Design of an origami structured deployable s-band helical antenna for 6U cubesats

Abstract

This study covers the design, simulations, tests, and prototyping process of a deployable S-band helical antenna for 6U CubeSats. The antenna was developed to provide high gain and circular polarization. Furthermore, compactly stored and reliably deployed within the satellite and designated to operate in the 2- 4 GHz frequency range with 2267 MHz center frequency. The antenna has a target gain of 10 dB which is a promising RF characteristic to achieve efficient satellite communication. Factors such as assembly, deployment mechanism, cost, weight, placement on the CubeSat configuration are examined and explained through the design decisions. Silver-plated aluminum, gold-plated titanium and copper were considered as conductive materials in the design, while polyamide film is preferred as mechanical structure materials during material selection process. The deployment mechanism was designed to be reliably deployed with the contribution of potential energy stored in the helical wire and origami structure. The relationship between the wire antenna and is Kapton® 300 HN polyimide film as a foldable origami-based structure, which increases its compactness and deployability is developed. To verify the RF performance of the wire design, electromagnetic simulations were performed and analyzed in ANSYS HFSS software such parameters as radiation pattern, impedance matching and return loss (S11). The feasibility of the deployment mechanism was provided and evaluated with mechanical and kinematic modeling conducted in CATIA software. Then, 3D printed prototypes were produced and tested with spectrum analyzer and, after that, in an anechoic chamber. Tests were applied to examine the antenna operability and solidity in space environment. The results of the study are obtained that the helical antenna provides high gain and circular polarization and it is a suitable candidate for CubeSat communication systems for deep space and Earth observation missions. In addition to developing a good balance between size, gain and directivity, it is emphasized that a reliable deployment mechanism is a critical design component. As future work, alternative structures such as quadrifilar helix (QHA) or log-periodic antennas are also planned to be considered and compared in terms of performance optimization, producing the antenna as a space-qualified product to be launched into space after conducting necessary environmental testing such as TVAC (thermal vacuum chamber) and considering the different kinds of conductive materials to conduct better RF performance.