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Effects of fuel movement on aircraft response to thrust application
Hanke, C. Rodney
Hanke, C. Rodney
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t1966_Hanke.pdf
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1966-01
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Abstract
An analog simulation of the B-52 H airplane is used to study the effects of fuel motion on controllability of the aircraft during a large thrust increase as might be used in an aborted landing.
If full thrust is added without a change in stabilizer trim position, the aircraft cannot be successfully controlled with elevator alone. The effects of changing fuel damping or baffling, limiting the applied thrust, and using stabilizer trim control for improvement of controllability are investigated.
Limiting the thrust change with a throttle stop is the most effective method of reducing the airframe response to throttle inputs. Large fuel damping provides the pilot with additional time to initiate stabilizer trim but is ineffective in reducing the final value airframe response. Normal stabilizer trim rate of 0.6 deg/sec coupled with elevator control is adequate to prevent the airplane from pitching into a stall even for maximum thrust change.
Table of Contents
Summary -- List of symbols -- Introduction -- Fuel dynamics -- Equations of motion -- Analysis of results -- Conclusions -- References -- Appendix
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Thesis (M.S.)-- Wichita State University, College of Engineering, Dept. of Aeronautical Engineering
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Wichita State University
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Wichita State University