DOCSLIB.ORG

Minotaur I Users Guide

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Minotaur I Users Guide ORBITAL SCIENCES CORPORATION January 2006 Minotaur I User’s Guide Release 2.1 Approved for Public Release Distribution Unlimited Copyright 2006 by 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 thoughout. Major updates include All • Performance plots • Environments • Payload accommodations • Added 61 inch fairing option 2.1 TM-14025B Jan 2006 General nomenclature, history, and administrative updates All (no technical updates) • Changed “Minotaur” to “Minotaur I” • Updated launch history • Corrected contact information Release 1.1 January 2006 ii Minotaur I User’s Guide 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. The launch services described herein are available for US Government sponsored missions via the United States Air Force (USAF) Space and Missile Systems Center, Detachment 12, Rocket Systems Launch Program (RSLP). Readers desiring further information on Minotaur I should contact the USAF Program Office: USAF SMC Det 12/RP 3548 Aberdeen Ave SE Kirtland AFB, NM 87117-5778 Telephone: (505) 846-8957 Fax: (505) 846-5152 Additional copies of this User's Guide and Technical information may also be requested from Orbital at: Orbital Suborbital Program - Mission Development Orbital Sciences Corporation Launch Systems Group 3380 S. Price Road Chandler, AZ 85248 Telephone: (480) 814-6566 E-mail: [email protected] Release 1.1 January 2006 iii Minotaur I User’s Guide Preface THIS PAGE LEFT INTENTIONALLY BLANK Release 1.1 January 2006 iv Minotaur I User’s Guide Table of Contents PAGE 1. INTRODUCTION...................................................................................................................................... 1 2. MINOTAUR I LAUNCH SERVICE ........................................................................................................... 3 2.1. Minotaur I Launch System Overview ............................................................................................ 3 2.2. Minotaur I Launch Service ............................................................................................................ 4 2.3. Minotaur I Launch Vehicle ............................................................................................................ 4 2.3.1. Lower Stack Assembly.............................................................................................................. 4 2.3.2. Upper Stack Assembly.............................................................................................................. 5 2.4. Launch Support Equipment .......................................................................................................... 6 3. GENERAL PERFORMANCE ................................................................................................................... 9 3.1. Mission Profiles............................................................................................................................. 9 3.2. Launch Sites ................................................................................................................................. 9 3.3. Performance Capability............................................................................................................... 10 3.4. Injection Accuracy....................................................................................................................... 10 3.5. Payload Deployment................................................................................................................... 19 3.6. Payload Separation..................................................................................................................... 20 3.7. Collision/Contamination Avoidance Maneuver ........................................................................... 20 4. PAYLOAD ENVIRONMENT................................................................................................................... 21 4.1. Steady State and Transient Acceleration Loads......................................................................... 21 4.1.1. Standard Payload Isolation System ........................................................................................ 23 4.2. Payload Vibration Environment .................................................................................................. 23 4.3. Payload Shock Environment.......................................................................................................24 4.4. Payload Acoustic Environment ................................................................................................... 24 4.5. Payload Structural Integrity and Environments Verification........................................................ 24 4.5.1. Recommended Payload Testing and Analysis ....................................................................... 25 4.6. Thermal and Humidity Environments.......................................................................................... 26 4.6.1. Ground Operations.................................................................................................................. 26 4.6.2. Powered Flight ........................................................................................................................ 27 4.6.3. Nitrogen Purge (non-standard service)................................................................................... 27 4.7. Payload Contamination Control .................................................................................................. 28 4.8. Payload Electromagnetic Environment....................................................................................... 28 5. PAYLOAD INTERFACES ...................................................................................................................... 31 5.1. Standard Payload Fairing (50 Inch Diameter) ............................................................................ 31 5.1.1. Payload Dynamic Design Envelope........................................................................................ 31 5.1.2. Payload Access Door.............................................................................................................. 31 5.1.3. Increased Volume Payload Fairing (61 Inch Diameter - Non-Standard) ................................ 31 5.2. Payload Mechanical Interface and Separation System .............................................................. 31 Release 1.1 January 2006 v Minotaur I User’s Guide Table of Contents PAGE 5.2.1. Standard Non-Separating Mechanical Interface..................................................................... 34 5.2.2. Separating Mechanical Interface............................................................................................. 34 5.3. Payload Electrical Interfaces....................................................................................................... 34 5.3.1. Standard Payload/Minotaur I Electrical Interface, With A Payload Provided Separation System .................................................................................................................. 34 5.3.2. Payload Interface Circuitry ...................................................................................................... 36 5.3.3. Payload Battery Charging ....................................................................................................... 36 5.3.4. Payload Command and Control.............................................................................................. 36 5.3.5. Pyrotechnic Initiation Signals ..................................................................................................36 5.3.6. Payload Discrete Telemetry .................................................................................................... 36 5.3.7. Payload Analog Telemetry ...................................................................................................... 37 5.3.8. Payload Separation Monitor Loopbacks ................................................................................. 37 5.3.9. Telemetry Interfaces ............................................................................................................... 38 5.3.10. Non Standard Electrical Interfaces ....................................................................................... 38 5.3.11. Electrical Launch Support Equipment................................................................................... 38 5.4. Payload Design Constraints........................................................................................................ 39 5.4.1. Payload Center of Mass Constraints ...................................................................................... 39 5.4.2. Final Mass Properties Accuracy.............................................................................................. 39 5.4.3. Pre-Launch Electrical Constraints........................................................................................... 39 5.4.4. Payload EMI/EMC Constraints...............................................................................................
Load more

Recommended publications
  • Launch and Deployment Analysis for a Small, MEO, Technology Demonstration Satellite
    46th AIAA Aerospace Sciences Meeting and Exhibit AIAA 2008-1131 7 – 10 January 20006, Reno, Nevada Launch and Deployment Analysis for a Small, MEO, Technology Demonstration Satellite Stephen A. Whitmore* and Tyson K. Smith† Utah State University, Logan, UT, 84322-4130 A trade study investigating the economics, mass budget, and concept of operations for delivery of a small technology-demonstration satellite to a medium-altitude earth orbit is presented. The mission requires payload deployment at a 19,000 km orbit altitude and an inclination of 55o. Because the payload is a technology demonstrator and not part of an operational mission, launch and deployment costs are a paramount consideration. The payload includes classified technologies; consequently a USA licensed launch system is mandated. A preliminary trade analysis is performed where all available options for FAA-licensed US launch systems are considered. The preliminary trade study selects the Orbital Sciences Minotaur V launch vehicle, derived from the decommissioned Peacekeeper missile system, as the most favorable option for payload delivery. To meet mission objectives the Minotaur V configuration is modified, replacing the baseline 5th stage ATK-37FM motor with the significantly smaller ATK Star 27. The proposed design change enables payload delivery to the required orbit without using a 6th stage kick motor. End-to-end mass budgets are calculated, and a concept of operations is presented. Monte-Carlo simulations are used to characterize the expected accuracy of the final orbit.
    [Show full text]
  • Small Space Launch: Origins & Challenges Lt Col Thomas H
    Small Space Launch: Origins & Challenges Lt Col Thomas H. Freeman, USAF, [email protected], (505)853-4750 Maj Jose Delarosa, USAF, [email protected], (505)846-4097 Launch Test Squadron, SMC/SDTW Small Space Launch: Origins The United States Space Situational Awareness capability continues to be a key element in obtaining and maintaining the high ground in space. Space Situational Awareness satellites are critical enablers for integrated air, ground and sea operations, and play an essential role in fighting and winning conflicts. The United States leads the world space community in spacecraft payload systems from the component level into spacecraft, and in the development of constellations of spacecraft. The United States’ position is founded upon continued government investment in research and development in space technology [1], which is clearly reflected in the Space Situational Awareness capabilities and the longevity of these missions. In the area of launch systems that support Space Situational Awareness, despite the recent development of small launch vehicles, the United States launch capability is dominated by an old, unresponsive and relatively expensive set of launchers [1] in the Expandable, Expendable Launch Vehicles (EELV) platforms; Delta IV and Atlas V. The EELV systems require an average of six to eight months from positioning on the launch table until liftoff [3]. Access to space requires maintaining a robust space transportation capability, founded on a rigorous industrial and technology base. The downturn of commercial space launch service use has undermined, for the time being, the ability of industry to recoup its significant investment in current launch systems.
    [Show full text]
  • Minotaur I User's Guide
    This page left intentionally blank. Minotaur I User’s Guide Revision Summary TM-14025, Rev. D 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 · Performance plots · Environments · Payload accommodations · Added 61 inch fairing option 3.0 TM-14025B Mar 2014 Extensively Revised All 3.1 TM-14025C Sep 2015 Updated to current Orbital ATK naming. All 3.2 TM-14025D Sep 2018 Branding update to Northrop Grumman. All 3.3 TM-14025D Sep 2020 Branding update. All Updated contact information. Release 3.3 September 2020 i Minotaur I User’s Guide Revision Summary TM-14025, Rev. D This page left intentionally blank. Release 3.3 September 2020 ii Minotaur I User’s Guide Preface TM-14025, Rev. D PREFACE This Minotaur I User's Guide is intended to familiarize potential space launch vehicle users with the Mino- taur 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. The launch services described herein are available for US Government sponsored missions via the United States Air Force (USAF) Space and Missile Systems Center (SMC), Advanced Systems and Development Directorate (SMC/AD), Rocket Systems Launch Program (SMC/ADSL). For technical information and additional copies of this User’s Guide, contact: Northrop Grumman
    [Show full text]
  • Aas 14-281 Suborbital Intercept And
    AAS 14-281 SUBORBITAL INTERCEPT AND FRAGMENTATION OF ASTEROIDS WITH VERY SHORT WARNING TIMES Ryan Hupp,∗ Spencer Dewald,∗ and Bong Wiey The threat of an asteroid impact with very short warning times (e.g., 1 to 24 hrs) is a very probable, real danger to civilization, yet no viable countermeasures cur- rently exist. The utilization of an upgraded ICBM to deliver a hypervelocity as- teroid intercept vehicle (HAIV) carrying a nuclear explosive device (NED) on a suborbital interception trajectory is studied in this paper. Specifically, this paper focuses on determining the trajectory for maximizing the altitude of intercept. A hypothetical asteroid impact scenario is used as an example for determining sim- plified trajectory models. Other issues are also examined, including launch vehicle options, launch site placement, late intercept, and some undesirable side effects. It is shown that silo-based ICBMs with modest burnout velocities can be utilized for a suborbital asteroid intercept mission with an NED explosion at reasonably higher altitudes (> 2,500 km). However, further studies will be required in the following key areas: i) NED sizing for properly fragmenting small (50 to 150 m) asteroids, ii) the side effects caused by an NED explosion at an altitude of 2,500 km or higher, iii) the rapid launch readiness of existing or upgraded ICBMs for a suborbital asteroid intercept with short warning times (e.g., 1 to 24 hrs), and iv) precision ascent guidance and terminal intercept guidance. It is emphasized that if an earlier alert (e.g., > 1 week) can be assured, then an interplanetary inter- cept/fragmentation may become feasible, which requires an interplanetary launch vehicle.
    [Show full text]
  • Minotuar-User-Guide-3.Pdf
    This page left intentionally blank. Minotaur IV • V • VI User’s Guide Revision Summary TM-17589, Rev. E REVISION SUMMARY VERSION DOCUMENT DATE CHANGE PAGE 1.0 TM-17589 Jan 2005 Initial Release All 1.1 TM-17589A Jan 2006 General nomenclature, history, and administrative up- All dates (no technical updates) 1. Updated launch history 2. Corrected contact information 2.0 TM-17589B Jun 2013 Extensively Revised All 2.1 TM-17589C Aug 2015 Updated to current Orbital ATK naming. All 2.2 TM-17589D Aug 2015 Minor updates to correct Orbital ATK naming. All 2.3 TM-17589E Apr 2019 Branding update to Northrop Grumman. All Corrected Figures 4.2.2-1 and 4.2.2-2. Corrected Section 6.2.1, paragraph 3. 2.4 TM-17589E Sep 2020 Branding update. All Updated contact information. Updated footer. Release 2.4 September 2020 i Minotaur IV • V • VI User’s Guide Revision Summary TM-17589, Rev. E This page left intentionally blank. Release 2.4 September 2020 ii Minotaur IV • V • VI User’s Guide User’s Guide Preface TM-17589, Rev. E The information provided in this user’s guide is for initial planning purposes only. Information for develop- ment/design is determined through mission specific engineering analyses. The results of these analyses are documented in a mission-specific Interface Control Document (ICD) for the payloader organization to use in their development/design process. This document provides an overview of the Minotaur system design and a description of the services provided to our customers. For technical information and additional copies of this User’s
    [Show full text]
  • Orbital Sciences 2013 Annual Report Final Version.Pdf
    Orbital Sciences Corporation 2013 ANNUAL REPORT Antares Test Flight Launched 9 Research Rockets Launched in Second Wallops Island, VA Quarter Orbital Sciences Corporation YEAR IN REVIEW 41 Space Missions Conducted and 37 Rockets and Satellites Sold in 2013 Coyote Target Launched Azerspace/Africasat-1a San Nicolas Island, CA Satellite Launched Orbital Wins Order for Kourou, French Guiana Thaicom 8 Satellite Missile Defense Interceptor Launched Vandenberg AFB, CA Orbital Selected to Develop Stratolaunch Vehicle Coyote Target Launched San Nicolas Island, CA JANUARY FEBRUARY MARCH APRIL MAY JUNE Landsat 8 Satellite 3 Coyote Targets Launched Orbital Wins NASA Launched Vandenberg AFB, CA TESS Satellite Contract San Nicolas Island, CA Orbital Wins New Satellite to identify Earth- Interceptor Order like planets Antares Stage One Hot-Fire Test Conducted Wallops Island, VA Orbital Wins NASA ICON Satellite Contract Satellite to study the Sun’s effect on the Ionosphere Coyote Target Launched 5 Antares Engines Tested 3 Research Rockets San Nicolas Island, CA Launched in First Quarter 9 Research Rockets 4 Research Rockets Launched in Second Launched in Third Quarter Quarter 2 Coyote Targets Launched Orbital Receives New San Nicolas Island, CA Target Vehicle Order Pegasus Launched IRIS Satellite Vandenberg AFB, CA Minotaur V Debut Additional Military Launched LADEE Lunar SES-8 Satellite Satellite Order Received Probe Launched 2 Coyote Targets Wallops Island, VA Cape Canaveral, FL Launched Kauai, HI JULY AUGUST SEPTEMBER OCTOBER NOVEMBER DECEMBER Antares
    [Show full text]
  • Sale Price Drives Potential Effects on DOD and Commercial Launch Providers
    United States Government Accountability Office Report to Congressional Addressees August 2017 SURPLUS MISSILE MOTORS Sale Price Drives Potential Effects on DOD and Commercial Launch Providers Accessible Version GAO-17-609 August 2017 SURPLUS MISSILE MOTORS Sale Price Drives Potential Effects on DOD and Commercial Launch Providers Highlights of GAO-17-609, a report to congressional addressees Why GAO Did This Study What GAO Found The U.S. government spends over a The Department of Defense (DOD) could use several methods to set the sale billion dollars each year on launch prices of surplus intercontinental ballistic missile (ICBM) motors that could be activities as it strives to help develop a converted and used in vehicles for commercial launch if current rules prohibiting competitive market for space launches such sales were changed. One method would be to determine a breakeven and assure its access to space. Among price. Below this price, DOD would not recuperate its costs, and, above this others, one launch option is to use price, DOD would potentially save. GAO estimated that DOD could sell three vehicles derived from surplus ICBM Peacekeeper motors—the number required for one launch, or, a “motor set”—at motors such as those used on the Peacekeeper and Minuteman missiles. a breakeven price of about $8.36 million and two Minuteman II motors for about The Commercial Space Act of 1998 $3.96 million, as shown below. Other methods for determining motor prices, such prohibits the use of these motors for as fair market value as described in the Federal Accounting Standards Advisory commercial launches and limits their Board Handbook, resulted in stakeholder estimates ranging from $1.3 million per use in government launches in part to motor set to $11.2 million for a first stage Peacekeeper motor.
    [Show full text]
  • Minotaur V Space Launch Vehicle for Small, Cost-Effective Moon Exploration Missions
    Minotaur V Space Launch Vehicle for Small, Cost-Effective Moon Exploration Missions Scott Schoneman 14 August 2007 21st Annual AIAA/USU Conference on Small Satellites Innovation You Can Count On™ Minotaur Family of Launch Vehicles 2 Minotaur Family Flight History and Firm Manifest 3 Minotaur IV Has an Extensive, Proven Heritage 4 Minotaur V Origins z Minotaur V is Five Stage Evolution of Minotaur IV ¾ Adds Upper Stage for High Energy Missions: MTO, GTO, TLI, and Beyond ¾ Retains Reuse of Reliable, Proven Solid Rocket Motors z Detailed Trade Study Resulted in Selection of Upper Stage Motors ¾ STAR 48BV for Stage 4 ¾ STAR 37 Options for Stage 5 – 37FM for Spin-Stabilized – 37FMV for 3-Axis Stabilized 5 Minotaur V - STAR 37FMV Stage 5 Configuration (3-axis Stabilized) z Extensive Minotaur-Family Heritage Composite Clamshell Fairing and Commonality z Flight Proven 92” Taurus Design ¾ Flight Proven OSP Avionics and Stage 5 Assembly Flight Software w/ Heritage of 10 z STAR 37FMV Solid Rocket Motor or more Flights ¾ Thrust Vector Controlled z OSP-Standard Avionics z Uses STAR 48 and STAR 37 Upper ¾ Only Subset Required to Fly Stage 5 Stage Motors z Cold Gas Attitude Control System (ACS) ¾ Extensive STAR Motor Flight z Composite Structure History Guidance Control Assembly (GCA)/Stage 4 ¾ Flight Qualified Flexseal and z GCA Design Shared with Minotaur III & IV Actuator System z OSP-Standard Flight Proven Avionics ¾ Split Between S4 and S5 z Performance: z Cold Gas ACS ¾ 721kg to GPS Transfer Orbit z Stage 4 STAR 48BV SRM (55 deg, Direct Ascent
    [Show full text]
  • Small Launchers in a Pandemic World - 2021 Edition of the Annual Industry Survey
    SSC21- IV-07 Small Launchers in a Pandemic World - 2021 Edition of the Annual Industry Survey Carlos Niederstrasser Northrop Grumman Corporation 45101 Warp Drive, Dulles, VA 20166 USA; +1.703.406.5504 [email protected] ABSTRACT Even with the challenges posed by the world-wide COVID pandemic, small vehicle "Launch Fever" has not abated. In 2015 we first presented this survey at the AIAA/USU Conference on Small Satellites1, and we identified twenty small launch vehicles under development. By mid-2021 ten vehicles in this class were operational, 48 were identified under development, and a staggering 43 more were potential new entrants. Some are spurred by renewed government investment in space, such as what we see in the U.K. Others are new commercial entries from unexpected markets such as China. All are inspired by the success of SpaceX and the desire to capitalize on the perceived demand caused by the mega constellations. In this paper we present an overview of the small launch vehicles under development today. When available, we compare their capabilities, stated mission goals, cost and funding sources, and their publicized testing progress. We also review the growing number of entrants that have dropped out since we first started this report. Despite the COVID-19 pandemic, one system became operational in the past 12 months and two or three more systems hope to achieve their first successful launch in 2021. There is evidence that this could be the year when the small launch market finally becomes saturated; however, expectations continue to be high and many new entrants hope that there is room for more providers.
    [Show full text]
  • Behind Text.” Should Automatically to Edge (8.5 X 11)
    Insert Cover jpeg here. Make wrapping “Behind Text.” Should automatically to edge (8.5 x 11). JEFFREY C. BOULWARE Jeffrey C. Boulware is a senior project engineer in The Aerospace Corporation’s National Systems Group where he conducts strategic planning for long-term enterprise acquisitions. Prior to joining Aerospace in January 2018, he served as a civil servant in the Air Force’s ICBM System Directorate in key leadership positions related to the modernization and sustainment of ICBM weapon systems. He holds a master’s degree in military operational art and science from Air University and a Ph.D. in mechanical and aerospace engineering from Utah State University. ABOUT THE CENTER FOR SPACE POLICY AND STRATEGY The Center for Space Policy and Strategy is dedicated to shaping the future by providing nonpartisan research and strategic analysis to decisionmakers. The Center is part of The Aerospace Corporation, a nonprofit organization that advises the government on complex space enterprise and systems engineering problems. The views expressed in this publication are solely those of the author(s), and do not necessarily reflect those of The Aerospace Corporation, its management, or its customers. For more information, go to www.aerospace.org/policy or email [email protected]. Summary The options for post-retirement uses of intercontinental ballistic missiles (ICBMs) are controlled by Title 51, Section 50134, of the U.S. Code. This policy prohibits the transfer of ICBM systems to private industry for commercial space launch purposes. Advocates for change would like to create a low-cost launch service provider whereas opponents to changing the policy argue this would unbalance the commercial launch market and stifle innovation from emerging companies.
    [Show full text]
  • 2013 Commercial Space Transportation Forecasts
    Federal Aviation Administration 2013 Commercial Space Transportation Forecasts May 2013 FAA Commercial Space Transportation (AST) and the Commercial Space Transportation Advisory Committee (COMSTAC) • i • 2013 Commercial Space Transportation Forecasts About the FAA Office of Commercial Space Transportation The Federal Aviation Administration’s Office of Commercial Space Transportation (FAA AST) licenses and regulates U.S. commercial space launch and reentry activity, as well as the operation of non-federal launch and reentry sites, as authorized by Executive Order 12465 and Title 51 United States Code, Subtitle V, Chapter 509 (formerly the Commercial Space Launch Act). FAA AST’s mission is to ensure public health and safety and the safety of property while protecting the national security and foreign policy interests of the United States during commercial launch and reentry operations. In addition, FAA AST is directed to encourage, facilitate, and promote commercial space launches and reentries. Additional information concerning commercial space transportation can be found on FAA AST’s website: http://www.faa.gov/go/ast Cover: The Orbital Sciences Corporation’s Antares rocket is seen as it launches from Pad-0A of the Mid-Atlantic Regional Spaceport at the NASA Wallops Flight Facility in Virginia, Sunday, April 21, 2013. Image Credit: NASA/Bill Ingalls NOTICE Use of trade names or names of manufacturers in this document does not constitute an official endorsement of such products or manufacturers, either expressed or implied, by the Federal Aviation Administration. • i • Federal Aviation Administration’s Office of Commercial Space Transportation Table of Contents EXECUTIVE SUMMARY . 1 COMSTAC 2013 COMMERCIAL GEOSYNCHRONOUS ORBIT LAUNCH DEMAND FORECAST .
    [Show full text]
  • Orion Motor Series
    Propulsion Products Catalog ORION MOTOR SERIES AFFORDABLE, LOW-RISK FLEXIBLE CAPABILITIES The Orion family of motors began with three stages originally designed for use on the Pegasus® launch vehicle. Modifications to the original three Orion motors, first for extended length (XL) versions and subsequently for skirt, nozzle, and other smaller differences, have accommodated additional applications and enhanced performance capabilities. Vehicle applications successfully flown using Orion motors include Pegasus, Taurus®, Pegasus XL, Minotaur®, Hyper-X, Taurus® Lite, and Taurus XL launch vehicles, and the Ground-based Midcourse Defense ground-based interceptor. New applications continue to evolve, such as target vehicle configurations for the Missile Defense Agency. The multiple configurations and applications currently existing demonstrate that these flight-proven motors are readily adaptable to a wide range of launch scenarios (e.g., ground-start, air-start, silo-launched, etc.) and missions. Northrop Grumman has also demonstrated support for their deployment and use at a wide range of launch sites and field locations, including multiple non-Continental United States launch sites. Further, it should be noted that much of the adaptation has been accomplished with only relatively minor changes (skirt thicknesses and hole patterns, nozzle length, etc.), with little or no changes to the basic motor. The current major vehicle applications and variants for Orion motors are shown in the table on the following page. The motor identification key provides a further explanation for nomenclature designations in the Orion motor series. Inquiries regarding our Orion motor products should be directed to our business development representatives at [email protected]. This document does not contain technical data as defined in the ITAR, 22 CFR 120.10; 7 or technology as defined under EAR (15 CFR 730-774).
    [Show full text]