate and are moderately spaced, the edge effect of the four-corner hoisting points and the stress interference between the adjacent hoisting points are avoided, and the bearing capacity of the hoisting points is brought into full play. Connection without additional bending moment is achieved between the hoisting points and the adapter-connection support in a ball pad mode. The hoisting points are in lateral screw connection through large buried parts, the buried parts are in similarly elliptical shape,a bearing stress concentration area is subjected to covering enhancement, repeated thickness changes are adopted, and effective diffusion of concentrated load is guaranteed.
Description
technical field [0001] The invention relates to a lifting device and a lifting method for a satellite, in particular to a multi-lifting point, large-load and lightweight lifting device suitable for a large-mass satellite (the maximum mass exceeds 9000kg), and belongs to the technical field of mechanical structures. Background technique [0002] In the past, the weight of satellites was usually less than 5000kg, and the lifting points of the whole satellite were located on the top of the whole satellite, and the number was usually four. For satellites in the form of honeycomb sandwich structure panels, lifting joints are usually pre-embedded in the honeycomb sandwich structure panels near the lifting point. Transfer of star lifting load. However, with this kind of lifting joint, most of the load of the honeycomb sandwich panel near the lifting point is borne by the side panel in contact with the lifting tool, while the other side panel is less stressed, and a large additiona...
Claims
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IPC IPC(8): B66C1/10
CPCB66C1/10
Inventor 高峰王晓宇石文静邓宇华
Owner BEIJING INST OF SPACECRAFT SYST ENG