A rocket motor for a gun-fired projectile is configured stiffen the burnable propellant in the rocket motor during burning and/or protect the rocket motor from the pressure that occurs during firing of the projectile from the gun. The rocket motor may include a rigid structure that is integrated into the burnable propellant grain to stabilize the burnable propellant grain during burning of the burnable propellant grain. The rigid structure has a matrix or truss-like shape that extends into the depth of the burnable propellant grain. The rocket motor may include a baffled end cap that covers a nozzle of the rocket motor. The end cap defines a baffled path through the end cap to dampen gas flow into the nozzle and prevent particles of the gun propellant from entering the rocket motor. A rocket motor may implement the rigid structure or the baffled end cap, or both structures.

A solid rocket motor includes a propellant grain structure defining an axial bore and a vortex inducing feature.

A solid rocket motor includes a propellant grain structure defining an axial bore and a vortex inducing feature.

A hybrid-like liquid fuel motor (the motor) may include a port surrounded by a wall. Surrounding the wall are a plurality of chambers and segmented walls to separate the chambers. In some instances, a single helix chamber may surround the wall, and may operate similar to that of a segmental chamber. During operation of the motor, gas flows from one end of the port to another end of the port. As the walls surrounding the port begin to disintegrate, liquid fuel within chambers begins to begin to mix with the flow of gas. As the segmented walls between the chambers begin to disintegrate, liquid from the other chambers begin to mix with the flow of gas, creating a metering of the liquid fuel.

A hybrid-like liquid fuel motor (the motor) may include a port surrounded by a wall. Surrounding the wall are a plurality of chambers and segmented walls to separate the chambers. In some instances, a single helix chamber may surround the wall, and may operate similar to that of a segmental chamber. During operation of the motor, gas flows from one end of the port to another end of the port. As the walls surrounding the port begin to disintegrate, liquid fuel within chambers begins to begin to mix with the flow of gas. As the segmented walls between the chambers begin to disintegrate, liquid from the other chambers begin to mix with the flow of gas, creating a metering of the liquid fuel.

Apparatus, methods and computer programs are provided. In one example, an apparatus is a rocket motor, comprising: a casing having a length dimension, a width dimension and a depth dimension, wherein the length dimension is greater than the width dimension and greater than the depth dimension; and propellant, located inside the casing, arranged to generate a force in a direction that is substantially perpendicular to the length dimension of the casing.

Apparatus, methods and computer programs are provided. In one example, an apparatus is a rocket motor, comprising: a casing having a length dimension, a width dimension and a depth dimension, wherein the length dimension is greater than the width dimension and greater than the depth dimension; and propellant, located inside the casing, arranged to generate a force in a direction that is substantially perpendicular to the length dimension of the casing.

A solid rocket motor includes a propellant grain structure defining an axial bore and a vortex inducing feature.

A hybrid-like liquid fuel motor (the motor) may include a port surrounded by a wall. Surrounding the wall are a plurality of chambers and segmented walls to separate the chambers. In some instances, a single helix chamber may surround the wall, and may operate similar to that of a segmental chamber. During operation of the motor, gas flows from one end of the port to another end of the port. As the walls surrounding the port begin to disintegrate, liquid fuel within chambers begins to begin to mix with the flow of gas. As the segmented walls between the chambers begin to disintegrate, liquid from the other chambers begin to mix with the flow of gas, creating a metering of the liquid fuel.