home
***
CD-ROM
|
disk
|
FTP
|
other
***
search
/
TPUG - Toronto PET Users Group
/
TPUG Users Group CD
/
TPUG Users Group CD.iso
/
COMAL
/
U-User Group
/
(k)ud.d64
/
txt.w&b
< prev
next >
Wrap
Text File
|
2007-02-28
|
6KB
|
228 lines
╫┼╔╟╚╘ AND ┬┴╠┴╬├┼
BY ╟╥ ╥OBERTS
┴ ╞┼╫ ╘╚╔╬╟╙ ╘╧ ╦╬╧╫ ┴╬─ ╥┼═┼═┬┼╥
╘HIS PROGRAM IS NOT FOR EVERYONE ┬╒╘
IF IT IS NEEDED IT SHOULD SAVE LOTS
OF PAPER ┴╬─ MATH.
╔T WAS WRITTEN FOR A PERSONAL NEED
AND IS FOR VERY SPECIALIZED USE.
╞╧╥ ─┼╘┼╥═╔╬╔╬╟ ╘╚┼ ├┼╬╘┼╥ ╧╞ ╟╥┴╓╔╘┘
OF SIMPLE AIR-VEHICLES EFFECTED BY
┼┴╥╘╚'╙ ╟╥┴╓╔╘┘ IN OUR ATMOSPHERE.
╦┼┼╨ & ╨╥┼╙┼╥╓┼ ─┼╘┴╔╠┼─ ╥┼├╧╥─╙!
╘HIS INCLUDES POWERED AND NONPOWERED,
AIRCRAFT, EXCEPT LIGHTER-THAN-AIR.
╘HE PROGRAM CAN BE EASILY MODIFIED TO
TAKE CARE OF HIGH PERFORMANCE AUTO'S,
┴╘╓'S, BOATS, MOTORCYCLES, AND ┘┼╙,
EVEN ┼╔╟╚╘┼┼╬ ╫╚┼┼╠┼╥╙, BUT AS YOU
WILL SEE, THE PROCESS OF GATHERING
THE DATA NEEDED TO ACCOMPLISH THE
DESIRED RESULT ═╔╟╚╘ ╬╧╘ ┬┼ ╫╧╥╘╚ ╘╚┼
┼╞╞╧╥╘ ╥┼╤╒╔╥┼─!
╘HOSE WITH PRODUCTION TYPE AIRCRAFT
CAN MOST LIKELY SKIP THE REMAINDER OF
THESE COMMENTS AND GET TO THE MEAT OF
THE PROBLEM OF ═╧╓╔╬╟. ├╚┴╬╟╔╬╟,
┴──╔╬╟, AND ╥┼═╧╓╔╬╟ EQUIPMENT/
ACCESSORIES, INCLUDING ╞╒┼╠ WEIGHT/
CONSUMPTION IN MODERN DAY HIGH
PERFORMANCE AIRCRAFT WHERE ═┴╪ ╟╥╧╙╙
╫┼╔╟╚╘ FOR ╘┴╦┼╧╞╞ AND/OR ╠┴╬─╔╬╟ IS
OF PRIME CONSIDERATION FOR THE ╙┴╞┼╘┘
OF CREW/ OCCUPANTS/ AIRCRAFT.
┘OUR ┴IRCRAFT ╠╧╟ ┬╧╧╦ AND ╧╨┼╥┴╘╧╥╙
═┴╬╒┴╠ SHOULD HAVE ALL THE DATA
REQUIRED FOR USING THIS PROGRAM.
├╧╬╞╧╥═ ╘╧ ╘╚┼ ─┴╘┴ ╘╚┼╥┼╔╬! ┴ & ╨'S
SHOULD FIND THE PROGRAM USEFUL. ┴╘╥
PILOTS ═╒╙╘ HAVE A BETTER WAY!
╞OR THOSE LIKE MYSELF, WITH
┼╪╨┼╥╔═┼╬╘┴╠ AIRCRAFT, THE PROGRAM
SHOULD TAKE CARE OF YOUR PRESENT AND
FUTURE NEEDS CONCERNING ╫┼╔╟╚╘ AND
┬┴╠┴╬├┼.
├┴╒╘╔╧╬!
├╚┼├╦ ╘╚╔╙ ╨╥╧╟╥┴═ ┴╟┴╔╬╙╘ ┴ ╨╥╧╓┼╬
═┼╘╚╧─ ╧╞ ╧┬╘┴╔╬╔╬╟ ╘╚┼ ├╧╥╥┼├╘
╥┼╙╒╠╘╙ ┬┼╞╧╥┼ ╒╬╥┼╙╘╥╔├╘┼─ ╒╙┼. ╔╘
╔╙ ╬╧╘ ├┼╥╘╔╞╔┼─! ┘╧╒ ┴╥┼ ╥┼╙╨╧╬╙╔┬╠┼
╞╧╥ ╘╚┼ ╥┼╙╒╠╘╙
╞╧╥ ╘╚╧╙┼ ╧╘╚┼╥╙ ├╧╬├┼╥╬┼─
┴ MOVING VEHICLE'S PERFORMANCE CAN BE
IMPROVED IF THE WEIGHT OF THE VEHICLE
IS DISTRIBUTED TO THE SUPPORTING
POINTS IN A MANNER THAT WILL CAUSE
THE VEHICLE TO REACT IN A
PREDETERMINED WAY TO A GIVEN SET OF
CONDITIONS.
┴IRCRAFT ARE UNIQUE WHEN COMPARED TO
EARTHBOUND VEHICLES IN THAT AS THEY
BECOME AIRBORNE THE SUPPORT FOR THE
MASS IS TRANSFERRED FROM THE GEAR TO
THE AIRFOIL (WING/WINGS) WHICH IS
DESIGNED TO FUNCTION BEST WHEN THE
VEHICLE IS LOADED IN A MANNER THAT
PLACES THE SUPPORTED WEIGHT WITHIN
SPECIFIED LIMITS ALONG THE CHORD AND
THE SPAN OF THE AIRFOIL/S.
╘HE CHORD BEING THE DISTANCE FROM THE
LEADING EDGE TO THE TRAILING EDGE OF
AIRFOIL AND THE SPAN BEING THE LENGTH
OF THE AIRFOIL FROM THE ATTACH POINT
TO THE OUTERMOST TIP.
╘HOSE OF YOU WITH EARTHBOUND VEHICLES
ARE NOT NORMALY 'PRIVY' TO THESE
PREDETERMINED ENGINEERING DATA AND
MUST EXPERIMENT ON YOUR OWN TO
DETERMINE THE ╧╨╘╔═╒═ BALANCE FOR THE
INTENDED USE AND PERFORMANCE REQUIRED
OF THE EARTHBOUND VEHICLE!
╧╬┼ WAY OF DETERMINING THE WEIGHT
DISTRIBUTION OF A VEHICLE(MASS) IS TO
DETERMINE THE WEIGHT AT EACH
SUPPORTING POINT, I.E., THE WHEELS,
OR WHATEVER. ├ASE OF A BOAT--THE
SUPPORT POINTS MUST BE ESTABLISHED-3
ARE ENOUGH-BOW AND TWO AT THE
TRANSOM/STERN-EQUIDISTANCE FROM THE
CENTERLINE. ╘O OBTAIN THESE DATA, THE
MASS MUST BE ╠┼╓┼╠, LATERALLY AND
LONGITUDINALLY, ON THE SCALE AT EACH
POINT. 3 POINTS-3 SCALES; 4 POINTS-4
SCALES,ETC
╒╙┼ ┴├├╒╥┴╘┼ ╙├┴╠┼╙!!
╞╒┼╠, ╧╔╠, ╫┴╘┼╥/┴╬╘╔╞╥┼┼┌┼ ETC.
═┴╦┼╙ ╘╚┼ ╩╧┬ ╙╔═╨╠┼ ╔╞ ┴╠╠ ┴╘
├┴╨┴├╔╘┘ ┼STABLISH THE ├┼╬╘┼╥╠╔╬┼
LONGITUDINALLY BY MEASUREMENT-LATERAL
CENTER. ─ROP PLUM BOBS FROM THE
CENTERLINE AT THE EXTREMITIES AND
SNAP A CHALK LINE ON THE FLOOR. ═ARK
THE EXTREMITIES ON THE CHALK LINE.
╞ORWARD MARK IS ─┴╘╒═ FOR FUTURE
CONPUTATIONS. ╞ROM EASILY
IDENTIFIABLE POINTS ON THE STRUCTURE,
DROP A PLUM BOB, MARK, AND MAKE A
NOTE TO IDENTIFY THE POINT CHOSEN,
FOR FUTURE USE. ╘HE MORE POINTS
CHOSEN THE BETTER.
╔F AT LEAST SOME OF THESE POINTS
EXTEND TO THE UPPER INTERIOR/EXTERIOR
FOR LATER IDENTIFICATION, THEY WILL
BE OF PRIME IMPORTANCE TO YOU LATER.
├HOOSE POINTS EASILY DEFINABLE:
PROMINENT STRUCTURE/PERMENENT
EQUIMENT. ╠ATERAL WEIGHT DIFFERENCES
CAN BE EQUALIZED BY ADDING, REMOVING,
OR MOVING EQUIPMENT/WEIGHT.
╦┼┼╨ ┴ ╥┼├╧╥─ ╧╞ ╫╘. ├╚┴╬╟┼╙ & ╬╧╘┼
╘╚┼ ╠╧├┴╘╔╧╬ ╧╞ ┴╬┘╘╚╔╬╟ ┴──┼─/
═╧╓┼─/ ╥┼═╧╓┼─. ═AKE LATERAL
DISTRIBUTION AS EQUAL AS POSSIBLE FOR
THE INITIAL DETERMINATION OF THE
├┼╬╘┼╥ ╧╞ ╟╥┴╓╔╘┘ (├╟).
╔F YOU NEED A LATERAL OFF-BALANCE
CONDITION, ADD THE NECESSARY WT.
LATER.
╠ET THE LONGITUDINAL WEIGHT
DISTRIBUTION FALL WHERE IT MAY FOR
NOW. ╘HE PROGRAM WILL FIND THE ├╟ FOR
YOU.
╥┼├╧╥─ ╘╚┼ ╫┼╔╟╚╘ ╙╚╧╫╬ ╧╬ ┼┴├╚ ╙├┴╠┼
AND DOUBLE CHECK THAT YOU CAN
IDENTIFY EACH OF THE WEIGH POINTS AS
INCHES FROM THE FORWARDMOST MARK ON
THE ├┼╬╘┼╥╠╔╬┼ ─┴╘╒═ ╥┼═┼═┬┼╥
─┴╘╒═ WILL ╬┼╓┼╥ CHANGE UNLESS YOU
ADD LENGTH/WEIGHT FORWARD OF ─┴╘╒═.
╘HE PROGRAM DOES THIS MATH FOR YOU
BUT A FEW DEFINITIONS SEEM TO BE IN
ORDER.
CG=TOTAL MOMENT/TOTAL WEIGHT
MOMENT=ARM*WEIGHT
ARM=INCHES (AFT) OF DATUM
╘OTAL MOMENTS & WEIGHTS ARE THE SUMS
OF THE ABOVE COMPUTATIONS.
╘OTAL ═╧═┼╬╘╙ (┼┴├╚ WEIGH POINT
┴╥═╪╫╘)
╘OTAL ╫┼╔╟╚╘(SUM OF EACH SCALE
READING)
┼╪┴═╨╠┼: (DATA PICKED RANDOMLY)
╞OR CONVENTIONAL TAILDRAGGER
AIRCRAFT-
╠EFT GEAR WT.=392 LBS.
╥T. GEAR WT.=393 LBS.
╘AIL WHEEL WT.=49 LBS.
╠. GEAR ARM= 41 INCHES.
╥. GEAR ARM= 41 INCHES.
╘. GEAR ARM=288 INCHES.
═OMENT 1 (╠ OR ╥)=392 ╪ 41=16072
IN/LBS
═OMENT 2 (OTHER) =393 ╪ 41=16113
IN/LBS
═OMENT 3 =49 ╪ 288=14112
IN/LBS
╘OTAL WT.=392+393+49=834 LBS.
╘OTAL ═OMENT=46297 IN/LBS.
├╟=46297/834=55.512 IN.AFT OF ─┴╘╒═
╫HETHER A AIRVEHICLE IS CONTROLLABLE
IS DETERMINED BY THE DESIGNER AND
DEPENDS ON THE AIRFOIL DESIGN AND
WHERE IT IS LOCATED ON THE AIRFRAME.
╘HE DESIGNER, WILL ESTABLISH A ═┴╪
FORWARD AND A ═┴╪ AFT CG LIMIT.
╘╚┴╘'╙ ╚╧╫├╧═┼ ╫┼╔╟╚╘ & ┬┴╠┴╬├┼!
─┼╞╔╬╔╘╔╧╬: ┬┴╠┴╬├┼-LOCATION OF THE
├╟ ON THE LONGITUDINAL AXIS OF A
AIRCRAFT. ╧THER TYPES OF VEHICLES
WILL PROBABLY NOT HAVE THIS SAFETY
LUXURY BUT THEN, OPERATION IS NOT IN
SUCH A CRITICAL ENVIRONMENT!
─ON'T FORGET THE PASSENGERS - ┴LLOW A
REASONABLE WEIGHT AVERAGE LIKE
160/170 LBS. OR THE KNOWN VALUE. ╦EEP
RECORD: FUEL/OIL TANK CENTER ARMS.