Cubesat Solar Panel Deployment Mechanism

Cubesats have a mass of no more than 1 33 kilograms 2 9 lb per unit and often use commercial off the shelf cots components for their electronics and structure.

Cubesat solar panel deployment mechanism. The deployment mechanisms designed for the albus are an attempt to eliminate all deployment consumables or even human factors like winding strap wire to allow a reliable and resettable means to deploy structures on a cubesat. The panels come in 1 6u size with sun and temperature sensors and other custom options available on request. Table 2 also presents examples of various satellites with similar solar panel deployment shapes. Other types of deployables flown on cubesats include deployable solar panels that fold up along the sides of the cubesat as well as deployable antennas.

Cubesats are commonly put in orbit by deployers on the international space station or launched as secondary payloads on a launch vehicle. The deployment mechanism of the solar panel is one of the main considerations for the shape of the entire cubesat. Table 2 shows the mission for each satellite being operated and the shape of the solar panel deployment. The feasibility of using pogo pins as a solar panel s release mechanism was successfully verified through validation tests.

The deployment system is based on a plastic fiber wire and thermal cutters guaranteeing a suitable level of reliability. Depending on the configuration one or two radios in the cubesat can connect to the antenna system by means of miniature rf connectors. G sab deployment tumbles the cubesat requiring long stabilization whereas xsas can deploy without inducing additional rotations upon the satellite. The exa dsa 1a titanium deployable solar array for 1u is the entry level product of a family of deployable solar arrays based on artificial muscles for cubesats in the range of 1u to 6u.

That work introduced the use of a niti based sma in conjunction with an al bushing to create a holding and release function on the mechanism which secures mechanical releases in a nonexplosive manner increasing the probability of success while eliminating. A unique solar panel deployment mechanism using shape memory alloy sma for cubesats was developed by perez. Thanks to its very thin and customisable design it fits on all cubesat structures and subsystems such as isis antenna system. Its space qualified cells are provided with extensive characterization and test reports.

Rf phasing balun circuitry ties the antennas together in a turnstile configuration. The arrays are composed by 5 panels 3 on top 2 on bottom that attached to the cubesat structure just as another solar panel and once in orbit deploys to full extension includes deploy and release contact sensors and custom options are available on requests like sun and temperature sensors 7 panel. A prototype of the system has been realized for a 3u cubesat consisting of two deployable solar panel systems made of three solar panels each for a total of six deployed solar panels.