dc.contributor.author |
Eshelby, M. E. |
|
dc.date.accessioned |
2009-05-15T09:26:10Z |
|
dc.date.available |
2009-05-15T09:26:10Z |
|
dc.date.issued |
1979-01 |
|
dc.identifier.uri |
http://hdl.handle.net/1826/3392 |
|
dc.description.abstract |
The longitudinal handling qualities of light aircraft have
traditionally been assessed in terms of the slope of the static
stability trim curves. This method of assessment is simple in terms
of analysis as well as being a relatively easy task for the pilot to
perform. The theory is however based on a simple linearised model of
.
the aircraft'and omits, amongst other things, the effects of power.
A comparison between the estimated and measured trim curves of a
typical light aircraft shows that the linearised theory severely
overestimates its static stability. A design based on the linear
assumptions would be unlikely to comply with airworthiness requirements.
In Part II the main omissions from the linearised model are
considered individually and their effect on the trim curves found.
In Part I the individual contributions from Part II are used to
complete the full, non-linear, trim equations and these are solved in
terms of elevator angle and incidence to trim, n and
ä. The solution
shows that the non-linear analysis provides a good simulation of the
flight measured trim curve data thus verifying the methods of
estimation developed in Part II.
The trim curves are considered in terms of incidence and
lift coefficient and show that assumption of a linear lift-incidence
relationship may cause some misleading interpretations of the trim
curves drawn in terms of lift coefficient. |
en_UK |
dc.language.iso |
en |
en_UK |
dc.publisher |
Cranfield University |
en_UK |
dc.title |
A non-linear analysis of the longitudinal static stability of light, multi-engined aircraft |
en_UK |
dc.type |
Thesis or dissertation |
en_UK |
dc.type.qualificationlevel |
Doctoral |
en_UK |
dc.type.qualificationname |
PhD |
en_UK |