Pipistrel Sinus 503 User Manual

52
SINUS motorglider
www.pipistrel.si
REV. 0
53
SINUS motorglider
www.pipistrel.si
REV. 0
Sample CG calculation
Guidelines
Gtotal is the total mass of empty aircraft. All calculations can be performed with aircraft empty
weight and empty weight centre of gravity (c.g.), as the pilots sits directly below the centre of gravity
and do not cause the c.g. to be shifted. The amount of fuel quantity also has no impact on the c.g..
WARNING! Both pilots’ weight and weight of fuel do not inuence c.g. or their inuence is
insignicant. However, baggage can inuence the c.g. severely and may cause the aircraft to
become uncontrollable!
Basic CG formulas and calculation
The below instructions are valid for Sinus Tail Wheel and Nose Wheel editions. Read thoroughly. Note
also that the basic c.g. at 287 mm will be used purely as an example.
First, weigh the aircraft according to the procedure described in this chapter and write down values
of G1 (sum of scale readings at main wheels) and G2 (scale reading at tail/front wheel). Then calcu-
late the position of c.g. in milimeters (mm) from the datum (wing’s leading edge at wing root).
For Tail wheel edition of Sinus ultralight motorglider use the following formula:
where:
G2tail is the scale reading at the tail wheel,
Gtotal is the sum of G1 and G2tail (G1+G2tail), a.k.a. aircraft empty weight
a is the distance from main wheel axis to wing’s leading edge,
b is the distance between main and tail wheel axis.
For Nose wheel edition of Sinus ultralight motorglider use the following formula:
where:
G2back is the sum of scale readings at both main (back) wheels,
Gtotal is the sum of G1 and G2back (G1+G2back), a.k.a. aircraft empty weight
a is the distance from nose wheel axis to wing’s leading edge,
b is the distance from main wheel axis to wing’s leading edge,
c = (a+b) is the sum of both distances above.
Second, determine the c.g. position in percentage (%) of Mean Aerodynamic Chord (MAC) with fol-
lowing the formula:
where:
CGmm is the position of CG in milimeters (mm),
R is the dierence between wing’s leading edge and MAC’s leading edge (69 mm),
MAC is the Mean Aerodynamic Chord (869 mm).
CG
G b
G
a
G m
m
G
mm mm
mm
tail
tota
l
tail
total
=
·
+ =
·
+ =
2 2 4300
110 287
CG
G c
G
a
G m
m
G
mm mm
mm
back
total
back
total
=
·
- =
·
- =
1 1 1525
1020 287
CG
CG
R
MA
C
mm mm
mm
MAC
mm
%
. %=
-
· =
-
· =
100
287 69
869
100 25 1
Weight and balance

Pipistrel Sinus 503 Specifications

General

Brand	Pipistrel
Model	Sinus 503
Category	Aircrafts
Language	English