Volume 37 No 1 Feb-Mar 1986.pdf - Lakes Gliding Club
Volume 37 No 1 Feb-Mar 1986.pdf - Lakes Gliding Club
Volume 37 No 1 Feb-Mar 1986.pdf - Lakes Gliding Club
Create successful ePaper yourself
Turn your PDF publications into a flip-book with our unique Google optimized e-Paper software.
JUUAN ROSS<br />
Ware all familiar with tug aeroplanes and<br />
accept that they land trailing their tow cables,<br />
not questioning Ille hazards 01' inconvenience<br />
this causes. 'If it were possible to rewind the<br />
tow cable fully into the tug, four important<br />
benefits would ,be realised.<br />
,Hsl, operations wourld t!e safer - persons<br />
and objects wou'ld not be struck.<br />
Secondly, the cost 01 replacing broken cables<br />
and repairing, damage caused by cable strikes<br />
would be saved.<br />
Thrclly, tug utilisation would be improved by<br />
as much as '20% ona typical launch cycle - the<br />
absence 01 a cable lraiing below the tug allows<br />
a 'lower 'approach, hence a touchllown closer to<br />
the boundary fence, and less time is spent taxying<br />
back; also for reconnection, the cable has<br />
only to be pulled out from the tug's tail.<br />
Finally, cables longer than the current norm<br />
may 'be titted, being rewound for landing.<br />
longer cables would reduce the danger resulting<br />
from the glider rising too high on tow.<br />
I discussed the potential for a cable rewinding<br />
system during 1'984 at laSham and Southdown<br />
GCs. Tne Opinions and comments received<br />
were most encouraging and I decided to design<br />
and evaluate an aerotow cable rewind system<br />
for the third year project section of my degree<br />
course,<br />
An elementary rewind system had recently<br />
been tried at the Booker GC. It was unsatisfactory<br />
for a number of reasons. Rewind took<br />
9O-120sec and was only completed when the<br />
lug was very close to the ground. lihe control<br />
system waS too simple-, the pilot being expected<br />
to switch off the rewind motor whefl all the cable<br />
was wound in. The jettison system severed the<br />
cable; apparently quite a few cables were accidentally<br />
broken in this way and, once spliced,<br />
the.y would not fit into the small bore conduits<br />
used. Perhaps most significantly, no indication<br />
was given to the pilot when full cable rewind had<br />
been achieved. The pilot was forced to use a<br />
crude mirror system to view the cable periodically,<br />
seriously adding to his already high workroad<br />
close to the ground.<br />
Based on the results of discussions and the<br />
Booker experience a brief specification was<br />
drawn up.<br />
1. Rewind time: to be 45sec for a 200ft cable.<br />
2. Cable type: to tle up to 300ft of conventional<br />
7mm diameter cable fitted with Ottfur or T0St<br />
rings.<br />
3. Operation: a single command from the pilot<br />
should Initiate rewind, lihe pilot must be<br />
informed by Indicator lamp of full rewind. After<br />
landing the cable must be unwindable without<br />
pilot Intervention: nevertheless U must not wind!<br />
out under air or taxying toads. Whenever fully'<br />
unwound the cable mus.t be jettisonable.<br />
4. PUot workload: this must not be increased<br />
by the system.<br />
5. Tug performance, weight and balance must<br />
nOf be significantly altered.<br />
A system layout was developed and is illustrated<br />
in, Fig 1. The system is electrically powered,<br />
using the tug's 12v DC circuit. An electric<br />
clutch is used in conjunction with an Irreversibly<br />
geared motor: it the clutch is kept energised<br />
then the cable will not drag out. A tail mounted<br />
microswitch, pressed by the- launch point i'lelper<br />
who will pull out the cable, releases the clutch.<br />
AEROTOW CABLE<br />
REWIND SYSTEM<br />
This is a summary of the work Julian did for his final year project of<br />
his BSc course in aeronautics and astronautics at Southampton<br />
University and which was supported by the BGA via the 1984<br />
Churchill Award.<br />
Fig 1. The system layout.<br />
,1,'.1,'"<br />
tug structure<br />
'''-../<br />
I' i', ,. "\<br />
""~--_:_..:;,..~<br />
conduit<br />
winch<br />
interface structure<br />
emergency rel'ease cable<br />
A switch in the cockpit. starts both clutch and<br />
molar, rewinding the cable. A stop piece Is<br />
attached to the cab'le, very ,close to the glider<br />
end: this activates 'a second microswitch at the<br />
tail, stopping the molor, but allowing: Ihe clutch<br />
tQ stay energised.<br />
Direct tension forces are reacted a\ the winch<br />
itself, through the interface structure to the tug<br />
airframe. Sidetoads are reacted at the tail.<br />
Fig 2. The system fitted to a tug.<br />
stop mechanism<br />
also supporting<br />
tailwheel<br />
Light alloy is used for much 01 the system,<br />
giving low weight combined with good strength.<br />
The Aotable exception is the 300mm diameter<br />
cable drum, which is of GRP.<br />
A modular approach is applied to the desigrl:<br />
this permits simple maintenance, rearrangement<br />
for different tug types and easy 'upgrading<br />
or modification of individual modules. Fig 2 illustrates<br />
the system fitted to a tug.<br />
Winch unit dimensions are: max height<br />
300mm; max length 300mm; max width 420mm.<br />
Weight is approximately 5kg without cable.<br />
A prototype system was constructed.<br />
Static load testing showed the prototype<br />
winch to nave a :safe margin of strength. Strain<br />
gauge resUlts showed fhat no stresses were sufficiently<br />
high tQ give anxiety regarding fatigue,<br />
Bench running demonstrated correct functioning<br />
of the winch and control system. A drum<br />
rotation speed Of around, 240rpm was found to<br />
be 'necessary to obtain the specified rewind<br />
time. .<br />
One interesting result showed that the quality<br />
of cable winding on to the storage drum is very<br />
much dependent on the distance between the<br />
coiled cab'le sUrface and the point of feed.<br />
Unless this dimension Is kepf above a critical<br />
value, chaotic coiling occurs, taking excess volume<br />
and leading to tangling on unwinding,<br />
A production system is estimated to have Cl<br />
unit material and parts cost of £100, with unit<br />
construction time of between four and six man<br />
days. This shOUld lead 10 a basic cost of<br />
£200-250, fo which must be added fitting costs,<br />
22 SAILPLANE & GLIDING