An electrothermal deployment system may be configured for controlled release of various apparatus from their prelaunch stowage positions in small satellites. The deployment system includes a fusible line secured to a structural component of the satellite, as well as to various deployable apparatus secured to, within, or on the satellite. The deployable apparatus may include items such as solar panels and antennas. The deployment system includes an electrically resistive element such as a burn bar formed of a cylinder or tube, including a resistor pad overlying and/or incorporated within an exterior surface of the burn bar. The burn bar may be coupled to an electrical circuit configured to heat the resistor for the purpose of melting the fusible line secured in direct contact therewith, thus causing the fusible line to break to cause deployment. The fusible line is configured to remain in secure contact with the resistor until apparatus deployment.