A motor has an oxidizer injector, the oxidizer injector is mainly suitable for using in a combustion chamber, the oxidizer injector has a body having a first runner assembly and a second runner assembly arranged along an axis, the first runner assembly injects oxidizer into the combustion chamber to form a forward swirl, and the second runner assembly injects oxidizer into the combustion chamber to form a reverse swirl, the axial torsion generated by the forward swirl and the axial torsion generated by the reverse swirl counteract each other, so as to solve the problem of axial torsion imbalance in the combustion chamber.

A solid-propellant rocket engine (1) has a casing (2) and a thermal protection (15) internally coating the casing and delimiting a housing (17), which contains a mass of solid propellant (3); the thermal protection has a fixed portion (22) and at least one movable portion (23) that adheres to the mass of solid propellant (3) and can be moved from a back position to a forward position with respect to the fixed portion (22) through a thrust system obtained by pressuring a chamber 31 provided by installing a membrane 32 between the fixed portion 22 and the movable portion 23; the engine is tested by verifying the adhesion of the mass of solid propellant (3) to the movable portion (23) after having moved the movable portion (23) to the forward position by means of a thrust directed from the fixed portion towards the mass of solid propellant (3).

A method for non-destructively determining a mechanical property of a solid rocket motor propellant grain may comprise applying a force to a surface of the solid rocket motor propellant grain, wherein a deformation is formed on the surface of the solid rocket motor propellant grain in response to the applying, and calculating a value of the mechanical property of the solid rocket motor propellant grain based on the deformation. This process may be performed over time to determine a lifespan of the propellant grain.

A method for non-destructively determining a mechanical property of a solid rocket motor propellant grain may comprise applying a force to a surface of the solid rocket motor propellant grain, wherein a deformation is formed on the surface of the solid rocket motor propellant grain in response to the applying, and calculating a value of the mechanical property of the solid rocket motor propellant grain based on the deformation. This process may be performed over time to determine a lifespan of the propellant grain.

Coated Al—Li alloys, such as coated particles of Al—Li alloys, are provided. The coated alloys may be used in solid-rocket propellants. Additionally, methods of making such coated alloys, alloys coated with various methods, and solid-rocket propellants comprising such coated alloys are also provided.

Coated Al—Li alloys, such as coated particles of Al—Li alloys, are provided. The coated alloys may be used in solid-rocket propellants. Additionally, methods of making such coated alloys, alloys coated with various methods, and solid-rocket propellants comprising such coated alloys are also provided.

A solid-propellant rocket engine (1) has a casing (2) and a thermal protection (15) internally coating the casing and delimiting a housing (17), which contains a mass of solid propellant (3); the thermal protection has a fixed portion (22) and at least one movable portion (23) that adheres to the mass of solid propellant (3) and can be moved from a back position to a forward position with respect to the fixed portion (22) through a thrust system obtained by pressuring a chamber 31 provided by installing a membrane 32 between the fixed portion 22 and the movable portion 23; the engine is tested by verifying the adhesion of the mass of solid propellant (3) to the movable portion (23) after having moved the movable portion (23) to the forward position by means of a thrust directed from the fixed portion towards the mass of solid propellant (3).

An insulation precursor composition comprises ethylene propylene diene monomer, an aramid, and a bromine-containing flame retardant. Rocket motors comprising a case, an energetic material within the case, and an insulation material comprising a reaction produce of ethylene propylene diene monomer, an aramid, and a flame retardant comprising bromine are also disclosed. Related precursor compositions are also disclosed.

Apparatus, systems, and methods for enhancing solid propellant performance include seeding combusting energetic material, including solid propellant, with microwave energy at a controlled power and duration.

A rocket engine has: a combustion chamber having a chamber inlet for receiving an oxidizer and a chamber outlet for expelling combustion gases in an environment outside the combustion chamber; a manifold having a manifold inlet fluidly connectable to a source of the oxidizer and a manifold outlet; a catalyst having a catalyst inlet fluidly connected to the manifold outlet and a catalyst outlet; and an injector plate having a injector inlet fluidly connected to the catalyst outlet and an injector outlet fluidly connected to the chamber inlet.