Feasibility analysis of solar thermal propulsion system with thermal energy storage

Possessing relatively high specific impulse and moderate thrust levels, solar thermal propulsion (STP) is a promising candidate in spacecraft propulsion system. However, the traditional solar thermal propulsion system suffers from thrust failure in the shadow area, which seriously affects its applicability. In this paper, we investigate feasibility of regenerative solar thermal propulsion system (RSTP) incorporating thermal energy storage, which can effectively overcome unmatched synchronous working time and illumination time. A numerical model for RSTP considering the whole energy transfer process from light concentrating, heat storage, to thrust generation is built, which is verified by experiment measurements with relative errors less than 15 %. The result shows that the maximum time to complete heat storage is about 4000 s, which is within the illumination time for low Earth orbit. In the solar eclipse region, the thrust (Ft) and the specific impulse (Isp) of the system increase with the propellant flow rate, which can reach about 2 N and 690 s, respectively. What's more, the system can operate for around 100 s continuously at the maximum thrust in the shadow area. This work provides alter-native approaches for microsatellite propulsion with high specific impulse, high thrust, and continuous operation despite presence of solar eclipse.(c) 2022 COSPAR. Published by Elsevier B.V. All rights reserved.

Automated summary

This paper investigates the feasibility of a regenerative solar thermal propulsion system (RSTP) incorporating thermal energy storage to overcome the thrust failure issue in the shadow area. A numerical model is built to consider the entire energy transfer process and is verified through experimental measurements. The results show that the system can complete heat storage within the illumination time for low Earth orbit and achieve high thrust and specific impulse in the solar eclipse region. Additionally, the system can operate continuously in the shadow area for a certain duration. This work provides alternative approaches for microsatellite propulsion with high specific impulse, high thrust, and continuous operation.