Orbital Minotaur I Bedienungsanleitung

Minotaur I User’s Guide Table of Contents PAGE Figure 4.3-1. Payload Acoustic Environment during Liftoff and Flight ...

Minotaur I User’s Guide Table of Contents PAGE Figure 8.10-1. Minotaur I SRSS Significantly Attenuates Peak LV Dynamic Environments ...

Minotaur I User’s Guide Glossary 6DOF Six Degrees of Freedom A/D Arm/Disarm AADC Alaska Aerospace Development Corporation ACAT-1 Acquisition Catego

Minotaur I User’s Guide Glossary MTO Medium Transfer Orbit NASA National Aeronautics and Space Administration NCU Nozzle Control Unit NRE Non-Recur

Minotaur I User’s Guide Section 1.0 – Introduction 1. INTRODUCTION This User’s Guide is intended to familiarize payload mission planners with the

Minotaur I User’s Guide Section 1.0 – Introduction Minotaur I vehicle) and the existing ground support equipment that is used to conduct Minotaur

Minotaur I User’s Guide Section 1.0 – Introduction Figure 1.1-2. Space Launch Performance for the Minotaur Family Demonstrates a Wide Range of Pa

Minotaur I User’s Guide Section 2.0 – Minotaur I Configurations 2. MINOTAUR I CONFIGURATIONS 2.1. Minotaur I Launch System Overview The Minotau

Minotaur I User’s Guide Section 2.0 – Minotaur I Configurations Division (SDL). Orbital is the launch vehicle provider. This integrated team wi

Minotaur I User’s Guide Section 2.0 – Minotaur I Configurations Thrust Vector Control (LITVC) subsystem, S2 ignition safe/arm device, a Roll Contr

March 2014 Minotaur I User’s Guide Release 3.0 Approved for Public Release Distribution Unlimited ©2013 Orbital Sciences

Minotaur I User’s Guide Section 2.0 – Minotaur I Configurations 2.3.2.2. Attitude Control Systems The Minotaur I Control System provides three-

Minotaur I User’s Guide Section 2.0 – Minotaur I Configurations The TDRSS then relays the telemetry to the ground where it is routed to the Launch

Minotaur I User’s Guide Section 2.0 – Minotaur I Configurations 2.4. Launch Support Equipment The Minotaur I LSE is designed to be readily adaptab

Minotaur I User’s Guide Section 2.0 – Minotaur I Configurations Figure 2.4-1. Minotaur I EGSE Configuration Release 3.0 March 2014 10

Minotaur I User’s Guide Section 3.0 – General Performance 3. GENERAL PERFORMANCE 3.1. Mission Profiles Minotaur I can attain a range of posigrad

Minotaur I User’s Guide Section 3.0 – General Performance Figure 3.2-1. Flexible Processing and Portable GSE Allows Operations from Multiple Rang

Minotaur I User’s Guide Section 3.0 – General Performance 3.2.1. Western Launch Sites For missions requiring high inclination orbits (greater than

Minotaur I User’s Guide Section 3.0 – General Performance Table 3.3-1. Common Mission Options and Associated Masses (These Masses Must Be Subtrac

Minotaur I User’s Guide Section 3.0 – General Performance Figure 3.3-2. Minotaur I Performance Curves for KLC Launches Figure 3.3-3. Minotaur

Minotaur I User’s Guide Section 3.0 – General Performance Figure 3.3-4. Minotaur I Performance Curves for WFF Launches Figure 3.3-5. Minotaur

Minotaur I User’s Guide Revision Summary REVISION SUMMARY VERSION DOCUMENT DATE CHANGE PAGE 1.0 TM-14025 Mar 2002 Initial Release All

Minotaur I User’s Guide Section 3.0 – General Performance Figure 3.3-6. Minotaur I with 61” Fairing Performance Curves for KLC Launches Figure

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. In

Minotaur I User’s Guide Section 3.0 – General Performance 3.5. Payload Deployment Following orbit insertion, the Minotaur I Stage 4 avionics subs

Minotaur I User’s Guide Section 4.0 – Payload Environment 4. PAYLOAD ENVIRONMENT CAUTION The predicted environments provided in this user's

Minotaur I User’s Guide Section 4.0 – Payload Environment 4.1.1. Transient Loads During upper stage burnout, prior to staging, the transient loads

Minotaur I User’s Guide Section 4.0 – Payload Environment 4.1.2. Steady-State Acceleration Steady-state vehicle accelerations are determined from

Minotaur I User’s Guide Section 4.0 – Payload Environment 4.2. Payload Vibration Environment The in-flight random vibration curve shown in Figure

Minotaur I User’s Guide Section 4.0 – Payload Environment through 4.4. The payload design should comply with the testing and design factors of safe

Minotaur I User’s Guide Section 4.0 – Payload Environment provides conditioned air to the payload in the Payload Processing Facility (PPF) after fa

Minotaur I User’s Guide Section 4.0 – Payload Environment The fairing peak vent rate is typically less than 0.6 psi/sec. Fairing deployment will b

Minotaur I User’s Guide Preface PREFACE This Minotaur I User's Guide is intended to familiarize potential space launch vehicle users with th

Minotaur I User’s Guide Section 4.0 – Payload Environment Table 4.8-1 lists the frequencies and maximum radiated signal levels from vehicle antenn

Minotaur I User’s Guide Section 5.0 – Payload Interfaces 5. PAYLOAD INTERFACES This section describes the available mechanical, electrical and Lau

Minotaur I User’s Guide Section 5.0 – Payload Interfaces Figure 5.1.1.1-1. 50” Payload Fairing Dynamic Envelope with 38” (97 cm) Diameter Payloa

Minotaur I User’s Guide Section 5.0 – Payload Interfaces Figure 5.1.2.1-1. 61” Payload Fairing Dynamic Envelope with 38” (97 cm) Diameter Payloa

Minotaur I User’s Guide Section 5.0 – Payload Interfaces Figure 5.1.3-1. 50” Payload Fairing Access Door Placement Zone Release 3.0 March 2014

Minotaur I User’s Guide Section 5.0 – Payload Interfaces Figure 5.1.3-2. 61” Payload Fairing Access Door Placement Zone 5.2. Payload Mechanical

Minotaur I User’s Guide Section 5.0 – Payload Interfaces Figure 5.2.1-1. Minotaur Coordinate System Release 3.0 March 2014 33

Minotaur I User’s Guide Section 5.0 – Payload Interfaces 5.2.2. Orbital Supplied Mechanical Interface Control Drawing Orbital will provide a toler

Minotaur I User’s Guide Section 5.0 – Payload Interfaces provide LV minimum structural interface design criteria for shear, bending moment, axial

Minotaur I User’s Guide Section 5.0 – Payload Interfaces structure that supports the dual payload configuration includes a 50” cylindrical section

Minotaur I User’s Guide Table of Contents PAGE 1. INTRODUCTION ...

Minotaur I User’s Guide Section 5.0 – Payload Interfaces are within specified limits presented in Section 5.4.1. Separation velocities are usually

Minotaur I User’s Guide Section 5.0 – Payload Interfaces Figure 5.2.5.1-1. Orbital 38” Separation System Release 3.0 March 2014 38

Minotaur I User’s Guide Section 5.0 – Payload Interfaces 5.2.5.2. Planetary Systems Motorized Lightband (MLB) The Planetary Systems MLB, Figure 5.

Minotaur I User’s Guide Section 5.0 – Payload Interfaces 5.3. Payload Electrical Interfaces The payload electrical interface, shown in Figure 5.3-

Minotaur I User’s Guide Section 5.0 – Payload Interfaces Figure 5.3.1-1. Payload Umbilical 1:1 Pin Outs 5.3.2. Payload Interface Circuitry Stan

Minotaur I User’s Guide Section 5.0 – Payload Interfaces 10 mA. Separation breakwire monitors can be specified if required. The number of analog ch

Minotaur I User’s Guide Section 5.0 – Payload Interfaces 5.4. Payload Design Constraints The following sections provide design constraints to ensu

Minotaur I User’s Guide Section 5.0 – Payload Interfaces spacecraft, isolation system and/or separation system. Therefore, the final determination

Minotaur I User’s Guide Section 6.0 – Mission Integration 6. MISSION INTEGRATION 6.1. Mission Management Approach OSP-3 is managed through U.S.

Minotaur I User’s Guide Section 6.0 – Mission Integration The Minotaur organization uses highly skilled personnel with extensive Minotaur experienc

Minotaur I User’s Guide Table of Contents PAGE 4.7. Payload Contamination Control ...

Minotaur I User’s Guide Section 6.0 – Mission Integration The typical Mission Cycle interweaves the following activities: a. Mission management, d

Minotaur I User’s Guide Section 6.0 – Mission Integration A typical mission field integration schedule is provided in Figure 6.2-2. The field integ

Minotaur I User’s Guide Section 6.0 – Mission Integration 6.3. Mission Integration Process 6.3.1. Integration Meetings The core of the mission i

Minotaur I User’s Guide Section 6.0 – Mission Integration 6.4. Documentation Integration of the payload requires detailed, complete, and timely pr

Minotaur I User’s Guide Section 6.0 – Mission Integration 6.4.1.5. Payload Thermal Model for Integrated Thermal Analysis An integrated thermal ana

Minotaur I User’s Guide Section 6.0 – Mission Integration 6.4.2.1. Launch Vehicle to Payload ICD The launch vehicle-to-payload ICD details all of

Minotaur I User’s Guide Section 6.0 – Mission Integration 6.4.2.6. Missile System Pre-Launch Safety Package (MSPSP) Annex The MSPSP Annex document

Minotaur I User’s Guide Section 6.0 – Mission Integration 6.5. Safety 6.5.1. System Safety Requirements In the initial phases of the mission int

Minotaur I User’s Guide Section 7.0 – Ground and Launch Operations 7. GROUND AND LAUNCH OPERATIONS Minotaur ground and launch operations processi

Minotaur I User’s Guide Section 7.0 – Ground and Launch Operations 7.1. Launch Vehicle Integration Overview Orbital utilizes the same fundamental

Minotaur I User’s Guide Table of Contents PAGE 5.4.5. Payload Dynamic Frequencies ...

Minotaur I User’s Guide Section 7.0 – Ground and Launch Operations 7.1.3. Minuteman Motor Integration and Test Activities The Minuteman Stage 1 an

Minotaur I User’s Guide Section 7.0 – Ground and Launch Operations 7.2.1. Payload to Minotaur I Integration The integrated launch processing activ

Minotaur I User’s Guide Section 7.0 – Ground and Launch Operations 7.3.1. Booster Assembly Stacking/Launch Site Preparation Prior to the arrival o

Minotaur I User’s Guide Section 7.0 – Ground and Launch Operations 7.3.4. Launch The typical Minotaur final countdown procedure commences at 5 hou

Minotaur I User’s Guide Section 7.0 – Ground and Launch Operations 7.3.6. Launch Rehearsals Two rehearsals are conducted prior to each launch. Th

Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities 8. OPTIONAL ENHANCED CAPABILITIES The Minotaur launch service is structured

Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities locations on the fairing. Required door locations outside the allowable envel

Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities 8.6. Enhanced Contamination Control To meet the requirement for a low contami

Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities 8.6.4. Fairing Surface Cleanliness The inner surface of the fairing and expos

Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities sites, the LV switches telemetry output to the TDRSS antenna and points the a

Minotaur I User’s Guide Table of Contents PAGE 6.5. Safety ...

Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities each particular spacecraft and with location on the spacecraft. Generally, a b

Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities 8.13. Minotaur I Launch Vehicle Enhanced Performance Configuration 8.13.1.

Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities Figure 8.15-1. Typical Propellant Loading Schematic The scope of this enhan

Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities Figure 8.15-2. UPC Provides Reliable and Demonstrated Hydrazine Servicing fo

Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities 8.17. Poly-Pico Orbital Deployer (P-POD) When there is excess performance ava

Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities Minotaur I Lite provides a larger volume and greater stack height to the subor

Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities 8.19. Alternate Launch Location Orbital has extensive experience processing a

Minotaur I User’s Guide Appendix A APPENDIX A PAYLOAD QUESTIONNAIRE Release 3.0 March 2014 A-1

Minotaur I User’s Guide Appendix A SATELLITE IDENTIFICATION FULL NAME: ACRONYM: OWNER/OPERATOR: INTEGRATOR(s): SPACE CRAFT AND MISSION DESC

Minotaur I User’s Guide Appendix A LAUNCH WINDOW REQUIREMENTS NOMINAL LAUNCH DATE: LAUNCH SITE: OTHER CONSTRAINTS (if not already implicit from LA

Minotaur I User’s Guide Table of Contents PAGE 8.10. Payload Isolation System ...

Minotaur I User’s Guide Appendix A EARLY ON-ORBIT OPERATIONS Briefly describe the satellite early on-orbit operations, e.g., event triggers (separa

Minotaur I User’s Guide Appendix A SPACECRAFT PHYSICAL DIMENSIONS STOWED CONFIGURATION Length/Height: Diameter:

Minotaur I User’s Guide Appendix A SPACECRAFT MASS PROPERTIES* PRE-SEPARATION Inertia units:  lbm-in2  kg-m2 Mass:

Minotaur I User’s Guide Appendix A SPACECRAFT SLOSH MODEL* SLOSH MODEL UNDER 0 g Pendulum Mass:  lbm  kg Pen

Minotaur I User’s Guide Appendix A SPACECRAFT ENVIRONMENTS THERMAL DISSIPATION Spacecraft Thermal Dissipation, Pre-Launch Encapsulated:

Minotaur I User’s Guide Appendix A ELECTRICAL INTERFACE Bonding Requirements: Are Launch Vehicle Supplied Pyro Commands Required? Yes / No If Ye

Minotaur I User’s Guide Appendix A REQUIRED PASS-THROUGH SIGNALS Item # Pin Signal Name From LEV To Satellite Shielding Max Current (amps) Total

Minotaur I User’s Guide Appendix A MECHANICAL INTERFACE DIAMETER Describe Diameter of Interface (e.g. Bolt Circle, etc): SEPARATION SYSTEM Will

Minotaur I User’s Guide Appendix A GROUND SUPPORT EQUIPMENT Describe any additional control facilities (other than the baseline Support Equipment B

Minotaur I User’s Guide Appendix A GROUND SUPPORT EQUIPMENT (CONTINUED) LEV Describe (in the table below) Satellite EGSE to be located in the LEV.