一种2U立方星构型
By designing the layout of the main frame structure, solar panels, and antenna components, the problem of utilizing the launch vehicle's envelope space in the 2U CubeSat configuration was solved, resulting in a stable and reliable satellite configuration that meets the requirements for on-orbit flight and antenna field of view.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- AEROSPACE DONGFANGHONG SATELLITE
- Filing Date
- 2023-10-26
- Publication Date
- 2026-07-17
AI Technical Summary
How to design a more reasonable 2U CubeSat configuration to maximize the use of the launch vehicle's available envelope space, improve the satellite's carrying capacity, and meet the requirements for on-orbit flight.
The design incorporates a main frame structure combined with integrated and deployable solar panels, UV deployable antennas, GNSS antennas, and other components. It integrates electronic circuit boards using a stacked and control structure and achieves satellite-rocket separation through drawer-type installation, thus meeting the satellite's power supply, data transmission, and field of view requirements.
It achieves a stable and reliable satellite configuration, meets the stiffness and strength requirements during the launch flight phase, makes full use of the available envelope space of the launch vehicle, ensures the field of view requirements of antennas and sensitive devices, and has broad application and promotion value.
Smart Images
Figure CN117755517B_ABST