Document Outline

• 1. /INTRODUCTION
  • 1.1. Minotaur Family Performance and Capability
• 2. MINOTAUR IV CONFIGURATIONS
  • 2.1. Minotaur IV Launch System Overview
  • 2.2. Minotaur IV Launch Service
  • 2.3. Minotaur IV Launch Vehicle
    • 2.3.1. Stage 1, 2 and 3 Booster Assemblies
    • 2.3.2. Upper Stage Propulsion
    • 2.3.3. Guidance and Control Assembly (GCA)
      • 2.3.3.1. Avionics
      • 2.3.3.2. Attitude Control Systems
      • 2.3.3.3. Telemetry Subsystem
    • 2.3.4. Payload Interface
    • 2.3.5. Payload Fairing
    • 2.3.6. Minotaur IV Launch Vehicle Enhanced Performance Configurations
      • 2.3.6.1. Minotaur IV+ (STAR 48 Stage 4)
      • 2.3.6.2. Minotaur V (High Energy Performance)
      • 2.3.6.3. Minotaur VI
      • 2.3.6.4. Minotaur VI+ (High Energy Performance)
  • 2.4. Launch Support Equipment
• 3. GENERAL PERFORMANCE
  • 3.1. Mission Profiles
  • 3.2. Launch Sites
    • 3.2.1. Western Launch Sites
    • 3.2.2. Eastern Launch Sites
    • 3.2.3. Alternate Launch Sites
  • 3.3. Performance Capability
    • 3.3.1. Minotaur IV LEO Orbits
    • 3.3.2. Minotaur IV+ LEO Orbits
    • 3.3.3. Minotaur VI LEO Orbits
    • 3.3.4. Elliptical Orbits and High Energy Orbits
  • 3.4. Injection Accuracy
  • 3.5. Payload Deployment
  • 3.6. Payload Separation
  • 3.7. Collision/Contamination Avoidance Maneuver
• 4. PAYLOAD ENVIRONMENT
  • 4.1. Steady State and Transient Acceleration Loads
    • 4.1.1. Transient Loads
    • 4.1.2. Steady-State Acceleration
  • 4.2. Payload Vibration Environment
    • 4.2.1. Random Vibration
    • 4.2.2. Sine Vibration
  • 4.3. Payload Acoustic Environment
  • 4.4. Payload Shock Environment
  • 4.5. Payload Structural Integrity and Environments Verification
  • 4.6. Thermal and Humidity Environments
    • 4.6.1. Ground Operations
      • a. Dry Bulb Temperature: 13 to 29 C (55 to 85 F) controllable to ±5 C (±10 F) of setpoint
      • b. Temperature environment lower limit is 55 F (12.8 C) due to the upper stage motor limits.
      • c. Standard Setpoint = 18.3 C (65 F)
      • d. Dew Point Temperature: 3 to 17 C (38 to 62 F)
      • e. Relative Humidity: determined by drybulb and dew point temperature selections and generally controlled to within ±15%. Relative humidity is bound by the psychrometric chart and will be controlled such that the dew point within the fairing is never ...
      • f. Nominal Flow: 11.3 m3/min (400 cfm)
    • 4.6.2. Powered Flight
    • 4.6.3. Nitrogen Purge (Non-Standard Service)
  • 4.7. Payload Contamination Control
  • 4.8. Payload Electromagnetic Environment
• 5. PAYLOAD INTERFACES
  • 5.1. Payload Fairing
    • 5.1.1. 92” Standard Minotaur Fairing
      • 5.1.1.1. 92” Fairing Payload Dynamic Design Envelope
    • 5.1.2. Optional 110” Fairing
      • 5.1.2.1. 110” Fairing Payload Dynamic Design Envelope
    • 5.1.3. Payload Access Door
  • 5.2. Payload Mechanical Interface and Separation System
    • 5.2.1. Minotaur Coordinate System
    • 5.2.2. Orbital Supplied Mechanical Interface Control Drawing
    • 5.2.3. Standard Non-Separating Mechanical Interface
    • 5.2.4. Optional Mechanical Interfaces
      • 5.2.4.1. Payload Cone Interfaces
      • 5.2.4.2. Dual and Multi Payload Adapter Fittings
        • 5.2.4.2.1. Dual-Payload Adapter Fitting
        • 5.2.4.2.2. Multi-Payload Adapter Fitting (MPAF)
        • 5.2.4.2.3. Minotaur V and VI+ Payload Adapter Fitting
    • 5.2.5. Optional Separation Systems
      • 5.2.5.1. Orbital 38” Separation System
      • 5.2.5.2. Planetary Systems Motorized Lightband (MLB)
      • 5.2.5.3. RUAG 937 Separation Systems
  • 5.3. Payload Electrical Interfaces
    • 5.3.1. Payload Umbilical Interfaces
    • 5.3.2. Payload Interface Circuitry
    • 5.3.3. Payload Battery Charging
    • 5.3.4. Payload Command and Control
    • 5.3.5. Pyrotechnic Initiation Signals
    • 5.3.6. Payload Telemetry
    • 5.3.7. Payload Separation Monitor Loopbacks
    • 5.3.8. Telemetry Interfaces
    • 5.3.9. Non-Standard Electrical Interfaces
    • 5.3.10. Electrical Launch Support Equipment
  • 5.4. Payload Design Constraints
    • 5.4.1. Payload Center of Mass Constraints
    • 5.4.2. Final Mass Properties Accuracy
    • 5.4.3. Pre-Launch Electrical Constraints
    • 5.4.4. Payload EMI/EMC Constraints
    • 5.4.5. Payload Dynamic Frequencies
    • 5.4.6. Payload Propellant Slosh
    • 5.4.7. Payload-Supplied Separation Systems
    • 5.4.8. System Safety Constraints
• 6. MISSION INTEGRATION
  • 6.1. Mission Management Approach
    • 6.1.1. SD/SDL Mission Responsibilities
    • 6.1.2. Orbital Mission Responsibilities
      • a. Launch Vehicle Program Management
      • b. Mission Management
      • c. Engineering
      • d. Launch Site Operations
  • 6.2. Mission Planning and Development
    • a. Mission management, document exchanges, meetings, and formal reviews required to coordinate and manage the launch service.
    • b. Mission analyses and payload integration, document exchanges, and meetings.
    • c. Design, review, procurement, testing and integration of all mission-peculiar hardware and software.
    • d. Range interface, safety, and flight operations activities, document exchanges, meetings and reviews.
    • 6.2.1. Mission Assurance
  • 6.3. Mission Integration Process
    • 6.3.1. Integration Meetings
    • 6.3.2. Mission Design Reviews (MDR)
    • 6.3.3. Readiness Reviews
      • a. Pre-Ship Readiness Review (PSRR) — Conducted prior to committing flight hardware and personnel to the field. The PSRR provides testing results on all formal systems tests and reviews the major mechanical assemblies which are completed and ready for...
      • b. Incremental Readiness Review (IRR) – The quantity and timing of IRR(s) depends on the complexity and Mission Assurance Category of the mission. IRRs typically occur 2-12 months prior to the launch date. IRR provides an early assessment of the int...
      • c. Mission Readiness Review (MRR) — Conducted within 2 months of launch, the MRR provides a pre-launch assessment of integrated launch vehicle/payload/facility readiness prior to committing significant resources to the launch campaign.
      • d. Flight Readiness Review (FRR) – The FRR is conducted at L-10 days and determines the readiness of the integrated launch vehicle/payload/facility for a safe and successful launch. It also ensures that all flight and ground hardware, software, perso...
      • e. Launch Readiness Review (LRR) — The LRR is conducted at L-1 day and serves as the final assessment of mission readiness prior to activation of range resources on the day of launch.
  • 6.4. Documentation
    • 6.4.1. Customer-Provided Documentation
      • 6.4.1.1. Payload Questionnaire
      • 6.4.1.2. ICD Inputs
      • 6.4.1.3. Payload Mass Properties
      • 6.4.1.4. Payload Finite Element Model
      • 6.4.1.5. Payload Thermal Model for Integrated Thermal Analysis
        • a. Prelaunch ground operations;
        • b. Ascent from lift-off until fairing jettison; and
        • c. Fairing jettison through payload deployment.
      • 6.4.1.6. Payload Drawings
      • 6.4.1.7. Program Requirements Document (PRD) Mission Specific Annex Inputs
        • 6.4.1.7.1. Launch Operations Requirements (OR) Inputs
      • 6.4.1.8. Payload Launch Site Integration Procedures
      • 6.4.1.9. ICD Verification Documentation
    • 6.4.2. Orbital Produced Documentation, Data, and Analyses
      • 6.4.2.1. Launch Vehicle to Payload ICD
      • 6.4.2.2. ICD Verification Documentation
      • 6.4.2.3. Preliminary Mission Analyses
      • 6.4.2.4. Coupled Loads Analyses (CLA)
      • 6.4.2.5. Integrated Launch Site Procedures
      • 6.4.2.6. Missile System Pre-Launch Safety Package (MSPSP) Annex
      • 6.4.2.7. PRD Mission Specific Annex
      • 6.4.2.8. Launch Operation Requirements (OR)
      • 6.4.2.9. Mission Constraints Document (MCD)
      • 6.4.2.10. Final Countdown Procedure
      • 6.4.2.11. Post-Launch Analyses
  • 6.5. Safety
    • 6.5.1. System Safety Requirements
    • 6.5.2. System Safety Documentation
• 7. GROUND AND LAUNCH OPERATIONS
  • 7.1. Launch Vehicle Integration Overview
    • 7.1.1. Planning and Documentation
    • 7.1.2. Guidance and Control Assembly Integration and Test Activities
    • 7.1.3. PK Motor Integration and Test Activities
    • 7.1.4. Mission Simulation Tests
    • 7.1.5. Launch Vehicle Processing Facilities
  • 7.2. Payload Processing/Integration
    • 7.2.1. Payload Propellant Loading
  • 7.3. Launch Operations
    • 7.3.1. Booster Assembly Stacking/Launch Site Preparation
    • 7.3.2. Final Vehicle Integration and Test
    • 7.3.3. Launch Vehicle Arming
    • 7.3.4. Launch
    • 7.3.5. Launch Control Organization
    • 7.3.6. Launch Rehearsals
• 8. OPTIONAL ENHANCED CAPABILITIES
  • 8.1. Separation System and Optional Mechanical Interfaces
  • 8.2. Conditioned Air
  • 8.3. Nitrogen Purge
  • 8.4. Additional Access Panel
  • 8.5. Enhanced Telemetry
  • 8.6. Enhanced Contamination Control
    • 8.6.1. Low Outgassing Materials
    • 8.6.2. High Cleanliness Integration Environment
    • 8.6.3. HEPA-Filtered Fairing Air Supply
    • 8.6.4. Fairing Surface Cleanliness
  • 8.7. Secure FTS
  • 8.8. Over Horizon Telemetry
  • 8.9. Increased Insertion Accuracy
  • 8.10. Payload Isolation System
  • 8.11. Orbital Debris Mitigation
  • 8.12. Dual and Multi Payload Adapter Fittings
  • 8.13. Enhanced Performance
  • 8.14. Large Fairing
  • 8.15. Hydrazine Servicing
  • 8.16. Nitrogen Tetroxide Service
  • 8.17. Poly-Pico Orbital Deployer (P-POD)
  • 8.18. Suborbital Performance
  • 8.19. Alternate Launch Locations