DOCSLIB.ORG

Il Vettore Italiano VEGA

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Il Vettore Italiano VEGA IlIl vettorevettore ItalianoItaliano VEGAVEGA PresentePresente ee FuturoFuturo Pier Giuliano Lasagni Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 1 Settore Aerospaziale @ Copyright All rights reserved Outline Agenda - L’accesso allo spazio - I veicoli ed i sistemi propulsivi - Cos’è VEGA ? - Descizione del Lanciatore - Il mercato - L’approccio programmatico - Nuove tecnologie per il lanciatore - Nuove competenze tecniche - Nuove competenze gestionali - Stato del programma - L’evoluzione di VEGA Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 2 Settore Aerospaziale @ Copyright All rights reserved L’accesso allo spazio •L’accesso allo spazio rappresenta dunque un asset strategico per i paesi industrializzati • L’utilizzo commerciale dello spazio oggi è concentrato principalmente sulla messa in orbita di satelliti artificiali •Europei Russi Americani Cinesi hanno lanciatori capaci di garantire la messa in orbita di satelliti Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 3 Settore Aerospaziale @ Copyright All rights reserved I veicoli ed i sistemi propulsivi Come funziona un lanciatore: •Mettere in orbita un oggetto vuol dire aumentare progressivamente la sua velocità fino a fargli raggiungere una velocità che lo mette in rotazione stabile attorno alla terra • Un sistema di lancio (lanciatore) accelera dunque un oggetto fino a fargli raggiungere la velocità e la quota di messa in orbita Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 4 Settore Aerospaziale @ Copyright All rights reserved I veicoli ed i sistemi propulsivi Europa ARIANE V ARIANESPACE VEGA USA BOEING LAUNCH SERVICE DELTA IV DELTA II USA/Russia INTERNATIONAL LAUNCH SERVICE PROTON M USA ATLAS III ATLAS V LOCKHEED MARTIN LAUNCH SYSTEM Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 5 Settore Aerospaziale @ Copyright All rights reserved I veicoli ed i sistemi propulsivi … due sistemi propulsivi equipaggiano i lanciatori Casing and Igniter Internal Thermal Protection Propellant Grain Thrust Vector Control Nozzle Combustion Chamber Liquid Oxidizer (O2) Turbopump Liquid Fuel Turbo pump Nozzle Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 6 Settore Aerospaziale @ Copyright All rights reserved Che cos’è VEGA ? Vega è un lanciatore a quattro stadi basato principalmente sulla propulsione a solido con un alto livello di integrazione con il lanciatore Ariane 5 Height [m] 30 I Design drivers sono: Maximum diameter [m] 3.00 •Costo di Lancio Fairing diameter [m] 2.60 •Flessibilità di Missione Mass at Lift-off [kg] 137 000 Reference mission •Affidabilità 1500 performance [kg] •P/L & customer comfort Reliability 98% Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 7 Settore Aerospaziale @ Copyright All rights reserved Descrizione del lanciatore Payload Composite Z9 SRM Z23 SRM AVUM P80 SRM & IS 23 IS34 IS 01 IS 12 Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 8 Settore Aerospaziale @ Copyright All rights reserved Primo stadio Length [m] 11.714 P80 SRM + IS01 e IS12 Max diameter [m] 3.005 Mass at Lift-off [kg] 97 131 Separation plane Burn time [s] 106.8 Total Impulse [KN s] 242 721 Structural Ratio 9.05 % IS 12 Retro Rocket Assy P80 SRM IS 01 Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 9 Settore Aerospaziale @ Copyright All rights reserved Secondo stadio Z23 SRM Length [m] 8.451 Max diameter [m] 1.910 Mass at Lift-off [kg] 26 563 Burn time [s] 71.7 Total Impulse [KN s] 67 776 Structural Ratio 9.99 % Z23 SRM TVC Assy Base Cover Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 10 Settore Aerospaziale @ Copyright All rights reserved Terzo stadio Z9 SRM + IS23. Include Length [m] 4.376 base cover, TVC assy Max diameter [m] 1.910 Separation Mass at Lift-off [kg] 11 454 Plane Burn time [s] 109.6 Wiring tunnel Total Impulse [KN s] 29 272 Structural Ratio 12.1 % IS23 Z9 SRM Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 11 Settore Aerospaziale @ Copyright All rights reserved Quarto Stadio Include il Sistema propulsivo Bi- Length [m] 1.742 propellente, il TVC assy, il Roll & Max diameter [m] 1.910 Attitude Control System, la Mass at Lift-off [kg] 1044 maggior parte dell’avionica del lanciatore e sistemi di Burn time [s] 667 comunicazione. Total Impulse [KN s] 1 702 Structural Ratio 47.3 % AVUM & IS34 primary structure Avionic Module Propulsion and Roll & Attitude Control Module Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 12 Settore Aerospaziale @ Copyright All rights reserved Payload Composite Include il fairing, l’adattatore Length [m] 7.842 del payload e il relativi sistemi Max diameter [m] 2.600 di separazione Mass at Lift-off [kg] 619+P/L Burn time [s] - Total Impulse - Structural Ratio - Payload Adapter 937B Payload Fairing Payload Dynamic envelope Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 13 Settore Aerospaziale @ Copyright All rights reserved Z9 SRM Z23 SRM P80 SRM Note Thrust [KN] 313,6 1190,4 3039,1 [5] Burning Time [s] 111,14 72,153 106,862 [3] Mass [kg] 10938,7 25822,5 95805,1 [2] Propulsione:Propellant mass [kg] Solido10064,3 23908,9 88340,4 [1] Total Impulse [kN s] 29157,8 67567,1 242037,5 [4] MR 0,920 0,926 0,922 [2] Z9 SRM Z23 SRM P80 SRM Note [1] Including Igniter Propellant mass [2] For P80 SRM, total mass includes TVC subsystem Thrust [KN] 313,6 1190,4 3039,1 [5] [3] Burning time (action time T38, 1.5 bar) Burning Time [s] 111,14 72,153 106,862 [3] [4] Action Time Vacuum Total Impulse (up to T38) Mass [kg] 10938,7 25822,5 95805,1 [2] [5] Maximum Vacuum Thrust Propellant mass [kg] 10064,3 23908,9 88340,4 [1] Total Impulse [kN s] 29157,8 67567,1 242037,5 [4] MR 0,920 0,926 0,922 [2] [1] Including Igniter Propellant mass [2] For P80 SRM, total mass includes TVC subsystem [3] Burning time (action time T38, 1.5 bar) Igniter [4] Action Time Vacuum Total Impulse (up to T38) [5] Maximum Vacuum Thrust Propellant Finocil Thermal Protection CFRP case & skirt Nozzle Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 14 Settore Aerospaziale @ Copyright All rights reserved Propulsione: Liquido Un sistema propulsivo a liquido è basato su un ben consolidato motore a bi-propellente ed un innovativo sistema di espulsione propellente Il sistema di espulsione propellente è costituio da un bladder rinforzato con un polimero al fluoro. Propellants UDMH / NTO Mixture ratio 2 Propellant Pressure (MEOP) 35.6 bar Number of Propellant Tanks 4 Pressurisation Gas Helium Number of Gas Pressurisation Tanks1 Specific Impulse 315,5 s Total Impulse 17022 kN s Burning time (max.) 667 s Nominal Thrust in vacuum 2450 N Total Propellant Mass (Max filling) 550 Kg Unusable propellant Mass 23 Kg Mass Flow Rate 0.79186 Kg/s Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 15 Settore Aerospaziale @ Copyright All rights reserved Propulsione: Roll & Attitude Il sistema Roll & Attitude Control System è basato quasi integralmente sull’architettura e componeneti dell’Ariane 5. Roll Control durante le fasi di spinta Attitude Control durante le fasi di avvicinamento all’orbita e posizionamento del payload Propellants N2H4 Number of Thrusters 6 Number of Tanks 1 Pressurisation Gas GN2 Propellant Pressure (Blow Down) 26 - 8 bar Specific Impulse 230 s Total Impulse 76700 N s MIB 2,5 N s Nominal Thrust in vacuum (each thruster,220 BoL) N Total Propellant Mass (Max filling) 34 Kg Mass Flow Rate (each thruster, BoL) 0.098 Kg/s Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 16 Settore Aerospaziale @ Copyright All rights reserved Thrust Vector Control Un innovativo Thrust Vector Control elettromeccanico per i quattro stadi, che condividono tecnologie e componenti (HW & SW) Controller & LiIon Batteries Power Distribution Mass Power Torque Speed Stroke Band- width (kg) (kW) (Nm) (mm/ (mm) (Hz) s) Z23 15x2 14 12 208 221 8 (EMA) 18 (IPDU) 30* (BS) Z9 15x2 2.05 7.04 93 124 3.05 (EMA) 18 (IPDU) 10* (BS) AVUM 4x2 (EMA) 0.43 0.17 49 68,8 3.05 10* (IPDU) 8* (BS) Electro Mechanical Actuator Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 17 Settore Aerospaziale @ Copyright All rights reserved Avionica MFU SMU SRU OBC TVC EMA & IPDU Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 18 Settore Aerospaziale @ Copyright All rights reserved Il mercato di Vega Mercato Satellitare Numero di Paylaods da lanciare 2008-2104 accessibile ad Arianespace Orbite Non GEO Payloads Europeo Istituzionale Europeo Non-Istituzionale o Non Europeo Mercato dei Lanci Trend in crescita nel breve medio periodo Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA. Page 19 Settore Aerospaziale @ Copyright All rights reserved Il mercato di Vega Europa Cina India Long March Long March Long March Long March VEGA ROCKOT 2C 2D 3B 2F POSSIBILI FUTURI COMPETITORI Rockot dovrebbe non essere più disponibile dopo il 2009, Russia USA all’entrata in servizio di VEGA Long March e GSLV, classe Ariane 5, sono pericolosi competitori sul piano economico Ricerca ed Innovazione nel All information contained in this document is property of Avio SpA.
Load more

Recommended publications
  • 액체로켓 메탄엔진 개발동향 및 시사점 Development Trends of Liquid
    Journal of the Korean Society of Propulsion Engineers Vol. 25, No. 2, pp. 119-143, 2021 119 Technical Paper DOI: https://doi.org/10.6108/KSPE.2021.25.2.119 액체로켓 메탄엔진 개발동향 및 시사점 임병직 a, * ㆍ 김철웅 a⋅ 이금오 a ㆍ 이기주 a ㆍ 박재성 a ㆍ 안규복 b ㆍ 남궁혁준 c ㆍ 윤영빈 d Development Trends of Liquid Methane Rocket Engine and Implications Byoungjik Lim a, * ㆍ Cheulwoong Kim a⋅ Keum-Oh Lee a ㆍ Keejoo Lee a ㆍ Jaesung Park a ㆍ Kyubok Ahn b ㆍ Hyuck-Joon Namkoung c ㆍ Youngbin Yoon d a Future Launcher R&D Program Office, Korea Aerospace Research Institute, Korea b School of Mechanical Engineering, Chungbuk National University, Korea c Guided Munitions Team, Hyundai Rotem, Korea d Department of Aerospace Engineering, Seoul National University, Korea * Corresponding author. E-mail: [email protected] ABSTRACT Selecting liquid methane as fuel is a prevailing trend for recent rocket engine developments around the world, triggered by its affordability, reusability, storability for deep space exploration, and prospect for in-situ resource utilization. Given years of time required for acquiring a new rocket engine, a national-level R&D program to develop a methane engine is highly desirable at the earliest opportunity in order to catch up with this worldwide trend towards reusing launch vehicles for competitiveness and mission flexibility. In light of the monumental cost associated with development, fabrication, and testing of a booster stage engine, it is strategically a prudent choice to start with a low-thrust engine and build up space application cases.
    [Show full text]
  • The Annual Compendium of Commercial Space Transportation: 2012
    Federal Aviation Administration The Annual Compendium of Commercial Space Transportation: 2012 February 2013 About FAA 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 (2013) NOTICE Use of trade names or names of manufacturers in this document does not constitute an official endorsement of such products or manufacturers, either expressed or implied, by the Federal Aviation Administration. • i • Federal Aviation Administration’s Office of Commercial Space Transportation Dear Colleague, 2012 was a very active year for the entire commercial space industry. In addition to all of the dramatic space transportation events, including the first-ever commercial mission flown to and from the International Space Station, the year was also a very busy one from the government’s perspective. It is clear that the level and pace of activity is beginning to increase significantly.
    [Show full text]
  • Los Motores Aeroespaciales, A-Z
    Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 < aeroteca.com > Depósito Legal B 9066-2016 Título: Los Motores Aeroespaciales A-Z. © Parte/Vers: 1/12 Página: 1 Autor: Ricardo Miguel Vidal Edición 2018-V12 = Rev. 01 Los Motores Aeroespaciales, A-Z (The Aerospace En- gines, A-Z) Versión 12 2018 por Ricardo Miguel Vidal * * * -MOTOR: Máquina que transforma en movimiento la energía que recibe. (sea química, eléctrica, vapor...) Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 Este facsímil es < aeroteca.com > Depósito Legal B 9066-2016 ORIGINAL si la Título: Los Motores Aeroespaciales A-Z. © página anterior tiene Parte/Vers: 1/12 Página: 2 el sello con tinta Autor: Ricardo Miguel Vidal VERDE Edición: 2018-V12 = Rev. 01 Presentación de la edición 2018-V12 (Incluye todas las anteriores versiones y sus Apéndices) La edición 2003 era una publicación en partes que se archiva en Binders por el propio lector (2,3,4 anillas, etc), anchos o estrechos y del color que desease durante el acopio parcial de la edición. Se entregaba por grupos de hojas impresas a una cara (edición 2003), a incluir en los Binders (archivadores). Cada hoja era sustituíble en el futuro si aparecía una nueva misma hoja ampliada o corregida. Este sistema de anillas admitia nuevas páginas con información adicional. Una hoja con adhesivos para portada y lomo identifi caba cada volumen provisional. Las tapas defi nitivas fueron metálicas, y se entregaraban con el 4 º volumen. O con la publicación completa desde el año 2005 en adelante. -Las Publicaciones -parcial y completa- están protegidas legalmente y mediante un sello de tinta especial color VERDE se identifi can los originales.
    [Show full text]
  • The European Launchers Between Commerce and Geopolitics
    The European Launchers between Commerce and Geopolitics Report 56 March 2016 Marco Aliberti Matteo Tugnoli Short title: ESPI Report 56 ISSN: 2218-0931 (print), 2076-6688 (online) Published in March 2016 Editor and publisher: European Space Policy Institute, ESPI Schwarzenbergplatz 6 • 1030 Vienna • Austria http://www.espi.or.at Tel. +43 1 7181118-0; Fax -99 Rights reserved – No part of this report may be reproduced or transmitted in any form or for any purpose with- out permission from ESPI. Citations and extracts to be published by other means are subject to mentioning “Source: ESPI Report 56; March 2016. All rights reserved” and sample transmission to ESPI before publishing. ESPI is not responsible for any losses, injury or damage caused to any person or property (including under contract, by negligence, product liability or otherwise) whether they may be direct or indirect, special, inciden- tal or consequential, resulting from the information contained in this publication. Design: Panthera.cc ESPI Report 56 2 March 2016 The European Launchers between Commerce and Geopolitics Table of Contents Executive Summary 5 1. Introduction 10 1.1 Access to Space at the Nexus of Commerce and Geopolitics 10 1.2 Objectives of the Report 12 1.3 Methodology and Structure 12 2. Access to Space in Europe 14 2.1 European Launchers: from Political Autonomy to Market Dominance 14 2.1.1 The Quest for European Independent Access to Space 14 2.1.3 European Launchers: the Current Family 16 2.1.3 The Working System: Launcher Strategy, Development and Exploitation 19 2.2 Preparing for the Future: the 2014 ESA Ministerial Council 22 2.2.1 The Path to the Ministerial 22 2.2.2 A Look at Europe’s Future Launchers and Infrastructure 26 2.2.3 A Revolution in Governance 30 3.
    [Show full text]
  • Cfd Kinetic Scheme Validation for Liquid Rocket Engine Fuelled by Oxygen/Methane
    DOI: 10.13009/EUCASS2019-680 8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) CFD KINETIC SCHEME VALIDATION FOR LIQUID ROCKET ENGINE FUELLED BY OXYGEN/METHANE Pasquale Natale*, Guido Saccone** and Francesco Battista*** * Centro Italiano Ricerche Aerospaziali Via Maiorise, 81043 Capua (CE), Italy, [email protected] **Centro Italiano Ricerche Aerospaziali Via Maiorise, 81043 Capua (CE), Italy,[email protected] ***Centro Italiano Ricerche Aerospaziali Via Maiorise, 81043 Capua (CE), Italy,[email protected] Abstract In recent years, greater attention has been paid to green propellants, among those liquid methane is one of the most promising choice. This has also been encouraged by the abolition of hydrazine for its intrinsic human-rating concerns. On the other hand, the adoption of methane as a fuel introduces some issues about modelling. Detailed kinetic schemes are required to properly reconstruct combustion process. This is especially true for rocket propulsion problems, in which the combustion is characterized by high pressure and not stoichiometric mixture ratio. Moreover, detailed scheme may not be feasible for CFD applications, due to high computational cost. For this reason, adoption of reduced schemes is encouraged, even if detailed mechanism description is required. In the present work, a reduced kinetic scheme (HPRB, by CIRA) will be presented for a specific LRE application. Some experimental firing-tests (i.e. FSBB test-campaign) will then be compared with model results, in order to validate the proposed model. 1. Introduction Traditionally, high performance rocket engines have used LOX and hydrogen or LOX and kerosene, while, as such, methane has not yet been used in a commercial launch vehicle.
    [Show full text]
  • Modeling and Numerical Simulation of Ignition Transient of Large Solid Rocket Motor S
    Università degli Studi di Roma “La Sapienza” Scuola di Ingegneria Aerospaziale Dottorato di Ingegneria Aerospaziale XV Ciclo MODELING AND NUMERICAL SIMULATION OF IGNITION TRANSIENT OF LARGE SOLID ROCKET MOTOR S Dottorando Ferruccio Serraglia Tutore Prof. Marcello Onofri Correlatore Prof. Maurizio Di Giacinto Correlatore Prof. Bernardo Favini Anno Accademico 2002/2003 1 2 Index INTRODUCTION 1. PHENOMENOLOGY OF THE IGNITION TRANSIENT 10 1.1 GENERAL DESCRIPTION 10 1.2 IGNITION AND COMBUSTION OF SOLID PROPELLANTS 14 IGNITION 14 STEADY-STATE BURNING 19 TRANSIENT AND EROSIVE BURNING 21 1.3 MODELING SRM IGNITION TRANSIENT 23 1D MODELS: STATE OF THE ART 23 GENERAL DISCUSSION 29 2 PHYSICAL AND MATHEMATICAL MODEL 32 2.1 GASDYNAMIC MODEL 32 2.2 IGNITER MODEL AND IMPINGEMENT REGION 36 2.3 PROPELLANT SURFACE HEATING, IGNITION AND REGRESSION 41 IGNITION CRITERION 41 CONVECTIVE HEAT TRANSFER: IMPINGEMENT REGION. 41 CONVECTIVE HEAT TRANSFER: STANDARD REGION 44 RADIATIVE HEAT TRANSFER 45 PROPELLANT HEATING EVALUATION 48 BURNING RATE MODEL 51 SURFACE REGRESSION EVALUATION 52 3 NUMERICAL INTEGRATION TECHNIQUE 54 3.1 DISCRETIZED FLUID DYNAMIC MODEL AND SOLUTION 54 GODUNOV’S METHOD 55 APPLICATION OF THE MODIFIED ENO METHOD TO THE IGNITION TRANSIENT ANALYSIS. 57 RIEMANN PROBLEM 61 3.2 THE ESPRIT SIMULATION CODE 63 4 RESULTS 66 4.1 HEAD-END PRESSURE AND IGNITION SEQUENCE 66 SOLID ROCKET MOTOR # 1 ARIANE 4 SOLID BOOSTER (SRM #1) 66 SOLID ROCKET MOTOR # 2 ARIANE 5 SOLID BOOSTER (SRM #2) 68 SOLID ROCKET MOTOR # 3 VEGA, ZEFIRO SOLID ROCKET STAGE (SRM #3) 71 4.2
    [Show full text]
  • Vega: the European Small-Launcher Programme
    r bulletin 109 — february 2002 Vega: The European Small-Launcher Programme R. Barbera & S. Bianchi Vega Department, ESA Directorate of Launchers, ESRIN, Frascati, Italy Background The programme was adopted by ESA in June The origins of the Vega Programme go back to 1998, but the funding was limited to a Step 1, the early 1990s, when studies were performed with the aim of getting the full approval by the in several European countries to investigate the European Ministers meeting in Brussels in May possibility of complementing, in the lower 1999. This milestone was not met, however, payload class, the performance range offered because it was not possible to obtain a wide by the Ariane family of launchers. The Italian consensus from ESA’s Member States for Space Agency (ASI) and Italian industry, in participation in the programme. This gave rise to particular, were very active in developing a period of political uncertainty and to a series concepts and starting pre-development work of negotiations aimed at finding an agreeable based on established knowhow in solid compromise. It is important, on the other hand, propulsion. When the various configuration to record that during the same period the options began to converge and the technical technical definition work continued without feasibility was confirmed, the investigations major disruption, and development tests on the were extended to include a more detailed Zefiro motor were successfully conducted. definition in terms of a market analysis and related cost targets. The subsequent extension of the duration of Step 1 provided the opportunity to revisit and By the end of 2001, the development programme for Europe’s new update the market analysis, based on the small Vega launcher was well underway.
    [Show full text]
  • → TECHNOLOGIES for EUROPEAN LAUNCHERS an ESA Communications Production
    → TECHNOLOGIES FOR EUROPEAN LAUNCHERS An ESA Communications Production Publication Technologies for European launchers (ESA BR-316 June 2014) Production Editor A. Wilson Design/layout G. Gasperoni, Taua Publisher ESA Communications ESTEC, PO Box 299, 2200 AG Noordwijk, The Netherlands Tel: +31 71 565 3408 www.esa.int ISBN 978-92-9221-066-3 ISSN 1013-7076 Copyright © 2014 European Space Agency Cover image: ESA–S. Corvaja Contents → INTRODUCTION 02 → AVIONICS 04 → PROPULSION 14 → STRUCTURES 26 AND MECHANICAL ENGINEERING Introduction Technologies for European launchers and new market requirements For decades, the development of new launch systems has demonstrating new technologies in materials, structural and focused on increasing lift capability and reliability. Programmes mechanical components, as well as advanced avionics, under conducted on behalf of ESA have supported industry in acquiring flight conditions. and mastering the basic and advanced technologies required to develop, manufacture and operate the most successful launch – The Intermediate Experimental Vehicle (IXV) is a testbed vehicles of their times. for technologies required for atmospheric reentry and recovery. These include highly autonomous and modular Although Ariane has been setting the standard for the launch subsystems that will help to expand the flight envelope able industry worldwide for more than 25 years, new challenges will to be accessed in the future. have to be met in the coming years to ensure the viability of Europe’s autonomous access to space and to keep the – As the ESA launcher technology programme, FLPP is maturing competitiveness of the European space transportation industry, technologies to enable and sustain the development and whose skills are recognised at international level and have evolution of current and future launchers.
    [Show full text]
  • Paolo Bellomi
    Paolo Bellomi Date of birth: 30/10/1958 Nationality: Italian Gender Male (+39) 3286128385 [email protected] www.linkedin.com/in/paolo-bellomi-78a872160 via Pontina 428, 00128, Roma, Italy WORK EXPERIENCE 01/06/2021 – CURRENT – Colleferro, Italy CHIEF TECHNICAL OFFICER – AVIO S.P.A. As Chief Technical Officer, he validates the Flight Worthiness of the products and services of Avio, including the Launch System and the mission preparation for Vega family. In the meantime he is in charge of the pre-competitive research, the product strategy and technological roadmap for Avio and takes care of several new initiatives (as the Space Propulsion Test Facility, located in Sardinia). He is the CEO of SpaceLab, an Avio and ASI (Italian Space Agency) company. He supports Avio CEO on a number of tasks, including Merger and Acquisition opportunities scouting and evaluation. 01/01/2013 – 31/05/2021 – Colleferro (RM) TECHNICAL DIRECTOR – AVIO S.P.A. Managed the directorate of Engineering and Product Development in Avio S.p.A. As Senior Vice President, he was in charge of the design, development and qualification of Avio S.p.A. products, in both space and defense application domain. He was the owner of the company development process, and as such, he led a 200-persons team; he technically drove a plethora of lower tier contractors or partners. In this position, he contributed to the European decision making for the space transportation systems Ariane 6 and Vega C: in particular he fostered the need for development of Solid Rocket Motor common, to Ariane 62 and 64 and Vega C and subsequently Vega E family.
    [Show full text]
  • Conceptual Design for Vega New Upper Stage
    62nd International Astronautical Congress, Cape Town, SA. Copyright ©2011 by the International Astronautical Federation. All rights reserved. IAC-11-D2.3.4 VENUS - CONCEPTUAL DESIGN FOR VEGA NEW UPPER STAGE Dr. Menko Wisse Astrium Space Transportation, Launchers, Bremen, Germany, [email protected] Georg Obermaier Astrium Space Transportation, Propulsion & Equipment, Munich, Germany, [email protected] Etienne Dumont DLR-SART, Bremen, Germany, [email protected] Thomas Ruwwe DLR Space Administration, Bonn, Germany, [email protected] With the first launch of VEGA approaching, the European launch vehicle family will soon be completed. VEGA aims at transporting small research- and earth observation satellites to Low Earth Orbit (LEO). Ongoing investigations show the opportunity for a performance improvement of the launcher to cope with the market demand for evolution in P/L mass. Therefore, studies to enhance the capabilities of the launch vehicle were started. The German Space Administration (DLR) has funded the VENUS (VEGA New Upper Stage) studies on behalf of the German Federal Ministry of Economics and Technology with Astrium Space Transportation as Prime Contractor and the DLR institute for Space Launcher Systems Analysis (SART) as subcontractor, in order to identify and assess the potential of increasing the upper stage performance. The second slice of the study, the so-called VENUS-2 study (support code FKZ50RL0910), was started in July 2009 and has been finalized mid 2011. VENUS- 2 aims at investigating possible evolutions of the VEGA-launcher upper stage. In particular, conceptual lay-outs for new storable propellant upper stages have been investigated including engines. The VENUS-2 study is divided into three study phases.
    [Show full text]
  • Download Here Avio's Company Profile
    SPACE IS CLOSER CORPORATE PROFILE Where we come from Avio is a space propulsion leader, with over 1,000 employees located in Italy, France and French Guiana. Since its foundation in 1912, the company has played a key role in the design, manufacturing and integration of space launcher systems and tactical missiles. With such a long history and track record, Avio today has extensive expertise in solid and liquid propulsion systems, chemicals and propellants, composite materials, system integration, experimental testing, flight and simulation software, on-board avionics and satellite launch operations. Evolving towards the future Since 2017 Avio has been listed on the STAR segment of the Italian Stock Exchange and was the first rocket manufacturing company in the world to become a public company with over 70% of its share capital floating on the market. With such a set-up Avio is today equipped to accelerate its investment ambitions, pursuing rapid growth for the future. In recent years Avio has delivered revenue growth at an average annual rate in excess of 15%. Our mission Our mission is to provide reliable and competitive access to space to improve life on earth. To this end, Avio has developed the Vega Launch System, a combination of launchers and adapters to carry any small-medium satellite into Low Earth Orbit on single, dual or multi-payload missions, serving any type of customer globally. Avio is committed to over time deliver new versions of the Vega system to continuously improve reliability, flexibility and cost-competitiveness. Vega Launchers Avio has designed, manufactured and assembled solid and liquid propulsion systems for more than 50 years.
    [Show full text]
  • Arianespace Procures First Batch of Upgraded Vega-C Rockets, Preps for Last Ariane 5 Order
    Arianespace procures first batch of upgraded Vega-C rockets, preps for last Ariane 5 order September 28, 2017 Stephen Clark This artist’s illustration shows the lineup of European rockets currently flying or scheduled to debut in the next few years. From left to right: Vega, Vega-C, Ariane 5 ECA, Ariane 62 and Ariane 64. Credit: ESA–David Ducros, Jacky Huart, 2016 Arianespace has split its third order of Vega rockets from Italy’s Avio between old and new versions of the solid-fueled booster, as officials prepare to build a final batch of around 18 Ariane 5 rockets before switching to the next-generation Ariane 6 in the early 2020s. The French launch company announced Wednesday the signature of a long-anticipated contract for 10 more Vega launchers from Avio, Vega’s prime contractor. It marks the third order of Vega rockets from the Italian manufacturer, bringing the total number of Vega vehicles purchased to 26. Six of the vehicles ordered by Arianespace will come in the same basic Vega configuration that has successfully launched 10 times since debuting in February 2012. Avio will also build the first four upgraded Vega-C launchers, featuring more powerful rocket motors and an enlarged payload fairing to haul bigger satellites into orbit. Meanwhile, Arianespace is in the final stages of negotiating with its parent company, Ariane Group, to order around 18 more Ariane 5 rockets, the last batch of Ariane 5s to be built after more than 20 years of launches. Arianespace expects to sell the additional Ariane 5 flights to commercial customers and European governments for launches through the early 2020s.
    [Show full text]