Cone-prism transition type honeycomb interlayer bearing cylinder structure
A honeycomb interlayer and bearing tube technology, which is applied in the directions of artificial satellites, astronautical equipment, and astronautical aircraft, can solve the problems of redundancy, inapplicability, and failure to meet the main load bearing capacity, and achieve a simple and reliable force transmission path. The effect of improving the carrying capacity and facilitating on-orbit maintenance operations
Pending Publication Date: 2022-01-11
BEIJING INST OF SPACECRAFT SYST ENG
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[0003] The existing satellite configuration has the following disadvantages: 1. The maximum main load bearing capacity of the top surface of the central tube satellite structure is about 3000kg, which does not meet the main load carrying capacity of more than 6000kg; 2. The instrument and equipment inside the box structure transmit force The path is indirectly transmitted to the central load-bearing cylinder through the structural plate, which is relatively redundant; 3. The equipment is installed inside the box and is not suitable for on-orbit maintenance operations
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[0027] In order to enable those skilled in the art to better understand the solutions of the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application.
[0028] In order to realize the satellite platform structural configuration system that can meet the large load, the instruments and equipment are directly installed on the side wall surface of the load-bearing cylinder, and can be maintained on orbit, such as figure 1 As shown, a cone-prism transitional honeycomb sandwich load-bearing cylinder structure includes a star-arrow docking frame 1, a honeycomb sandwich cone shell structure 2, a transition frame 3, a load installation frame 8, and a plurality of honeycomb panels, wherein the honeycomb panels The number N of blocks satisfies: N is an even number not less than 8, and N honeycomb panels can form a regular N-gon.
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The invention provides a cone-prism transition type honeycomb interlayer bearing cylinder structure. The cone-prism transition type honeycomb interlayer bearing cylinder structure comprises a satellite-rocket butt joint frame, a honeycomb interlayer conical shell structure, a transition frame, a load mounting frame and a plurality of honeycomb plates. In order to further improve the main load bearing capacity of the satellite, optimize the force transmission path of the main structure and be suitable for on-orbit maintenance operation, the satellite structure adopts the design of integrating main force bearing and equipment installation, namely, the main force bearing structure adopts a regular polygon prism honeycomb wall plate structure configuration form, the radius of the bearing cylinder can be increased as much as possible under the condition that the mass of the bearing cylinder is fixed, so that the stress radius is increased, the structural instability is avoided, and the bearing cylinder can bear the main load of more than 6000 kg on the top surface of the bearing cylinder; meanwhile, the honeycomb prism wall plate is transited through the honeycomb interlayer conical barrel, and butt joint with a carrier rocket is facilitated.
Description
technical field [0001] The invention belongs to the technical field of mechanical structures, and in particular relates to a cone-prism transition type honeycomb sandwich load-bearing cylinder structure. Background technique [0002] The traditional satellite main structure adopts a box-type configuration formed by a circular load-bearing cylinder + a honeycomb structure plate. The central bearing cylinder is used to bear the main load of the satellite launching section. The bottom surface of the load-bearing cylinder provides the docking interface of the star and arrow, the inner wall provides the storage tank interface, the outer wall provides the honeycomb panel installation interface, and the top surface provides the main load interface. Box-type honeycomb panels are used to install instruments and equipment. [0003] The existing satellite configuration has the following disadvantages: 1. The maximum main load bearing capacity of the top surface of the central tube sa...
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Login to View More IPC IPC(8): B64G1/10B64G1/22
CPCB64G1/10B64G1/22
Inventor 高峰张涛涛石文静张琳许焕宾白刚
Owner BEIJING INST OF SPACECRAFT SYST ENG