Prestressed thin-walled conical multi-rod parallel-parallel space deployment mechanism for spacecraft

Abstract

The invention provides a spacecraft prestressed thin-walled conical multi-rod parallel-parallel space deployment mechanism, which is characterized in that it is applied to the field of spacecraft, including spacecraft, thin-walled rods, loads, load brackets, speed-limiting slots, Shaft and flange. The thin-walled rod is tapered as a whole, the end of the thin-walled rod with a larger diameter is a large end, and the end with a smaller diameter is a small end. A rotating shaft is installed in the semi-enclosed space surrounded by the load bracket, and there is also a speed-limiting slot on the load bracket, and the speed-limiting slot is a bar-shaped gap of equal width opened on the load bracket. The large end of the thin-walled rod is fixed on the spacecraft through the flange, and the small end of the thin-walled rod is fixed on the load through the speed limiting slot. The flattened thin-walled rods achieve a high curling ratio of the thin-walled rods, enabling the spacecraft to obtain a large-sized unfolded structure under the limitation of an effective folded size space. And it can complete self-stretching without electric power, chemical energy, pneumatic and other power and driving devices.

Description

technical field [0001] The invention relates to a large-scale space deployment mechanism of a spacecraft, which is widely used in large-scale deployment antennas, solar panels, space manipulators, space platforms, etc., and specifically relates to a prestressed thin-walled conical multi-rod parallel-parallel space deployment mechanism for spacecraft The invention is especially suitable for a large-scale antenna unfolding mechanism and belongs to the field of spacecraft. Background technique [0002] In recent decades, with the rapid development of the spacecraft field, the application requirements for large space antennas have become more and more urgent, and it is hoped that the size of the antenna will become larger and larger. Due to the limitation of the carrying space of the aerospace vehicle, the antenna must be folded and stored in the fairing during the launch phase. After the spacecraft enters orbit, the antenna will be unfolded to the working state by its own power...

AI Technical Summary

Problems solved by technology

However, with the increase of component size, the reduction of structural weight, the weakening of stiffness and the increase of operating speed, the elastic deformation of components has become a factor that cannot be ignored, and often becomes a key factor for the normal operation of space antennas.

Various types of deployable antennas currently in use and being developed are various in terms of their structures, including planar array deployable antennas, integral deployable antennas, radial rib deployable antennas, and ring rib deployable antennas. If Without a high degree of operational reliability, it is difficult to deploy the antenna accurately, and the consequence will be that the satellite cannot be applied and fails after launch

The space structure is becoming larger and more complex, but the storage space for the carrying mass and payload of the spacecraft is limited, and the quality and size of the thin-walled rods of the rigid spacecraft will be greatly restricted

Images