Aerospace Control and Guidance Systems Committee

Announcements

You must first log in to access prior meeting presentations, register for a meeting, or nominate some for the Ward Award.

If you do not have a login account, or cannot remember the email address associated with your account, please click on the Application Form link below.

Login

Site Search

Search our site:

Upcoming Events

Photos

Meeting Highlights New!

Subcommittee S

Prior Meetings

Abstracts may be viewed by anyone. Presentations are only available to active members who have logged in.

Meeting 133
(coming soon)

Meeting 132
(coming soon)

Home

Ward Memorial Award

Planning Advisory Board

Downloads

Constitution and By-Laws

About

History

Contact Us

← Return to agenda

Meeting	ACGS Committee Meeting 108 - Gettysburg - October 2011
Agenda Location	6 1st ANNUAL DAVE WARD MEMORIAL LECTURE 6.0 An Integrated Approach to the Dynamic Analysis of Flexible Launch Vehicles
Title	An Integrated Approach to the Dynamic Analysis of Flexible Launch Vehicles
Presenter	Jeb Orr
Affiliation	NASA Marshall Space Flight Center
Available Downloads*	presentation
	Downloads are available to members who are logged in and either Active* or attended this meeting.
Abstract	An Integrated Approach to the Dynamic Analysis of Flexible Launch Vehicles Jeb S. Orr SAIC Space Engineering Technology Division MSFC Control Systems Design and Analysis Branch (EV41) (256) 961-0150 Abstract: A straightforward and generalized technique is presented for modeling flexible launch vehicles with multiple actuated nozzles and sloshing propellant. The effects of nozzle inertial coupling, elasticity, and slosh are incorporated without restrictions on the position, orientation, or number of model elements. The formulation of the flight dynamics is based on a vector extension of the classical perturbation methods and in fact generates the classical models as a special case. Compared with a Newton-Euler approach, the integrated technique directly yields the correct motion equations and can be used for large-scale stability analysis and numerical optimization of the flight control system parameters. The model is shown to be extensible to high-fidelity time-domain trajectory simulation through the application of a special form of Lagrange’s equations in quasi-coordinates.