DOCSLIB.ORG

A Survey of Automatic Control Methods for Liquid-Propellant Rocket Engines

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
A Survey of Automatic Control Methods for Liquid-Propellant Rocket Engines A survey of automatic control methods for liquid-propellant rocket engines Sergio Pérez-Roca, Julien Marzat, Hélène Piet-Lahanier, Nicolas Langlois, Francois Farago, Marco Galeotta, Serge Le Gonidec To cite this version: Sergio Pérez-Roca, Julien Marzat, Hélène Piet-Lahanier, Nicolas Langlois, Francois Farago, et al.. A survey of automatic control methods for liquid-propellant rocket engines. Progress in Aerospace Sciences, Elsevier, 2019, pp.1-22. 10.1016/j.paerosci.2019.03.002. hal-02097829 HAL Id: hal-02097829 https://hal.archives-ouvertes.fr/hal-02097829 Submitted on 12 Apr 2019 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. A survey of automatic control methods for liquid-propellant rocket engines Sergio Perez-Roca´ a,c,∗, Julien Marzata,Hel´ ene` Piet-Lahaniera, Nicolas Langloisb, Franc¸ois Faragoc, Marco Galeottac, Serge Le Gonidecd aDTIS, ONERA, Universit´eParis-Saclay, Chemin de la Huniere, 91123 Palaiseau, France bNormandie Universit´e,UNIROUEN, ESIGELEC, IRSEEM, Rouen, France cCNES - Direction des Lanceurs, 52 Rue Jacques Hillairet, 75612 Paris, France dArianeGroup SAS, Forˆetde Vernon, 27208 Vernon, France Abstract The main purpose of this survey paper is to review the field of convergence between the liquid-propellant rocket- propulsion and automatic-control disciplines. A comprehensive collection of academic works and some industrial developments are summarised and discussed, making the link to the current context of launcher reusability. The main control problem in liquid-propellant rocket engines (LPRE), the target of this survey, generally consists in tracking set-points in combustion-chamber pressure and mixture ratio, their main operating quantities. This goal is attained via the adjustment of flow-control valves while complying with operating constraints. Each aspect of control systems, ranging from modelling to the actual control techniques, is reviewed and subsequently related to the rest of aspects. The comparison of the different approaches points to the general use of linearised models about concrete operating points for deriving steady-state controllers, which in most cases are of PID type. Other more sophisticated approaches present in the literature, incorporating some nonlinear, hybrid or robust techniques, improve certain aspects of performance and robustness. Nevertheless, no fully nonlinear or hybrid frameworks, which may allow the control of a wider throttling domain, have been published. In addition, control during the thermally and structurally demanding transient phases is usually in open loop, and hence with low correction margins. This sort of control enhancements, probably together with more sophisticated monitoring architectures, would serve to extend the life of LPRE, a significant factor in their reusability. Therefore, this survey intends to draw a path for the future control design trends which will certainly be more suitable for reusable LPRE. Keywords: Liquid-propellant rocket engines, automatic control, thermodynamic systems, reusability, modelling, review. 1. Introduction since rocket engines are complex two-sided technologi- cal assets (with military and civil uses), generally need- The automatic control of liquid-propellant rocket ing wide technical know-how. But it could also mean propulsion systems is a specific field that presents mul- that this bi-disciplinary topic has not been extensively tiple goals and constraints and that in practical terms tackled by the research community. Hence, the ex- tends to be simplified for adapting to the restrictive real pected benefits of this article are two-fold. On the one space-engineering scenarios. hand, it is intended to provide the designers of liquid- Even if the first reference reviewed dates from the propellant rocket engines (LPRE) with possibilities to 1950s, a relatively low number of publications cover- enhance their control systems, seeing the current evolv- ing both disciplines at the same time can be found in ing context of reusable launchers. On the other hand, the literature. This fact might stem from intentional the automatic-control community may find challenging confidentiality strategies by companies and agencies, cutting-edge applications of their control techniques. Therefore, background introductions on each field are provided throughout the article. ∗Corresponding author. The automatic control of any type of system generally Phone: +33180386657 Email address: [email protected] (Sergio pursues that the system behaves as expected, according Perez-Roca)´ to some predefined references. In the case of LPRE, Postprint accepted in Progress in Aerospace Sciences April 2, 2019 Nomenclature e Subscript for nozzle exit HMS Health Monitoring System t Subscript for throat HPT High-Pressure Turbine m˙ Mass flow [kg=s] ICS Intelligent Control System γ Specific heat ratio [-] JAXA Japanese Aerospace Exploration Agency ! Rotational speed [rad=s] LCH4 Liquid Methane Φ Heat transfer [W] LEC Life-Extending Control ρ Density [kg=m3] LFT Linear Fractional Transformation c Subscript for cavity/combustion/chamber LH2 Liquid Hydrogen A Area [m2] LMI Linear Matrix Inequality A; B; C; D Standard state-space matrices LOX Liquid Oxygen C∗ Characteristic exhaust speed [m=s] LPRE Liquid-Propellant Rocket Engine F Thrust [N] LPV Linear Parameter-Varying 2 g0 Standard gravity acceleration [m=s ] LQG/LTR Linear Quadratic Gaussian/Loop Transfer- H Enthalpy [J=kg] function Recovery Isp Specific impulse [s] LQR Linear-quadratic regulator 2 ITP Shaft inertia [kg · m =s] LS Least Squares kres Component’s resistance coefficient [1=(kgm)] LVDT Linear Variable Differential Transformer L Length [m] // Liquid MBFD Model-based fault detection M Molecular weight [kg=mol] MFV Main Fuel Valve MR Mixture ratio [-] MIMO Multi-Input Multi-Output p Pressure [Pa; bar] MOV Main Oxidiser Valve R Gas constant [J=kgK] MPC Model Predictive Control s Laplace variable NASA National Aeronautics and Space Administration T Temperature [K] NLP Nonlinear Programming t Time [s] O, ox Oxidiser Tq Torque [Nm] ODE Ordinary Differential Equations u Control input [m=s] OL Open Loop V Volume [m3] OPOV Oxidiser Preburner Oxidiser Valve x State vector PI Proportional-Integrator Controller y Output vector PID Proportional-Integrator-Derivative Controller H1 H infinity norm for robust control PLC Programmable Logic Controller ACC Active Combustion Control PRBS Pseudorandom Binary Sequence CC, C Combustion chamber PWM Pulse-Width Modulation CL Closed Loop RC Reconfigurable Control CNES Centre National d’Etudes´ Spatiales RML Recursive Maximum Likelihood DF Describing functions RREC Robust Rocket Engine Concept ESA European Space Agency RTD Resistance Temperature Devices F, fu Fuel RVDT Rotary Variable Differential Transformer FDD Fault Detection and Diagnosis SISO Single-Input Single-Output FDI Fault Detection and Isolation SQP Sequential Quadratic Programming FPOV Fuel Preburner Oxidiser Valve SSME Space Shuttle Main Engine FTCS Fault-tolerant Control Systems TCV Thrust Control Valve GG, G Gas generator TP Turbopump HIL Hardware in the Loop TVC Thrust-Vector Control 2 the system studied in this paper, these references gener- constant of the mixture, g0 is the standard gravity accel- ally correspond to the two variables defining its operat- eration, pe is the exhaust pressure, CF is the thrust co- ing envelope: combustion-chamber pressure (related to efficient and Isp is the specific impulse. The latter is the thrust) and mixture ratio (oxidiser to fuel ratio), which ratio of thrust to ejected mass flow, and hence represents are usually controlled via adjustable valves. In order the efficiency of the engine. Mixture ratio (MR), defined to explain the physical meaning of these variables and as the ratio between oxidiser and fuel mass flows, has an components, an introduction to the working principles influence on the previous formulae via Tc and thermo- of rocket engines seems necessary. dynamic properties like γ and R. Several types of LPRE cycles have been conceived re- 1.1. Rocket engine generalities garding the manner in which propellants are fed to the main thrust chamber (compound of combustion cham- Chemical rocket engines, mainly used to propel ber and convergent-divergent nozzle), but the main ele- launch vehicles and spacecraft, can be classified in the ments in a LPRE cycle remain the same: first place according to the state in which the chemi- cal propellant is stored: i.e. solid-propellant, liquid- • Propellant tanks: cryogenic or not (low tempera- propellant and hybrid (mixture of both) engines. In- tures preferred for low-density propellants such as deed, propellants nature determines to a great extent the hydrogen). conception of these systems. The chemical compounds • Pipe lines: ducts joining the different elements. furnished to the rocket engine undergo several thermo- dynamic transformations throughout their flow through • Valves: control components guiding and/or regu- the engine lines and components. The main phenomena lating propellants flow through the system. They are their combustion and expansion,
Load more

Recommended publications
  • Report Resumes
    REPORT RESUMES ED 019 218 88 SE 004 494 A RESOURCE BOOK OF AEROSPACE ACTIVITIES, K-6. LINCOLN PUBLIC SCHOOLS, NEBR. PUB DATE 67 EDRS PRICEMF.41.00 HC-S10.48 260P. DESCRIPTORS- *ELEMENTARY SCHOOL SCIENCE, *PHYSICAL SCIENCES, *TEACHING GUIDES, *SECONDARY SCHOOL SCIENCE, *SCIENCE ACTIVITIES, ASTRONOMY, BIOGRAPHIES, BIBLIOGRAPHIES, FILMS, FILMSTRIPS, FIELD TRIPS, SCIENCE HISTORY, VOCABULARY, THIS RESOURCE BOOK OF ACTIVITIES WAS WRITTEN FOR TEACHERS OF GRADES K-6, TO HELP THEM INTEGRATE AEROSPACE SCIENCE WITH THE REGULAR LEARNING EXPERIENCES OF THE CLASSROOM. SUGGESTIONS ARE MADE FOR INTRODUCING AEROSPACE CONCEPTS INTO THE VARIOUS SUBJECT FIELDS SUCH AS LANGUAGE ARTS, MATHEMATICS, PHYSICAL EDUCATION, SOCIAL STUDIES, AND OTHERS. SUBJECT CATEGORIES ARE (1) DEVELOPMENT OF FLIGHT, (2) PIONEERS OF THE AIR (BIOGRAPHY),(3) ARTIFICIAL SATELLITES AND SPACE PROBES,(4) MANNED SPACE FLIGHT,(5) THE VASTNESS OF SPACE, AND (6) FUTURE SPACE VENTURES. SUGGESTIONS ARE MADE THROUGHOUT FOR USING THE MATERIAL AND THEMES FOR DEVELOPING INTEREST IN THE REGULAR LEARNING EXPERIENCES BY INVOLVING STUDENTS IN AEROSPACE ACTIVITIES. INCLUDED ARE LISTS OF SOURCES OF INFORMATION SUCH AS (1) BOOKS,(2) PAMPHLETS, (3) FILMS,(4) FILMSTRIPS,(5) MAGAZINE ARTICLES,(6) CHARTS, AND (7) MODELS. GRADE LEVEL APPROPRIATENESS OF THESE MATERIALSIS INDICATED. (DH) 4:14.1,-) 1783 1490 ,r- 6e tt*.___.Vhf 1842 1869 LINCOLN PUBLICSCHOOLS A RESOURCEBOOK OF AEROSPACEACTIVITIES U.S. DEPARTMENT OF HEALTH, EDUCATION & WELFARE OFFICE OF EDUCATION K-6) THIS DOCUMENT HAS BEEN REPRODUCED EXACTLY AS RECEIVED FROM THE PERSON OR ORGANIZATION ORIGINATING IT.POINTS OF VIEW OR OPINIONS STATED DO NOT NECESSARILY REPRESENT OFFICIAL OFFICE OF EDUCATION POSITION OR POLICY. 1919 O O Vj A PROJECT FUNDED UNDER TITLE HIELEMENTARY AND SECONDARY EDUCATION ACT A RESOURCE BOOK OF AEROSPACE ACTIVITIES (K-6) The work presentedor reported herein was performed pursuant to a Grant from the U.
    [Show full text]
  • To All the Craft We've Known Before
    400,000 Visitors to Mars…and Counting Liftoff! A Fly’s-Eye View “Spacers”Are Doing it for Themselves September/October/November 2003 $4.95 to all the craft we’ve known before... 23rd International Space Development Conference ISDC 2004 “Settling the Space Frontier” Presented by the National Space Society May 27-31, 2004 Oklahoma City, Oklahoma Location: Clarion Meridian Hotel & Convention Center 737 S. Meridian, Oklahoma City, OK 73108 (405) 942-8511 Room rate: $65 + tax, 1-4 people Planned Programming Tracks Include: Spaceport Issues Symposium • Space Education Symposium • “Space 101” Advanced Propulsion & Technology • Space Health & Biology • Commercial Space/Financing Space Space & National Defense • Frontier America & the Space Frontier • Solar System Resources Space Advocacy & Chapter Projects • Space Law and Policy Planned Tours include: Cosmosphere Space Museum, Hutchinson, KS (all day Thursday, May 27), with Max Ary Oklahoma Spaceport, courtesy of Oklahoma Space Industry Development Authority Oklahoma City National Memorial (Murrah Building bombing memorial) Omniplex Museum Complex (includes planetarium, space & science museums) Look for updates on line at www.nss.org or www.nsschapters.org starting in the fall of 2003. detach here ISDC 2004 Advance Registration Form Return this form with your payment to: National Space Society-ISDC 2004, 600 Pennsylvania Ave. S.E., Suite 201, Washington DC 20003 Adults: #______ x $______.___ Seniors/Students: #______ x $______.___ Voluntary contribution to help fund 2004 awards $______.___ Adult rates (one banquet included): $90 by 12/31/03; $125 by 5/1/04; $150 at the door. Seniors(65+)/Students (one banquet included): $80 by 12/31/03; $100 by 5/1/04; $125 at the door.
    [Show full text]
  • PRESS RELEASE Safran Appointments
    PRESS RELEASE Safran appointments June 28, 2021 Two appointments to Safran's Executive Committee Effective July 1, 2021, Stéphane Cueille is named CEO of Safran Electrical & Power. He takes over from Alain Sauret, who is retiring. Olivier Andriès, CEO of Safran, said, “I would like to sincerely thank Alain Sauret, who joined the Group almost 40 years ago at our legacy company, Labinal. He went on to transform the company into a world-class center of electrical system excellence. Safran Electrical & Power is today a cornerstone of our decarbonized aviation roadmap.” Holding the rank of Ingénieur de l’Armement (defense scientist), Stéphane Cueille was seconded to Snecma1 from 1998 to 2001 to work on ceramic matrix composites (CMC). He returned to the French defense procurement agency DGA in 2001, taking various management positions in the aircraft propulsion sector. In 2005 he was placed in charge of the Missiles-Space unit in the industrial affairs department (S2IE). In 2008, he returned to Snecma, starting in the turbine blade quality department at the Gennevilliers plant. He was subsequently named repair general manager in Snecma’s Military Engine division, then director of the turbine blade center of excellence. / Safran Mereis / Capa/ Safran/ MereisCapa/ Safran / In May 2013 he was appointed Managing Director of Aircelle Ltd, the UK subsidiary of Aircelle2 based in Burnley. In January 2015 he was named head of Safran Tech, the Stéphanie Group's Research & Technology (R&T) center, and then in 2016 was appointed Senior Executive Vice President R&T and Christophe Innovation, also becoming a member of the Safran Executive © Committee.
    [Show full text]
  • Numerical Investigation of a 7-Element GOX/GCH4 Subscale Combustion Chamber
    DOI: 10.13009/EUCASS2017-173 7TH EUROPEAN CONFERENCE FOR AERONAUTICS AND AEROSPACE SCIENCES (EUCASS) Numerical Investigation of a 7-Element GOX/GCH4 Subscale Combustion Chamber ? ? ? Daniel Eiringhaus †, Daniel Rahn‡, Hendrik Riedmann , Oliver Knab and Oskar Haidn‡ ?ArianeGroup Robert-Koch-Straße 1, 82024 Taufkirchen, Germany ‡Institute of Turbomachinery and Flight Propulsion (LTF), Technische Universität München (TUM) Boltzmannstr. 15, 85748 Garching, Germany [email protected] †Corresponding author Abstract For future liquid rocket engines methane has become the focus of several studies on alternative fuels in the western hemisphere. At ArianeGroup numerical simulation tools have been established as a powerful instrument in the design process. In order to achieve the same confidence level for CH4/O2 as for H2/O2 combustion, the applied numerical models have to be adapted and validated against sufficient test data. At the Chair of Space Propulsion at the Technical University of Munich (TUM) several combustion cham- bers have been designed and tests at different operating points have been conducted. In this paper one of these subscale combustion chambers with calorimetric cooling and seven shear coaxial injection elements running on gaseous methane and oxygen is used to examine ArianeGroup’s in-house tools for combustion chamber performance analysis. 1. Introduction Current development programs in many space-faring nations focus on launchers utilizing a propellant combination of liquid oxygen (LOX) and liquid methane (CH4). In Europe, hydrocarbons have been identified as an alternative fuel in the frame of the Future Launcher Preparatory Programme (FLPP).14, 23 Major industrial development of methane / oxy- gen rocket engines is ongoing in the United States at SpaceX with the Raptor engine (staged combustion), at Blue Origin with the BE-4 engine (staged combustion) and in Europe at ArianeGroup with the Prometheus engine (gas gen- erator).
    [Show full text]
  • Qualification Over Ariane's Lifetime
    r bulletin 94 — may 1998 Qualification Over Ariane’s Lifetime A. González Blázquez Directorate of Launchers, ESA, Paris M. Eymard Groupe Programme CNES/Arianespace, Evry, France Introduction Similarly, the RL10 engine on the Centaur stage The primary objectives of the qualification of the Atlas launcher has been the subject of an activities performed during the operational ongoing improvement programme. About 5000 lifetime of a launcher are: tests were performed before the first flight, and – to verify the qualification status of the vehicle 4000 during the subsequent ten years. – to resolve any technical problems relating to subsystem operations on the ground or in On-going qualification activities of a similar flight. nature were started for the Ariane-3 and 4 launchers in 1986, and for Ariane-5 in 1996. Before focussing on the European family of They can be classified into two main launchers, it is perhaps informative to review categories: ‘regular’ and ‘one-off’. just one or two of the US efforts in the area of solid and liquid propulsion in order to put the Ariane-3/4 accompanying activities Ariane-related activities into context. Regular activities These activities are mainly devoted to In principle, the development programme for a launcher ends with the verification of the qualification status of the qualification phase, after which it enters operational service. In various launcher subsystems. They include the practice, however, the assessment of a launcher’s reliability is a following work packages: continuing process and qualification-type activities proceed, as an – Periodic sampling of engines: one HM7 and extension of the development programme (as is done in aeronautics), one Viking per year, tested to the limits of the over the course of the vehicle’s lifetime.
    [Show full text]
  • Safran Aircraft Engines Download
    SAFRAN AIRCRAFT ENGINES This is a multi-site certificate, additional site details are listed in the appendix to this certificate 10 ALLEE DU BREVENT - COURCOURONNES 91019 EVRY CEDEX - FRANCE Bureau Veritas Certification certify that the Management System of the above organisation has been audited in accordance with the relevant Aerospace Supplier Quality system Certification Scheme EN 9104-001:2013 and found to be in accordance with the requirements of the management system standard detailed below: Standard EN 9100:2018 AS 9100:D - JISQ 9100:2016 Scope of certification DESIGN, DEVELOPMENT, PRODUCTION, DISTRIBUTION, TEST AND SERVICING OF CIVIL AND MILITARY AIRCRAFT ENGINES - DESIGN, DEVELOPMENT, PRODUCTION, DISTRIBUTION, TEST AND SERVICING SATELLITE AND SPACECRAFT PROPULSION SYSTEMS - ASSOCIATED SERVICES PROVIDED TO CIVIL AND MILITARY CUSTOMERS. Certification structure : Campus Certification Issue date: 15 September 2018 Subject to the continued satisfactory operation of the organization’s Management System, this certificate expires on (Certification Expiry date): 14 September 2021 Original certification date: 15 July 2004 Certificate : 7098050-Rev0 Date: 06 September 2018 File number : FR044707-1 Jacques Matillon – Managing DIrector Bureau Veritas Certification France 60, avenue du Général de Gaulle – Immeuble Le Guillaumet - 92046 Paris La Défense Further clarifications regarding the scope of this certificate the applicability of the management system requirements may be obtained by consulting the organization. To check this certificate validity, please call + 33(0) 1 41 97 00 60. APPENDIX SAFRAN AIRCRAFT ENGINES Standard EN 9100:2018 AS 9100:D - JISQ 9100:2016 Scope of certification Site Address Scope 10 ALLEE DU BREVENT COURCOURONNES SIEGE CENTRAL FUNCTIONS 91019 EVRY CEDEX, France RUE HENRI AUGUSTE INDUSTRIALIZATION AND MANUFACTURING OF PARTS AND EVRY-CORBEIL DESBRUÈRES - BP 81 COMPONENTS FOR AIRCRAFT ENGINES.
    [Show full text]
  • High-Thrust In-Space Liquid Propulsion Stage: Storable Propellants
    View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by Institute of Transport Research:Publications Space Propulsion 2014 – ID 2968378 High-Thrust in-Space Liquid Propulsion Stage: Storable Propellants Etienne Dumont, Alexander Kopp, Carina Ludwig, Nicole Garbers DLR, Space Launcher Systems Analysis (SART), Bremen, Germany [email protected] Abstract In the frame of a project funded by ESA, a consortium led Subscripts, Abbreviations by Avio in cooperation with Snecma, Cira, and DLR is ATV Automated Transfer Vehicle performing the preliminary design of a High-Thrust in- CDF Concurrent Design Facility Space Liquid Propulsion Stage for two different types of ECSS European Cooperation on Space manned missions beyond Earth orbit. For these missions, Standardization one or two 100 ton stages are to be used to propel a Elec assy electronic assembly manned vehicle. Three different propellant combinations; EPS Etage à propergols stockables (Ariane 5’s LOx/LH2, LOx/CH4 and MON-3/MMH are being storable propellant stage) compared. GNC Guidance Navigation and Control HTS High-Thrust Stage The preliminary design of the storable variant (MON- IF Interface 3/MMH) has been performed by DLR. The Aestus II ISS International Space Station engine with a large nozzle expansion ratio has been LEO Low Earth Orbit chosen as baseline. A first iteration has demonstrated, that LEOP Launch and Early Orbit Phase it indeed provides the best performance for the storable LH2 Liquid Hydrogen propellant combination, when considering all engines LOx Liquid Oxygen available today or which may be available in a short- to MLI Multi-Layer Insulation medium term.
    [Show full text]
  • Aerospace Dimensions Leader's Guide
    Leader Guide www.capmembers.com/ae Leader Guide for Aerospace Dimensions 2011 Published by National Headquarters Civil Air Patrol Aerospace Education Maxwell AFB, Alabama 3 LEADER GUIDES for AEROSPACE DIMENSIONS INTRODUCTION A Leader Guide has been provided for every lesson in each of the Aerospace Dimensions’ modules. These guides suggest possible ways of presenting the aerospace material and are for the leader’s use. Whether you are a classroom teacher or an Aerospace Education Officer leading the CAP squadron, how you use these guides is up to you. You may know of different and better methods for presenting the Aerospace Dimensions’ lessons, so please don’t hesitate to teach the lesson in a manner that works best for you. However, please consider covering the lesson outcomes since they represent important knowledge we would like the students and cadets to possess after they have finished the lesson. Aerospace Dimensions encourages hands-on participation, and we have included several hands-on activities with each of the modules. We hope you will consider allowing your students or cadets to participate in some of these educational activities. These activities will reinforce your lessons and help you accomplish your lesson out- comes. Additionally, the activities are fun and will encourage teamwork and participation among the students and cadets. Many of the hands-on activities are inexpensive to use and the materials are easy to acquire. The length of time needed to perform the activities varies from 15 minutes to 60 minutes or more. Depending on how much time you have for an activity, you should be able to find an activity that fits your schedule.
    [Show full text]
  • GAM-2020-LPA Large Passenger Aircraft Innovative Aircraft
    PROJECT GAM-2020-LPA Large Passenger Aircraft Innovative Aircraft Demonstrator Platform Funding: European (Horizon 2020) Duration: Jan 2020 - Dec 2021 Status: Ongoing Total project cost: €142,140,284 EU contribution: €106,688,121 Call for proposal: H2020-IBA-CS2-GAMS-2019 CORDIS RCN : 231017 Objectives: The main objective for the Clean Sky 2 Large Passenger Aircraft Programme (LPA) is to further mature and validate key technologies such as advanced wings and empennages design, making use of hybrid laminar airflow wing developments, the integration of most advanced engines into the large passenger aircraft aircraft design as well as an all-new next generation fuselage cabin and cockpit-navigation. Dedicated demonstrators are dealing with research on the best opportunities to combine radical propulsion concepts, and the opportunities to use scalled flight testing for the maturation and validation of these concepts via scalled flight testing. Components of hybrid electric propulsion concepts are developed and tested in a major ground based test rig. The LPA program is also contributing with a major work package to the E-Fan X program. The R&T activities in the LPA program is split in 21 so-called demonstrators. In the project period 2020 and 2021 a substantial number of hardware items ground and flight test items will be manufactured, assembled tested. For some large items like the Multifunctional Fuselage demonstrators or the HLFC wing ground demonstrator the detailed design and manufacturing of test items will be commenced. For the great majority of contributing technologies a Technology Readiness level (TRL) 3 or 4 will be accomplished or even exceeded.
    [Show full text]
  • On Orbital Debris JEFF FOUST, COLLEGE PARK, Md
    NOVEMBER 24, 2014 SPOTLIGHT Clyde Space See page 12 www.spacenews.com VOLUME 25 ISSUE 46 $4.95 ($7.50 Non-U.S.) PROFILE/22> YVONNE PENDLETON DIRECTOR, SOLAR SYSTEM EXPLORATION RESEARCH VIRTUAL INSTITUTE INSIDE THIS ISSUE LAUNCH INDUSTRY Swift Development of Ariane 6 Urged Applauding the end of a French-German impasse over the Ariane 6 rocket, the European Satellite Operators Association said the vehicle needs to be in service as quickly as possible. See story, page 8 ATK Hints at Antares Engine Selection Alliant Techsystems Chief Executive Mark DeYoung said there are no near-term liquid- propulsion alternatives to Russian engines for U.S. rockets. See story, page 6 ESA PHOTO Virginia May Seek Federal Funds for Wallops > “We have found a compromise that is OK for both countries, for the other participating states and also for industry,” Brigitte Zypries (above), Germany’s Virginia’s two U.S. senators said they may seek federal funds to cover $20 million in repairs to the space minister, said of an agreement under which Germany and France will back the Ariane 6 rocket and scrap the Ariane 5 Midlife Evolution. Wallops Island launch pad damaged when Orbital Sciences’ Antares exploded. See story, page 6 MILITARY SPACE Protected Tactical Waveform Taking Shape German-French Compromise The U.S. Air Force is expected to demonstrate its protected tactical waveform in new modems and reworked terminals as early as 2018. See story, page 11 U.S. To Grant Indirect Access to Space Fence Paves Direct Path to Ariane 6 The Pentagon’s international space surveillance partners will have indirect access to data from the Air Force’s next-generation Space Fence tracking system.
    [Show full text]
  • Rocket Propulsion Fundamentals 2
    https://ntrs.nasa.gov/search.jsp?R=20140002716 2019-08-29T14:36:45+00:00Z Liquid Propulsion Systems – Evolution & Advancements Launch Vehicle Propulsion & Systems LPTC Liquid Propulsion Technical Committee Rick Ballard Liquid Engine Systems Lead SLS Liquid Engines Office NASA / MSFC All rights reserved. No part of this publication may be reproduced, distributed, or transmitted, unless for course participation and to a paid course student, in any form or by any means, or stored in a database or retrieval system, without the prior written permission of AIAA and/or course instructor. Contact the American Institute of Aeronautics and Astronautics, Professional Development Program, Suite 500, 1801 Alexander Bell Drive, Reston, VA 20191-4344 Modules 1. Rocket Propulsion Fundamentals 2. LRE Applications 3. Liquid Propellants 4. Engine Power Cycles 5. Engine Components Module 1: Rocket Propulsion TOPICS Fundamentals • Thrust • Specific Impulse • Mixture Ratio • Isp vs. MR • Density vs. Isp • Propellant Mass vs. Volume Warning: Contents deal with math, • Area Ratio physics and thermodynamics. Be afraid…be very afraid… Terms A Area a Acceleration F Force (thrust) g Gravity constant (32.2 ft/sec2) I Impulse m Mass P Pressure Subscripts t Time a Ambient T Temperature c Chamber e Exit V Velocity o Initial state r Reaction ∆ Delta / Difference s Stagnation sp Specific ε Area Ratio t Throat or Total γ Ratio of specific heats Thrust (1/3) Rocket thrust can be explained using Newton’s 2nd and 3rd laws of motion. 2nd Law: a force applied to a body is equal to the mass of the body and its acceleration in the direction of the force.
    [Show full text]
  • 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.
    [Show full text]