Orbital Minotaur VI - Manual (Page 35)

Minotaur IV • V • VI User’s Guide Section 3.0 – General Performance
3.3. Performance Capability
Minotaur IV performance curves for circular orbits of various altitudes and inclinations are shown on the
next several pages for launches from all four Spaceports in metric and English units. These performance
curves provide the total mass above the standard, non-separating interface. The mass of the separation
system, and any Payload Adapter (PLA) that is attached to the 38.81 in. interface, is to be accounted for
in the payload mass allocation. Table 3.3-1 shows a number of common options and the mass associated
with each . Figures 3.3-1 and 3.3-2 show relative performance of the Minotaur IV family of launch vehicles
for representative launches from KLC and CCAFS.
Table 3.3-1. Common Mission Options and Associated Masses
(These Masses Must Be Subtracted from the LV Performance)
Option
Total Mass (kg)
(These Masses Must Be
Subtracted from the LV
Performance)
Portion of Total Mass
That Remains with SV
Post Separation (kg)
Enhanced Telemetry 9.85 0
TDRSS 8.54 0
62” Payload Adapter Cone
1
-10.32 0
Two Piece Payload Adapter Cone (92” to 38”)
1
9.07 0
38” Orbital Separation System
2
12.24 4.0
38” RUAG Low Shock Separation System (937S)
2
19.89 6.16
38” RUAG Separation System (937B)
2
18.25 5.18
38” Lightband
2
8.85 2.52
38” Softride and Ring
3
9 to 18 0
Notes:
1
For more information on these payload cone options, refer to Table 5.2.4.1-1.
2
For more information on these separation system options, refer to Table 5.2.5-1.
3
A range is provided for the softride option; actual mass is based on satellite requirements.
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