Turbojet Runs Precursor to Hypersonic Engine Heat Exchanger Tests
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Module 1: Hypersonic Atmosphere Lecture1: Characteristics of Hypersonic Atmosphere
NPTEL –Aerospace Module 1: Hypersonic Atmosphere Lecture1: Characteristics of Hypersonic Atmosphere 1.1 Introduction Hypersonic flight has special traits, some of which are seen in every hypersonic flight. Presence of these particular features during a flight is highly dependant on type of trajectory, configuration etc. In short it is the mission requirement which decides the nature of hypersonic atmosphere encountered by the flight vehicle. Some missions are designed for high deceleration in outer atmosphere during reentry. Hence, those flight vehicles experience longer flight duration at high angle of attacks due to which blunt nosed configuration are generally preferred for such aircrafts. On the contrary, some missions are centered on low flight duration with major deceleration closer to earth surface hence these vehicles have sharp nose and low angle of attack flights. Reentry flight path of hypersonic vehicle is thus governed by the parameters called as ballistic parameter and lifting parameter. These parameters are obtained by applying momentum conservation equation in the direction of the flight path and normal to it. Velocity-altitude map of the flight is thus made from the knowledge of these governing flight parameters, weight and surface area. Ballistic parameter is considered for non lifting reentry flights like flight path of Apollo capsule, however lifting parameter is considered for lifting reentry trajectories like that of space shuttle. Therefore hypersonic flight vehicles are classified in four different types based on the design constraints imposed from mission specifications. 1. Reentry Vehicles (RV): These vehicles are typically launched using rocket propulsion system. Reentry of these vehicles is controlled by control surfaces. -
Notes on Earth Atmospheric Entry for Mars Sample Return Missions
NASA/TP–2006-213486 Notes on Earth Atmospheric Entry for Mars Sample Return Missions Thomas Rivell Ames Research Center, Moffett Field, California September 2006 The NASA STI Program Office . in Profile Since its founding, NASA has been dedicated to the • CONFERENCE PUBLICATION. Collected advancement of aeronautics and space science. The papers from scientific and technical confer- NASA Scientific and Technical Information (STI) ences, symposia, seminars, or other meetings Program Office plays a key part in helping NASA sponsored or cosponsored by NASA. maintain this important role. • SPECIAL PUBLICATION. Scientific, technical, The NASA STI Program Office is operated by or historical information from NASA programs, Langley Research Center, the Lead Center for projects, and missions, often concerned with NASA’s scientific and technical information. The subjects having substantial public interest. NASA STI Program Office provides access to the NASA STI Database, the largest collection of • TECHNICAL TRANSLATION. English- aeronautical and space science STI in the world. language translations of foreign scientific and The Program Office is also NASA’s institutional technical material pertinent to NASA’s mission. mechanism for disseminating the results of its research and development activities. These results Specialized services that complement the STI are published by NASA in the NASA STI Report Program Office’s diverse offerings include creating Series, which includes the following report types: custom thesauri, building customized databases, organizing and publishing research results . even • TECHNICAL PUBLICATION. Reports of providing videos. completed research or a major significant phase of research that present the results of NASA For more information about the NASA STI programs and include extensive data or theoreti- Program Office, see the following: cal analysis. -
Performances of a Small Hypersonic Airplane (Hyplane)
Politecnico di Torino Porto Institutional Repository [Proceeding] PERFORMANCES OF A SMALL HYPERSONIC AIRPLANE (HYPLANE) Original Citation: Savino R.; Russo G.; D’Oriano V.; Visone M.; Battipede M.; Gili P. (2014). PERFORMANCES OF A SMALL HYPERSONIC AIRPLANE (HYPLANE). In: 65th International Astronautical Congress„ Toronto, Canada, 29 September - 3 October 2014. pp. 1-13 Availability: This version is available at : http://porto.polito.it/2591763/ since: February 2015 Publisher: International Astronautical Federation (IAF) Terms of use: This article is made available under terms and conditions applicable to Open Access Policy Article ("Public - All rights reserved") , as described at http://porto.polito.it/terms_and_conditions. html Porto, the institutional repository of the Politecnico di Torino, is provided by the University Library and the IT-Services. The aim is to enable open access to all the world. Please share with us how this access benefits you. Your story matters. (Article begins on next page) 65th International Astronautical Congress, Toronto, Canada. Copyright ©2014 by the Authors. Published by the IAF, with permission and released to the IAF to publish in all forms. IAC-14-D2.4 PERFORMANCES OF A SMALL HYPERSONIC AIRPLANE (HYPLANE) Raffaele Savino Department of Industrial Engineering, University of Naples “Federico II”, Italy Gennaro Russo Trans-Tech srl and Space Renaissance Italia, Italy Vera D’Oriano*, Michele Visone Blue Engineering, Italy Manuela Battipede, Piero Gili Department of Mechanical and Aerospace Engineering, Polytechnic of Turin, Italy In the present work a preliminary performance study regarding a small hypersonic airplane named HyPlane is presented. It is designed for long duration sub-orbital space tourism missions, in the frame of the Space Renaissance (SR) Italia Space Tourism Program. -
Getting Shipshape
AER October 2020 OSPACE DOES AEROSPACE HAVE A RACE PROBLEM? SECRETS FROM THE FALKLANDS AIR WAR POWERING UP ELECTRIC FLIGHT www.aerosociety.com October 2020 GETTING SHIPSHAPE Volume 47 Number 10 Volume UK F-35B FORCE GETS READY FOR FIRST OPERATIONAL CARRIER DEPLOYMENT Royal AeronauticaSociety OCTOBER 2020 AEROSPACE COVER FINAL.indd 1 18/09/2020 14:59 RAeS 2020 Virtual Conference Programme Join us from wherever you are in the world to experience high quality, informative content. Book early for our special introductory offer rates. STRUCTURES & MATERIALS UAS / ROTORCRAFT / AIR TRANSPORT GREENER BY DESIGN 7th Aircraft Structural Urban Air Mobility RAeS Climate Change Design Conference Conference 2020 Conference 2020 DATE NEW DATE DATE 8 October 22 - 23 October 3 - 4 November TIME TIME TIME 14:00 - 17:00 13:00 - 18:00 13:00 - 18:00 SCAN USING SCAN USING SCAN USING YOUR PHONE YOUR PHONE YOUR PHONE FOR MORE INFO FOR MORE INFO FOR MORE INFO Embark on your virtual learning journey with the RAeS Connect and interact with our speakers and ask questions live Engage and network with other professionals from across the world Meet our sponsors at our virtual exhibitor booths Access content post-event to continue your professional development For the full virtual conference programme and further details on what to expect visit aerosociety.com/VCP Volume 47 Number 10 October 2020 EDITORIAL Contents When global rules unravel Regulars 4 Radome 12 Transmission What price global standards, rules and regulations? Pre-pandemic there were The latest aviation and Your letters, emails, tweets aeronautical intelligence, and social media feedback. -
The SKYLON Spaceplane
The SKYLON Spaceplane Borg K.⇤ and Matula E.⇤ University of Colorado, Boulder, CO, 80309, USA This report outlines the major technical aspects of the SKYLON spaceplane as a final project for the ASEN 5053 class. The SKYLON spaceplane is designed as a single stage to orbit vehicle capable of lifting 15 mT to LEO from a 5.5 km runway and returning to land at the same location. It is powered by a unique engine design that combines an air- breathing and rocket mode into a single engine. This is achieved through the use of a novel lightweight heat exchanger that has been demonstrated on a reduced scale. The program has received funding from the UK government and ESA to build a full scale prototype of the engine as it’s next step. The project is technically feasible but will need to overcome some manufacturing issues and high start-up costs. This report is not intended for publication or commercial use. Nomenclature SSTO Single Stage To Orbit REL Reaction Engines Ltd UK United Kingdom LEO Low Earth Orbit SABRE Synergetic Air-Breathing Rocket Engine SOMA SKYLON Orbital Maneuvering Assembly HOTOL Horizontal Take-O↵and Landing NASP National Aerospace Program GT OW Gross Take-O↵Weight MECO Main Engine Cut-O↵ LACE Liquid Air Cooled Engine RCS Reaction Control System MLI Multi-Layer Insulation mT Tonne I. Introduction The SKYLON spaceplane is a single stage to orbit concept vehicle being developed by Reaction Engines Ltd in the United Kingdom. It is designed to take o↵and land on a runway delivering 15 mT of payload into LEO, in the current D-1 configuration. -
Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft Through Parametric Studies
energies Article Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft through Parametric Studies Andrew Ridgway, Ashish Alex Sam * and Apostolos Pesyridis College of Engineering, Design and Physical Sciences, Brunel University London, London UB8 3PH, UK; [email protected] (A.R.); [email protected] (A.P.) * Correspondence: [email protected]; Tel.: +44-1895-267-901 Received: 26 September 2018; Accepted: 7 December 2018; Published: 10 December 2018 Abstract: This paper aims to contribute to developing a potential combined cycle air-breathing engine integrated into an aircraft design, capable of performing flight profiles on a commercial scale. This study specifically focuses on the single expansion ramp nozzle (SERN) and aircraft-engine integration with an emphasis on the combined cycle engine integration into the conceptual aircraft design. A parametric study using computational fluid dynamics (CFD) have been employed to analyze the sensitivity of the SERN’s performance parameters with changing geometry and operating conditions. The SERN adapted to the different operating conditions and was able to retain its performance throughout the altitude simulated. The expansion ramp shape, angle, exit area, and cowl shape influenced the thrust substantially. The internal nozzle expansion and expansion ramp had a significant effect on the lift and moment performance. An optimized SERN was assembled into a scramjet and was subject to various nozzle inflow conditions, to which combustion flow from twin strut injectors produced the best thrust performance. Side fence studies observed longer and diverging side fences to produce extra thrust compared to small and straight fences. Keywords: scramjet; single expansion ramp nozzle; hypersonic aircraft; combined cycle engines 1. -
Scramjet Nozzle Design and Analysis As Applied to a Highly Integrated Hypersonic Research Airplane
NASA TECHN'ICAL NOTE NASA D-8334 d- . ,d d K a+ 4 c/) 4 z SCRAMJET NOZZLE DESIGN AND ANALYSIS AS APPLIED TO A HIGHLY INTEGRATED HYPERSONIC RESEARCH AIRPLANE Wi'llidm J. Smull, John P. Wehher, and P. J. Johnston i Ldngley Reseurch Center Humpton, Va. 23665 / NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. c. .'NOVEMBER 1976 TECH LIBRARY KAFB, NM I Illill 111 lllll11Il1 lllll lllll lllll IIll ~~ ~~- - 1. Report No. 2. Government Accession No. -. ___r_- --.-= .--. NASA TN D-8334 I ~~ 4. Title and ,Subtitle 5. Report Date November 1976 7. Author(sl 8. Performing Organization Report No. William J. Small, John P. Weidner, L-11003 and P. J. Johnston . ~ ~-.. ~ 10. Work Unit No. 9. Performing Organization Nwne and Address 505-11-31-02 NASA Langley Research Center 11. Contract or Grant No. Hampton, VA 23665 13. Type of Report and Period Covered ,. 12. Sponsoring Agency Name and Address Technical Note National Aeronautics and Space Administration 14. Sponsoring Agency Code Washington, DC 20546 -. I 15. Supplementary Notes -~ 16. Abstract The great potential expected from future air-breathing hypersonic aircraft systems is predicated on the assumption that the propulsion system can be effi- ciently integrated with the airframe. A study of engine-nozzle airframe inte- gration at hypersonic speeds has been conducted by using a high-speed research- aircraft concept as a focus. Recently developed techniques for analysis of scramjet-nozzle exhaust flows provide a realistic analysis of complex forces resulting from the engine-nozzle airframe coupling. Results from these studies show that by properly integrating the engine-nozzle propulsive system with the airframe, efficient, controlled and stable flight results over a wide speed range. -
Royal Aeronautical Society Award Winners 2020
Royal Aeronautical Society T: +44 (0)20 7670 4300 No. 4 Hamilton Place E: [email protected] London W1J 7BQ www.aerosociety.com United Kingdom PRESS RELEASE FOR IMMEDIATE RELEASE 30 November 2020 ROYAL AERONAUTICAL SOCIETY AWARD WINNERS 2020 The Royal Aeronautical Society is proud to announce the 2020 winners of the global aerospace community’s most prestigious and long-standing awards honouring achievement and innovation. The virtual celebration, held 23-28 November, saw leaders in aviation, aerospace and space recognised for their significant contributions from space innovation to supporting humanitarian aid and addressing social barriers through flight. Several representatives of the space industry received awards, with Dr Alice Bunn and Dr Ashitey Trebi-Ollennu receiving Silver Award Medals for their major contributions. Dr Bunn for her role in developing and implementing UK Space Policy and Dr Trebi-Ollennu for his contribution to the successful development and delivery of the Instrument Deployment System on the InSight Mars Mission. It enabled the first robotic deployment by NASA of a seismometer on another planet. Harbour Air Group founder, Greg McDougall received a Bronze award for establishing North America’s first carbon-neutral airline in 2007, which also facilitated the world’s first commercial electric flight in 2019. The Sir Ralph Robins Medal for mid-career engineers demonstrating outstanding engineering leadership, was won by Dr Helen Webber, for her achievements in delivering a major engineering project, leadership of a significant team, delivering a major new project and creating commercial success. Dr Webber was responsible for delivering the High Temperature Heat Exchanger (HTX) design, build and test programme conditions. -
Chap21 Rockets Fundamentals.Pdf
Chapter 21.indd 449 1/9/08 12:12:24 PM There is an explanation for everything that a rocket does. The explanation is most always based on the laws of physics and the nature of rocket propellants. Experimentation is required to find out whether a new rocket will or will not work. Even today, with all the knowledge and expertise that exists in the field of rocketry, experimentation occasionally shows that certain ideas are not practical. In this chapter, we will look back in time to the early developers and users of rocketry. We will review some of the physical laws that apply to rocketry, discuss selected chemicals and their combinations, and identify the rocket systems and their components. We also will look at the basics of rocket propellant efficiency. bjectives Explain why a rocket engine is called a reaction engine. Identify the country that first used the rocket as a weapon. Compare the rocketry advancements made by Eichstadt, Congreve and Hale. Name the scientist who solved theoretically the means by which a rocket could escape the earth’s gravitational field. Describe the primary innovation in rocketry developed by Dr. Goddard and Dr. Oberth. Explain the difference between gravitation and gravity. Describe the contributions of Galileo and Newton. Explain Newton’s law of universal gravitation. State Newton’s three laws of motion. Define force, velocity, acceleration and momentum. Apply Newton’s three laws of motion to rocketry. Identify two ways to increase the thrust of a rocket. State the function of the combustion chamber, the throat, and nozzle in a rocket engine. -
Hypersonic Air Intake Design for High Performance and Starting
Hypersonic Air Intake Design for High Performance and Starting Sannu Mölder, Evgeny Timofeev Department of Mechanical Engineering, McGill University 817 Sherbrooke St. W. Montreal, P.Q. CANADA [email protected] SUMMARY Hypersonic air intake performance is defined in terms of intake capability and efficiency. The propensity for intake flow starting is measured by the Startability Index – a parameter inversely related to capability that is shown to be a meaningful and convenient measure of the startability for a hypersonic air intake. It is shown that the basic Busemann flow is adaptable to the design of high-performance air intakes. Proper choice of the strength of the terminal shock yields high-performance, modular, intake shapes, with low internal contractions, that are capable of spontaneous starting with overboard mass spillage. Some practical designs and applications are presented. 1.0 INTRODUCTION Air-breathing aero-engines such as ramjets and scramjets, operating at supersonic and hypersonic speeds, ingest air through a converging air intake1. For both ramjets and scramjets at these speeds, convergence causes enough compression that no further mechanical compression is required before combustion. In a scramjet, the static temperature at combustor entry is high enough to cause the injected fuel to ignite spontaneously. The resulting lack of mechanical complexity, with practically no moving parts, puts the ramjet as well as the scramjet to overall advantage over the turbojet engine even at low Mach numbers where turbojet thermodynamic performance may exceed that of the ramjet/scramjet. For useful engine operation, at some flight conditions, the intake duct shape must be such that the required air mass flow in the duct is predictable, stable, properly conditioned (uniform in some sense) and thermodynamically efficient. -
Reusable Launch Systems Aerospace
Nov, 2010 DEPARTMENT OF REUSABLE LAUNCH SYSTEMS AEROSPACE ENGINEERING Soumik Bose Keshav Kishore Anand Indian Institute Of Technology, Kharagpur 1 INTRODUCTION A hundred years ago, on December 17, 1903, Wilbur and Orville Wright successfully achieved a piloted, powered flight. Though the Wright Flyer I flew only 10 ft off the ground for 12 seconds, traveling a mere 120 ft, the aeronautical technology it demonstrated paved the way for passenger air transportation. Man had finally made it to the air. The Wright brother’s plane of 1903 led to the development of aircrafts such as the WWII Spitfire, and others. In 1926 the first passenger plane flew holiday makers from American mainland to Havana and Bahamas. In 23 years the world had moved from a plane that flew 120 ft and similar planes that only a chosen few could fly, to one that can carry many passengers. In October 1957, man entered the space age. Russia sent the first satellite, the Sputnik, and in April 1961, Yuri Gagarin became the first man on space. In the years since Russia and United States has sent many air force pilots and a fewer scientists, engineers and others. But even after almost 50 years, the number of people who has been to space is close to 500. The people are losing interest in seeing a chosen few going to space and the budgets to space research is diminishing. The space industry now makes money by taking satellites to space. But a major factor here is the cost. At present to put a single kilogram into orbit will cost you between $10000 and $20000. -
Provisional Technical Program
ISABE 2019 22 - 27 SEPTEMBER INTERNATIONAL SOCIETY FOR AIR BREATHING ENGINES CANBERRA, AUSTRALIA Table of Content Welcome to Canberra, Australia 5 Committee 6 Conference Schedule 7 Conference Venues 8 Social Events 10 Accompanying Persons 11 Invited Speakers 12 Discussion Panel 13 Nothing but Monday 23 September: Technical Session 14 green skies Tuesday 24 September: Technical Session 19 ahead Wednesday 25 September: Technical Session 26 Thursday 26 September: Technical Session 29 Friday 27 September: Technical Session 36 Gas turbines are more efficient than ever. And we’re making sure they get even more so. But Rolls-Royce is also working on tomorrow, pioneering hybrid-electric Venue Map 39 and all-electric power. This quiet revolution will soon offer the opportunity for more sustainable growth and reduced carbon emissions. It is the fundamental change we need to lower our collective impact on the environment. Speaker Instructions 40 Pioneering the power that matters Find out more: rolls-royce.com/electrification ISABE 2019 Sponsors 41 WELCOME TO CANBERRA, AUSTRALIA Australia is a strong and prosperous nation that, given its location in the Southern Hemisphere, bridging the Indian, Pacific and Southern Oceans, relies heavily on airbreathing propulsion to remain an integral part of the world. As a consequence, Australia is strongly dependent It is populated by all manner of native flora and upon the gas turbine for air transport to service our fauna most especially our kangaroos. Furthermore, tourist industry and maintain international trade via Canberra is best experienced during the September our own airlines and those that service our shores. Spring time when we will host ISABE2019, which The Australian Defence Force are also heavy users will also coincide with the start of Canberra’s famous of gas turbines in their aircraft, ships and even tanks.