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Vulcan Centaur
VULCAN CENTAUR The Vulcan Centaur rocket design leverages the flight-proven success of the Delta IV and Atlas V launch vehicles while introducing new technologies and innovative features to ensure a reliable and aordable space launch service. Vulcan Centaur will service a diverse range of markets including 225 ft commercial, civil, science, cargo and national security space customers. 1 The spacecraft is encapsulated in a 5.4-m- (17.7-ft-) diameter payload fairing (PLF), a sandwich composite structure made with a vented aluminum-honeycomb core and graphite-epoxy face sheets. The bisector (two-piece shell) PLF encapsulates the spacecraft. The payload attach fitting (PAF) is a similar sandwich composite structure creating the mating interface from spacecraft to second stage. The PLF separates using a debris-free horizontal and vertical separation system with 2 200 ft spring packs and frangible joint assembly. The payload fairing is available in the 15.5-m (51-ft) standard and 21.3-m (70-ft) 1 long configurations. The Centaur upper stage is 5.4 m (17.7 ft) in diameter and 3 11.7 m (38.5 ft) long with a 120,000-lb propellant capacity. Its propellant tanks are constructed of pressure-stabilized, corrosion-resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen-fueled vehicle, with two RL10C 4 engines. The Vulcan Centaur Heavy vehicle, flies the upgraded 2 Centaur using RL10CX engines with nozzle extensions. The 5 175 ft cryogenic tanks are insulated with spray-on foam insulation (SOFI) to manage boil o of cryogens during flight. An aft equipment shelf provides the structural mountings for vehicle electronics. -
Sns College of Technology
SNS COLLEGE OF TECHNOLOGY (An Autonomous Institution) DEPARTMENT OF AERONAUTICAL ENGINEERING Subject Code & Name: 16AE409 ROCKETS AND MISSILES Date: 16.08.19 DAY: 01 UNIT: 4: STAGING OF ROCKETS AND MISSILES TOPIC: 1: TWO MARK QUESTION & ANSWER 1. Define multistage rocket. A multistage (or) multistep rocket is a series of individual vehicles or stages each with its own structure, tanks and engines. The stages are so connected that each operates in turn accelerating the remaining stages and the payload before being detached from them. 2. Nomenclature of the multistage rocket. 3. Write the different types of stage separation techniques. 1. By helical compression springs 2. By short duration solid propellant rockets. 4. Separation of stages with in the atmosphere The burnout of the first stage generally occurs within the upper region of the atmosphere i) Firing in the hole technique ii) Ullage rocket techniques. 5. Advantages of Multistage rocket design. Higher payload Enough to accelerate the initial mass Long-range Easy thrust programming K.NEHRU, M.Tech.,(Ph.D) Assistant Professor 16AE409 ROCKETS AND MISSILES 6. Write the expression for sub rocket 1 and (i+1). Sub rocket 1 = Complete rocket Sub rocket (i+1) = sub rocketi - stagei 7. Write the expression for payload of sub rocket 1 and N. Payload sub rocket i = Sub rocket (i+1) Payload sub rocket N = Actual payload 8. Sketch the thrust to time variation graph of stage separation techniques. i) Firing in the hole technique i) Ullage rocket techniques. 9. Drawbacks of firing in the hole techniques. K.NEHRU, M.Tech.,(Ph.D) Assistant Professor 16AE409 ROCKETS AND MISSILES 1. -
Semi Cryogenic Technology for Gaganyaan: RSTV – in Depth
Semi Cryogenic Technology for Gaganyaan: RSTV – In Depth Anchor: Teena Jha Context: India's strategic partner Russia has offered its Semi Cryogenic engine technology and critical components for the Gaganyaan project. Gaganyaan: In 2018, India’s first manned space mission was announced by Prime Minister Narendra Modi in his Independence Day speech. Gaganyaan will be the Indian crewed orbital spacecraft intended to be the basis of Indian Human Space Flight Program. With Gaganyaan, India will become only the 4th country after Russia, the USA and China to send humans to space. It will be ISRO’s next big project after the anticipated soft landing of Chandrayaan 2 on the lunar The target is to launch it before the 75 year celebration of India’s independence. Before the manned mission scheduled for December 2021, two unmanned tests will be carried out in December 2020 and July 2021. ISRO’s indigenous mission will be assisted by few other countries in selecting and training astronauts. According to ISRO, a budget of Rs 10,000 Cr. has been set aside for putting the infrastructure in place. It is described as a national mission than an ISRO mission. The Spacecraft: The spacecraft will take 3 Indian astronauts, who will be known as ‘vyomnauts’ (in Sanskrit ‘vyom’ means space. It will circle the earth for 7 days from a distance of 300-400 km. It will be launched by India’s biggest rocket GSLV Mk 3 from Sriharikotta. The 7 ton spacecraft will orbit the earth at an altitude of 400km for up to 7 days. -
Rocket Nozzles: 75 Years of Research and Development
Sådhanå Ó (2021) 46:76 Indian Academy of Sciences https://doi.org/10.1007/s12046-021-01584-6Sadhana(0123456789().,-volV)FT3](0123456789().,-volV) Rocket nozzles: 75 years of research and development SHIVANG KHARE1 and UJJWAL K SAHA2,* 1 Department of Energy and Process Engineering, Norwegian University of Science and Technology, 7491 Trondheim, Norway 2 Department of Mechanical Engineering, Indian Institute of Technology Guwahati, Guwahati 781039, India e-mail: [email protected]; [email protected] MS received 28 August 2020; revised 20 December 2020; accepted 28 January 2021 Abstract. The nozzle forms a large segment of the rocket engine structure, and as a whole, the performance of a rocket largely depends upon its aerodynamic design. The principal parameters in this context are the shape of the nozzle contour and the nozzle area expansion ratio. A careful shaping of the nozzle contour can lead to a high gain in its performance. As a consequence of intensive research, the design and the shape of rocket nozzles have undergone a series of development over the last several decades. The notable among them are conical, bell, plug, expansion-deflection and dual bell nozzles, besides the recently developed multi nozzle grid. However, to the best of authors’ knowledge, no article has reviewed the entire group of nozzles in a systematic and comprehensive manner. This paper aims to review and bring all such development in one single frame. The article mainly focuses on the aerodynamic aspects of all the rocket nozzles developed till date and summarizes the major findings covering their design, development, utilization, benefits and limitations. -
Status of the Space Shuttle Solid Rocket Booster
The Space Congress® Proceedings 1980 (17th) A New Era In Technology Apr 1st, 8:00 AM Status of The Space Shuttle Solid Rocket Booster William P. Horton Solid Rocket Booster Engineering Office, George C. Marshall Space Flight Center, Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Horton, William P., "Status of The Space Shuttle Solid Rocket Booster" (1980). The Space Congress® Proceedings. 3. https://commons.erau.edu/space-congress-proceedings/proceedings-1980-17th/session-1/3 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]. STATUS OF THE SPACE SHUTTLE SOLID ROCKET BOOSTER William P. Horton, Chief Engineer Solid Rocket Booster Engineering Office George C. Marshall Space Flight Center, AL 35812 ABSTRACT discuss retrieval and refurbishment plans for Booster reuse, and will address Booster status Two Solid Rocket Boosters provide the primary for multimission use. first stage thrust for the Space Shuttle. These Boosters, the largest and most powerful solid rocket vehicles to meet established man- BOOSTER CONFIGURATION rated design criteria, are unique in that they are also designed to be recovered, refurbished, It is appropriate to review the Booster config and reused. uration before describing the mission profile. The Booster is 150 feet long and is 148 inches The first SRB f s have been stacked on the in diameter (Figure 1), The inert weight Mobile Launch Platform at the Kennedy Space is 186,000 pounds and the propellant weight is Center and are ready to be mated with the approximately 1.1 million pounds for each External Tank and Orbiter in preparation for Booster. -
Atlas V Cutaway Poster
ATLAS V Since 2002, Atlas V rockets have delivered vital national security, science and exploration, and commercial missions for customers across the globe including the U.S. Air Force, the National Reconnaissance Oice and NASA. 225 ft The spacecraft is encapsulated in either a 5-m (17.8-ft) or a 4-m (13.8-ft) diameter payload fairing (PLF). The 4-m-diameter PLF is a bisector (two-piece shell) fairing consisting of aluminum skin/stringer construction with vertical split-line longerons. The Atlas V 400 series oers three payload fairing options: the large (LPF, shown at left), the extended (EPF) and the extra extended (XPF). The 5-m PLF is a sandwich composite structure made with a vented aluminum-honeycomb core and graphite-epoxy face sheets. The bisector (two-piece shell) PLF encapsulates both the Centaur upper stage and the spacecraft, which separates using a debris-free pyrotechnic actuating 200 ft system. Payload clearance and vehicle structural stability are enhanced by the all-aluminum forward load reactor (FLR), which centers the PLF around the Centaur upper stage and shares payload shear loading. The Atlas V 500 series oers 1 three payload fairing options: the short (shown at left), medium 18 and long. 1 1 The Centaur upper stage is 3.1 m (10 ft) in diameter and 12.7 m (41.6 ft) long. Its propellant tanks are constructed of pressure-stabilized, corrosion-resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen-fueled vehicle. It uses a single RL10 engine producing 99.2 kN (22,300 lbf) of thrust. -
GSLV Mk. II Launch Vehicle
Launch Vehicle Library Compiled by Patrick Blau GSLV Mk. II Launch Vehicle The Geosynchronous Satellite Launch Vehicle, better known by its abbreviation GSLV, is an Indian expendable launch system that was developed and is operated by the Indian Space Research Organization. The GSLV project was initiated back in the 1990s when India determined that it needed its own launch capability for Geosynchronous Satellites to become independent from other launch providers. At the time, India was relying on Russian/Soviet launch vehicles for heavy satellite launches. With the emergence of commercial launch providers, such as Arianespace, India shifted its GSO Satellites to those while GSLV was being developed. The launch system uses a large number of heritage components already employed on the Polar Satellite Launch Vehicle that first flew in 1993. The three-stage GSLV has an improved performance over four-stage PSLV with the addition of strap-on liquid-fueled boosters and a cryogenic upper stage. GSLV uses a combination of solid fueled, liquid-fueled and cryogenic stages. The vehicle weighs 414,000 Kilograms at liftoff standing 49 meters tall with a core diameter of 2.8 meters. The first stage is the S139 solid-fueled stage that is also used on PSLV. Around the core, four strap-on liquid-fueled boosters are mounted each featuring a Vikas engine using storable propellants. The second stage is also a storable propellant stage using a single modified Vikas engine while the third stage is a cryogenic stage using liquid Oxygen and liquid Hydrogen that is consumed by an ICE engine. The vehicle can deploy payloads of up to 2,500 Kilograms to a Geosynchronous Transfer Orbit, Low Earth Orbit Capability is 5,000kg. -
Abstract US Patent References
Architecture for Reusable Responsive Exploration Systems: ARES - Platform and Reusable Responsive Architecture for Innovative Space Exploration: PRAISE (Part 1) PATENT PENDING Abstract A comprehensive Modular Reusable Responsive Space Exploration Platform (Architecture) composed of multiple modular reusable elements such that the assemblies can be flexibly configured into systems for low earth orbits launches and for long-range exploration such as orbits to moon, Lagrange points and others. This platform & architecture is named as Architecture for Reusable Responsive Exploration System (acronym ARES) / Platform and Reusable Responsive Architecture for Innovative Space Exploration (acronym PRAISE), in short ARES/PRAISE or simply ARES. It is also known as Alpha Spaces Architecture and Platform (acronym ASAP), in short as “αPlatform” or “αArchitecture”, or “αAres”. As an example, the configuration involves reusable lightweight wing, core stage, (optional booster stages) combination of expendable upper stage and reusable crew capsule. Further, the expendable upper stage can be re-used to serve as in-orbit fuel depots and for other innovative uses. This is first part of the multi part patent application. Inventor: Atreya, Dinesh S. US Patent References US Patent 6158693 - Recoverable booster stage and recovery method US Patent 4878637 - Modular space station US Patent 6726154 - Reusable space access launch vehicle system US Patent 6113032 - Delivering liquid propellant in a reusable booster stage US Patent 4557444 - Aerospace vehicle US Patent 4880187 - Multipurpose modular spacecraft US Patent 4452412 - Space shuttle with rail system and aft thrust structure securing solid rocket boosters to external tank US Patent 4802639 - Horizontal-takeoff transatmospheric launch system US Patent 4884770 - Earth-to-orbit vehicle providing a reusable orbital stage US Patent 4265416 - Orbiter/launch system U.S. -
Space News Update – May 2019
Space News Update – May 2019 By Pat Williams IN THIS EDITION: • India aims to be 1st country to land rover on Moon's south pole. • Jeff Bezos says Blue Origin will land humans on moon by 2024. • China's Chang'e-4 probe resumes work for sixth lunar day. • NASA awards Artemis contract for lunar gateway power. • From airport to spaceport as UK targets horizontal spaceflight. • Russian space sector plagued by astronomical corruption. • Links to other space and astronomy news published in May 2019. Disclaimer - I claim no authorship for the printed material; except where noted (PW). INDIA AIMS TO BE 1ST COUNTRY TO LAND ROVER ON MOON'S SOUTH POLE India will become the first country to land a rover on the Moon's the south pole if the country's space agency "Indian Space Research Organisation (ISRO)" successfully achieves the feat during the country's second Moon mission "Chandrayaan-2" later this year. "This is a place where nobody has gone. All the ISRO missions till now to the Moon have landed near the Moon's equator. Chandrayaan-2, India’s second lunar mission, has three modules namely Orbiter, Lander (Vikram) & Rover (Pragyan). The Orbiter and Lander modules will be interfaced mechanically and stacked together as an integrated module and accommodated inside the GSLV MK-III launch vehicle. The Rover is housed inside the Lander. After launch into earth bound orbit by GSLV MK-III, the integrated module will reach Moon orbit using Orbiter propulsion module. Subsequently, Lander will separate from the Orbiter and soft land at the predetermined site close to lunar South Pole. -
The Annual Compendium of Commercial Space Transportation: 2017
Federal Aviation Administration The Annual Compendium of Commercial Space Transportation: 2017 January 2017 Annual Compendium of Commercial Space Transportation: 2017 i Contents 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 art: Phil Smith, The Tauri Group (2017) Publication produced for FAA AST by The Tauri Group under contract. 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. ii Annual Compendium of Commercial Space Transportation: 2017 GENERAL CONTENTS Executive Summary 1 Introduction 5 Launch Vehicles 9 Launch and Reentry Sites 21 Payloads 35 2016 Launch Events 39 2017 Annual Commercial Space Transportation Forecast 45 Space Transportation Law and Policy 83 Appendices 89 Orbital Launch Vehicle Fact Sheets 100 iii Contents DETAILED CONTENTS EXECUTIVE SUMMARY . -
Evolved Expendable Launch Operations at Cape Canaveral, 2002-2009
EVOLVED EXPENDABLE LAUNCH OPERATIONS AT CAPE CANAVERAL 2002 – 2009 by Mark C. Cleary 45th SPACE WING History Office PREFACE This study addresses ATLAS V and DELTA IV Evolved Expendable Launch Vehicle (EELV) operations at Cape Canaveral, Florida. It features all the EELV missions launched from the Cape through the end of Calendar Year (CY) 2009. In addition, the first chapter provides an overview of the EELV effort in the 1990s, summaries of EELV contracts and requests for facilities at Cape Canaveral, deactivation and/or reconstruction of launch complexes 37 and 41 to support EELV operations, typical EELV flight profiles, and military supervision of EELV space operations. The lion’s share of this work highlights EELV launch campaigns and the outcome of each flight through the end of 2009. To avoid confusion, ATLAS V missions are presented in Chapter II, and DELTA IV missions appear in Chapter III. Furthermore, missions are placed in three categories within each chapter: 1) commercial, 2) civilian agency, and 3) military space operations. All EELV customers employ commercial launch contractors to put their respective payloads into orbit. Consequently, the type of agency sponsoring a payload (the Air Force, NASA, NOAA or a commercial satellite company) determines where its mission summary is placed. Range officials mark all launch times in Greenwich Mean Time, as indicated by a “Z” at various points in the narrative. Unfortunately, the convention creates a one-day discrepancy between the local date reported by the media and the “Z” time’s date whenever the launch occurs late at night, but before midnight. (This proved true for seven of the military ATLAS V and DELTA IV missions presented here.) In any event, competent authorities have reviewed all the material presented in this study, and it is releasable to the general public. -
Make the Most of Destination Moon
Challenger Center® and NASA eClips™ Make the Most of Destination Moon PRE-MISSION ASTRONAUT TRAINING (~30 MIN) Prepare your class of Astronauts for a richer virtual mission experience by helping them learn more about mapping, tracking and structure, and engines before the mission. Mapping Tracking and Structure Engines Divide the group into teams of three. Each person in the group will watch a different NASA eClips™ video or listen to the Innovation Now podcast to become an expert on one of the three topics. Mapping Experts Tracking and Structure Engine Experts Real World: Lunar Innovation Now: Launchpad: Apollo 11 - Reconnaissance Orbiter Weather or Not to Challenges of Landing on the Resources Launch Moon • Why is returning to • Why is it important • What criteria should be the Moon important? to conduct weather considered for determining What kinds of checks prior to a landing site? questions can we launch? • Why would landing in a answer through • What conditions crater have presented establishing a could affect a problems for the Apollo Essential launch and must be questions “sustainable astronauts? presence” there? considered? guide experts • How have we built as they watch our understanding of their video. the Moon? • What kinds of tests must scientists and engineers conduct to know a spacecraft is ready for launch? AFTER • How has the Lunar • What is a “Go / No • How did the Apollo viewing the Reconnaissance Go” Poll? astronauts help make a • What are some “do return to the Moon video, experts Orbiter been able to not launch” criteria possible? report map the Moon? that might scrub a findings to • Why was an orbiter the right spacecraft launch? their team.