College of Aeronautics Reportshttp://dspace.lib.cranfield.ac.uk/handle/1826/172018-03-24T21:34:19Z2018-03-24T21:34:19ZAddendum to type record. Avro "Lancaster" Mk.1 P. A. 474 Type record No. 1/P1/Lancaster. Investigation of boundary layer conditions on wings. M.O.S. Contract No.6/Aircraft/9807/C. B. 6(a)College of Aeronautics, Department of Aircraft Designhttp://dspace.lib.cranfield.ac.uk/handle/1826/103282016-08-17T09:25:29Z1956-01-01T00:00:00ZAddendum to type record. Avro "Lancaster" Mk.1 P. A. 474 Type record No. 1/P1/Lancaster. Investigation of boundary layer conditions on wings. M.O.S. Contract No.6/Aircraft/9807/C. B. 6(a)
College of Aeronautics, Department of Aircraft Design
Introduction
The investigation involves, briefly, the mounting of a wing
of 45' sweep-back in a dorsal position on the fuselage of
'Lancaster' P.A.474 such that wing incidence will be variable
in flight over a 20 range, i.e. ± 100.
A ‘partial chord’ technique for swept wings has been
established by the College using a similar wing mounting
configuration on an Avro 'Anson' Aircraft and this technique has
been applied to the current investigation.
1956-01-01T00:00:00ZThe elastic stability of sandwich platesHunter-Tod, J. H.http://dspace.lib.cranfield.ac.uk/handle/1826/95782015-10-15T16:26:43Z1949-03-01T00:00:00ZThe elastic stability of sandwich plates
Hunter-Tod, J. H.
This paper treats the elastic stability of supported
rectangular plates of sandwich construction with isotropic and
aeolotropic fillings under compression and shear loading.
Formulae are developed for critical stresses for flat and
curved panels in compression and flat panels in shear for the
buckling of the whole panel, also for the wrinkling or local
failure of the faces of flat panels in compression. A method
is indicated for calculating the critical load of a cylinder
in pure bending.
It is established that for a wide range of conditions
the critical stress for panels buckling in compression is
independent of the form of the filling providing it is
symmetrical about the normal; of the elastic constants of
the filling only the transverse shear is of concern. As a
result a simple extension of the equivalent plate theory of
greatly improved accuracy is developed enabling the use of
equations treating the plate as a whole.
1949-03-01T00:00:00ZMeasurement of the derivative 'ZW' for an oscillating aerofoilBuchan, A. L.Harris, K. D.http://dspace.lib.cranfield.ac.uk/handle/1826/95772015-10-15T16:16:59Z1950-06-01T00:00:00ZMeasurement of the derivative 'ZW' for an oscillating aerofoil
Buchan, A. L.; Harris, K. D.
This report presents the results of experimental
measurements of the damping derivative coefficient zw for
constant chord rigid wings of various aspect ratios having
sweepback angles of zero and 450.
The results for the rectangular wings Flow substantial
agreement with the unsteady aerofoil theory developed
by TI.P. Jones $2) The dependence of Zvi upon frequency parameter
is as given by theory and is much less than for two dimensional
flow, but the numerical results are approximately
10 per cent below the theoretical. This is attributed to the
large trailing edge angle 22° of the N.A.C.A. 0020 section
used for the model aerofoils.
The effect of sweepback is to decrease the numerical
value of z , but this effect is much less pronounced, for low
than for high aspect ratios. For aspect ratios 5 and 3
the numerical value is greater than would be given by a factor
of proportionality equal to the cosine of the angle of
sweepback.
The measurements were corrected for tunnel interference
by a method based on the theoretical work of 7.P.Jones.(1)
1950-06-01T00:00:00ZLaplace plane GeoSAR feasibility study: summary of the group design project MSc in astronautics and space engineering 2014-15, Cranfield UniversityHobbs, Stephenhttp://dspace.lib.cranfield.ac.uk/handle/1826/95702015-10-08T09:15:18Z2015-10-07T00:00:00ZLaplace plane GeoSAR feasibility study: summary of the group design project MSc in astronautics and space engineering 2014-15, Cranfield University
Hobbs, Stephen
Students of the MSc course in Astronautics and Space Engineering 2014-15 at Cranfield University
performed a feasibility study of a geosynchronous radar mission for their group project. This report
summarises the students' work and their findings.
The report consists of an overview and discussion of the technical work of the project and a
compilation of the executive summaries which describe the special contributions of each student.
The mission studied is a geosynchronous synthetic aperture radar Earth observation mission
using the Laplace orbit plane to reduce station-keeping propulsion demand. User applications are
drawn from a wide range of sectors (agriculture, meteorology, geohazards, etc.) and are translated
into system design requirements. The proposed mission design uses satellites with 13 m diameter
antennas and a total electrical power demand of 6 kW.
The mission seems feasible, although further study is recommended especially for the areas of
_ orbit selection with respect to user requirements, imaging performance and orbit maintenance,
_ mass budget (driven largely by the propulsion system),
_ user requirements, imaging performance and operational imaging modes,
_ opportunities for improved imaging with a constellation.
2015-10-07T00:00:00Z