Attitude guidance for spinning vehicles with independent pitch and yaw control

Creagh, Michael and Mee, David (2010) Attitude guidance for spinning vehicles with independent pitch and yaw control. Journal of Guidance, Control and Dynamics, 33 3: 915-922.

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Author Creagh, Michael
Mee, David
Title Attitude guidance for spinning vehicles with independent pitch and yaw control
Journal name Journal of Guidance, Control and Dynamics   Check publisher's open access policy
ISSN 0731-5090
1533-3884
Publication date 2010-05
Sub-type Article (original research)
DOI 10.2514/1.44430
Volume 33
Issue 3
Start page 915
End page 922
Total pages 8
Place of publication Orlando, Florida, U.S.
Publisher American Institute of Aeronautics and Astronautics (AIAA)
Collection year 2011
Language eng
Subject 0901 Aerospace Engineering
Formatted abstract The design and simulation of an attitude guidance and control scheme for a spinning aerospace vehicle is detailed. The basis for the guidance law is the projection of the angular-velocity vector onto a plane normal to the desired heading. The result of the projection is an attitude error that can be converted to pitch-and yaw-rate commands for an autopilot. Two single-input/single-output controllers are used in this paper, which in turn issue flap defiection commands. An asymmetrical vehicle spinning at 1.5 Hz with independent pitch-and yaw-flap sets is simulated in a six-degree-of-freedom simulation. It is shown to perform successful attitude maneuvers for two different cases. In one case, the basic guidance law is used. This results in a settling time of approximately 1.0 s. The next case performs the maneuver with a modified guidance law that includes decoupling terms. This case results in a settling time of 0.6 s. The guidance law has a number of possible applications. These include stability augmentation and redundancy, alternatives in fin Configurations for vehicles, and reduction in number of necessary control surfaces.
Copyright © 2009.
Keyword Attitude error
Attitude maneuver
Design and simulation
Fin configuration
Guidance and control
Guidance laws
Settling time
Single input/single outputs
Six-degree-of-freedom
Spinning vehicles
Yaw control
Q-Index Code C1
Q-Index Status Confirmed Code
Institutional Status UQ
Additional Notes [Also] "Presented as Paper 0516 at the 47th AIAA Aerospace Sciences Meeting, Orlando, FL, 5–8 January 2009; received 18 March 2009; revision received 10 December 2009; accepted for publication 17 February 2010. Copyright © 2010 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved."

Document type: Journal Article
Sub-type: Article (original research)
Collections: School of Mechanical & Mining Engineering Publications
Official 2011 Collection
 
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Created: Sun, 06 Jun 2010, 00:04:17 EST