Time Optimal State Feedback Control with Application to a Spacecraft with Cold Gas Propulsion

Samuel J. Kitchen-McKinley; Sergey V. Drakunov

doi:10.1016/j.ifacol.2017.08.1366

Time Optimal State Feedback Control with Application to a Spacecraft with Cold Gas Propulsion

Samuel J. Kitchen-McKinley, Sergey V. Drakunov

Embry-Riddle Aeronautical University

Research output: Contribution to journal › Article › peer-review

Abstract

A cold gas propulsion system is well suited to provide the required thrust for a small surveyor spacecraft operated near an asteroid or planetary surface. The cold gas propellant can obtained in-situ from local surface or atmospheric constituents. For small spacecraft, the cold gas system may be limited to only on-off control of the main tank where the generated thrust is directly dependent on the tank pressure. As such the thrust will slowly decrease as the propellant is expended. A state feedback, time optimal, control law is developed for a vehicle with propellant is expended. A state feedback, time optimal, control law is developed for a vehicle with decreasing thrust in translational motion. The success of the control law is shown in simulation.

Original language	American English
Journal	IFAC PapersOnLine
Volume	50
DOIs	https://doi.org/10.1016/j.ifacol.2017.08.1366
State	Published - Jul 1 2017
Externally published	Yes

Keywords

Control of systems in vehicles
Guidance
navigation and control of vehicles
Space exploration and transportation
Optimal control theory
Variable structure control

Disciplines

Navigation, Guidance, Control and Dynamics
Propulsion and Power
Space Vehicles
Systems Engineering and Multidisciplinary Design Optimization

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Time Optimal State Feedback Control with Application to a SpacecrFinal published version, 1.28 MBLicense: CC BY

Cite this

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title = "Time Optimal State Feedback Control with Application to a Spacecraft with Cold Gas Propulsion",

abstract = " A cold gas propulsion system is well suited to provide the required thrust for a small surveyor spacecraft operated near an asteroid or planetary surface. The cold gas propellant can obtained in-situ from local surface or atmospheric constituents. For small spacecraft, the cold gas system may be limited to only on-off control of the main tank where the generated thrust is directly dependent on the tank pressure. As such the thrust will slowly decrease as the propellant is expended. A state feedback, time optimal, control law is developed for a vehicle with propellant is expended. A state feedback, time optimal, control law is developed for a vehicle with decreasing thrust in translational motion. The success of the control law is shown in simulation.",

keywords = "Control of systems in vehicles, Guidance, navigation and control of vehicles, Space exploration and transportation, Optimal control theory, Variable structure control",

author = "Kitchen-McKinley, \{Samuel J.\} and Drakunov, \{Sergey V.\}",

year = "2017",

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doi = "10.1016/j.ifacol.2017.08.1366",

language = "American English",

volume = "50",

journal = "IFAC PapersOnLine",

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T1 - Time Optimal State Feedback Control with Application to a Spacecraft with Cold Gas Propulsion

AU - Kitchen-McKinley, Samuel J.

AU - Drakunov, Sergey V.

PY - 2017/7/1

Y1 - 2017/7/1

N2 - A cold gas propulsion system is well suited to provide the required thrust for a small surveyor spacecraft operated near an asteroid or planetary surface. The cold gas propellant can obtained in-situ from local surface or atmospheric constituents. For small spacecraft, the cold gas system may be limited to only on-off control of the main tank where the generated thrust is directly dependent on the tank pressure. As such the thrust will slowly decrease as the propellant is expended. A state feedback, time optimal, control law is developed for a vehicle with propellant is expended. A state feedback, time optimal, control law is developed for a vehicle with decreasing thrust in translational motion. The success of the control law is shown in simulation.

AB - A cold gas propulsion system is well suited to provide the required thrust for a small surveyor spacecraft operated near an asteroid or planetary surface. The cold gas propellant can obtained in-situ from local surface or atmospheric constituents. For small spacecraft, the cold gas system may be limited to only on-off control of the main tank where the generated thrust is directly dependent on the tank pressure. As such the thrust will slowly decrease as the propellant is expended. A state feedback, time optimal, control law is developed for a vehicle with propellant is expended. A state feedback, time optimal, control law is developed for a vehicle with decreasing thrust in translational motion. The success of the control law is shown in simulation.

KW - Control of systems in vehicles

KW - Guidance

KW - navigation and control of vehicles

KW - Space exploration and transportation

KW - Optimal control theory

KW - Variable structure control

UR - https://commons.erau.edu/publication/1946

U2 - 10.1016/j.ifacol.2017.08.1366

DO - 10.1016/j.ifacol.2017.08.1366

M3 - Article

SN - 2405-8963

VL - 50

JO - IFAC PapersOnLine

JF - IFAC PapersOnLine

ER -

Time Optimal State Feedback Control with Application to a Spacecraft with Cold Gas Propulsion

Abstract

Keywords

Disciplines

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