Abstract: An isolable double-walled insulation tank for a launch vehicle includes a hollow open cylinder part having upper and lower end portions that are open in an upright state; an upper cap part for sealing the upper end portion of the open cylinder part; and a lower cap part for sealing the lower end portion of the open cylinder part. The open cylinder part includes a flat plate part having a flat outer peripheral surface; an uneven part slidably fitted and coupled to the flat plate part; and a plurality of load-dispersing spaces which are ring-shaped according to a portion of the uneven part being spaced from the flat plate part, and which are arranged to be spaced apart in the height direction of the open cylinder part.

Abstract: A roll control thruster controls the attitude of a launch vehicle by using the oxidizer filled in an oxidizer tank, and includes: a thruster tank that is charged using a portion of the oxidizer stored in the oxidizer tank; a thruster line that is branched from the thruster tank and forms a supply path of the oxidizer stored in the thruster tank; a thruster valve that is provided in the thruster line and opens and closes the thruster line or adjusts the opening degree of the thruster line; a thruster module that is connected to the thruster line and injects the oxidizer, supplied via the thruster line, in order to control the attitude of the launch vehicle; and a thruster control module that controls the operation of the thruster valve and the supply of oxidizer to the thruster module.

Abstract: An electrical umbilical system for a space launch vehicle, using an electromagnet includes a connection module which is provided to a launch vehicle unit flyable by means of thrust; and an umbilical unit which is provided to a tower unit supporting the launch vehicle unit so as to stand upright, and which is capable of being electrically connected to the connection module. The umbilical unit includes a supply module which is capable of electrically connected to the connection module; a connection drive module which is coupled to the tower unit and connects the supply module to the connection module; a weight body which is coupled to the tower unit so as to be vertically movable; a drive line which connects the supply module and the weight body; and a guide roller which is rotatably coupled to the tower unit and supports the drive line.

Abstract: Proposed is a hybrid rocket engine using an electric motor-driven oxidizer pump, the hybrid rocket engine including: an oxidizer tank configured to store the oxidizer; an oxidizer pump configured to pressurize the oxidizer by being connected to the oxidizer tank through a first oxidizer supply line; a drive unit including an electric motor configured to drive the oxidizer pump and a battery configured to supply power to the electric motor; an auxiliary oxidizer line configured to guide the oxidizer from the oxidizer tank to the electric motor to cool the electric motor; an oxidizer recirculation line configured to recharge oxidizer vapor, generated through heat exchange between the electric motor and the oxidizer, to the oxidizer tank, thereby pressurizing an inner side of the oxidizer tank; and a combustion chamber configured to combust the oxidizer and fuel by being connected to the oxidizer pump through a second oxidizer supply line.