Attitude guidance and control for a spinning, asymmetrical rocket payload

Creagh, Michael A. and Mee, David J. (2011). Attitude guidance and control for a spinning, asymmetrical rocket payload. In: , AIAC14 Fourteenth Australian International Aerospace Congress. AIAC14 Fourteenth Australian International Aerospace Congress, Melbourne, Australia, (). 28 February - 3 March 2011.

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Name Description MIMEType Size Downloads
Author Creagh, Michael A.
Mee, David J.
Title of paper Attitude guidance and control for a spinning, asymmetrical rocket payload
Conference Paper Type Fully Published Paper
Conference name AIAC14 Fourteenth Australian International Aerospace Congress
Conference location Melbourne, Australia
Conference dates 28 February - 3 March 2011
Proceedings title AIAC14 Fourteenth Australian International Aerospace Congress
Place published Melbourne, Australia
Publisher Australian International Aerospace Congress
Publication date 2011
Total pages 12
Collection year 2012
Language eng
Abstract/Summary This paper demonstrates a guidance and control scheme for a spinning, aerodynamically asymmetrical vehicle. Attitude manoeuvres of such a vehicle are complicated primarily by the fact that the dynamics cannot be linearised in a mathematically well-posed way. In the proposed scheme, a non-linear guidance law acts as an outer loop to issue commands to an autopilot system. The guidance law accepts sensor inputs and desired attitude information and calculates pitch and yaw-rate commands for autopilot input, based on error in attitude and additional compensation terms derived from Euler’s rotational equations. The autopilot control system consists of two self-adaptive single-input, single-output (SISO) proportional plus integral controllers, derived using the pole placement technique. A numerical 6 degreeof- freedom simulation shows that a 4.24 kg, unpowered supersonic payload, called the HyShot Stability Demonstrator, that starts at Mach 3.5 would be capable of attitude manoeuvres at a spin-rate of 2.0 Hz.
Keyword Guidance
Control
Flight mechanics
Spinning
Missile
Autopilot
Attitude
Q-Index Code EX
Q-Index Status Confirmed Code
Institutional Status UQ

Document type: Conference Paper
Sub-type: Fully Published Paper
Collections: School of Mechanical & Mining Engineering Publications
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Created: Mon, 30 Jan 2012, 14:20:40 EST by Katie Gollschewski on behalf of School of Mechanical and Mining Engineering