公开(公告)号：US20190153981A1

公开(公告)日：2019-05-23

申请号：US16184209

申请日：2018-11-08

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Jongwon CHAE

IPC: F02K9/97

Abstract: The present invention relates to a thruster having a combustion chamber and a nozzle portion using a honeycomb structure, and more particularly, to a thruster having a combustion chamber and a nozzle portion using a honeycomb structure in which a wall reinforcement including honeycomb structures and heat-resistant paints provided in the honeycomb structures are bonded to a wall constituting a combustion chamber portion and a nozzle portion to increase durability and strength against a mechanical load such as vibrations, impact, or the like, due to combustion of a high-temperature and high-speed propellant and a heat-fluid load such as heat transfer and a temperature load, and a thickness of the wall of the existing combustion chamber and nozzle portion may thus be decreased, such that a weight of the thruster may further be decreased and durability of the wall may be increased.