Drag-compensated missile

Claim 1

A MISSILE DISPOSED FOR FLIGHT ACCORDING TO A PLANNED TRAJECTORY INCLUDING BOOSTER PROPULSION AND SUSTAINER PROPULSION PASSES OF FLIGHT, SAID MISSILE COMPRISING: A ROTARY HOUSING ASSEMBLY; FINS FIXED TO THE OUTSIDE OF SAID ASSEMBLY, EACH FIN BEING AT A SLIGHT ANGLE TO A PLANE THRU THE LONGITUDINAL AXIS OF THE HOUSING ASSEMBLY WHEREBY THE MISSILE IS ARROW-STABILIZED, IS ROTATED AT A NON-GYROSCOPIC SPEED, AND THE ACCURACY-DISTRUBING EFFECT OF THRUST MALALIGNMENT LARGELY IS BALANCED OUT; A BOOSTER WITHIN SAID HOUSING ASSEMBLY COMPORISING A BOOSTER ROCKET-MOSOT NOZZLE FOR THE EXIT OF PROPULSIVE GAS; A SUSTAINER WITHIN SAID ASSEMBLY FOR MAINTAINING THE MISSILE ON ITS TRAJECTORY AFTER BURNOUT OF SAID BOOSTER, COMPRISING A SUSTAINER ROCKET-MOTOR NOZZLE; MEANS DISPOSED IN SAID SHELL FOR CUTOFF OF SAID BOOSTER MOTOR AND IGNITION OF SAID SUSTAINER MOTOR, RESPONSIVE TO SAID MISSILE ATTAINING A PREDETERMINED VELOCITY IN THE TRAJECTORY; ACCELEROMETER MEANS, MOUNTED IN SAID ASSEMBLY SUBSTANTIALLY ON SAID LONGITUDINAL AXIS, FOR MEASURING ACCELERATIONS AND FOR SUPPLYING