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EURASIA Russian Heavy Artillery
EURASIA Russian Heavy Artillery: Leaving Depots and Returning to Service OE Watch Commentary: The Soviet Union developed large caliber artillery, such as the 2S4 ‘Tyulpan’ 240mm mortar and the 2S7 ‘Pion’ 203mm howitzer, to suppress lines of communication, destroy enemy headquarters, tactical nuclear weapons, logistic areas, and other important targets and to destroy urban areas and field fortifications. After the end of the Cold War, the Russian Federation placed most of these large caliber artillery systems into long-term storage depots for several reasons. The first is that they were intended to deliver nuclear, as well as conventional, munitions (the end of the Cold War meant that a long-range tactical nuclear weapon delivery was no longer needed). Another reason is that better tube (2S19M Msta-SM) and missile (MLRS/SRBM/GLCM) systems, such as new 300mm MLRS platforms, the Iskander missile system, and the 2S19M Msta-SM 152mm howitzer, allow Russia to fulfill many of the same tasks as large caliber artillery to varying degrees. The 2S4 ‘Tyulpan’ self-propelled mortar is equipped with a 240mm 2B8 mortar mounted on a modified Object 123 tracked chassis (similar to the 2S3 Akatsiya self-propelled howitzer) with a V-59 V-12, 520 horsepower diesel engine, capable of 60 km/h road speed. The Tyulpan has a crew of four, but five additional crewman are carried in the support vehicle that typically accompanies it. The system is capable of firing conventional, chemical, and nuclear munitions at a rate of one round per minute, although Russia reportedly now only has conventional munitions in service. -
Orion Capsule Launch Abort System Analysis
Orion Capsule Launch Abort System Analysis Assignment 2 AE 4802 Spring 2016 – Digital Design and Manufacturing Georgia Institute of Technology Authors: Tyler Scogin Michel Lacerda Jordan Marshall Table of Contents 1. Introduction ......................................................................................................................................... 4 1.1 Mission Profile ............................................................................................................................. 7 1.2 Literature Review ........................................................................................................................ 8 2. Conceptual Design ............................................................................................................................. 13 2.1 Design Process ........................................................................................................................... 13 2.2 Vehicle Performance Characteristics ......................................................................................... 15 2.3 Vehicle/Sub-Component Sizing ................................................................................................. 15 3. Vehicle 3D Model in CATIA ................................................................................................................ 22 3.1 3D Modeling Roles and Responsibilities: .................................................................................. 22 3.2 Design Parameters and Relations:............................................................................................ -
Materials for Liquid Propulsion Systems
https://ntrs.nasa.gov/search.jsp?R=20160008869 2019-08-29T17:47:59+00:00Z CHAPTER 12 Materials for Liquid Propulsion Systems John A. Halchak Consultant, Los Angeles, California James L. Cannon NASA Marshall Space Flight Center, Huntsville, Alabama Corey Brown Aerojet-Rocketdyne, West Palm Beach, Florida 12.1 Introduction Earth to orbit launch vehicles are propelled by rocket engines and motors, both liquid and solid. This chapter will discuss liquid engines. The heart of a launch vehicle is its engine. The remainder of the vehicle (with the notable exceptions of the payload and guidance system) is an aero structure to support the propellant tanks which provide the fuel and oxidizer to feed the engine or engines. The basic principle behind a rocket engine is straightforward. The engine is a means to convert potential thermochemical energy of one or more propellants into exhaust jet kinetic energy. Fuel and oxidizer are burned in a combustion chamber where they create hot gases under high pressure. These hot gases are allowed to expand through a nozzle. The molecules of hot gas are first constricted by the throat of the nozzle (de-Laval nozzle) which forces them to accelerate; then as the nozzle flares outwards, they expand and further accelerate. It is the mass of the combustion gases times their velocity, reacting against the walls of the combustion chamber and nozzle, which produce thrust according to Newton’s third law: for every action there is an equal and opposite reaction. [1] Solid rocket motors are cheaper to manufacture and offer good values for their cost. -
Interstellar Probe on Space Launch System (Sls)
INTERSTELLAR PROBE ON SPACE LAUNCH SYSTEM (SLS) David Alan Smith SLS Spacecraft/Payload Integration & Evolution (SPIE) NASA-MSFC December 13, 2019 0497 SLS EVOLVABILITY FOUNDATION FOR A GENERATION OF DEEP SPACE EXPLORATION 322 ft. Up to 313ft. 365 ft. 325 ft. 365 ft. 355 ft. Universal Universal Launch Abort System Stage Adapter 5m Class Stage Adapter Orion 8.4m Fairing 8.4m Fairing Fairing Long (Up to 90’) (up to 63’) Short (Up to 63’) Interim Cryogenic Exploration Exploration Exploration Propulsion Stage Upper Stage Upper Stage Upper Stage Launch Vehicle Interstage Interstage Interstage Stage Adapter Core Stage Core Stage Core Stage Solid Solid Evolved Rocket Rocket Boosters Boosters Boosters RS-25 RS-25 Engines Engines SLS Block 1 SLS Block 1 Cargo SLS Block 1B Crew SLS Block 1B Cargo SLS Block 2 Crew SLS Block 2 Cargo > 26 t (57k lbs) > 26 t (57k lbs) 38–41 t (84k-90k lbs) 41-44 t (90k–97k lbs) > 45 t (99k lbs) > 45 t (99k lbs) Payload to TLI/Moon Launch in the late 2020s and early 2030s 0497 IS THIS ROCKET REAL? 0497 SLS BLOCK 1 CONFIGURATION Launch Abort System (LAS) Utah, Alabama, Florida Orion Stage Adapter, California, Alabama Orion Multi-Purpose Crew Vehicle RL10 Engine Lockheed Martin, 5 Segment Solid Rocket Aerojet Rocketdyne, Louisiana, KSC Florida Booster (2) Interim Cryogenic Northrop Grumman, Propulsion Stage (ICPS) Utah, KSC Boeing/United Launch Alliance, California, Alabama Launch Vehicle Stage Adapter Teledyne Brown Engineering, California, Alabama Core Stage & Avionics Boeing Louisiana, Alabama RS-25 Engine (4) -
The Army's New Multiple Rocket Launcher-A Shining Example of A
The Army's New Multiple Rocket Launcher-A Shining Example of a Weapon That Works The military forces of the United States and its NATO partners have no hope nor intention of matching the Warsaw Pact gun-for-gun or tank for-tank. Instead we and our allies plan to rely from the onset of hostil ities in Europe on tactics and weapons which would blunt the initial attack and deliver a knockout blow to the Soviet second echelon forces before they could exploit any initial success. To give our Army the wherewithal to fight a numerically superior foe and win, we have organized and trained balanced ground fighting forces capable of successful combat against any army in the world. Of equal import, we are providing our soldiers with the weap ons and equipment to exhibit a credi ble deterrence to war-armaments like the M1 Abrams tank and its compan ion, the Bradley infantry fighting ve hicle, the AH-64 Apache attack heli copter and the UH -60 utility helicopter. In addition the Army is quietly field ing another new system that could provide the firepower edge our sol diers need. That weapon is the Multi ple Launch Rocket System (MLRS), and it is described by the general in charge of Army research and develop ment as "the best piece of equipment that we have fielded for close support of the battlefield since World War II." The MLRS is a highly reliable, ex tremely accurate field artillery rocket system with which three soldiers can deliver the volume of firepower that would normally require nearly a bat talion of heavy artillery. -
Delta IV Parker Solar Probe Mission Booklet
A United Launch Alliance (ULA) Delta IV Heavy what is the source of high-energy solar particles. MISSION rocket will deliver NASA’s Parker Solar Probe to Parker Solar Probe will make 24 elliptical orbits an interplanetary trajectory to the sun. Liftoff of the sun and use seven flybys of Venus to will occur from Space Launch Complex-37 at shrink the orbit closer to the sun during the Cape Canaveral Air Force Station, Florida. NASA seven-year mission. selected ULA’s Delta IV Heavy for its unique MISSION ability to deliver the necessary energy to begin The probe will fly seven times closer to the the Parker Solar Probe’s journey to the sun. sun than any spacecraft before, a mere 3.9 million miles above the surface which is about 4 OVERVIEW The Parker percent the distance from the sun to the Earth. Solar Probe will At its closest approach, Parker Solar Probe will make repeated reach a top speed of 430,000 miles per hour journeys into the or 120 miles per second, making it the fastest sun’s corona and spacecraft in history. The incredible velocity trace the flow of is necessary so that the spacecraft does not energy to answer fall into the sun during the close approaches. fundamental Temperatures will climb to 2,500 degrees questions such Fahrenheit, but the science instruments will as why the solar remain at room temperature behind a 4.5-inch- atmosphere is thick carbon composite shield. dramatically Image courtesy of NASA hotter than the The mission was named in honor of Dr. -
Protecting Commercial Aviation Against the Shoulder-Fired Missile
INFRASTRUCTURE, SAFETY, AND ENVIRONMENT THE ARTS This PDF document was made available from www.rand.org as a public CHILD POLICY service of the RAND Corporation. CIVIL JUSTICE EDUCATION Jump down to document ENERGY AND ENVIRONMENT 6 HEALTH AND HEALTH CARE INTERNATIONAL AFFAIRS The RAND Corporation is a nonprofit research NATIONAL SECURITY POPULATION AND AGING organization providing objective analysis and effective PUBLIC SAFETY solutions that address the challenges facing the public SCIENCE AND TECHNOLOGY and private sectors around the world. SUBSTANCE ABUSE TERRORISM AND HOMELAND SECURITY TRANSPORTATION AND INFRASTRUCTURE Support RAND WORKFORCE AND WORKPLACE Browse Books & Publications Make a charitable contribution For More Information Visit RAND at www.rand.org Explore RAND Infrastructure, Safety, and Environment View document details Limited Electronic Distribution Rights This document and trademark(s) contained herein are protected by law as indicated in a notice appearing later in this work. This electronic representation of RAND intellectual property is provided for non- commercial use only. Permission is required from RAND to reproduce, or reuse in another form, any of our research documents for commercial use. This product is part of the RAND Corporation occasional paper series. RAND occasional papers may include an informed perspective on a timely policy issue, a discussion of new research methodologies, essays, a paper presented at a conference, a conference summary, or a summary of work in progress. All RAND occasional papers -
Rebel Forces in Northern Mali
REBEL FORCES IN NORTHERN MALI Documented weapons, ammunition and related materiel April 2012-March 2013 Co-published online by Conflict Armament Research and the Small Arms Survey © Conflict Armament Research/Small Arms Survey, London/Geneva, 2013 First published in April 2013 All rights reserved. No part of this publication may be reproduced, stored in a retrieval system, or transmitted in any form or by any means without the prior permission in writing of Conflict Armament Research and the Small Arms Survey, or as expressly permitted by law, or under terms agreed with the appropriate reprographics rights organisation. Enquiries concerning reproduction outside the scope of the above should be sent to the secretary, Conflict Armament Research ([email protected]) or the secretary, Small Arms Survey ([email protected]). Copy-edited by Alex Potter ([email protected]) Reviewed by Alex Diehl and Nic Jenzen-Jones Cover image: © Joseph Penny, 2013 Above image: Design and layout by Julian Knott (www.julianknott.com) © Richard Valdmanis, 2013 TABLE OF CONTENTS About 4 3.7 M40 106 mm recoilless gun 11 Abbreviations and acronyms 5 4. Light Weapons Ammunition 12 Introduction 6 4.1 12.7 x 108 mm ammunition 12 4.2 14.5 x 115 mm ammunition 12 1. Small Arms 7 4.3 PG-7 rockets 13 1.1 Kalashnikov-pattern 7.62 x 39 mm assault 4.4 OG-82 and PG-82 rockets 13 rifles 7 4.5 82 mm mortar bombs 14 1.2 FN FAL-pattern 7.62 x 51 mm rifle 7 4.6 120 mm mortar bombs 14 1.3 G3-pattern 7.62 x 51 mm rifle 7 4.7 Unidentified nose fuzes 14 1.4 MAT-49 9 x 19 mm sub-machine gun 7 4.8 F1-pattern fragmentation grenades 15 1.5 RPD-pattern 7.62 x 39 mm light 4.9 NR-160 106 mm HEAT projectiles 15 machine gun 7 1.6 PK-pattern 7.62 x 54R mm general-purpose 5. -
Development of a 10 Kn LOX/HTPB Hybrid Rocket Engine Through Successive Development and Testing of Scaled Prototypes
DOI: 10.13009/EUCASS2017-334 7TH EUROPEAN CONFERENCE FOR AERONAUTICS AND AEROSPACE SCIENCES (EUCASS) Development of a 10 kN LOX/HTPB Hybrid Rocket Engine through Successive Development and Testing of Scaled Prototypes Maximilian Bambauer and Markus Brandl WARR (TUM) c/o TUM Lehrstuhl für Raumfahrttechnik Boltzmannstraße 15 D-85748 Garching bei München [email protected] [email protected] · Abstract The development of a hybrid flight engine for a sounding rocket requires intensive preparation work and pretests. To obtain better understanding of the difficulties in design and operation that occur with LOX/HTPB rocket engines, four rocket engines with increasing size and thrust level are successively developed and manufactured. Listed chronologically, those engines are the demonstrator engine, the sub- scale engine with a cylindrical grain geometry and later a star shaped geometry, the full-scale test engine and the full-scale flight version. At first a small-scale technology demonstrator was developed. It pro- duced a mean thrust of 160N for 5s and had the purpose to validate the design calculations and to gain first experiences with the use of cryogenic propellants, especially regarding cooldown procedures. Based on this test results the so-called sub-scale engine was developed and tested. The engine can be operated with two grain configurations, using either a cylindrical grain or a star shaped grain. The star shaped grain geometries are realized, using an additive manufactured core, outside of which the HTPB is casted. In the low thrust configuration, the engine is operated using a cylindrical single port HTPB grain and it produces a thrust of about 540 N for a duration of 10 s. -
Fighting Vehicle Technology
Fighting Vehicle Technology 41496_DSTA 60-77#150Q.indd 1 5/6/10 12:44 AM ABSTRACT Armoured vehicle technology has evolved ever since the first tanks appeared in World War One. The traditional Armoured Fighting Vehicle (AFV) design focuses on lethality, survivability and mobility. However, with the growing reliance on communications and command (C2) systems, there is an increased need for the AFV design to be integrated with the vehicle electronics, or vetronics. Vetronics has become a key component of the AFV’s effectiveness on the battlefield. An overview of the technology advances in these areas will be explored. In addition, the impact on the human aspect as a result of these C2 considerations will be covered. Tan Chuan-Yean Mok Shao Hong Vince Yew 41496_DSTA 60-77#150Q.indd 2 5/6/10 12:44 AM Fighting Vehicle Technology 62 and more advanced sub-systems will raise the INTRODUCTION question of how the modern crew is able to process and use the information effectively. On the modern battlefield, armies are moving towards Network-Centric Warfare TECHNOLOGIES IN AN (NCW). Forces no longer fight as individual entities but as part of a larger system. Each AFV entity becomes a node in a network where information can be shared, and firepower can Firepower be called upon request. AFVs are usually equipped with weapon Key to this network fighting capability is the stations for self-protection and the communications and command (C2) system. engagement of targets. Depending on By enabling each force to be plugged into the threat, some are equipped with pintle the C2 system, information can be shared mount systems for light weapons (e.g. -
IB-220 Appraisal-Of-PLA-Artillery
D W LAN ARFA CENTRE FOR LAND WARFARE STUDOR RE IES F S E T R U T D N IE E S C CLAWS VI CT N O SIO 31 CLAWS RY VI D W THROUGH LAN ARFA OR RE F S E T R U T D N IE E S C CLAWS VI CT N OR ISIO Y THROUGH V ISSUE BRIEF No. 220 April 2020 Brig Vivek Verma is Former Deputy Director, Appraisal of Centre for Land Warfare Studies and Senior D W Research Fellow, USI of India, New Delhi. LAN ARFA PLA ArtilleryOR RE F S ModernisationE T R U T D Trigger forN China’s Artillery Modernisation IE China hasE been closely monitoring American Key Points S and RussianC doctrinal and weapon modernisation programmes. It is looking to counter them through either asymmetric means or by building matching capabilities. 1. 2014 Russo-Ukrainian conflict demonstrated Hu Jintao initiated the “New Historic effectiveness of artillery in a hostile electronic Missions” in 2004 based on the lessons of environment. foreign intervention during 1995-96 Taiwan- 2. It reaffirmed Chinese artillery development plan Strait crisis and 2003 Gulf War. The mission as it realised that it can outgun the US military, its directed People’s Liberation Army (PLA) to peer competitor, in this area. develop a range of systems to deter and deny foreign force projections. The 2019 white paper 3. Taiwan and Tibet contingencies form the basis of on “China’s National Defence in New Era” PLA artillery modernisation drive. talks about preparation for military struggle 4. -
The Delta Launch Vehicle- Past, Present, and Future
The Space Congress® Proceedings 1981 (18th) The Year of the Shuttle Apr 1st, 8:00 AM The Delta Launch Vehicle- Past, Present, and Future J. K. Ganoung Manager Spacecraft Integration, McDonnell Douglas Astronautics Co. H. Eaton Delta Launch Program, McDonnell Douglas Astronautics Co. Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Ganoung, J. K. and Eaton, H., "The Delta Launch Vehicle- Past, Present, and Future" (1981). The Space Congress® Proceedings. 7. https://commons.erau.edu/space-congress-proceedings/proceedings-1981-18th/session-6/7 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. THE DELTA LAUNCH VEHICLE - PAST, PRESENT AND FUTURE J. K. Ganoung, Manager H. Eaton, Jr., Director Spacecraft Integration Delta Launch Program McDonnell Douglas Astronautics Co. McDonnell Douglas Astronautics Co. INTRODUCTION an "interim space launch vehicle." The THOR was to be modified for use as the first stage, the The Delta launch vehicle is a medium class Vanguard second stage propulsion system, was used expendable booster managed by the NASA Goddard as the Delta second stage and the Vanguard solid Space Flight Center and used by the U.S. rocket motor became Delta's third stage. Government, private industry and foreign coun Following the eighteen month development program tries to launch scientific, meteorological, and failure to launch its first payload into or applications and communications satellites.