Hans Immich - Academia.edu (original) (raw)

Papers by Hans Immich

Research paper thumbnail of Advanced ceramic matrix composite materials for current and future propulsion technology applications

Acta Astronautica, 2004

Current rocket engines, due to their method of construction, the materials used and the extreme l... more Current rocket engines, due to their method of construction, the materials used and the extreme loads to which they are subjected, feature a limited number of load cycles. Various technology programmes in Europe are concerned, besides developing reliable and rugged, low cost, throwaway equipment, with preparing for future reusable propulsion technologies. One of the key roles for realizing reusable engine components is the use of modern and innovative materials. One of the key technologies which concern various engine manufacturers worldwide is the development of ÿbre-reinforced ceramics-ceramic matrix composites. The advantages for the developers are obvious-the low speciÿc weight, the high speciÿc strength over a large temperature range, and their great damage tolerance compared to monolithic ceramics make this material class extremely interesting as a construction material. Over the past years, the Astrium company (formerly DASA) has, together with various partners, worked intensively on developing components for hypersonic engines and liquid rocket propulsion systems. In the year 2000, various hot-ÿring tests with subscale (scale 1:5) and full-scale nozzle extensions were conducted. In this year, a further decisive milestone was achieved in the sector of small thrusters, and long-term tests served to demonstrate the extraordinary stability of the C/SiC material. Besides developing and testing radiation-cooled nozzle components and small-thruster combustion chambers, Astrium worked on the preliminary development of actively cooled structures for future reusable propulsion systems. In order to get one step nearer to this objective, the development of a new ÿbre composite was commenced within the framework of a regionally sponsored programme. The objective here is to create multidirectional (3D) textile structures combined with a cost-e ective inÿltration process. Besides material and process development, the project also encompasses the development of special metal/ceramic and ceramic/ceramic joining techniques as well as studying and verifying non destructive investigation processes for the purpose of testing components.

Research paper thumbnail of Technology developments for expander cycle engine thrust chambers

35th Joint Propulsion Conference and Exhibit, 1999

Research paper thumbnail of Plug nozzles: summary of flow features and engine performance - Overview of RTO/AVT WG 10 subgroup 1

40th AIAA Aerospace Sciences Meeting & Exhibit, 2002

Public reporting burden for the collection of information is estimated to average 1 hour per resp... more Public reporting burden for the collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to a penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number.

Research paper thumbnail of Combustion chamber with increased heat input into a cooling device

Beschrieben wird eine Brennkammer fur ein Raketentriebwerk zum Ausstos einer heisen Gasstromung m... more Beschrieben wird eine Brennkammer fur ein Raketentriebwerk zum Ausstos einer heisen Gasstromung mit einer Kuhleinrichtung sowie einer an die Kuhleinrichtung zum Inneren der Brennkammer hin angrenzende inneren Brennkammerwand. Die innere Brennkammerwand weist Vertiefungen auf, die derart ausgebildet sind, dass eine stabile Grenzschicht der Gasstromung, die im Betrieb der Brennkammer im Bereich der inneren Brennkammerwand ausgebildet wird, im Bereich der Vertiefungen stromungstechnisch destabilisiert wird. Die Vertiefungen sind als Rillen ausgebildet, die um maximal 45° gegen die Umfangsrichtung der Brennkammer geneigt sind.

Research paper thumbnail of Thrust chamber technology developments for future launch vehicle liquid rocket engines

37th Joint Propulsion Conference and Exhibit, 2001

At Astrium, Space Infrastructure Division (SI), enabling technology developments for next generat... more At Astrium, Space Infrastructure Division (SI), enabling technology developments for next generation semi-reusable and reusable liquid rocket engines are being undertaken. This paper summarises the present status and the main results of these technology developments for the following main thrust chamber components:

Research paper thumbnail of Technology developments for cryogenic rocket engines

36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2000

Research paper thumbnail of Technology developments for thrust chambers of future launch vehicle liquid rocket engines

Acta Astronautica, 2003

In this paper an overview of recent technology developments for thrust chambers of future launch ... more In this paper an overview of recent technology developments for thrust chambers of future launch vehicle liquid rocket engines at Astrium, Space Infrastructure Division (SI), is shown.The main technology. developments shown in this paper are: •Technologies Technologies for enhanced heat transfer to the coolant for expander cycle engines•Advanced injector head technologies•Advanced combustion chamber manufacturing technologies.The main technologies for enhanced heat transfer investigated by subscale chamber hot-firing tests are: •Increase of chamber length•Hot gas side ribs in the chamber•Artificially increased surface roughness.The developments for advanced injector head technologies were focused on the design of a new modular subscale chamber injector head. This injector head allows for an easy exchange of different injection elements: By this, cost effective hot-fire tests with different injection element concepts can be performed.The developments for advanced combustion chamber manufacturing technologies are based on subscale chamber tests with a new design of the Astrium subscale chamber. The subscale chamber has been modified by introduction of a segmented cooled cylindrical section which gives the possibility to test different manufacturing concepts for cooled chamber technologies by exchanging the individual segments. The main technology efforts versus advanced manufacturing technologies shown in this paper are: •Soldering techniques•Thermal barrier coatings for increased chamber life.A new technology effort is dedicated especially to LOX/Hydrocarbon propellant combinations. Recent hot fire tests on the subscale chamber with Kerosene and Methane as fuel have already been performed. A comprehensive engine system trade-off between the both propellant combinations (Kerosene vs. Methane) is presently under preparation.

Research paper thumbnail of Ceramic Matrix Composites: A Challenge in Space‐Propulsion Technology Applications

… Journal of Applied …, 2005

Schmidt, S., Beyer, S., Immich, H., Knabe, H., Meistring, R. and Gessler, A.(2005), Ceramic Matri... more Schmidt, S., Beyer, S., Immich, H., Knabe, H., Meistring, R. and Gessler, A.(2005), Ceramic Matrix Composites: A Challenge in Space-Propulsion Technology Applications. International Journal of Applied Ceramic Technology, 2: 85–96. doi: 10.1111/j. 1744-7402.2005. 02010 ...

Research paper thumbnail of Cooling for a combustion chamber for rockets

Research paper thumbnail of Combustion chamber with enhanced heat transfer to a cooling device

Research paper thumbnail of Rocket engine combustion chamber with enhanced heat transfer to cooling jacket

Research paper thumbnail of Technologies for Thrust Chambers of Future Launch Vehicle Liquid Rocket Engines

38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2002

Research paper thumbnail of Impulsive motion of a suspension: Effect of antisymmetric stresses and particle rotation

International Journal of Multiphase Flow, 1980

Research paper thumbnail of Critical assessment of the linear plug nozzle concept

37th Joint Propulsion Conference and Exhibit, 2001

Research paper thumbnail of Plug engine systems for future launch vehicle applications

29th Joint Propulsion Conference and Exhibit, 1993

Research paper thumbnail of FESTIP technology developments in liquid rocket propulsion for reusable launch vehicles

32nd Joint Propulsion Conference and Exhibit, 1996

Research paper thumbnail of Status of the FESTIP rocket propulsion technology programme

33rd Joint Propulsion Conference and Exhibit, 1997

Research paper thumbnail of Cryogenic liquid rocket engine technology developments within the German National Technology Programme

33rd Joint Propulsion Conference and Exhibit, 1997

Research paper thumbnail of Cryogenic engines in Western Europe - From exploratory developments to Vulcain and Vinci

35th Joint Propulsion Conference and Exhibit, 1999

Research paper thumbnail of Advanced Rocket Nozzles

Journal of Propulsion and Power, 1998

Research paper thumbnail of Advanced ceramic matrix composite materials for current and future propulsion technology applications

Acta Astronautica, 2004

Current rocket engines, due to their method of construction, the materials used and the extreme l... more Current rocket engines, due to their method of construction, the materials used and the extreme loads to which they are subjected, feature a limited number of load cycles. Various technology programmes in Europe are concerned, besides developing reliable and rugged, low cost, throwaway equipment, with preparing for future reusable propulsion technologies. One of the key roles for realizing reusable engine components is the use of modern and innovative materials. One of the key technologies which concern various engine manufacturers worldwide is the development of ÿbre-reinforced ceramics-ceramic matrix composites. The advantages for the developers are obvious-the low speciÿc weight, the high speciÿc strength over a large temperature range, and their great damage tolerance compared to monolithic ceramics make this material class extremely interesting as a construction material. Over the past years, the Astrium company (formerly DASA) has, together with various partners, worked intensively on developing components for hypersonic engines and liquid rocket propulsion systems. In the year 2000, various hot-ÿring tests with subscale (scale 1:5) and full-scale nozzle extensions were conducted. In this year, a further decisive milestone was achieved in the sector of small thrusters, and long-term tests served to demonstrate the extraordinary stability of the C/SiC material. Besides developing and testing radiation-cooled nozzle components and small-thruster combustion chambers, Astrium worked on the preliminary development of actively cooled structures for future reusable propulsion systems. In order to get one step nearer to this objective, the development of a new ÿbre composite was commenced within the framework of a regionally sponsored programme. The objective here is to create multidirectional (3D) textile structures combined with a cost-e ective inÿltration process. Besides material and process development, the project also encompasses the development of special metal/ceramic and ceramic/ceramic joining techniques as well as studying and verifying non destructive investigation processes for the purpose of testing components.

Research paper thumbnail of Technology developments for expander cycle engine thrust chambers

35th Joint Propulsion Conference and Exhibit, 1999

Research paper thumbnail of Plug nozzles: summary of flow features and engine performance - Overview of RTO/AVT WG 10 subgroup 1

40th AIAA Aerospace Sciences Meeting & Exhibit, 2002

Public reporting burden for the collection of information is estimated to average 1 hour per resp... more Public reporting burden for the collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to a penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number.

Research paper thumbnail of Combustion chamber with increased heat input into a cooling device

Beschrieben wird eine Brennkammer fur ein Raketentriebwerk zum Ausstos einer heisen Gasstromung m... more Beschrieben wird eine Brennkammer fur ein Raketentriebwerk zum Ausstos einer heisen Gasstromung mit einer Kuhleinrichtung sowie einer an die Kuhleinrichtung zum Inneren der Brennkammer hin angrenzende inneren Brennkammerwand. Die innere Brennkammerwand weist Vertiefungen auf, die derart ausgebildet sind, dass eine stabile Grenzschicht der Gasstromung, die im Betrieb der Brennkammer im Bereich der inneren Brennkammerwand ausgebildet wird, im Bereich der Vertiefungen stromungstechnisch destabilisiert wird. Die Vertiefungen sind als Rillen ausgebildet, die um maximal 45° gegen die Umfangsrichtung der Brennkammer geneigt sind.

Research paper thumbnail of Thrust chamber technology developments for future launch vehicle liquid rocket engines

37th Joint Propulsion Conference and Exhibit, 2001

At Astrium, Space Infrastructure Division (SI), enabling technology developments for next generat... more At Astrium, Space Infrastructure Division (SI), enabling technology developments for next generation semi-reusable and reusable liquid rocket engines are being undertaken. This paper summarises the present status and the main results of these technology developments for the following main thrust chamber components:

Research paper thumbnail of Technology developments for cryogenic rocket engines

36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2000

Research paper thumbnail of Technology developments for thrust chambers of future launch vehicle liquid rocket engines

Acta Astronautica, 2003

In this paper an overview of recent technology developments for thrust chambers of future launch ... more In this paper an overview of recent technology developments for thrust chambers of future launch vehicle liquid rocket engines at Astrium, Space Infrastructure Division (SI), is shown.The main technology. developments shown in this paper are: •Technologies Technologies for enhanced heat transfer to the coolant for expander cycle engines•Advanced injector head technologies•Advanced combustion chamber manufacturing technologies.The main technologies for enhanced heat transfer investigated by subscale chamber hot-firing tests are: •Increase of chamber length•Hot gas side ribs in the chamber•Artificially increased surface roughness.The developments for advanced injector head technologies were focused on the design of a new modular subscale chamber injector head. This injector head allows for an easy exchange of different injection elements: By this, cost effective hot-fire tests with different injection element concepts can be performed.The developments for advanced combustion chamber manufacturing technologies are based on subscale chamber tests with a new design of the Astrium subscale chamber. The subscale chamber has been modified by introduction of a segmented cooled cylindrical section which gives the possibility to test different manufacturing concepts for cooled chamber technologies by exchanging the individual segments. The main technology efforts versus advanced manufacturing technologies shown in this paper are: •Soldering techniques•Thermal barrier coatings for increased chamber life.A new technology effort is dedicated especially to LOX/Hydrocarbon propellant combinations. Recent hot fire tests on the subscale chamber with Kerosene and Methane as fuel have already been performed. A comprehensive engine system trade-off between the both propellant combinations (Kerosene vs. Methane) is presently under preparation.

Research paper thumbnail of Ceramic Matrix Composites: A Challenge in Space‐Propulsion Technology Applications

… Journal of Applied …, 2005

Schmidt, S., Beyer, S., Immich, H., Knabe, H., Meistring, R. and Gessler, A.(2005), Ceramic Matri... more Schmidt, S., Beyer, S., Immich, H., Knabe, H., Meistring, R. and Gessler, A.(2005), Ceramic Matrix Composites: A Challenge in Space-Propulsion Technology Applications. International Journal of Applied Ceramic Technology, 2: 85–96. doi: 10.1111/j. 1744-7402.2005. 02010 ...

Research paper thumbnail of Cooling for a combustion chamber for rockets

Research paper thumbnail of Combustion chamber with enhanced heat transfer to a cooling device

Research paper thumbnail of Rocket engine combustion chamber with enhanced heat transfer to cooling jacket

Research paper thumbnail of Technologies for Thrust Chambers of Future Launch Vehicle Liquid Rocket Engines

38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2002

Research paper thumbnail of Impulsive motion of a suspension: Effect of antisymmetric stresses and particle rotation

International Journal of Multiphase Flow, 1980

Research paper thumbnail of Critical assessment of the linear plug nozzle concept

37th Joint Propulsion Conference and Exhibit, 2001

Research paper thumbnail of Plug engine systems for future launch vehicle applications

29th Joint Propulsion Conference and Exhibit, 1993

Research paper thumbnail of FESTIP technology developments in liquid rocket propulsion for reusable launch vehicles

32nd Joint Propulsion Conference and Exhibit, 1996

Research paper thumbnail of Status of the FESTIP rocket propulsion technology programme

33rd Joint Propulsion Conference and Exhibit, 1997

Research paper thumbnail of Cryogenic liquid rocket engine technology developments within the German National Technology Programme

33rd Joint Propulsion Conference and Exhibit, 1997

Research paper thumbnail of Cryogenic engines in Western Europe - From exploratory developments to Vulcain and Vinci

35th Joint Propulsion Conference and Exhibit, 1999

Research paper thumbnail of Advanced Rocket Nozzles

Journal of Propulsion and Power, 1998