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Investigation of eye movements of an aircraft pilot under blind approach conditions
No full textEye movement patterns were obtained of a pilot in an
aircraft fitted with a standard R.A.F. blind flying panel on
several approaches under Standard Beam Approach conditions,
These patterns were obtained by photographing the
reflection of the pilot's eyes in a mirror attached to the
instrument panel.
The results show the
1) Proportion of time spent on each instrument,
2) Duration of the fixation time on each instrument,
3) Frequency of the eye fixations,
4) Sequence of eye movements.
It was originally intended to investigate the eye
movements on an I.L.S. approach using the Zero Reader and. I.L.S.
Cross Pointer independently. Unforseen difficulties and delays,
however, prevented the completion of this part of the investigation
Characteristics of the high temperature mechanisms of creep and recovery in graphite
No full textThe report summarizes the first year's work
carried out on an investigation into the high
temperature mechanisms of creep and recovery in
graphite. This work has been devoted to the
building of an experimental apparatus capable of
exerting creep loads in the temperature range
2000°C — 3000°C. A full description of the apparatus
is given and its further potential discussed.
Detailed figures are included on the labour expended
together with a summary of property acquired for use
on the contract
'Heat transfer at low temperature in the entry section of a solid propellant rocket nozzle'
No full textHeat transfer in the converging section of the nozzle of
a simulated solid propellant rocket with a star-shaped conduit
has been investigated in the following way:
(a) Area-average heat transfer has been measured on a room temperature
rig, with and without a simulated charge.
(b) Theoretical heat transfer has been calculated without
the charge (axisymmetric laminar flow).
(0) An attempt has been made to predict the detailed
distribution of heat transfer by measurements of mass
transfer on a nozzle made of napthalene.
(d) Flow visualisation has been performed on a water-rig … [cont.]
The design of a hydrostatic lubrication arrangement for the horizontal and transverse slides of a no. 3 archdale vertical milling machine
No full textThe Department of Production and Industrial Administration of
The College of Aeronautics has made a detailed analysis into the
performance of numerically controlled machine tools, and this shows
that when these machines are operating under light cutting loads, the
total envelope tolerance is about 0.003 ins. Further investigation
into the source of the errors showed that about 80 per cent of this
error was due to mechanical mechanisms in the machine tool. The
electronic equipment operated inside a total band of 0.0004 ins. over
small distances, and 0.0006 ins. over 10 inches. This situation
appeared to justify a comprehensive survey into the methods which may
be used to improve the mechanical performance of these machines.
After due consideration had been given to a number of possible
alternatives, it was decided to fit hydrostatic lubrication to the
slides, nut and screw arrangement, and the thrust bearings used on
the X and Y axes of an existing No. 3 Archdale Milling Machine.
The Z axis was not included in the redesign, because analysis showed
that a new head casting would have been necessary. It was thought
that this additional expense was not justified and that the data
obtained from an examination of the performance given by the X and
Y axes would show whether the system could be used with advantage
in the design of new machines. The paper gives details of the
calculations used to establish the dimensions of the new features
fitted to the machine to satisfy the target performance conditions
which appeared to be possible and are given in the introduction.
The authors would like to express their appreciation to James
Archdale and Co. for making a machine available for this investigation,
to the Staveley Research Department, and in particular to Mr. Graham,
Mr. Harris, Mr. Huntley) M r. Cummings and Mr. Hayward
Aerodynamic characteristics of two low aspect ratio rectangular wings at Mach 2
No full textThis note summarises the important results
of a detailed experimental investigation into the flow
and pressure distribution over two rectangular single
wedge wings. The experiments were carried out .in the
9" x 9" supersonic tunnel at the College of Aeronautics, 6
at a Mach number of 2.0 and a Reynolds number of 2.5 x 10
per foot. Both wings had a chord of 3 inches and a
total wedge angle of 6°. They had no real trailing
edge, but were faired into a cylindrical support which
could be rolled and pitched in the tunnel. Wing A was
of 2 inch1span, giving an aspect ratio of 0.67. `Ting B
was of 1 1/4 inch span, 0.42 aspect ratio. 132 pressure
tappings 4 were spaced regularly over half of one surface
of each wing, and up to 19 pressure readings could be
taken simultaneously on vertical mercury manometers.
models were pressure plotted at pitch angles of 0°,
2 1/2°, 5°, 7 1/2°, 10°, 15°, 20°, 25°, and 30°, and at all
roll angles at intervals of 30°. Since each wing was
symmetrical about the centreline, the complete pressure
distribution over all surfaces at any roll angle Ø could
he obtained from the readings taken on the one surface
at Ø, 180°- Ø, 180° + Ø, and 360°- Ø. The pressure
readings were then integrated to give the forces and
moments on the complete wing… [cont.]
A study of the thermal degradation of an amine-cured epoxide resin at temperatures below 350 degrees C
No full textAn epoxy resin made by the reaction of the diglycidyl ether of
bis-phenol A and diaminodiphenyl methane was thermally degraded in vacuo
at temperatures between 200°C and 350°C. The effect of degradation was
examined by means of measurement of changes in the dielectric properties of
the material and also by examination of compounds evolved by the cured resin.
Definite evidence for the evolution of N-methyl aniline and N:N-dimethylaniline
is advanced and added evidence for a dehydration reaction is put forward.
Possible degradation mechanisms are discussed
Low speed aerodynamic characteristics of 60 degrees rounded leading-edge delta wing with vortex flaps
No full textLow speed wind tunnel measurements have been made on a 1.15m span 60º delta wing with rounded leading-edge vortex flaps. the purpose of the measurements was to assess the benefits of the measurements was to assess the benefits of the rounded leading-edge vortex flaps on the lift/drag ratio. The force and surface pressure measurements were made at a Reynolds number based on the centreline chord of 2x106. The increase in the radius of the rounded leading-edge reduces the drag significantly both with and without flap deflection except in the minimum drag region. Deflecting the rounded leading-edge vortex flap improves the lift/drag ratio compared with the sharp edged vortex flap at relatively higher lift coefficients. The greatest percentage improvement in the lift/drag ratio compared with the sharp edged flat delta wing is more than 50% at a lift coefficient of 0.5 for the rounded edge delta wing with flap deflected.The Universit
Initial review of research into the application of modified stepwise regression for the estimation of aircraft stability and control parameters
No full text
Lunar South Pole Mission (LSPM) :
No full textThis report is a summary of the group design project of the MSc in Astronautics
and Space Engineering at Cranfield University for the year 1996/97. The project
was a feasibility study of a European unmanned mission to the lunar south pole
to carry out scientific study. The mission proposed uses two spacecraft: (1) an
orbiter to take images of the proposed landing site, to measure the Moon’s
gravitational field, and to act as a communications relay, and (2) a larger
lander which carries a small rover and a crate probe. The orbiter is launched
first (if gravity and image data are not already available) so that the lander’s
landing site can be selected. The main goal is scientific study of the
permanently dark craters at the lunar south pole. The baseline design (developed
to the depth of a feasibility study) meets the stated requirements and is
comparable to ESA’s medium class missions (cost ~