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An Adaptive System for Load Relief and Accurate Control of Launch VehiclesAn adaptive load relief control system for a SATURN type vehicle which significantly reduces aerodynamically induced structural loads without incurring excessive velocity dispersions has been studied. This control system utilizes pendulous accelerometers to measure the angle between the total vehicle acceleration vector and the vehicle body. This measurement is used to fly the vehicle along the nominal trajectory to minimize velocity dispersions. However, if unusually high values of wind velocity are encountered, the system will cause the vehicle to turn into the wind to reduce the lateral structural loads. Results of an anal6g computer study show that the adaptive system can reduce aerodynam3cally induced peak structural loads as much as 50 percent under those encountered using conventional control techniques. relief is used only when required, velocity dispersions are held to a minimum.
Document ID
19640011625
Acquisition Source
Marshall Space Flight Center
Document Type
Reprint (Version printed in journal)
Authors
Klenk, W. J.
(Space Technology Labs., Inc. Redondo Beach, CA, United States)
Date Acquired
August 2, 2013
Publication Date
January 1, 1964
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER-64-239
Meeting Information
Meeting: 1st AIAA Annual Meeting
Location: Washington, D.C.
Country: United States
Start Date: June 29, 1964
End Date: July 2, 1964
Accession Number
64N21539
Funding Number(s)
CONTRACT_GRANT: NAS8-5051
Distribution Limits
Public
Copyright
Other
Keywords
ADAPTIVE CONTROL SYSTEM
SATURN LAUNCH VEHICLE

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