Accession Number : ADD013482

Title :   Method for Steering a Solid Propellant Ballistic Vehicle.

Descriptive Note : Patent, Filed 25 Aug 80, patented 14 Jun 83,

Corporate Author : DEPARTMENT OF THE NAVY WASHINGTON DC

Personal Author(s) : Howard, Peter B ; Boelitz, Martin V ; De Swarte, Thomas W

Report Date : 14 Jun 1983

Pagination or Media Count : 6

Abstract : A method for steering solid propellant ballistic vehicles during powered flight which eliminates the requirement for cutoff control by allowing simultaneous fuel depletion and velocity to be gained, nulling. The vehicle booster is steered along a velocity trajectory of length equal to the remaining velocity capability, VCAP, which results in a fuel inefficient trajectory. The trajectory is divided basically into three phases and exit phase, a fuel depletion guidance (FDG) phase and a short phase of constant attitude thrusting just prior to final stage burnout. For the exit phase the launch azimuth and the pitch over magnitude can be varied from their usual fuel-efficient values. During fuel-depletion guidance the additional degree of freedom is the angle, theta between VG and the desired thrust direction.

Descriptors :   *STEERING, *GUIDED MISSILES, *SOLID PROPELLANT ROCKET ENGINES, *PATENTS, ATTITUDE(INCLINATION), AZIMUTH, BALLISTICS, BOOSTER ROCKET ENGINES, DEGREES OF FREEDOM, DEPLETION, EFFICIENCY, EXITS, FUELS, GUIDANCE, LAUNCHING, LENGTH, SHORT RANGE(TIME), THRUST, TRAJECTORIES, VEHICLES, VELOCITY, SURFACE LAUNCHED

Subject Categories : Solid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE