Spin-stabilized orbital rocket guidance

Abstract

Technologies for guidance of a spin-stabilized orbital rocket are described herein. The spin-stabilized rocket includes a guidance controller. The guidance controller computes parameters of a burn of a second-stage engine of the rocket to reach a desired nominal orbit subsequent to burnout of the first stage of the rocket. The guidance controller computes the burn parameters of the second-stage engine based upon one or more desired orbit parameters and a current position and velocity of the rocket. The computation of the burn parameters is based upon a simulated point-mass model of the motion of the rocket. The guidance controller then controls the rocket to initiate a second-stage burn having the computed burn parameters.