Orbital Minotaur I - Manual (Page 10)

Minotaur I User’s Guide Table of Contents
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Figure 4.3-1. Payload Acoustic Environment during Liftoff and Flight ....................................................... 23
Figure 4.2-1. Payload Random Vibration Environment during Flight ........................................................ 23
Figure 4.4-1. Maximum Shock Environment – Launch Vehicle to Payload ............................................... 24
Figure 4.4-2. Maximum Shock Environment – Payload to Launch Vehicle ............................................... 24
Figure 4.6.1-1. Minotaur I HVAC System Provides Conditioned Air to the Payload.................................. 25
Figure 4.6.2-1. Typical Minotaur I Fairing Pressure Profile ....................................................................... 26
Figure 5.1.1.1-1. 50” Payload Fairing Dynamic Envelope with 38” (97 cm) Diameter
Payload Interface ............................................................................................................ 29
Figure 5.1.2.1-1. 61” Payload Fairing Dynamic Envelope with 38” (97 cm) Diameter
Payload Interface ............................................................................................................ 30
Figure 5.1.3-1. 50” Payload Fairing Access Door Placement Zone .......................................................... 31
Figure 5.2.1-1. Minotaur Coordinate System ............................................................................................. 33
Figure 5.2.4.1.1-1. COSMIC Spacecraft Configuration Utilized the Orbital MicroStar Bus to
Fly Six SVs ................................................................................................................... 35
Figure 5.2.4.1.1-2. JAWSAT Multiple Payload Adapter Load Bearing Spacecraft .................................... 35
Figure 5.2.4.1.1-3. Five Bay Multiple Payload Adapter Concept ............................................................... 36
Figure 5.2.4.1.2-1. DPAF Configuration ..................................................................................................... 36
Figure 5.2.5.1-1. Orbital 38” Separation System ....................................................................................... 38
Figure 5.2.5.2-1. 38” Planetary Sciences Motorized Lightband ................................................................ 39
Figure 5.2.5.3-1. RUAG 937S 38” Separation System ............................................................................. 39
Figure 5.3-1. Payload Electrical Interface Block Diagram Payload Interface Circuitry .............................. 40
Figure 5.3.1-1. Payload Umbilical 1:1 Pin Outs ......................................................................................... 41
Figure 6.1-1. Mission Integration Team ..................................................................................................... 45
Figure 6.2-1. Typical Minotaur Mission Integration Schedule .................................................................... 47
Figure 6.2-2. Typical Mission Field Integration Schedule .......................................................................... 48
Figure 7-1. Hardware Flow – Factory to Launch Site ................................................................................ 55
Figure 7.1-1. Launch Vehicle Processing Flow.......................................................................................... 56
Figure 7.1.5-1. Minotaur I Processing Is Performed at the MPF at VAFB ................................................. 57
Figure 7.3.4-1. Notional Minotaur Countdown Timeline ........................................................................... 60
Figure 7.3.4-2. Minotaur I Prepared for Launch ......................................................................................... 60
Figure 8.3-1. GN
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Purge Interface To Minotaur Fairing (Flyaway at Liftoff) .............................................. 62
Figure 8.4-1. Multiple Access Doors Were Demonstrated on the Optional Minotaur I Large Fairing ........ 63
Figure 8.6-1. Minotaur Team Has Extensive Experience in a Payload Processing
Clean Room Environment ..................................................................................................... 64
Figure 8.7-1. Orbital’s Secure FTS System Block Diagram ....................................................................... 65
Figure 8.8-1. TDRSS 20W LCT2 Transmitter and Cavity Backed S-band Antenna .................................. 66
Figure 8.8-2. TDRSS Notional Telemetry Flow.......................................................................................... 66
Release 3.0 March 2014 ix