| 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. |
| Filed: 7/24/2019 |
| Application Number: 16/521001 |
| This invention was made with Government support under Contract No. DE-NA0003525 awarded by the United States Department of Energy/National Nuclear Security Administration. The Government has certain rights in the invention. |
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