Owing to manufacturing errors, the surface accuracy of a mesh reflector antenna decreases after fabrication compared with the design results; thus, it is necessary to adjust the surface before launching. The adjustment is faced with 3 problems: First, the prototype physical model is unknown; i.e., the physical model with manufacturing errors is different from the mathematical model. Second, the adjustment target is difficult to determine; i.e., the antenna is adjusted on ground but works in space; there is a problem of an inconsistent adjustment target due to the different environments. Third, the efficiency is low; i.e., the larger the aperture is, the more complex the structure is and the longer the adjustment time is; the efficiency restricts the antenna development cycle. To address these problems, a surface adjustment method considering the space–ground consistency of the adjustment target is proposed in this study. First, the characteristics of the cable-net structure were analyzed, and a method to modify the mathematical model by measuring part of the cable force of the physical model is proposed, which reduces the difference between 2 models. Second, based on the sensitivity matrix, an adjustment method for selecting key cables is proposed. Third, the influence of gravity and temperature on the surface was analyzed, and a preadjustment method considering the space–ground consistency of the adjustment target is proposed. Finally, simulation and prototype experiments were conducted to verify the accuracy and efficiency of the proposed methods, which can effectively support the ground preadjustment of a large-aperture mesh reflector antenna and improve the surface accuracy on orbit.

Continuously improving the performance of satellite antennas has always been one of the goals in the field of antennas. However, the contradiction between the payload volume and mass of the launch vehicle and the antenna size makes achieving this goal challenging. In this article, we propose a deployable helical antenna that can be mounted on a CubeSat. It achieves controllable deployment and retraction of a large-sized helical antenna using bistable composite slit tube (BCST) and enhances the overall stiffness of the antenna after deployment using tensioned strings. Compared to existing spaceborne helical antennas, the larger deployment size improves the gain the antenna can provide, while the smaller stowage volume allows it to be carried on a CubeSat. Then, the structural performance of the antenna is analyzed, and the results show that this design susbstantially enhances the structural stiffness of the antenna, achieving a fundamental frequency of 6.87 Hz. It also reduces the deformation of the antenna, minimizing performance fluctuations caused by disturbances. This design enables a 2-m helical antennas to be installed on small satellites, expanding the use cases for helical antennas. Moreover, this controllable deployment method allows the helical antenna to achieve additional functionalities.