Adaptive Thermal Control Coating for Radiation Hardening of Spacecraft

The purpose of this SBIR phase I proposal is to design and demonstrate the feasibility of processing the adaptive thermal control material system (TCMS) that is radiation hardened. Through this proposal the engineered TCMS for the space craft protection is envisioned for the needed survivability and better protection of the space assets and the investments. The goal here is to develop an adaptive TCMS that will protect spacecraft structures and payload electronics from high flux radiation doses from the natural solar storm induced events and possible manmade nuclear threats in a given orbit. The new TCMS designs as well as the processing approaches can provide the usual TCMS functions in reliable and space stable manner, plus a charge storage coating to meet the desired goal, where one can adapt to accommodate high dose of electron flux by storing and dissipating the charges per the designed time constants chosen for the material design. Under this new suggested approach, the adaptive TCMS and ESD capable thermal control material system is allowed to accumulate as much charge as possible through a designed storage mechanism with the goal of maintaining surface voltage to acceptable small values (< 10 volts say), and with possible elimination of the dielectric breakdowns, and the electrical discharges. To fulfill this goal of the solicitation, a TCMS design shall provide good passive thermal control performance by providing: low space stable Solar Absorbtance, & high thermal emittance, good adhesion to various technologically important substrates and thermal cycling resistance for the needed operational temperature limits set by the mission orbital needs, along with needed good electrical properties to assure low acceptable surface charging using currently available second surface mirror technology in conjunction with the suggested transparent space stable multilayer ceramic capacitor stack for the charge storage. Finally, the suggested material design can meet reliability needs of the space environment for a typical ten year mission lifetime and conform to the mission space qualification requirements including high vacuum, microgravity, radiation, atomic oxygen, low out gassing, and high launch loads, because most of the suggested material components are chosen from the materials that have been either already qualified as space materials or have been flown on some missions for other intent. BENEFIT: MILITARY APPLICATION: Military satellites are required to survive natural radiation that affects their operation. This work will enhance the capabilities of future satellites to meet this requirement. COMMERCIAL APPLICATION: Commercial satellites must be capable of surviving natural radiation that exists in the space environment. This work will enhance the ability of commercial satellites to survive natural radiation.