Orbital Minotaur I - Manual (Page 31)

Minotaur I User’s Guide Section 3.0 – General Performance
Figure 3.3-8. Minotaur I with 61” Fairing Performance Curves for WFF Launches
3.4. Injection Accuracy
Minotaur I injection accuracy limits are summarized in Table 3.4-1. Better accuracy can likely be provided
depending on specific mission characteristics. For example, heavier payloads will typically have better
insertion accuracy, as will higher orbits. Furthermore, an enhanced option for increased insertion
accuracy is also available (Section 8.9). It utilizes the flight proven Hydrazine Auxiliary Propulsion System
(HAPS) developed on the Pegasus program.
Table 3.4-1. Minotaur I Injection Accuracy
Error Type
Tolerance
(Worst Case)
Error Source
Altitude
(Insertion Apse)
±18.5 km (10 nmi)
Stage 4 motor performance uncertainty and guidance
algorithm uncertainty
Altitude
(Non-Insertion Apse)
±92.6 km (50 nmi)
Stage 4 motor performance and guidance algorithm
uncertainty and navigation (INS) error
Altitude
(Mean)
±55.6 km (30 nmi)
Stage 4 motor performance and guidance algorithm
uncertainty and navigation (INS) error
Inclination ±0.2°
Guidance algorithm uncertainty and navigation
(INS) error
Release 3.0 March 2014 18