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Title: 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.

Inventors:
Issue Date:
Research Org.:
Sandia National Lab. (SNL-NM), Albuquerque, NM (United States)
Sponsoring Org.:
USDOE National Nuclear Security Administration (NNSA)
OSTI Identifier:
1892785
Patent Number(s):
11292617
Application Number:
16/521,001
Assignee:
National Technology & Engineering Solutions of Sandia, LLC (Albuquerque, NM)
Patent Classifications (CPCs):
B - PERFORMING OPERATIONS B64 - AIRCRAFT B64G - COSMONAUTICS
DOE Contract Number:  
NA0003525
Resource Type:
Patent
Resource Relation:
Patent File Date: 07/24/2019
Country of Publication:
United States
Language:
English

Citation Formats

Gilkey, Jeffrey C. Spin-stabilized orbital rocket guidance. United States: N. p., 2022. Web.
Gilkey, Jeffrey C. Spin-stabilized orbital rocket guidance. United States.
Gilkey, Jeffrey C. Tue . "Spin-stabilized orbital rocket guidance". United States. https://www.osti.gov/servlets/purl/1892785.
@article{osti_1892785,
title = {Spin-stabilized orbital rocket guidance},
author = {Gilkey, Jeffrey C.},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2022},
month = {4}
}

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