Cubesat Solar Panel Deployment Mechanism

Depending on the configuration one or two radios in the cubesat can connect to the antenna system by means of miniature rf connectors.

Cubesat solar panel deployment mechanism. Thanks to its very thin and customisable design it fits on all cubesat structures and subsystems such as isis antenna system. 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. The deployment system relies on a thermal knife composed of one wire and two redundant heating elements per tape. 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. Table 2 also presents examples of various satellites with similar solar panel deployment shapes. Its space qualified cells are provided with extensive characterization and test reports. This deployment mechanism is a part that must be defined by the user because it will be used for mission dependent tasks or other purposes.

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. Cubesats are commonly put in orbit by deployers on the international space station or launched as secondary payloads on a launch vehicle. 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. 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.

The deployment mechanism of the solar panel is one of the main considerations for the shape of the entire cubesat. 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. 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. The panels come in 1 6u size with sun and temperature sensors and other custom options available on request.

A unique solar panel deployment mechanism using shape memory alloy sma for cubesats was developed by perez. The deployment system is based on a plastic fiber wire and thermal cutters guaranteeing a suitable level of reliability. G sab deployment tumbles the cubesat requiring long stabilization whereas xsas can deploy without inducing additional rotations upon the satellite.