Vortrag Raketenantriebe und Raketentreibstoffe · 06.06.2016 Folie/Slide: 2. MBDA Germany Sites and...
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Vortrag Raketenantriebe und Raketentreibstoffe
Transcript of Vortrag Raketenantriebe und Raketentreibstoffe · 06.06.2016 Folie/Slide: 2. MBDA Germany Sites and...
Vortrag Raketenantriebe und Raketentreibstoffe
MBDAGroup Structure
37,5 % 25 %37,5 %
100 %
MBDA Germany
100 %
MBDA France
100 %
MBDA Spain
100 %
MBDA Inc.
MBDA Italy
MBDA UK
100 %
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Bayern-Chemie is the Competence Center for Missile Propulsion Systems within MBDAand for the German MoD
06.06.2016 Folie/Slide: 2
MBDA GermanySites and Offices
Office Berlin
Office Koblenz
Office BerlinOffice Bonn
Schrobenhausen1,080 Employees
Test Centre FreinhausenUlm70 Employees
Aschau160 EmployeesSales in 2015: € 50 million
0 p oyees
Orlando (MEADS Int.) Sales in 2015: € 50 million
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Bayern-Chemie is the Competence Center for Missile Propulsion Systems within MBDAand for the German MoD
06.06.2016 Folie/Slide: 3
BAYERN-CHEMIEAktivitäten
SpaceSpace AviationMilitary
Solid Rocket Motors
Air Dominance
Air DominanceGround Based Air Defence
B ttl fi ld E t
Solid Ramjet Propulsion Launch
De-Orbiting
Hypervelocity
Deep Stall Recovery
Gasdynamic Systems
Ser ices
Battlefield Engagement
Air DominanceBattlefield EngagementMaritime Applications
Emergency Systems
C lti & T ti
Testing
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Services Life Cycle Management Consulting & Testing Consulting & Testing
06.06.2016 Folie/Slide: 4
Festtreibstoffe – Double BaseZusammensetzung und Leistungsdaten
• Formulation Nitrocellulose / Nitroglycerine / Plasticizer / Stabilizer / Modifier
• Characteristics
• Invisible and non corrosive exhaust gases (70:1, mass %)
CO 30 - 40 % H2O 5 - 15 %
CO2 30 - 40 % N2 10 - 20 % C (s) 0 1 1 % Pb 0 1 1 %
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06.06.2016 Folie/Slide: 5
Cu (s) 0.1 - 1 % Pb 0.1- 1 %H2 1 - 5 % Pb (l) 0.1 - 1 %
Festtreibstoffe - Composites
• High performance: HTPB AP Al (> 5%)• High performance: HTPB – AP – Al (> 5%)• Reduced smoke: HTPB – AP – Al (< 5%)• Green: HTPB – AP – NaNO3• Gas generator: HTPB AN (phase stabilised)• Gas generator: HTPB – AN (phase stabilised)• Energetic Binder GG GAP – Sr(NO3)2• Fuel rich GG: CTPB – AP – B – Mg – Al • Smokeless: GAP – ADNSmokeless: GAP ADN
• Aluminium, Boron, Magnesium Fuel• Ammonium Dinitramide Oxidizer• Ammonium Nitrate, Ammonium Perchlorate Oxidizer,• Carboxyl Terminated Polybutdiene Inert Binder• Glycidyl Azide Polymer Energetic Binder• Hydroxyl Terminated Polybutadiene Inert Binder• Strontium nitrate Sr(NO3)2 Oxidizer
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06.06.2016 Folie/Slide: 6
( 3)2 • Sodium nitrate NaNO3 Oxidizer
Festtreibstoffe – CompositesLeistungsdaten
Description Isp (70:1)[m/s]
Density [kg/m3]
STANAG P/S
T-range [°C]
High performance 2530 - 2590 1700 - 1840 CC -54+71
Reduced smoke 2280 - 2410 1640 - 1730 AC -54+71
Green (AP / NaNO3) 2160 - 2380 1170 - 1820 AC -54+71
Gas Generator (AN) 1930 1480 - 1520 - -54+71
Energetic Binder GG (GAP) 1850 2290 - -30+71
Fuel Rich GG (Boron) heat value 25-35 MJ / kg 1200 - 1700 CC -54+71
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06.06.2016 Folie/Slide: 7
Schema und Funktion eines Feststoffantriebs
Bild: DLRBild: DLR
Video: YouTube
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06.06.2016 Folie/Slide: 8
Innenballistische Parameter
•
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06.06.2016 Folie/Slide: 9
Bild: Horst W. Köhler - Feststoffraketenantriebe
Beispiele von Treibsatzgeometrien vs. Schubverlauf
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06.06.2016 Folie/Slide: 10
Wirkungsgrad von chemischen Antrieben
Bild: Horst W Köhler Feststoffraketenantriebe
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06.06.2016 Folie/Slide: 11
Bild: Horst W. Köhler - Feststoffraketenantriebe
Beispiele zum Aufbau von Feststoffmotoren
Treibstoff
Anzünder
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06.06.2016 Folie/Slide: 12
BC • Composite Propellant Solid Rocket Motors - Overview
► Propulsion system► Propulsion system• Extensive engineering and design capabilities• Rich portfolio on concepts and solutions • Full testing and verification
► HTPB propellants► HTPB propellants• High performance smoke reduced propellants• High burning rates
► CTPB propellants► Experience with steel and fibre reinforced resin structures► Thermal insulation materials► Double-/Multipulse Technology
• Flight-demonstrated mature solution for LFK-NG • Flight-demonstrated solution for hypervelocity motors
(HFK II case)
► Hypervelocity/high performance motors
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• High strength / lightweight design• Conical motor for Ma-7 technology missile HFK II
06.06.2016 Folie/Slide: 13
BC • Double-Base Propellant Solid Rocket Motors - Overview
• Propulsion system• Extensive engineering and design capabilities• Rich portfolio on concepts and solutions • Full testing and verificationFull testing and verification
• Extruded double-base propellants• Minimum smoke propellant• Wide range of burning rates• Wide range of propellant grain configurations
• High heating resistant cast inhibition • Experience with steel and fibre reinforcedp
resin structures• Boost-sustain motor with high turn-down ratio• Cost-effective solutions for small rocket motors
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Cost effective solutions for small rocket motors
06.06.2016 Folie/Slide: 14
BC • HFK I - Hypervelocity Missile I - high acceleration rocket motor -
Task KE-weapon system predominantly for anti tank application.Application of technology to air-defence missile with dual pulse motor and lateral thrust devices
Customer BAAINBw / BMVg
Technology High performance composite propellantin light weight structure (CFRP-Case).Mi il l it M h 5Missile velocity > Mach 5
Programme Experimental test flights of 5 missilesscope
Mil t D i f t i d t ti t t 1990 1993 Milestones Design, manufacturing and static tests 1990 - 1993
First test flight 1993
Test flight with lateralthrust modules 1995, 1997
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06.06.2016 Folie/Slide: 15
Bayern-Chemie • Air Breathing Propulsion - METEOR / BVRAAM
Task Development and production of a propulsion system for the BVRAAM missile
Customer
Technology
MBDA (UK)
Throttleable ducted rocket (TDR) with high energy boron filled
Programme
g gygas-generatorNozzleless booster
Development and productiongscope
Milestones
p pof > 2000 motors
Development 2000 - 2011
Serial production 2012 ff
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Serial production 2012 ff
06.06.2016 Folie/Slide: 16
Qualifikation STANAG Sled Test
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06.06.2016 Folie/Slide: 17
Qualifikation: Prüfstandsversuch
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06.06.2016 Folie/Slide: 18
