Control laws for minimum orbital changes - The satellite retrieval problem, part 2

Research output: Contribution to conferencePaper

Abstract

On a number of occasions, upper stage failures have left satellites stranded in low Earth orbit. In order for a safe retrieval by the space shuttle, firing the engine may be necessary to remove unused propellants. If the satellite is already in a shuttle-type orbit, then the thrust must be controlled to minimize changes in semi-major axis, eccentricity, and inclination. The accepted strategy has been to vary the thrust direction to only modulate the inclination. This paper uses a set of blended extremal controls that minimizes changes in semi-major axis, eccentricity, and inclination. This requires the solution of a nonlinear programming problem using a set of optimization variables to blend the contributions of the extremal controls. A number of fully three-dimensional cases are examined and the solutions found do not include inclination modulation. A set of realistic thrust directions is presented along with the effects of the maneuver on the orbital elements.

Original languageEnglish (US)
Pages540-546
Number of pages7
StatePublished - Dec 1 2000
EventAstrodynamics Specialist Conference 2000 - Dever, CO, United States
Duration: Aug 14 2000Aug 17 2000

Other

OtherAstrodynamics Specialist Conference 2000
CountryUnited States
CityDever, CO
Period8/14/008/17/00

Fingerprint

inclination
retrieval
Orbits
Satellites
thrust
orbitals
Space shuttles
Nonlinear programming
Propellants
eccentricity
Earth (planet)
Modulation
nonlinear programming
Engines
space shuttles
orbital elements
propellants
low Earth orbits
maneuvers
engines

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Astronomy and Astrophysics

Cite this

Cichan, T., Melton, R. G., & Spencer, D. B. (2000). Control laws for minimum orbital changes - The satellite retrieval problem, part 2. 540-546. Paper presented at Astrodynamics Specialist Conference 2000, Dever, CO, United States.
Cichan, Timothy ; Melton, Robert Graham ; Spencer, David Bradley. / Control laws for minimum orbital changes - The satellite retrieval problem, part 2. Paper presented at Astrodynamics Specialist Conference 2000, Dever, CO, United States.7 p.
@conference{134619d50397400a8705961c109d22a5,
title = "Control laws for minimum orbital changes - The satellite retrieval problem, part 2",
abstract = "On a number of occasions, upper stage failures have left satellites stranded in low Earth orbit. In order for a safe retrieval by the space shuttle, firing the engine may be necessary to remove unused propellants. If the satellite is already in a shuttle-type orbit, then the thrust must be controlled to minimize changes in semi-major axis, eccentricity, and inclination. The accepted strategy has been to vary the thrust direction to only modulate the inclination. This paper uses a set of blended extremal controls that minimizes changes in semi-major axis, eccentricity, and inclination. This requires the solution of a nonlinear programming problem using a set of optimization variables to blend the contributions of the extremal controls. A number of fully three-dimensional cases are examined and the solutions found do not include inclination modulation. A set of realistic thrust directions is presented along with the effects of the maneuver on the orbital elements.",
author = "Timothy Cichan and Melton, {Robert Graham} and Spencer, {David Bradley}",
year = "2000",
month = "12",
day = "1",
language = "English (US)",
pages = "540--546",
note = "Astrodynamics Specialist Conference 2000 ; Conference date: 14-08-2000 Through 17-08-2000",

}

Cichan, T, Melton, RG & Spencer, DB 2000, 'Control laws for minimum orbital changes - The satellite retrieval problem, part 2' Paper presented at Astrodynamics Specialist Conference 2000, Dever, CO, United States, 8/14/00 - 8/17/00, pp. 540-546.

Control laws for minimum orbital changes - The satellite retrieval problem, part 2. / Cichan, Timothy; Melton, Robert Graham; Spencer, David Bradley.

2000. 540-546 Paper presented at Astrodynamics Specialist Conference 2000, Dever, CO, United States.

Research output: Contribution to conferencePaper

TY - CONF

T1 - Control laws for minimum orbital changes - The satellite retrieval problem, part 2

AU - Cichan, Timothy

AU - Melton, Robert Graham

AU - Spencer, David Bradley

PY - 2000/12/1

Y1 - 2000/12/1

N2 - On a number of occasions, upper stage failures have left satellites stranded in low Earth orbit. In order for a safe retrieval by the space shuttle, firing the engine may be necessary to remove unused propellants. If the satellite is already in a shuttle-type orbit, then the thrust must be controlled to minimize changes in semi-major axis, eccentricity, and inclination. The accepted strategy has been to vary the thrust direction to only modulate the inclination. This paper uses a set of blended extremal controls that minimizes changes in semi-major axis, eccentricity, and inclination. This requires the solution of a nonlinear programming problem using a set of optimization variables to blend the contributions of the extremal controls. A number of fully three-dimensional cases are examined and the solutions found do not include inclination modulation. A set of realistic thrust directions is presented along with the effects of the maneuver on the orbital elements.

AB - On a number of occasions, upper stage failures have left satellites stranded in low Earth orbit. In order for a safe retrieval by the space shuttle, firing the engine may be necessary to remove unused propellants. If the satellite is already in a shuttle-type orbit, then the thrust must be controlled to minimize changes in semi-major axis, eccentricity, and inclination. The accepted strategy has been to vary the thrust direction to only modulate the inclination. This paper uses a set of blended extremal controls that minimizes changes in semi-major axis, eccentricity, and inclination. This requires the solution of a nonlinear programming problem using a set of optimization variables to blend the contributions of the extremal controls. A number of fully three-dimensional cases are examined and the solutions found do not include inclination modulation. A set of realistic thrust directions is presented along with the effects of the maneuver on the orbital elements.

UR - http://www.scopus.com/inward/record.url?scp=84894453576&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84894453576&partnerID=8YFLogxK

M3 - Paper

AN - SCOPUS:84894453576

SP - 540

EP - 546

ER -

Cichan T, Melton RG, Spencer DB. Control laws for minimum orbital changes - The satellite retrieval problem, part 2. 2000. Paper presented at Astrodynamics Specialist Conference 2000, Dever, CO, United States.