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Load alleviation maneuvers for a launch vehicleThis paper addresses the design of a forward-looking autopilot that is capable of employing a priori knowledge of wind gusts ahead of the flight path to reduce the bending loads experienced by a launch vehicle. The analysis presented in the present paper is only preliminary, employing a very simple vehicle dynamical model and restricting itself to wind gusts of the form of isolated spikes. The main result of the present study is that linear quadratic regulator (LQR) based feedback laws are inappropriate to handle spike-type wind perturbations with large amplitude and narrow base. The best performance is achieved with an interior-point penalty optimal control formulation which can be well approximated by a simple feedback control law. Reduction of the maximum bending loads by nearly 50% is demonstrated.
Document ID
19950049761
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Seywald, Hans
(Analytical Mechanics Associates, Inc. Hampton, VA, US, United States)
Bless, Robert R.
(Lockheed Engineering and Sciences Co., Hampton, VA US, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: Spaceflight mechanics, 1993; AAS(AIAA Spaceflight Mechanics Meeting, 3rd, Pasadena, CA, Feb. 22-24, 1993, Parts 1 & 2 . A95-81344
Publisher: American Astronautical Society (Advances in the Astronautical Sciences, Vol. 82, Pts. 1 & 2)
ISSN: 0065-3438
Subject Category
Launch Vehicles And Space Vehicles
Accession Number
95A81360
Funding Number(s)
CONTRACT_GRANT: NAS1-18935
CONTRACT_GRANT: NAS1-19000
Distribution Limits
Public
Copyright
Other

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