Ракетный блок. Star-48BV. [Редактировать]

Технические характеристики

#ХарактеристикаЗначение
1Длина, метра2.08
2Стартовая масса, кг2164.5
3ТопливоTP-H-3340
4Тяга (средняя), кНьютон68.6
5Тяга (максимальная), кНьютон77.8
6Удельный импульс, секунд288
7Время работы, секунд84.1
8Масса (топлива), кг2010.0
9Масса (конструкции), кг58.3
10Диаметр, метра1.24
11Материал (конструкции)титан

Найдено 13 документов по запросу «Star-48BV». [Перейти к поиску]


Дата загрузки: 2017-03-09
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0.05/5
... .............................................................................................................................. ES-1 Our First Visit to a Star . ........................................................................................................ ES-1 Solar Probe1 Science Objectives... course, because the Sun, being a star, is not readily approachable, but... live. Our First Visit to a Star Two of the transformative advances... control system consists of three star trackers, an internally redundant inertial... Cycle 25 in ~2022. with a Star-48BV third stage has been baselined... can be Atlas V 551 with a Star-48BV third stage. The used during... noise and degrade a star tracker’s ability to detect star constellations needed to... uncertainty, Solar Probe1 uses three star trackers facing in orthogonal directions... IMU (4/3 redund.) P Main spacecraft bus Star tracker (3) Solar horizon sensor F PSE.... The G&C subsystem consists of three star trackers and one internally redundant... redundant Payload DPU Attitude Determination 3 star trackers Internally redundant IMU Internally...: short duration Solar Horizon Sensor Star tracker-low rates Solar Horizon... LGA Solar Arrays Attitude Determination Star tracker IMU 4.4.3  Fault Management. The... as coronal lighting effects on star trackers or torques induced by... Atlas V 551 launch vehicle with a Star-48BV third stage. The mass summary... CD HI HGA Star trackers (3) EPI-low LGA (2) Star trackers (3) +Z FIA, FEA... total) HI Primary solar arrays (2) Star trackers (3) +Z +Z +Y Instrument axial boom –X +X –Y Figure... the Solar Probe1 to the Star-48B third stage and provides... the secondary solar array system. STAR-48 third-stage motor C-C TPS... to these limits. Battery, HGA, star tracker, and solar array temperatures... 130 HGA –90 to 1250 Star tracker –20 to 160 Primary... card contains interfaces to the star trackers, IMU, SHS, reaction wheels... attitude information from the three star trackers and IMU via the... point thrusters for TCMs. Three star trackers and a high-precision, internally... will be determined by the star trackers and the IMU. The use of star trackers in the near-Sun... design addresses by mounting the star trackers so that their fields... used as a backup to the star trackers to propagate attitude for... a solar encounter if all three star trackers are temporarily blinded. The... the event of long-duration star tracker blinding, system resets, or... head 2 Sun sensor data Star tracker data Star tracker electronics (4) Optical head... Inertial attitude Inertial Angular attitude Star rates quaternion Attitude tracker determination... must be taken to select star trackers that will perform well... or more potentially suitable candidate star trackers were identified in existing... particles will be seen by a star tracker that is viewing the... degrading the performance of the star tracker. As noted above, this... Atlas V 551 launch vehicle with a Star-48BV third stage for cost; however...: First Mission to the Nearest Star. Report of the Science 5-2 5.  References...



Дата загрузки: 2017-02-22
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0.02/5
... STAR MOTOR SERIES ................................................................................................. 57 STAR 3 TE-M-1082-1 ...................................................................................... 63 STAR 3A TE-M-1089 ....................................................................................... 64 STAR... STAR 6B TE-M-790-1 ...................................................................................... 71 STAR 8 TE-M-1076-1 ...................................................................................... 72 STAR 9 TE-M-956-2 ........................................................................................ 73 STAR 12GV TE-M-951 .................................................................................... 74 STAR............................................................................................. 85 STAR 27H TE-M-1157 ...................................................................................... 86 STAR 30 SERIES ............................................................................................................. 87 STAR 30BP TE-M-700-20 ............................................................................... 88 STAR 30C...-1 ............................................................................... 98 STAR 48 SERIES ............................................................................................................. 99 STAR 48A TE-M-799-1 .................................................................................. 100 STAR 48A TE-M-799 ..................................................................................... 101 STAR 48B TE-M-711-17 ................................................................................ 102 STAR 48B TE-M-711-18 ................................................................................ 103 STAR 48BV TE-M-940-1 ............................................................................... 104 STAR 63 SERIES ........................................................................................................... 105 STAR 63D TE-M-936 ..................................................................................... 106 STAR 63F TE-M-963-2 .................................................................................. 107 STAR 75 SERIES ........................................................................................................... 109 STAR 75 TE-M-775-1 .................................................................................... 110 STAR 92 SERIES ........................................................................................................... 111 STAR 92 ............................................................................................................. 112 STAR STAGES..., ordnance, and stage products. STAR 30BP STAR 30E STAR 30BP Motor Was Stretched... design features from the STAR 5CB, STAR 5D, and STAR 5E designs to... than the STAR 30BP case. Like the STAR 30BP, the STAR 30C uses...; Dated 07 August 2012 103 STAR 48BV TE-M-940-1 MOTOR DIMENSIONS Motor... ....................................... 54.8:1 Type ............................................. Vectorable, ±4 deg The STAR 48BV has been qualified (1993) as...



Дата загрузки: 2016-10-31
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0.15/5
... (Enhanced) LOX/RP, AJ26 30B STAR 48BV Antares 130 also includes a second... (Enhanced) LOX/RP, AJ26 30XL STAR 48BV allows Orbital to offer the... chosen. An optional 3-axis stabilized STAR48BV third stage is also available... the addition of an optional STAR 48BV third stage (see Section 8). 3.1. Mission... for various configurations utilizing the STAR 48BV enhancement from WFF is provided... enhanced configurations with the ATK STAR 48BV as a third stage are used... stage currently flown on Orbital’s STAR™ bus Geosynchronous (GEO) satellites. The... stage and the addition of a STAR 48BV SRM third stage. 8.13.1. Antares... 8.13.2. Antares STAR 48BV Third Stage Orbital offers the STAR 48BV SRM as a high... Figure 8.13-1. The 3-axis stabilized STAR 48BV third stage provides a significant performance... shown in Sections 3.3 and 3.4. The STAR 48BV third stage leverages Orbital’s flight.... The ATK STAR 48BV SRM is derived from the STAR 48 motor line.... The vectorable nozzle on the STAR 48BV is used by the Minotaur... joint is placed between the STAR 48BV and the second stage to... the Antares 122 configuration. The STAR 48BV motor has a diameter of 1,245...



Дата загрузки: 2017-03-18
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0/5
...) deep Fourth Stage: — Star 48BV solid fuel rocket — The 48BV solid rocket motor... kg) LADEE Launch Fifth Stage: — Star 37FM solid fuel rocket — The... the Minotaur V is powered by a Star 48BV engine, burning 84.8 seconds. The... the Minotaur V is powered by a Star 37FM engine, burning 63.5 seconds... plug-and-play systems. two star trackers, reaction wheels, and an...



Дата загрузки: 2016-10-31
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0.07/5
... STAR 5CB. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72 STAR 5D . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73 STAR 5F . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74 STAR 6B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 75 STAR 8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76 STAR 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .77 STAR 12GV. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 78 STAR 13B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 79 STAR... STAR 48A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 104 STAR 48A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105 STAR 48B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 106 STAR 48B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 107 STAR 48BV. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 108 STAR 63 SERIES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 109 STAR 63D. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 110 STAR 63F . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 111 STAR...; Dated 05 April 2016 107 STAR 48BV TE-M-940-1 MOTOR DIMENSIONS Motor... thrust, lbf..........................................17,490 The STAR 48BV has been qualified (1993) as... is currently developing a STAR stage based on the STAR 48BV motor for a 2018... capability are shown below. The STAR 48BV stage provides guidance, control, sequencing... operation. In this application, the STAR 48BV motor is part of the... Stage Design Based on the STAR 48BV Motor 118 Approved for Public...



Дата загрузки: 2016-12-24
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0.22/5
...) deep Fourth Stage: — Star 48BV solid fuel rocket — The 48BV solid rocket motor... kg) LADEE Launch Fifth Stage: — Star 37FM solid fuel rocket — The... the Minotaur V is powered by a Star 48BV engine, burning 84.8 seconds. The... the Minotaur V is powered by a Star 37FM engine, burning 63.5 seconds... plug-and-play systems. two star trackers, reaction wheels, and an...



Дата загрузки: 2017-01-30
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0.26/5
Fact Sheet Minotaur V Quick Facts High Energy Space Launch Vehicle System Features Overview •N ear term cost effective support of high energy trajectory missions Minotaur V is a five stage evolutionary version of the Minotaur IV Space Launch Vehicle (SLV) to provide a costeffective capability to launch U.S. Government-sponsored small spacecraft into high energy trajectories, including Geosynchronous Transfer Orbits (GTO) as well as translunar and beyond. The Minotaur V concept leverages Orbital’s flight proven heritage of the Minotaur family of launch vehicles to create a low-risk, readily-developed system. •S traight forward five stage evolution of Minotaur IV SLV •E xtensive use of flight-proven boosters, subsystems, and software • I nertially-guided or spinning Stage 5 configuration options available •P ortable ground support systems allow multiple spaceport launch capability (California, Florida, Alaska, Mid-Atlantic) •M ission success ensured by mature systems and processes including Orbital’s rigorous mission assurance program, full government insight, and independent assessment The Minotaur V avionics, structures, and fairing are common with the Minotaur IV SLV, with relatively minor changes to create the five stage configuration. Moreover, the avionics and flight software are highly common across all Minotaur family vehicles. The first three stages of the Minotaur V are former Peacekeeper solid rocket motors with over 50 flights of Minotaur V provides cost-effective support of small GEO and lunar missions. each stage. The fourth and fifth stages are commercial STAR ™ motors. The stage four motor is a STAR48BV configuration. The fifth stage can be either attitude controlled or spinning. For a spin-stabilized upper stage, a STAR™ 37FM is used while a STAR ™ 37FMV, with gimballed, flexseal nozzle, is used for 3-axis stabilized control. The Minotaur family of launch vehicles are provided via the Orbital/Suborbital Program (OSP) managed by the U.S. Air Force Space and Missile Systems Center (SMC), Space Development and Test Directorate (SMC/SD) Launch Systems Division (SMC/SDL) located at Kirtland Air Force Base, New Mexico. Minotaur V is a low risk direct evolution of Minotaur IV. Minotaur V Performance 1800 Minotaur V • Minotaur V has a GTO capability of 532 kg 1600 1400 - 185 km x 35786 km @ 28.5 degree inclination, 180 AoP Payload (kg) • Minotaur V has a MTO capability at 39 degrees of 650 kg from CCAFS - 185 km x 20,200 km at 39 Degree inclination, 180 AoP 1200 1000 800 • Minotaur V has a MTO capability at 55 degrees of 603 kg from WFF Inclination: 37.8˚ Direct Ascent Perigee: 185 km No Argument of Perigee Restriction 600 400 - 185 km x 20,200 km at 55 Degrees inclination, no AoP constraint -60 • Minotaur V has a TLI capability of 342 kg -40 -20 0 20 40 C3 (km2/s2) Payload Accommodations Ø0.48 m (19.2 in) • Flight proven fairing shared with Minotaur IV • Attitude controlled or spinning final stage • Well defined environments from extensive flight data and well characterized upper stages • ISO 8 (100 k) to ISO 7 (10 k) cleanliness with temperature and humidity control 0.87 m (34.5 in) 1.52 m (60.0 in) Ø1.33 m (Ø52.5 in) • Various flight-proven separation systems available, including low shock designs 1.72 m (67.7 in) Ø2.05 m (Ø80.9 in) Ø38.81 in Interface (No Sep System) STAR 37 Secondary Payload Volume (Negotiable) Fairing Sep Plane For technical details or questions please contact Orbital at: Copies of the Minotaur User's Guide can be downloaded from: Additional information should be obtained from the USAF OSP Office minotaur@orbital.com www.orbital.com USAF SMC Space Development and Test Directorate (SMC/SD) Launch Systems Division (SMC/SDL) Kirtland AFB, NM 87117-5778 (505) 853-5533 (505) 853-0507 Orbital Sciences Corporation 45101 Warp Drive • Dulles, Virginia 20166 ©2013 Orbital Sciences Corporation BR06006_1619 • www.orbital.com 60



Дата загрузки: 2016-10-31
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0.19/5
Minotaur IV Space Launch Vehicle FACT SHEET Overview FAC T S AT A G L A N C E The flight proven Minotaur IV Space Launch Vehicle (SLV) provides an extremely cost-effective and capable space solution for U.S. Governmentsponsored spacecraft. The combination of three government-furnished solid rocket stages, a commercial solid rocket upper stage, and Orbital ATK’s flight-proven systems and processes provide an unmatched mix of value and performance. The integration of government motors with commercial boosters and state-of-the-art hardware is one of Orbital ATK’s unique strengths from experience spanning several decades. System Features • Full spacecraft integration support, including mission management, spacecraft interface support (power, telemetry, sequencing, attitude control, and deployment), through launch operations and post-launch performance evaluation • Flexible design enables multiple mission tailoring options For the Minotaur IV, the standard Minotaur family avionics, flight software, and subsystems are integrated into a Guidance Control Assembly (GCA) which also incorporates the Stage 4 Orion 38 solid rocket motor. An optional Star48BV motor has been flight demonstrated and is available for additional performance in the Minotaur IV+ configuration. The Minotaur family of launch vehicles are provided via the Orbital/Suborbital Program (OSP) and managed by the U.S. Air Force Space and Missile Systems Center (SMC), Advanced Systems and Development Directorate (SMC/AD), Rocket Systems Launch Program (SMC/ADSL) located at Kirtland Air Force Base, New Mexico. • Cost effective space launch • Responsive launch solutions available • Mission success is ensured by mature systems and processes that include Orbital ATK’s rigorous mission assurance program and categories of mission assurance to meet customers’ needs - Categories range from a basic FAA licensed launch to full Government insight and independent assessment Additional payload accommodation details can be found in the Minotaur IV Users Guide. • Multiple spaceport launch capability (California, Florida, Alaska, Mid-Atlantic) using portable ground support equipment Minotaur IV Performance 1600 • System performance assured from extensive booster motor flight history of more than 50 flights each 1400 • Typical orbit accuracy better than ±5 km insertion apse, ±25 km non-insertion apse, and ±0.1o inclination (3-sigma values) • Cold gas attitude control system readily accommodates a variety of spacecraft mission requirements, including precise separation pointing and post-boost maneuvers • Minotaur IV with optional STAR48BV Stage 4 provides up to 200 kg increased performance to LEO and support for HEO missions 1200 Payload (kg) • Optional enhanced insertion accuracy available CCAFS 28.5° WFF 43° VAFB 72° Kodiak 63.4° VAFB Sun-Synch * * NOTE: Payload Mass includes Adapter Cone, Separation System and Other MissionSpecific Hardware 1000 800 600 * Detailed Analysis Needed for Missions to these Altitude/Inclination Combinations 400 200 400 600 800 1000 1200 1400 1600 1800 Orbit Altitude (km) Payload Accommodations Ø0.48 m (19.2 in) • Standard 2.34 m (92 in) diameter spacecraft fairing • Mission-specific fairing access doors for spacecraft support 0.87 m (34.5 in) • Spacecraft and fairing assembly integrated independently from launch vehicle stages • Well-defined launch environments derived from extensive flight data 1.52 m (60.0 in) Ø1.33 m (Ø52.5 in) • Temperature, humidity, and cleanliness control through lift-off • Standard 986 mm (38.81 in) diameter bolted interface with optional spacecraft support options Ø2.05 m (Ø80.9 in) - Single and multiple spacecraft adaptors - Various flight-proven spacecraft separation systems available, including low-shock designs 2.87 m (113.3 in) • Multiple Payload Adapter Fitting (MPAF) option • Hydrazine upper stage for multiple orbit altitude capabilities or increased orbital insertion accuracy Ø38.81 in Interface (No Sep System) Fairing Sep Plane Standard Fairing Technical Details minotaur@orbitalatk.com Key Contacts Terry Luchi Program Manager, Minotaur Warren Frick Program Manager, Advanced Projects (480) 814-6107 terry.luchi@orbitalatk.com (703) 948-8192 warren.frick@orbitalatk.com OrbitalATK.com ©2015 Orbital ATK, Inc. All Rights Reserved. BR06005_3862



Дата загрузки: 2017-02-23
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0/5
Antares™ Medium-Class Space Launch Vehicle LAUNCH VEHICLE Medium Class FACTS AT A GLANCE Overview Designed to provide responsive and low-cost access to space, Antares is a two-stage vehicle (with optional third stage) that provides low-Earth orbit (LEO) launch capability for payloads weighing over 7,000 kg. Internally funded by Orbital, Antares completed a risk reduction mission and a demonstration of commercial re-supply services for the International Space Station (ISS) under a NASA Commercial Orbital Transportation Services (COTS) agreement in 2013. Orbital commenced delivery of cargo to the International Space Station under the NASA Commercial Resupply Services (CRS) contract in 2014. The Antares launch system utilizes Orbital's proven MACH avionics system and many management approaches, engineering standards, production and test processes common to Orbital’s family of successful small-class Pegasus® and Minotaur launch vehicles. The Antares design is being upgraded with newly-built RD-181 first stage engines to provide greater payload performance and increased reliability. Orbital is modifying the rocket’s first stage systems in anticipation of hot fire testing in late 2015. The company is currently targeting a return to flight in 2016 with launches projected in the first, second and fourth quarters to fulfill the company’s agreement with NASA to deliver supplies to the International Space Station. Key Features • Capable of launching single and multiple payloads • Provides substantial payload performance into a variety of low inclination low-Earth and sun-synchronous orbits and interplanetary trajectories • Initial launch capability from Wallops Flight Facility (WFF), Virginia • 3.9 meter fairing accommodates large payloads Over 7,000 kg to low-Earth orbit Mission Partners Orbital Sciences Corporation Prime integrator, systems engineering, avionics, primary structure, testing and software. Overall Stage 1 development and integration. KB Yuzhnoye/Yuzhmash Stage 1 core design, production and verification Energomash • Incorporates both solid and liquid stages and flight-proven technologies • Streamlined vehicle/payload integration and testing via simplified interfaces reduce time from encapsulation to lift-off Medium-class space launch vehicle utilizes systems from other Orbital product lines and Zenit heritage • Also compatible with the Western Range at Vandenberg Air Force Base (VAFB), Eastern Range at Cape Canaveral Air Force Station (CCAFS) and the Kodiak Launch Complex (KLC) Stage 1 engines ATK Stage 2 motor Antares ™ Expanded View Performance Payload Fairing Antares Performance to Circular Orbits (WFF) • Diameter: 3.9 m 7000 • Height: 9.9 m Antares Performance to Circular Orbits (WFF) 231 • Separation: Non-contaminating frangible ring Optional STAR™ 48-Based Third Stage Stage 2 Payload Mass (kg) 6000 • Structure: Honeycomb core, composite face Optional BiPropellant Third Stage (BTS) Optional Stage 2 • ATK CASTOR 30XL solid motor with Helium pressure regulated bi-propellant propulsion system using nitrogen tetroxide and hydrazine (Orbital GEOStar™ bus heritage) thrust vectoring • Thrust vector guidance and control 4000 3000 1000 100 300 400 500 600 700 Circular Orbit Altitude (km) 800 900 o 5000 • 3-axis stabilized satellite orbit insertion Antares Performance to 38 High Energy Orbits (WFF) 4500 4000 3500 3000 232 2500 2000 Stage 1 1500 • Two NPO Energomash RD-181 engines with independent thrust vectoring 1000 • Liquid oxygen/kerosene fueled 200 Antares Performance to 38˚ High Energy Orbits (WFF) Payload Mass (kg) • MACH avionics 230 5000 2000 • ATK STAR 48BV high energy upper stage solid rocket motor • ATK CASTOR® 30B solid motor (CASTOR 120 heritage) with thrust vectoring 38o 51.6o 60o 500 −50 −40 −30 −20 −10 0 2 2 C3 Energy (km /s ) 10 20 30 • Orbital responsible for system development and integration • Core tank design and design verification by KB Yuzhnoye (Zenit-derived) • Core tank production by Yuzhmash • Avionics stage controller uses flight-proven Orbital MACH components Key Contacts Mark Pieczynski VP Southern California Engineering Center and Space Launch Business Development (714) 677-2444 pieczynski.mark@orbital.com Warren Frick Program Manager Advanced Projects (703) 948-8192 frick.warren@orbital.com Orbital Sciences Corporation 45101 Warp Drive • Dulles, Virginia 20166 ©2014 Orbital Sciences Corporation FS007_06_3891 • www.orbital.com Antares Configuration Numbering First Stage Second Stage Third Stage 2 – Two NPO Energomash RD-181 Lox/ Kerosene Fueled Engines 2 – CASTOR 30B Solid Motor 0 – None 3 – CASTOR 30XL Solid Motor 1 – Bi-Propellant Third Stage (BTS) 2 – Star 48-Based Third Stage



Дата загрузки: 2016-10-31
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0.3/5
Minotaur V Space Launch Vehicle for High Energy Missions FACT SHEET Overview FAC T S AT A G L A N C E The flight proven Minotaur V is a five stage evolutionary version of the Minotaur IV Space Launch Vehicle (SLV) to provide a cost-effective capability to launch U.S. Government-sponsored small spacecraft into high energy trajectories, including Geosynchronous Transfer Orbits (GTO) as well as translunar and beyond. System Features • Cost effective support of high energy trajectory missions • Five stage evolution of Minotaur IV SLV The Minotaur V leverages Orbital ATK’s flight proven heritage of the Minotaur family of launch vehicles to create a low-risk, dependable launch system. • Flight-proven boosters, subsystems, and software • Inertially-guided or spinning Stage 5 configuration options available The Minotaur V avionics, structures, and fairing are common with the Minotaur IV SLV, with relatively minor changes to create the five stage configuration. Moreover, the avionics and flight software are highly common across all Minotaur family vehicles. The first three stages of the Minotaur V are former Peacekeeper solid rocket motors with over 50 flights of each stage. The fourth and fifth stages are commercial STAR™ motors. The stage four motor is a STAR48BV configuration. The fifth stage can be either attitude controlled or spinning. For a spin-stabilized upper stage, a STAR™ 37FM is used while a STAR™ 37FMV, with gimballed, flexseal nozzle, is used for 3-axis stabilized control. • Portable ground support systems allow multiple spaceport launch capability (California, Florida, Alaska, Mid-Atlantic) Minotaur V • Mission success is ensured by mature systems and processes that include Orbital ATK’s rigorous mission assurance program and categories of mission assurance to meet customers’ needs - Categories range from a basic FAA licensed launch to full Government insight and independent assessment The Minotaur family of launch vehicles are provided via the Orbital/Suborbital Program (OSP) and managed by the U.S. Air Force Space and Missile Systems Center (SMC), Advanced Systems and Development Directorate (SMC/AD), Rocket Systems Launch Program (SMC/ADSL) located at Kirtland Air Force Base, New Mexico. Minotaur V Performance 1800 • Minotaur V has a GTO capability of 532 kg 1600 - 185 km x 35786 km @ 28.5o inclination, 180 AoP • Minotaur V has a MTO capability at 39o of 650 kg from CCAFS - 185 km x 20,200 km at 39o inclination, 180 AoP 1400 Payload (kg) Minotaur V Inclination: 37.8˚ Direct Ascent Perigee: 185 km No Argument of Perigee Restriction 1200 1000 800 • Minotaur V has a MTO capability at 55o of 603 kg from WFF 600 400 - 185 km x 20,200 km at 55o inclination, no AoP constraint -60 • Minotaur V has a TLI capability of 342 kg -40 -20 0 20 40 60 C3 (km2/s2) Payload Accommodations Ø0.48 m (19.2 in) • Flight proven fairing shared with Minotaur IV 0.87 m (34.5 in) • Attitude controlled or spinning final stage • Well defined environments from extensive flight data and well characterized upper stages • ISO 8 (100 k) to ISO 7 (10 k) cleanliness with temperature and humidity control • Various flight-proven separation systems available, including low shock designs 1.52 m (60.0 in) 1.72 m (67.7 in) Ø38.81 in Interface (No Sep System) Ø1.33 m (Ø52.5 in) Ø2.05 m (Ø80.9 in) STAR 37 Secondary Payload Volume (Negotiable) Fairing Sep Plane Technical Details minotaur@orbitalatk.com Key Contacts Terry Luchi Program Manager, Minotaur Warren Frick Program Manager, Advanced Projects (480) 814-6107 terry.luchi@orbitalatk.com (703) 948-8192 warren.frick@orbitalatk.com OrbitalATK.com ©2015 Orbital ATK, Inc. All Rights Reserved. BR06006_3862