ABCDEFGHIJKLMNOPQRSTUVWXYZ
1
###########################################################
2
Sinjid's Single Body Orbital Calculator
3
###########################################################
4
5
Step 1:
Go to File > Make a Copy... to have your own version of this spreadsheet
If you are increasing the accuracy or otherwise changing the format of your own copy:
6
Step 2:
Select a body from the dropdown list
The orbital period box of row 1 and darkness period boxes will not change like the others
7
Step 3:
Input cells on the table are highlighted light green
as I made use of CONCATENATE and ROUND so that it would display in hr:min:s format
8
Find the row with the two inputs you are looking for
9
Step 4:
Put in your numbers and behold the answers you seek
10
See below for examples
11
12
Body:Minmus
13
Mass (kg):2.65E+19
14
μ (m^3/s^2):1.77E+09
15
Radius (m):6.00E+04
16
17
Meters from Sea LevelHours:Minutes:SecondsMeters per SecondMeters from Body CenterRow
18
OrbitalMax DarknessOrbital Velocity atΔV to Circularize at
19
Apoapsis*Periapsis*PeriodEccentricityApoapsisPeriapsisApoapsisPeriapsisSemi-Major AxisSemi-Minor Axis
20
776,580100,00014:36:331:17:20.679261362031498,290365,8591
21
100715,78511:13:201:51:210.856234186230417,943215,9272
22
357,943357,94311:13:200:30:530.000656500417,943417,9433
23
24
* When entering values for Apoapsis and/or Periapsis the two are interchangeable
25
26
Eg. 1
You want a circular orbit (Eccentricity of 0) around Kerbin with an
|Eg. 2
You want to evenly distribute 3 sattelites into the
27
orbital period of 1 and a half hours
|
orbit we found in the first example. To do this we'll
28
1
Select Kerbin from the list
|
set one end of our orbit at the height of our final orbit
29
2
Find the row to input eccentricity and orbital period (row 3)
|
and find where we should place the other end so that
30
3
Enter 1:30:00 into the orbital period box and 0 into the
|
when our ship completes one orbit, satellites in the
31
eccentricity box|
final orbit will have travelled 1/3 or 2/3 of the way
32
4
The resulting orbit has an altitude of 776,580 m
|
around their own orbit
33
-----------------------------------------------------------------------------------------------------------------------------------------------------1
Copy the Apoapsis or Periapsis (They'll be the same)
34
Eg. 3
We can use this table to give us a good approximation of how much
|from row 3.
35
ΔV we'll have to spend to complete examples 1 and 2
|2
Row 2 is what we are going to use now as it's inputs
36
from LKO|
are apoapsis and orbital period
37
1
Use row one to set a circular, 100 km orbit (or wherever else you're
|3
Right click > Paste special > Paste VALUES only
38
starting from)|
into the apoapsis box
39
2
Take note of the orbital velocity of 2246 m/s
|
If you try entering 0:30:00 into the period box the
40
3
Change the row 1 apoapsis (or periapsis) to be our final height (776,580 m)
periapsis will become a negative number, which means
41
4
Now take note that the velocity at periapsis is now 2586 m/s, this is
|
it is BELOW THE SURFACE
42
different from our starting velocity by 340 m/s. That is how much ΔV
|
instead enter 1:00:00
43
you'll spend going from your starting orbit to the new orbit
|4
See that you must have a periapsis of 124,474 m
44
Note that this is the same as the ΔV to circularize at periapsis, this is
to evenly distribute your satellites AND that the
45
because going from an elliptical orbit to circular costs the same ΔV as
circularization burn will require ~272 m/s ΔV
46
doing it the other way around. (This is true for changing between any 2 orbits)
47
5
Now compare your orbital velocity at periapsis of row 1 (what we just set)
48
and row 2 (from example 2), they are different by 15 m/s. Again this
|
49
is how much ΔV it'll cost to raise your periapsis from 100 km to ~124 km
50
6
Finally, take note of the ΔV to circularize at apoapsis of row 2 is 272 m/s
51
(We also saw this in example 2)
|
52
7
Adding them all up we get 340 + 15 + 272 = 627 m/s
|
53
This means that performing our examples would cost us approximately
54
627 m/s of ΔV|
55
56
57
58
59
60
61
62
63
64
65
66
67
68
69
70
71
72
73
74
75
76
77
78
79
80
81
82
83
84
85
86
87
88
89
90
91
92
93
94
95
96
97
98
99
100