The present invention relates to a liquid rocket engine impact load structural response prediction method. The present invention aims to provide the liquid rocket engine impact load structural response prediction method in order to solve the technical prob...

The engine has an igniter comprising a catalyst unit (5) in a form of an electrical heated cartridge or pill made of ceramic or metallic material. The catalyst unit is provided with a surface coating of polycrystalline platinum. The catalyst unit is arrang...

The engine has a combustion chamber (3), where a control device controls a mass flow to the chamber. The engine is operated with gaseous fuel, which contains reacting gas i.e. vapor of cryogenically stored liquid gas. The liquid gas is liquid hydrogen and ...

A propulsion device operated in a bi-liquid mode uses a safe hydrogen peroxide as oxidizer (30) and yet has a large thrust and high response performance. A preheated net (18) is provided in a combustion chamber (14). Both of an oxidizer supply means (10) a...

A rocket engine suitable for using for an educational program uses a liquid phase propellant (102A) having a predetermined boiling point and a heating substance (102B) having a temperature higher than the boiling point. The engine has an inner wall (103B) ...

The engine (1) for the propulsion of the upper stage of a space launcher has a longitudinal axis (L-L) and comprises a central core (7) and a functional lateral cone shaped surface (9) whose base (10) is located on the side of the engine. Pressurized gas f...