Orbital Case 02: ISS in Spherical Gravity

Orbital scenario 2 tests an idealized International Space Station in a nearly circular orbit.


Constants and Models

This scenario uses an idealized International Space Station vehicle model, specified here. The MET atmosphere model defines atmospheric properties based on time, position, and solar effects specified here. The gravitational model used was an inverse-square gravitation field, specified here. The geodesy model used for this scenario is the WGS-84 rotating model, specified here.


Initial Conditions

Scenario Orbital Case 02: Keplerian Propagation
Vehicle ISS
Orbit Type Nearly Circular
Atmospheric Model [1] F10.7= 128.8 10-22 watt / m2 / Hz
ap= 15.7
Time 2007/324:00:00:00 (UTC)
Duration 28,800 s
Gravitation Model Order Inverse Square Gravity Gradient Effects Off
Planetary Ephemeris
Sun/Moon Perturbations		 Off
Off
Initial states
Aerodynamic Characteristics
 Sref (m2)
CL
CD
CY
Cl
Cm
Cn
 1,400
0.0
0.0
0.0
0.0
0.0
0.0
J2000 Position
(m)		 X Position
Y Position
Z Position 		-4,292,653.41
955,168.47
5,139,356.57
J2000 Velocity
(m/s)		 X Velocity
Y Velocity
Z Velocity 		109.649663
-7,527.726490
1,484.521489
Attitude (LVLH)
(deg)
(3-2-1 Sequence)		 Roll
Pitch
Yaw 		0.000000
-11.600000
0.000000
Inertial Rotation Rate (Body Axes)
(deg/s)		 Roll Rate
Pitch Rate [2]
Yaw Rate 		0.000000
-0.06499944198233
0.000000

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Errata

Below is the list of erratum that are relevant to changes made on this page that no longer match the report. The full list can be found on the Home Page.

[1] For each orbital IC table with the Atmospheric Model enabled replace Ap with ap: Volume II Report ↩︎

[2] Pages 70 through 92, Tables 47 through 72, row 9, column 2 each scenario that specifies an initial inertial pitch rate of -0.065 deg/s should be either -0.06499944198233 deg/s for “Nearly circular” scenarios and -0.06429904441202 deg/s for "Highly elliptical" scenarios to match the precision of the data provided: Volume II Report ↩︎