Atmospheric Case 17: Two-Stage Rocket, Sea-Level Launch

Atmospheric scenario 17 tests an idealized two-stage rocket launched from sea-level and reaches a highly elliptical orbit without guidance.


Constants and Models

This scenario uses the Two-Stage Rocket vehicle model, specified here. The 1976 STD atmosphere model defines atmospheric properties at various altitudes, specified here. The two-stage rocket's source of gravity is the J2 gravity model, specified here. The geodesy model used for this scenario is the WGS-84 rotating model, specified here.


Initial Conditions

Scenario Atmospheric Case 17: Flight of Two-Stage Launch Vehicle
Vehicle Two-Stage Rocket
Geodesy WGS-84 rotating
Atmosphere US 1976 STD; no wind
Gravitation J2 Duration 200 s
Initial states
Mass Properties (First Stage)
m (kg)
x (m)
y (m)
z (m)
Additional Mass and Aerodynamic Characteristics Specified Here
Full Empty
314,000 134,000
16.918790 9.421642
0 0
0 0
Mass Properties (Second Stage)
m (kg)
x (m)
y (m)
z (m)
Full Empty
99,000 19,000
4.797980 3.947368
0 0
0 0
Geodetic Position
(deg, deg, ft MSL)		 Latitude
Longitude
Altitude, Mean Sea Level 		0
0
0
Velocity (NED Frame)
(ft/s)		 X Velocity (North)
Y Velocity (East)
Z Velocity (Down) 		0
0
-0.32808399
Body Attitude (NED Frame)
(deg)
(3-2-1 Rotation)		 Roll
Pitch
Yaw 		0
55.22
90
Body Angular Rate (NED Frame) [1]
(deg/s)		 Roll Rate
Pitch Rate
Yaw Rate 		0
0
0

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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] Page 56, the Rate section should specify body-axis quantities relative to the local frame: Volume II Report ↩︎