March 2014 Minotaur I User’s Guide Release 3.0 Approved for Public Release Distribution Unlimited ©2013 Orbital Sciences Corporation All Rights Reserved.
Minotaur I User’s Guide Revision Summary REVISION SUMMARY VERSION DOCUMENT DATE CHANGE PAGE 1.0 TM-14025 Mar 2002 Initial Release All 2.0 TM-14025A Oct 2004 Changes throughout. Major updates include All 3.0 Release 3.
Minotaur I User’s Guide Preface PREFACE This Minotaur I User's Guide is intended to familiarize potential space launch vehicle users with the Minotaur I launch system, its capabilities and its associated services. All data provided herein is for reference purposes only and should not be used for mission specific analyses. Detailed analyses will be performed based on the requirements and characteristics of each specific mission.
Minotaur I User’s Guide Table of Contents PAGE INTRODUCTION ................................................................................................................................. 1 1. 1.1. 2. Minotaur Family Performance and Capability ............................................................................... 2 MINOTAUR I CONFIGURATIONS ..................................................................................................... 4 2.1. Minotaur I Launch System Overview .........
Minotaur I User’s Guide Table of Contents 4.7. PAGE Payload Contamination Control .................................................................................................. 26 4.8. Payload Electromagnetic Environment ....................................................................................... 26 5. PAYLOAD INTERFACES.................................................................................................................. 28 5.1. Payload Fairing ............................
Minotaur I User’s Guide Table of Contents 5.4.5. PAGE Payload Dynamic Frequencies ................................................................................................ 43 5.4.6. Payload Propellant Slosh ........................................................................................................ 44 5.4.7. System Safety Constraints ...................................................................................................... 44 6. MISSION INTEGRATION....................
Minotaur I User’s Guide Table of Contents PAGE Safety .......................................................................................................................................... 54 6.5. 6.5.1. System Safety Requirements .................................................................................................. 54 6.5.2. System Safety Documentation ................................................................................................ 54 7.
Minotaur I User’s Guide Table of Contents 8.10. PAGE Payload Isolation System ............................................................................................................ 66 8.11. Orbital Debris Mitigation .............................................................................................................. 67 8.12. Dual and Multi Payload Adapter Fittings ..................................................................................... 67 8.13.
Minotaur I User’s Guide Table of Contents PAGE 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 .......................
Minotaur I User’s Guide Table of Contents PAGE Figure 8.10-1. Minotaur I SRSS Significantly Attenuates Peak LV Dynamic Environments ..................... 67 Figure 8.11-1. Operational and Disposal LEOs ......................................................................................... 67 Figure 8.13.1-1. Minotaur I Commercial Offers Exceptional Performance with Proven Reliability............ 68 Figure 8.15-1. Typical Propellant Loading Schematic ......................................................
Minotaur I User’s Guide 6DOF A/D AADC ACAT-1 ACS AFRL ait AIT AODS BCM BER C/CAM C/D CBOD CCAFS CDR CG CLA CLF CVCM DIACAP DoD DPAF ECU EGSE EMC EME EMI ER FAA FRR FTLU FTS GFE GFP GN2 GPB GPS GTO Release 3.
Minotaur I User’s Guide MTO NASA NCU NRE NTO ODM OR OSP-3 PAF PCM PDR PEM PPF P-POD PRD RAAN RCS RF RWG S/A SCAPE SD SDL SEB SLC-8 SLV SMC SRSS SSI START SV TDRSS TLI TML TVC UPC USA USAF VAFB WFF WP Release 3.
Minotaur I User’s Guide Section 1.0 – Introduction 1. INTRODUCTION This User’s Guide is intended to familiarize payload mission planners with the capabilities of the Orbital Suborbital Program 3 (OSP-3) Minotaur I Space Launch Vehicle (SLV) launch service. This document provides an overview of the Minotaur I system design and a description of the services provided to our customers.
Minotaur I User’s Guide Section 1.0 – Introduction Minotaur I vehicle) and the existing ground support equipment that is used to conduct Minotaur I operations. 1.1. Minotaur Family Performance and Capability Figure 1.1-1 shows the Minotaur family of launch vehicles, which is capable of launching a wide range of payload sizes and missions. Representative space launch performance across the Minotaur fleet is shown in Figure 1.1-2 to illustrate the relative capability of each configuration.
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 Payload Lift Capability Release 3.
Minotaur I User’s Guide Section 2.0 – Minotaur I Configurations 2. MINOTAUR I CONFIGURATIONS 2.1. Minotaur I Launch System Overview The Minotaur I launch vehicle, shown in Figure 2.1-1, was developed by Orbital for the United States Air Force (USAF) to provide a cost effective, reliable and flexible means of placing small satellites into orbit. Orbital is the launch vehicle developer and manufacturer under the Orbital Suborbital Program 3 (OSP-3) contract for the U.S. Air Force.
Minotaur I User’s Guide Section 2.0 – Minotaur I Configurations Division (SDL). Orbital is the launch vehicle provider. This integrated team will be referred to collectively as “OSP” throughout the User’s Guide. Where necessary, interfaces that are associated with a particular member of the team will be referred to directly (i.e., Orbital or SDL). OSP provides all of the necessary hardware, software and services to integrate, test and launch a payload into its prescribed orbit.
Minotaur I User’s Guide Section 2.0 – Minotaur I Configurations Thrust Vector Control (LITVC) subsystem, S2 ignition safe/arm device, a Roll Control System (RCS), and the Stage 2 MMODS FTS components. Attitude control during second stage burn is provided by the operational LITVC and hot gas roll control. 2.3.2. Upper Stack Assembly The Minotaur I Upper Stack is composed of the Stage 3 and 4 motors, their associated interstages, the avionics assembly, and, ultimately, the payload and payload fairing.
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-axis attitude control throughout boosted flight and coast phases. Stages 1 and 2 utilize the Minuteman Thrust Vector Control (TVC) systems. The Stage 1 TVC is a four-nozzle hydraulic system, while the Stage 2 system combines liquid injection for pitch and yaw control with hot gas roll control. Stages 3 and 4 utilize the same TVC systems as Minotaur IV.
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 Control Room for real-time telemetry updates. Reference Enhancements Section 8.8 for further details on this Over the Horizon Telemetry option. Minotaur telemetry is subject to the provisions of the Strategic Arms Reduction Treaty (START).
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 adaptable to varying launch site configurations with minimal unique infrastructure required. The EGSE consists of readily transportable consoles that can be housed in various facility configurations depending on the launch site infrastructure. The EGSE is composed of three primary functional elements: Launch Control, Vehicle Interface, and Telemetry Data Reduction.
Minotaur I User’s Guide Section 2.0 – Minotaur I Configurations Figure 2.4-1. Minotaur I EGSE Configuration Release 3.
Minotaur I User’s Guide Section 3.0 – General Performance 3. GENERAL PERFORMANCE 3.1. Mission Profiles Minotaur I can attain a range of posigrade and retrograde inclinations through the choice of launch sites made available by the readily adaptable nature of the Minotaur I launch system. A generic mission profile to a sun-synchronous orbit is shown in Figure 3.1-1. All performance parameters presented within this User’s Guide are typical for most expected payloads.
Minotaur I User’s Guide Section 3.0 – General Performance Figure 3.2-1. Flexible Processing and Portable GSE Allows Operations from Multiple Ranges or Austere Site Options Figure 3.2-2. Launch Site Inclinations Release 3.
Minotaur I User’s Guide Section 3.0 – General Performance 3.2.1. Western Launch Sites For missions requiring high inclination orbits (greater than 60°), launches can be conducted from facilities at VAFB or Kodiak Island, AK, as shown in Figure 3.2-2. Inclinations below 72° from VAFB are possible, but require an out-of-plane dogleg, thereby reducing payload capability.
Minotaur I User’s Guide Section 3.0 – General Performance Table 3.3-1. Common Mission Options and Associated Masses (These Masses Must Be Subtracted from the LV Performance) Option (These Masses Must Be Subtracted from the LV Performance) Total Mass (kg) Portion of Total Mass That Remains with SV Post Separation (kg) 9.85 0 8.54 0 12.24 4.0 19.89 6.16 8.85 2.
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 I Performance Curves for CCAFS Launches Release 3.
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 I with 61” Fairing Performance Curves for VAFB Launches Release 3.
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 3.3-7. Minotaur I with 61” Fairing Performance Curves for CCAFS Launches Release 3.
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.
Minotaur I User’s Guide Section 3.0 – General Performance 3.5. Payload Deployment Following orbit insertion, the Minotaur I Stage 4 avionics subsystem can execute a series of ACS maneuvers to provide the desired initial payload attitude prior to separation. This capability may also be used to incrementally reorient Stage 4 for the deployment of multiple spacecraft with Table 3.5-1. Typical Pre-Separation Payload independent attitude requirements.
Minotaur I User’s Guide Section 4.0 – Payload Environment 4. PAYLOAD ENVIRONMENT CAUTION The predicted environments provided in this user's guide are for initial planning purposes only. Environments presented here bound a generic mission and should not be used in mission specific analyses. Mission specific levels are provided as a standard service and documented or referenced in the mission ICD.
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 are relatively benign. There are significant transient loads that occur at both Stage 2 and Stage 3 ignition. During the transient portion of these ignition events, the steady state axial loads are relatively nonexistent.
Minotaur I User’s Guide Section 4.0 – Payload Environment 4.1.2. Steady-State Acceleration Steady-state vehicle accelerations are determined from the vehicle rigid body analysis. Drag, wind and motor thrust are applied to a vehicle model. A Monte Carlo analysis is performed to determine variations in vehicle acceleration due to changes in winds, motor performance and aerodynamics.
Minotaur I User’s Guide Section 4.0 – Payload Environment 4.2. Payload Vibration Environment The in-flight random vibration curve shown in Figure 4.2-1 encompasses all flight vibration environments. 4.3. Payload Acoustic Environment The acoustic levels during lift-off and powered flight will not exceed the flight limit levels shown in Figure 4.3-1. If the vehicle is launched over a flame duct, the acoustic levels can be expected to be lower than shown. This has been demonstrated with flight data. 4.4.
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 safety as found in MIL-HNBK-340A (ref. MIL-STD-1540B) and NASA GEVS Rev. A, June ‘96. The payload organization must provide Orbital with a list of the tests and test levels to which the payload was subjected prior to payload arrival at the integration facility. 4.6.
Minotaur I User’s Guide Section 4.0 – Payload Environment provides conditioned air to the payload in the Payload Processing Facility (PPF) after fairing integration and on the launch pad. For Minotaur I, conditioned air is not provided during transport and lifting operations. The conditioned air enters the fairing at a location forward of the payload, exits aft of the payload and is maintained up to 5 minutes prior to launch (for the 61” fairing, the conditioned air can be maintained until liftoff).
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 be initiated at a time in flight that the maximum dynamic pressure is less than 0.01 psf or the maximum free 2 molecular heating rate is less than 1135 W/m (0.1 2 BTU/ft /sec), as required by the payload. 4.6.3.
Minotaur I User’s Guide Section 4.0 – Payload Environment Table 4.8-1 lists the frequencies and maximum radiated signal levels from vehicle antennas that are located near the payload during ground operations and powered flight. Antennas located inside the fairing are inactive until after fairing deployment. The specific EME experienced by the payload during ground processing at the VAB and the launch site will depend somewhat on the specific facilities that are utilized as well as operational details.
Minotaur I User’s Guide Section 5.0 – Payload Interfaces 5. PAYLOAD INTERFACES This section describes the available mechanical, electrical and Launch Support Equipment (LSE) interfaces between the Minotaur I launch vehicle and the payload. 5.1. Payload Fairing 5.1.1. 50” Standard Minotaur I Fairing The standard payload fairing consists of two graphite composite halves, with a nosecap bonded to one of the halves, and a separation system. Each composite half is composed of a cylinder and an ogive section.
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 Payload Interface 5.1.2. Optional 61” Payload Fairing To fit payloads larger than those that can be accommodated by the standard 50” diameter fairing, a larger 61” diameter fairing is available as an enhancement. This structure uses an innovative diffusion-bonded titanium sandwich panel composed of titanium facesheets and titanium honeycomb core.
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 Payload Interface No part of the payload may extend aft of the payload interface plane without specific Orbital approval. Incursions to these zones may be approved on a case-by-case basis after additional verification that the incursions do not cause any detrimental effects.
Minotaur I User’s Guide Section 5.0 – Payload Interfaces Figure 5.1.3-1. 50” Payload Fairing Access Door Placement Zone Release 3.
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 Interface and Separation System Minotaur I provides for a standard non-separating payload interface and several optional Orbital-provided payload separation systems. Orbital will provide all flight hardware and integration services necessary to attach non-separating and separating payloads to Minotaur I.
Minotaur I User’s Guide Section 5.0 – Payload Interfaces Figure 5.2.1-1. Minotaur Coordinate System Release 3.
Minotaur I User’s Guide Section 5.0 – Payload Interfaces 5.2.2. Orbital Supplied Mechanical Interface Control Drawing Orbital will provide a toleranced Mechanical Interface Control Drawing (MICD) to the payload contractor to allow accurate machining of the fastener holes. The Orbital provided MICD is the only approved documentation for drilling the payload interface. 5.2.3.
Minotaur I User’s Guide Section 5.0 – Payload Interfaces provide LV minimum structural interface design criteria for shear, bending moment, axial and lateral loads, and stiffness. Another available approach involves the use of a spacecraft design using the Orbital MicroStar bus which was successfully developed and flown for ORBCOMM. The MicroStar bus features a circular design with an innovative, low-shock separation system.
Minotaur I User’s Guide Section 5.0 – Payload Interfaces structure that supports the dual payload configuration includes a 50” cylindrical section that is configurable in height depending on payload unique requirements. The primary payload is mounted to the top of this DPAF structure using a 38.8” separation system. The lower payload resides within the DPAF structure during flight through primary payload deployment.
Minotaur I User’s Guide Section 5.0 – Payload Interfaces Table 5.2.5-1. Minotaur I Separation System Options are within specified limits presented in Section 5.4.1. Separation velocities are usually optimized to provide the SV with the lowest separation velocity while ensuring recontact does not occur between the SV and the Minotaur upper stage after separation.
Minotaur I User’s Guide Section 5.0 – Payload Interfaces Figure 5.2.5.1-1. Orbital 38” Separation System Release 3.
Minotaur I User’s Guide Section 5.0 – Payload Interfaces 5.2.5.2. Planetary Systems Motorized Lightband (MLB) The Planetary Systems MLB, Figure 5.2.5.2-1, provides a fully qualified and flight proven low shock and lightweight option for use on Minotaur missions. Multiple sizes of MLBs have previously flown on Minotaur vehicles.
Minotaur I User’s Guide Section 5.0 – Payload Interfaces 5.3. Payload Electrical Interfaces The payload electrical interface, shown in Figure 5.3-1, supports battery charging, external power, discrete commands, discrete telemetry, analog telemetry, serial communication, SV separation indications, and up to 16 separate ordnance discretes. If an optional Orbital-provided separation system is utilized, Orbital will provide all the wiring through the separable interface plane.
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 Standard interface circuitry passing through the payload-to-launch vehicle electrical connections are shown in Figure 5.3-1. This figure details the interface characteristics for launch vehicle commands, discrete and analog telemetry, separation loopbacks, pyro initiation, and serial communications interfaces with the launch vehicle avionics systems. 5.3.3.
Minotaur I User’s Guide Section 5.0 – Payload Interfaces 10 mA. Separation breakwire monitors can be specified if required. The number of analog channels available for payload telemetry monitoring is dependent on the frequency of the data. Payload telemetry requirements and signal characteristics will be specified in the Payload ICD and should not change once the final telemetry format is released at approximately L-6 months.
Minotaur I User’s Guide Section 5.0 – Payload Interfaces 5.4. Payload Design Constraints The following sections provide design constraints to ensure payload compatibility with the Minotaur I launch vehicle. 5.4.1. Payload Center of Mass Constraints Along the Y and Z axes, the payload CG must be within 2.54 cm (1.0 in.) of the vehicle centerline and no more than 30 in. (76.2 cm) forward of the payload interface for the standard configuration. Payloads whose CG extend beyond the 2.54 cm (1.0 in.
Minotaur I User’s Guide Section 5.0 – Payload Interfaces spacecraft, isolation system and/or separation system. Therefore, the final determination of compatibility must be made on a mission-specific basis. 5.4.6. Payload Propellant Slosh A slosh model should be provided to Orbital in either the pendulum or spring-mass format. Data on first sloshing mode are required and data on higher order modes are desirable.
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. Air Force, Space and Missile Systems Center, Space Development and Test Directorate (SD) Launch Systems Division (SDL). SD/SDL serves as the primary point of contact for the payload customers for the Minotaur I launch service. The organizations involved with the mission integration team are shown in Figure 6.1-1.
Minotaur I User’s Guide Section 6.0 – Mission Integration The Minotaur organization uses highly skilled personnel with extensive Minotaur experience. The Minotaur program is led by a Program Director who reports directly to Orbital’s Launch Systems Group General Manager and has full responsibility for mission success. This direct line to executive management provides high visibility, ensuring access to critical organizational resources.
Minotaur I User’s Guide Section 6.0 – Mission Integration The typical Mission Cycle interweaves the following activities: 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.
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 integration schedule is adjusted as required based on the mission requirements, launch vehicle configuration and launch site selection. Figure 6.2-2. Typical Mission Field Integration Schedule 6.2.1. Mission Assurance The OSP-3 contract has three tailored levels of Mission Assurance (MA); Category 1, Category 2 and Category 3.
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 integration process consists of a series of Mission Integration and Range Working Groups (MIWG and RWG, respectively). The MIWG has responsibility for all physical interfaces between the payload and the launch vehicle. As such, the MIWG develops the Payload-to-Minotaur ICD in addition to all mission-unique analyses, hardware, software, and integrated procedures.
Minotaur I User’s Guide Section 6.0 – Mission Integration 6.4. Documentation Integration of the payload requires detailed, complete, and timely preparation and submittal of interface documentation. SD/SDL is the primary communication path with other U.S. Government agencies, which include—but are not limited to—the various Ranges and their support agencies, the U.S. Department of Transportation, U.S. State Department, and U.S. Department of Defense.
Minotaur I User’s Guide Section 6.0 – Mission Integration 6.4.1.5. Payload Thermal Model for Integrated Thermal Analysis An integrated thermal analysis can be performed for any payload as a non-standard service. A payload thermal model will be required from the payload organization for use in Orbital’s integrated thermal analysis if it is required. The analysis is conducted for three mission phases: a. Prelaunch ground operations b. Ascent from lift-off until fairing jettison c.
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 the mission-unique requirements agreed upon by Orbital and the customer. The ICD is a critical document used to ensure compatibility of all launch vehicle and payload interfaces, as well as defining all mission-specific and mission-unique requirements.
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 documents launch vehicle and payload safety information including an assessment of any hazards which may arise from mission-specific vehicle and/or payload functions, and is provided as an annex to the baseline Minotaur MSPSP. The customer must provide Orbital with all safety information pertaining to the payload.
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 integration effort, regulations and instructions that apply to spacecraft design and processing are reviewed. Not all safety regulations will apply to a particular mission integration activity. Tailoring the range requirements to the mission unique activities will be the first step in establishing the safety plan.
Minotaur I User’s Guide Section 7.0 – Ground and Launch Operations 7. GROUND AND LAUNCH OPERATIONS Minotaur ground and launch operations processing minimizes the handling complexity for both launch vehicle and payload. All launch vehicle motors, parts and completed subassemblies are delivered to the Minotaur Processing Facility (MPF) from either Orbital’s Chandler production facility, the assembly/motor vendor, or the Government. Ground and launch operations are conducted in three major phases: a.
Minotaur I User’s Guide Section 7.0 – Ground and Launch Operations 7.1. Launch Vehicle Integration Overview Orbital utilizes the same fundamental integration and process flow for all launch vehicles in the Minotaur family. A flow chart of the launch vehicle integration at the MPF is shown in Figure 7.1-1 for a VAFB Minotaur I launch. This minimizes the handling complexity for both vehicle and payload.
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 and 2 motors are refurbished at Hill Air Force Base. They also undergo ordnance and raceway installation before being shipped directly to the launch pad for emplacement. 7.1.4. Mission Simulation Tests Orbital will run three Mission Simulation Tests (MST) to verify the functionality of launch vehicle hardware and software (i.e., MST #1, MST #2, and MST #3).
Minotaur I User’s Guide Section 7.0 – Ground and Launch Operations 7.2.1. Payload to Minotaur I Integration The integrated launch processing activities are designed to simplify final launch processing while providing a comprehensive verification of the payload interface. The systems integration and test sequence is engineered to ensure all interfaces are verified. 7.2.2.
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 of the Minuteman boosters, the site is prepared for launch operations with the installation of the launch stand adapter. The Lower Stack Assembly, consisting of the Minuteman motors, is delivered directly to the launch pad from Hill Air Force Base.
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 hours prior to the required launch time. Figure 7.3.4-1 describes the nominal Minotaur I launch day flow. These activities methodically transition the vehicle from a safe state to that of launch readiness. Payload tasks, as necessary, are included in the countdown procedure and are coordinated by the Minotaur I Launch Conductor.
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. The first is conducted at approximately L-10 days and is used to acquaint the launch team with the communications systems, reporting, problem solving, launch procedures and constraints, and the decision making process. The first rehearsal is communications only (i.e., the Minotaur launch vehicle and payload are not powered on and range assets are not active).
Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities 8. OPTIONAL ENHANCED CAPABILITIES The Minotaur launch service is structured to provide a baseline vehicle configuration which is then augmented with optional enhancements to meet the unique needs of individual payloads. The baseline vehicle capabilities are defined in the previous sections and the optional enhanced capabilities are defined below.
Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities Figure 8.4-1. Multiple Access Doors Were Demonstrated on the Optional Minotaur I Large Fairing locations on the fairing. Required door locations outside the allowable envelope are evaluated on a mission-specific basis. Other fairing access configurations, such as small circular access panels, can be provided as non-standard, mission-specific enhancements.
Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities 8.6. Enhanced Contamination Control To meet the requirement for a low contamination environment, Orbital uses existing processes developed and demonstrated on the Minotaur and Pegasus programs. These processes are designed to minimize out-gassing, supply a Class 10,000 clean room environment, assure a high cleanliness payload envelope, and provide a HEPA-filtered, controlled humidity environment after fairing encapsulation.
Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities 8.6.4. Fairing Surface Cleanliness The inner surface of the fairing and exposed launch vehicle assemblies are cleaned to Visibly Clean Plus Ultraviolet cleanliness criteria which ensures no particulate matter visible with normal vision when inspected from 6 to 18 inches under 100 foot candle incident light, as well as when the surface is illuminated by black light at 3200 to 3800 Angstroms.
Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities sites, the LV switches telemetry output to the TDRSS antenna and points the antenna towards a TDRSS satellite. The TDRSS relays the telemetry to the ground where it is then routed to the launch control room (Figure 8.8-2). A cavity backed or phased array antenna can be used depending on data rate requirements. The TDRSS system proposed includes the launch vehicle design, analysis, hardware and launch vehicle testing.
Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities each particular spacecraft and with location on the spacecraft. Generally, a beneficial reduction in shock and vibration will also be provided. The isolation system does impact overall vehicle performance by approximately 9 to 18 kg (20 to 40 lb) and the available payload dynamic envelope by up to 5.08 cm (2.0”) axially and up to 2.54 cm (1.0”) laterally. 8.11.
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 Commercial The Minotaur I Commercial space launch vehicle represents a substantial (over 25%) increase in performance with minimal vehicle changes, shown in Figure 8.13.1-1. The configuration was established for payloads that do not have government sponsorship but require the highly reliable Minotaur I capability.
Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities Figure 8.15-1. Typical Propellant Loading Schematic The scope of this enhancement includes the procurement of hydrazine fuel, the preparation of documentation for fueling operations, the support of safety and integrated operations meetings, the provision of equipment needed for SCAPE operation, including personal protection equipment (if necessary) and fuel transfer cart, and all personnel required to conduct fuel loading operations.
Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities Figure 8.15-2. UPC Provides Reliable and Demonstrated Hydrazine Servicing for Minotaur 8.16. Nitrogen Tetroxide Service Under this enhancement, Orbital provides Nitrogen Tetroxide (NTO) loading service for the SV though a contract to UPC.
Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities 8.17. Poly-Pico Orbital Deployer (P-POD) When there is excess performance available on a Minotaur mission, there is an opportunity to fly one or more P-PODS. Small CubeSats deployed from customer provided P-PODs were successfully flown on multiple Minotaur missions. A single P-POD can deploy up to 3 CubeSats. The P-PODs are mounted on shock isolated plates located on the Orion 38 motor case (Figure 8.
Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities Minotaur I Lite provides a larger volume and greater stack height to the suborbital payload. For clearances to fairing deployment components and to maintain proven fairing deployment dynamics, a simple aluminum adapter cylinder is used between the 3/4 interstage and the avionics section. The adapter cylinder is the only new structure; the electrical and ordnance designs above and below remain unchanged from the standard Minotaur I.
Minotaur I User’s Guide Section 8.0 – Optional Enhanced Capabilities 8.19. Alternate Launch Location Orbital has extensive experience processing and launching out of multiple Government and commercial launch sites. Minotaur systems are designed to accommodate missions from multiple ranges with minimal dedicated infrastructure. The Minotaur flight safety systems and Range interface requirements are well documented and approved by multiple safety organizations.
Minotaur I User’s Guide Appendix A APPENDIX A PAYLOAD QUESTIONNAIRE Release 3.
Minotaur I User’s Guide Appendix A SATELLITE IDENTIFICATION FULL NAME: ACRONYM: OWNER/OPERATOR: INTEGRATOR(s): SPACE CRAFT AND MISSION DESCRIPTION ORBIT INSERTION REQUIREMENTS* SPHEROID Standard (WGS-84, Re = 6378.137 km) Other: ALTITUDE Insertion Apse: Opposite Apse: nmi ± or...
Minotaur I User’s Guide Appendix A LAUNCH WINDOW REQUIREMENTS NOMINAL LAUNCH DATE: LAUNCH SITE: OTHER CONSTRAINTS (if not already implicit from LAN or RAAN requirements, e.g., solar beta angle, eclipse time constraints, early on-orbit ops, etc): Release 3.
Minotaur I User’s Guide Appendix A EARLY ON-ORBIT OPERATIONS Briefly describe the satellite early on-orbit operations, e.g.
Minotaur I User’s Guide Appendix A SPACECRAFT PHYSICAL DIMENSIONS STOWED Length/Height: Diameter: CONFIGURATION in cm in cm Other Pertinent Dimension(s): Describe any appendages/antennas/etc which extend beyond the basic satellite envelope: ON-ORBIT Describe size and shape: CONFIGURATION If available, provide dimensioned drawings for both stowed and on-orbit configurations. Release 3.
Minotaur I User’s Guide Appendix A SPACECRAFT MASS PROPERTIES* PRE-SEPARATION Inertia units: Mass: 2 kg-m 2 2 kg-m 2 lbm-in lbm kg Ixx: Xcg: in cm Iyy: Izz: Ycg: in cm Ixy: Iyz: Zcg: POSTSEPARATION in cm Inertia units: Mass: Ixz: lbm-in lbm kg (non-separating adapter remaining with launch vehicle) Ixx: Xcg: in cm Iyy: Izz: Ycg: in cm Ixy: Iyz: Zcg: in cm Ixz: * Stowed configuration, spacecraft coordinate frame Release 3.
Minotaur I User’s Guide Appendix A SPACECRAFT SLOSH MODEL* SLOSH MODEL UNDER 0 g Pendulum Mass: lbm kg Pendulum Length: ft m Pendulum Xs: in cm Attachment Ys: in cm Point Zs: in cm Natural Frequency of Fundamental Sloshing Mode (Hz): SLOSH MODEL UNDER 1 g Pendulum Mass: lbm kg Pendulum Length: ft m Pendulum Xs: in cm Attachment Ys: in cm Point Zs: in cm Natural Frequency of Fundamental Sloshing Mode (Hz): , , ASCENT TRAJECTORY REQUIREMENTS 2
Minotaur I User’s Guide Appendix A SPACECRAFT ENVIRONMENTS THERMAL DISSIPATION Spacecraft Thermal Dissipation, Pre-Launch Encapsulated: Watts Approximate Location of Heat Source: Thermal Control Provisions: (Paint, Tape, etc.
Minotaur I User’s Guide Appendix A ELECTRICAL INTERFACE Bonding Requirements: Are Launch Vehicle Supplied Pyro Commands Required? Yes / No If Yes, magnitude: amps for msec (Standard Service is 10 amps for 100 msec) Are Launch Vehicles Supplied? Yes / No Discrete Commands Required? Yes / No If Yes, describe: Is Electrical Access to the Satellite Required... After Encapsulation? Yes / No at Launch Site Yes / No Is Satellite Battery Charging Required...
Minotaur I User’s Guide Appendix A REQUIRED PASS-THROUGH SIGNALS Item # Pin Signal Name From LEV To Satellite Shielding Max Total Line Current Resistance (amps) (ohms) 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 Release 3.
Minotaur I User’s Guide Appendix A MECHANICAL INTERFACE DIAMETER Describe Diameter of Interface (e.g.
Minotaur I User’s Guide Appendix A GROUND SUPPORT EQUIPMENT Describe any additional control facilities (other than the baseline Support Equipment Building (SEB) and Launch Equipment Vault (LEV)) which the satellite intends to use: SEB Describe (in the table below) Satellite EGSE to be located in the LSV. [Notes: Space limitations exist in the SEB.
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. [Notes: Space limitations exist in the LEV. 49 m (160 ft) umbilical cable length to spacecraft typical] Equipment Name / Type Approximate Size (LxWxH) Is UPS required for equipment in the LEV? Yes / No Is Phone/Fax connection required in the LEV? Yes / No Release 3.
