초록 ▼

A system for controlling the velocity and attitude of an exoatmospheric projectile (10) that spins about a spin axis (z). Several thrusters (e.g., 1-7) are disposed along the outer surface (8, 9, 11) of the projectile (10) for performing three prescribed functions. The number of thrusters (e.g., 1-7

A system for controlling the velocity and attitude of an exoatmospheric projectile (10) that spins about a spin axis (z). Several thrusters (e.g., 1-7) are disposed along the outer surface (8, 9, 11) of the projectile (10) for performing three prescribed functions. The number of thrusters (e.g., 1-7) is minimized to save weight. As few as four thrusters (1-4) can be used to perform the three prescribed functions, which are: (A) reorienting the spin axis (z) in inertial space, by firing the axial thrusters (1, 2, 6, 7); (B) adding velocity to the projectile (10) in any direction, without a concomitant change in the orientation of the spin axis (z), by firing continually a combination comprising at least one of the thrusters (1-7); and (C) changing the projectile\s spin rate (W), by firing one of the radial thrusters (3, 4). Nutation dampers, such as ball-in-tube nutation dampers (20), can be used to decrease the cone angle E and thereby improve the pointing accuracy of the spin axis (z).

대표청구항 ▼

A system for controlling the velocity and attitude of an exoatmospheric projectile spinning about a spin axis and having a generally cylindrical outer shape consisting of a generally cylindrical periphery whose long axis is the spin axis, and front and aft generally circular faces located at opposin

A system for controlling the velocity and attitude of an exoatmospheric projectile spinning about a spin axis and having a generally cylindrical outer shape consisting of a generally cylindrical periphery whose long axis is the spin axis, and front and aft generally circular faces located at opposing ends of the generally cylindrical periphery, said system comprising: a first axial thruster positioned on the front face and having a force vector pointing inwardly through the projectile; a second axial thruster positioned on the aft face and having a force vector pointing inwardly through the projectile; and first and second radial thrusters, positioned on the generally cylindrical periphery and each having a force vector pointing inwardly through the projectile and intersecting at a common point that is offset from the spin axis; wherein the spin axis can be reoriented in inertial space by firing the axial thrusters; velocity can be added to the projectile in any direction, without a concomitant change in orientation of the spin axis, by firing a combination comprising at least one of the thrusters; and the spin rate of the projectile can be changed by firing one of the radial thrusters.