A quasi-zero stiffness air flotation gravity unloading device
An unloading device, quasi-zero stiffness technology, applied in the simulation device of space navigation conditions, transportation and packaging, space navigation equipment and other directions, can solve the problems of complex system, achieve the effect of large bearing capacity and avoid damage
Active Publication Date: 2018-05-04
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology
These two devices both use active control to obtain constant force output, so a large number of accessories such as motors and sensors need to be added, and the system is relatively complicated.
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[0017] A quasi-zero stiffness air flotation gravity unloading device, which includes: porous air feet 101, height adjustment rods 102, transfer platforms 103, buckling beam support rods 104, buckling adjustment jackscrews 105, hinge blocks A106, buckling beams 107, Load platform 108 , coil spring 109 , hinge block B110 , bearing end cover A111 , linear bearing 112 , bearing end cover B113 and spring lock nut 114 .
[0018] A quasi-zero-rigidity air-floating unloading device has a symmetrical structure. The porous air foot 101 is connected to the air source, and an air film is formed between the test table surface to reduce sliding friction. One end of the height adjustment rod 102 is connected with the porous gas foot 101 by thread connection; the other end of the height adjustment rod 102 is connected with the transfer platform 103 by a thread connection; one end of the buckling beam support rod 104 is connected with the transfer platform 103, The connection method is screw c...
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Disclosed is a quasi-zero stiffness gas floating gravity discharge device. One end of each buckling beam support rod is fixedly connected with a switching platform, and the other end of each buckling beam support rod is movably connected with a corresponding hinge block A; one end of each buckling beam is inserted into a hollow hole in the corresponding hinge block A, and the other end of each buckling beam is inserted into a hollow hole in a corresponding hinge block B; buckling adjusting jackscrews are fixedly connected with the hinge blocks A, and the buckling adjusting jackscrews exert axial compressive load on the buckling beams; the hinge blocks B are movably connected with a load platform; a cylindrical guide part of the load platform penetrates holes in a bearing end cover A, a switching platform and a bearing end cover B in sequence, a linear bearing is located between the cylindrical guide part of the load platform and the wall hole of the switching platform, a spring lock nut is located at the underside of the switching platform and fixedly connected with the cylindrical guide part of the load platform, a spiral spring sleeves the cylindrical guide part of the load platform between the switching platform and the load platform, one end of the spiral spring is connected with the lower surface of the load platform, the other of the spiral spring is connected with the upper surface of the bearing end cover A, and the spiral spring is at a compressed state.
Description
technical field [0001] The invention belongs to the field of gravity unloading for ground tests of space mechanisms, in particular to a quasi-zero-rigidity air-floating gravity unloading device. Background technique [0002] In order to ensure the reliability of the in-orbit operation of the deployment mechanism on the spacecraft, the deployment test and dynamic test of the mechanism must be carried out on the ground. However, the spacecraft is in a zero-gravity state in orbit, while the ground is in a gravity environment. Therefore, the gravity unloading technology is a difficult problem that must be overcome in the ground test of spacecraft products. [0003] At present, there are two most commonly used gravity unloading technologies at home and abroad, one is the long rope suspension type, and the other is the air flotation type. [0004] In terms of long-rope suspension gravity unloading technology, in the "Design Method for Quasi-Zero Stiffness Non-linear Suspension S...
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IPC IPC(8): B64G7/00
CPCB64G7/00
Inventor 黎彪刘海平王兴泽盛聪张从发李潇刘冬徐燕菱从强
Owner BEIJING INST OF SPACECRAFT SYST ENG