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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