2017 REGISTRATION DOCUMENT Including the Annual Financial Report CONTENTS
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Call for M5 Missions
ESA UNCLASSIFIED - For Official Use M5 Call - Technical Annex Prepared by SCI-F Reference ESA-SCI-F-ESTEC-TN-2016-002 Issue 1 Revision 0 Date of Issue 25/04/2016 Status Issued Document Type Distribution ESA UNCLASSIFIED - For Official Use Table of contents: 1 Introduction .......................................................................................................................... 3 1.1 Scope of document ................................................................................................................................................................ 3 1.2 Reference documents .......................................................................................................................................................... 3 1.3 List of acronyms ..................................................................................................................................................................... 3 2 General Guidelines ................................................................................................................ 6 3 Analysis of some potential mission profiles ........................................................................... 7 3.1 Introduction ............................................................................................................................................................................. 7 3.2 Current European launchers ........................................................................................................................................... -
Robust Gas Turbine and Airframe System Design in Light of Uncertain
Robust Gas Turbine and Airframe System Design in Light of Uncertain Fuel and CO2 Prices Stephan Langmaak1, James Scanlan2, and András Sóbester3 University of Southampton, Southampton, SO16 7QF, United Kingdom This paper presents a study that numerically investigated which cruise speed the next generation of short-haul aircraft with 150 seats should y at and whether a con- ventional two- or three-shaft turbofan, a geared turbofan, a turboprop, or an open rotor should be employed in order to make the aircraft's direct operating cost robust to uncertain fuel and carbon (CO2) prices in the Year 2030, taking the aircraft pro- ductivity, the passenger value of time, and the modal shift into account. To answer this question, an optimization loop was set up in MATLAB consisting of nine modules covering gas turbine and airframe design and performance, ight and aircraft eet sim- ulation, operating cost, and optimization. If the passenger value of time is included, the most robust aircraft design is powered by geared turbofan engines and cruises at Mach 0.80. If the value of time is ignored, however, then a turboprop aircraft ying at Mach 0.70 is the optimum solution. This demonstrates that the most fuel-ecient option, the open rotor, is not automatically the most cost-ecient solution because of the relatively high engine and airframe costs. 1 Research Engineer, Computational Engineering and Design 2 Professor of Aerospace Design, Computational Engineering and Design, AIAA member 3 Associate Professor in Aircraft Engineering, Computational Engineering and Design, AIAA member 1 I. Introduction A. Background IT takes around 5 years to develop a gas turbine engine, which then usually remains in pro- duction for more than two decades [1, 2]. -
Introduction Firstly, We Have Given a Little Background of France, in Terms
Introduction Firstly, we have given a little background of France, in terms of its geographic, Demographic, political and economic characteristics and a brief History of France from its old age till the Modern times. Secondly, In order to find the absolute and comparative advantages of France, in terms of its international trade and economic prosperity, we have categorized the imports and exports of France into the following categories: Mineral products, Wood products, Metal products, Stones and glass products, Paper goods, Agriculture products, Animal products, Food stuffs, Weapons, Footwear and headwear, Animal hides, Textiles, Transportations, Machineries, Arts and antiques, Precious metals, Chemical products, instruments, plastics and rubbers. We have kept the imports/exports data of the year 2013 and 2014 under observations and had a relative comparison of France’s imports and exports commodities of these three years. The relative comparison of which are listed in the appendix, in terms of monetary value, percentage value of each categories and the overall imports and exports. Since, the imports and exports were in large numbers, thus we have taken the top 5 imports and exports of each category, as mentioned in the above paragraph, to find out the absolute and comparative advantages of France. Furthermore, we have: revealed the best comparative advantage by applying porter’s diamond model; determined the destination countries, where commodities are exported, by selecting a single company with in the industry that has the best comparative advantage. And finally, we determined the mode expansion using Foreign Direct Investment model. Background Geographically: France, with an Area of 643,801 Sq. -
Aerospace Engine Data
AEROSPACE ENGINE DATA Data for some concrete aerospace engines and their craft ................................................................................. 1 Data on rocket-engine types and comparison with large turbofans ................................................................... 1 Data on some large airliner engines ................................................................................................................... 2 Data on other aircraft engines and manufacturers .......................................................................................... 3 In this Appendix common to Aircraft propulsion and Space propulsion, data for thrust, weight, and specific fuel consumption, are presented for some different types of engines (Table 1), with some values of specific impulse and exit speed (Table 2), a plot of Mach number and specific impulse characteristic of different engine types (Fig. 1), and detailed characteristics of some modern turbofan engines, used in large airplanes (Table 3). DATA FOR SOME CONCRETE AEROSPACE ENGINES AND THEIR CRAFT Table 1. Thrust to weight ratio (F/W), for engines and their crafts, at take-off*, specific fuel consumption (TSFC), and initial and final mass of craft (intermediate values appear in [kN] when forces, and in tonnes [t] when masses). Engine Engine TSFC Whole craft Whole craft Whole craft mass, type thrust/weight (g/s)/kN type thrust/weight mini/mfin Trent 900 350/63=5.5 15.5 A380 4×350/5600=0.25 560/330=1.8 cruise 90/63=1.4 cruise 4×90/5000=0.1 CFM56-5A 110/23=4.8 16 -
CRUISE MISSILE THREAT Volume 2: Emerging Cruise Missile Threat
By Systems Assessment Group NDIA Strike, Land Attack and Air Defense Committee August 1999 FEASIBILITY OF THIRD WORLD ADVANCED BALLISTIC AND CRUISE MISSILE THREAT Volume 2: Emerging Cruise Missile Threat The Systems Assessment Group of the National Defense Industrial Association ( NDIA) Strike, Land Attack and Air Defense Committee performed this study as a continuing examination of feasible Third World missile threats. Volume 1 provided an assessment of the feasibility of the long range ballistic missile threats (released by NDIA in October 1998). Volume 2 uses aerospace industry judgments and experience to assess Third World cruise missile acquisition and development that is “emerging” as a real capability now. The analyses performed by industry under the broad title of “Feasibility of Third World Advanced Ballistic & Cruise Missile Threat” incorporate information only from unclassified sources. Commercial GPS navigation instruments, compact avionics, flight programming software, and powerful, light-weight jet propulsion systems provide the tools needed for a Third World country to upgrade short-range anti-ship cruise missiles or to produce new land-attack cruise missiles (LACMs) today. This study focuses on the question of feasibility of likely production methods rather than relying on traditional intelligence based primarily upon observed data. Published evidence of technology and weapons exports bears witness to the failure of international agreements to curtail cruise missile proliferation. The study recognizes the role LACMs developed by Third World countries will play in conjunction with other new weapons, for regional force projection. LACMs are an “emerging” threat with immediate and dire implications for U.S. freedom of action in many regions . -
Economic Feasibility Study for a 19 PAX Hybrid-Electric Commuter Aircraft
Air s.Pace ELectric Innovative Commuter Aircraft D2.1 Economic Feasibility Study for a 19 PAX Hybrid-Electric Commuter Aircraft Name Function Date Author: Maximilian Spangenberg (ASP) WP2 Co-Lead 31.03.2020 Approved by: Markus Wellensiek (ASP) WP2 Lead 31.03.2020 Approved by: Dr. Qinyin Zhang (RRD) Project Lead 31.03.2020 D2.1 Economic Feasibility Study page 1 of 81 Clean Sky 2 Grant Agreement No. 864551 © ELICA Consortium No export-controlled data Non-Confidential Air s.Pace Table of contents 1 Executive summary .........................................................................................................................3 2 References ........................................................................................................................................4 2.1 Abbreviations ...............................................................................................................................4 2.2 List of figures ................................................................................................................................5 2.3 List of tables .................................................................................................................................6 3 Introduction ......................................................................................................................................8 4 ELICA market study ...................................................................................................................... 12 4.1 Turboprop and piston engine -
Powerpoint Template with New NAHEMA Logo
5 & 6 OCTOBER 2016 LISBON, PORTUGAL 1. NH90 programme 2. JMAAN organization 3. EMAR Transition for NH90 (EMAR-T) 4. Conclusion NATO UNCLASSIFIED 2 1. NH90 programme 2. JMAAN organization 3. EMAR Transition for NH90 (EMAR-T) 4. Conclusion NATO UNCLASSIFIED 3 Corporate Identity: NAHEMO is a subsidiary body of NATO NAHEMA is the international programme office of NAHEMO Established: In 1992, in Aix-en-Provence (France) in vicinity of industrial consortium NHIndustries Mission: Management of the NH90 programme on behalf of the NAHEMO Nations, during the design & development, production & post-design and in-service support phases NATO UNCLASSIFIED 4 1 product: NH90 2 Versions: TTH, NFH >20 Variants: TGEA, GITA, TFRA, HITN, NBEN, NNLN, … Customer: NAHEMA 11 Nations: BEL, DEU, FRA, ITA, NLD, AUS, ESP, FIN, NOR, NZL, SWE, (GRC, OMN) Contractor: NHIndustries 4 Industries: AH, AHD, FK, LHD Design & Development (D&D) development of two versions TTH and NFH signed in 1992 Export Production Investment/ Production (PIP) production of the serial helicopters in different variants signed in 2000 (25 Contract Amendments so far) first serial helicopter delivered in 2006 (IOC) and 2012 (FOC) In-service support more than 240 helicopter in service with over 100k logged flight hours NATO UNCLASSIFIED 5 1. NH90 programme 2. JMAAN organization 3. EMAR Transition for NH90 (EMAR-T) 4. Conclusion NATO UNCLASSIFIED 6 JMAAN is a body of the NH90 Community JMAAN regulates all processes in the field of: • Military Design Organisation Approval • Rule-making -
SP's Naval Force June-July 2010
June-July l 2010 Volume 5 No 3 rs 100.00 (india-based buyer only) SP’s AN SP GUIDE PUBLICATION www.spsnavalforces.net ROUNDUP 3 PAGe STOP PRESS A Global Concern NAvAL vARIANT OF LCA ROLLS OUT India, in cooperation with its allies and friends The country’s first naval variant of Light Combat Aircraft, the LCA (Navy) Trainer around the world, will have to work to ensure Naval Project (NP)–1 was rolled out by the Defence Minister A.K. Antony from HAL that lawful private and public activities in the Aircraft Research and Design Centre at a glittering function in Bengaluru on July 6, maritime domain are protected against attack 2010. The Chief of Naval Staff Admiral Nirmal Verma, Secretary Defence Production by hostile exploitations R.K. Singh, Scientific Adviser to the Defence Minister, Dr. V.K. Saraswat, HAL Chair - man Ashok Nayak, Director Aeronautical Development Agency P.S. Subramanyam Cdr Sandeep Dewan were present on the occasion. The Defence Minister described the development as a ‘defining and memorable event’ for the nation. PAGe 4 Around the Sea A report on Commander Dilip Donde’s TeTe-e-TeTe successful completion of the first solo circumnavigation by an Indian Rear Admiral (Retd) Sushil Ramsay ‘Cooperation and interaction in the PAGe 6 Stealthy Ships maritime domain will continue to be an important aspect of IN’s vision’ PhotograPh: abhishek / sP guide Pubns Chief of Naval Staff Admi - ral Nirmal Verma , in an interaction with SP’s Naval The scope of accessing technologies from Forces , throws light on the the western world, so far denied to India, is security measures to deal witnessing an upward swing with the growing incidents Rear Admiral (Retd) Sushil Ramsay of piracy. -
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. -
Rotorcraft (2011)
Rotorcraft Overview The rotorcraft industry produces aircraft, powered by either turboshaft or reciprocating engines, capable of performing vertical take-off and landing (VTOL) operations. The rotorcraft sector includes helicopters, gyrocopters, and tiltrotor aircraft. Helicopters, which employ a horizontal rotor for both lift and propulsion, are the mainstay of the industry. Gyrocopters are produced in much smaller quantities, primarily for use in recreational flying. Tiltrotor aircraft, such as the V-22 Osprey1, can take off vertically and then fly horizontally as a fixed-wing aircraft. Rotorcraft are manufactured in most industrialized countries, based on indigenous design or in collaboration with, or under license from, other manufacturers. Manufacturers in the United States of civilian helicopters include American Eurocopter, Bell, Enstrom, Kaman, MD Helicopters, Robinson, Schweizer (now a subsidiary of Sikorsky), and Sikorsky. Bell moved its civilian helicopter production to Canada, with the last U.S. product completed in 1993.2 American Eurocopter—a subsidiary of the European manufacturer and subsidiary of EADS NV—has manufacturing and assembly facilities in Grand Prairie, Texas and Columbus, Missouri. European producers include AgustaWestland, Eurocopter, NHIndustries, and PZL Swidnik. Russian manufacturers including Mil Moscow, Kamov and Kazan helicopters, as well as a number of other rotorcraft related companies, have been consolidated under the Russian government majority-owned OAO OPK Oboronprom.3 (See this report’s Russia -
ESPA Ring Datasheet
PAYLOAD ADAPTERS | ESPA ESPA THE EVOLVED SECONDARY PAYLOAD ADAPTER ESPA mounts to the standard NSSL (formerly EELV) interface bolt pattern (Atlas V, Falcon 9, Delta IV, OmegA, Vulcan, Courtesy of Lockheed Martin New Glenn) and is a drop-in component in the launch stack. Small payloads mount to ESPA ports featuring either a Ø15-inch bolt circle with 24 fasteners or a 4-point mount with pads at each corner of a 15-inch square; both of these interfaces have become small satellite standards. ESPA is qualified to carry 567 lbs (257 kg), and a Heavy interface Courtesy of NASA (with Ø5/16” fastener hardware) has been introduced with a capacity of 991 lbs (450 kg). All small satellite mass capabilities require the center of gravity (CG) to be within 20 inches (50.8 cm) of the ESPA port surface. Alternative configurations can be accommodated. ESPA GRANDE ESPA Grande is a more capable version of ESPA with Ø24-inch ports; the ring height is typically 42 inches. The Ø24-inch port has been qualified by test to Courtesy of ORBCOMM & Sierra Nevada Corp. carry small satellites up to 1543 lb (700 kg). ESPA ESPA IS ADAPTABLE TO UNIQUE MISSION REQUIREMENTS • The Air Force’s STP-1 mission delivered multiple small satellites on an Atlas V. • NASA’s Lunar Crater Observation and Sensing Satellite (LCROSS): ESPA was the spacecraft hub for the LCROSS shepherding satellite in 2009. • ORBCOMM Generation 2 (OG2) launched stacks of two and three ESPA Grandes on two different Falcon 9 missions and in total deployed 17 satellites. -
Hi-Rel Solutions for Space Launch Vehicles a Single Network for All
© Airbus Safran Launchers 2016 © A Single Network for All Data Traffic Hi-Rel Solutions for Space Launch Vehicles www.tttech.com/space We are delighted that our network solution based on Deterministic Ethernet is providing a very powerful platform “ simplifying the electronic architectures of launch vehicles worldwide! Georg Kopetz, Member of the Executive Board, TTTech Computertechnik AG ” Over the last 25 years, space launch vehicle designs have utilized several different solutions for their on-board data handling. For the safety-critical command and control data, the very robust MIL-1553 bus served as a standard solution, originally designed as a military avionic data bus. For redundancy purposes, this widespread standard enforces two MIL-1553 buses running in parallel. This fact creates the first challenge, namely managing redundant fieldbuses in software and in parallel separate channels for additional data, e.g. telemetry. The second challenge arises from increasing data rates: MIL-1553 is limited to 1 Mbit/s, while there actually is both a need for higher control data rates and an interest in new types of sensors like video cameras. Adding more field buses would be possible, but would increase both weight and software complexity as well as qualification efforts. Finally, despite the need for higher bandwidth and a simplified network, no system cost increase can be tolerated, as in recent years the market for launch vehicles has become extremely competitive. This has led launch vehicle manufacturers worldwide to look for automotive or industrial solutions in order to reduce the cost of the electronics used throughout their vehicles. © Airbus Safran Launchers 2015 After several years of research funded by the ► French space agency (CNES) and afterwards by PROJECT ▼ the European Space Agency (ESA), architectures Launcher avionics A GLANCE AT based on TTEthernet are considered a great fit ► CHALLENGE for launch vehicles.