HAN-based monopropellant propulsion system with applications
Publisher: National Aeronautics and Space Administration, Publisher: National Technical Information Service, distributor in [Washington, DC], [Springfield, Va
Written in English
- Ammonium nitrates.,
- Compressed gas.
|Other titles||HAN based monopropellant propulsion system with applications|
|Statement||Robert S. Jankovsky and Steven R. Oleson.|
|Series||NASA technical memorandum -- 107407|
|Contributions||Oleson, Steven R., United States. National Aeronautics and Space Administration.|
|The Physical Object|
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HAN-based monopropellant propulsion system with applications Download PDF EPUB FB2
For the analysis, three propulsion system configurations are used to fulfill the mission AV requirements; a SOA nitrogen stored gas system, a SOA hydrazine monopropellant system, and a (projected) HAN-based monopropellant system. Figure 2 shows a schematic of the propulsion systems and Table II provides a breakdown of the assumed component Size: KB.
NASA Technical Memorandum HAN-Based Monopropellant Propulsion System With Applications Robert S. Jankovsky Lewis Research Center Cleveland, Ohio and Steven R.
O1eson NYMA. HAN-Based Monopropellant Propulsion System with Applications how a HAN-based monopropellant propulsion system fulfills small satellite propulsion requirements by providing mass and/or volume. HAN-based monopropellant propulsion system with applications (OCoLC) Material Type: Document, Government publication, National government publication, Internet resource: Document Type: Internet Resource, Computer File: All Authors / Contributors: Robert S Jankovsky; Steven R Oleson; Lewis Research Center.
HAN-based monopropellant propulsion system with applications [microform] / Robert S. Jankovsky and Steven R.
Oleson National Aeronautics and Space Administration ; National Technical Information Service, distributor [Washington, DC]: [Springfield, Va. NASA is developing a new monopropellant propulsion system for small, cost-driven spacecraft with AV requirements in the range of m/sec.
This system is based on a hydroxylammonium nitrate (HAN)/water/fuel monopropellant blend which is extremely dense, environmentally benign, and promises good performance and simplicity.
29 June | Journal of Propulsion and Power, Vol. 34, No. 5 Combustion Characteristics of a Hydroxylammonium-Nitrate-Based Monopropellant Thruster with Discharge Plasma System.
HAN-BASED MONOPROPELLANT ASSESSMENT FOR SPACECRAFT Robert S. Jankovsky Aerospace Engineer NASA Lewis Research Center Cleveland, Ohio Abstract The growing cost of space missions, the need for increased mission performance, and concerns associated with environmental issues are changing rocket design and propellant selection File Size: KB.
Hydroxylammonium-nitrate-based monopropellant thrusters have been continuously researched as a replacement for conventional hydrazine thrusters. An ignition system using the discharge plasma of noble gas, called a discharge plasma system, has been proposed in substitution for the conventional solid by: 4.
The final book chapter is dedicated to an historical survey of the Russian developments in solid rocket propulsion. No matter how impressive from both a theoretical and experimental viewpoint, for a variety of reasons, they are still little known, if not misunderstood, beyond the national barriers.
Feasible Study on Low Frequency Plasma Jet as Ignition System for HAN Based Propellant. Toshiaki Iizuka, Minori Komatsu Novel Glow Plug for Compact High Density Engine Applications Operating on Heavy Fuels.
Benjamin Development of a MEMS-based monopropellant micro Chemical Propulsion System. Markus Gauer, Dimitri Telitschkin, Ulrich. On-Board Chemical Propulsion Technology [Brian D. Reed, Nasa Technical Reports Server (Ntrs)] on *FREE* shipping on qualifying offers.
On-board propulsion functions include orbit insertion, orbit maintenance, constellation maintenance, precision positioning. Progress towards the Development of a Traveling Wave Direct Energy Converter for Aneutronic Fusion Propulsion Applications.
Andrew M. Chap The Effect of Iron Metal Ions and Chelating Agents of Iron on the Thermal Decomposition of HAN-Based Liquid Monopropellant. Rachid Amrousse Aerospace Vehicle Propulsion System Utilizing Enclosed. He will deliver a talk titled "Applications of Nanotechnology in Fuel Energy and Propulsion" The abstract of this work is presented below.
The modern advent of nano- science/technology is usually marked with a lecture delivered by the Noble laureate Richard Feynman in titled “There is Plenty of Room at the Bottom”.
AF-ME HAN based monopropellant Isp: s 12% higher than Hydrazine Specific weight: Hydrazine: Low toxicity, Can not freeze Aerojet, MPS Innovative Propulsion Solutions for Smallsats Ronald A. Spores, et. al., AIAA Busek, BXT-X5 Green Monopropellant Thruster MODEL: GR-1 Thrust: 1N MODEL: MPS Thrust: 1N, Isp: Furthermore, Wu et al characterized a HAN-based monopropellant LTCC microthruster with Ag electrodes used as electrolysis ignitors and catalyst, and reported a thrust of ~ mN.
Finally, in [ 21 ], the feasibility of fabricating a zirconia chemical microthruster through gel casting in. ] [Jankovsky, R., “HAN-Based Monopropellant Assessment for Spacecraft,” AIAA 96–, 32ndAIAA/ASME/SAE/ASEE Joint Propulsion Conference, Lake Buena Vista, FL, July ] Aerojet is currently owned by the company formerly known as the General Tire & Rubber Company, which changed its name to GenCorp in Richard A Yetter, G.
Risha, V. Yang and D. Fedorczyk,"Fundamental studies on electrolytic ignition of advanced han-based liquid propellants for space propulsion systems" M. Wu, V. Yang and Richard A Yetter,"A LTCC burner for studying micro flames". The CubeSat technology that is surveyed in this paper is the propulsion system.
A propulsion system is the primary mobility device of a spacecraft and helps with orbit modifications and attitude control. This paper provides an overview of micro-propulsion technologies that have been developed or are currently being developed for CubeSats.
The thrust history shows a maximum thrust of mN for the currently designed HAN-based liquid monopropellant micro-thruster. The impulse is × 10 −3 Ns. The energy input during the ignition process is J.
Experiments with different ignition voltage. Thermal decomposition of HAN-based monopropellant mixture using advanced mass spectrometer and high speed pyrolysis R.
Amrousse, T. Katsumi, Y. Mishima, and K. Hori. O Thermal cycle study of some phase-stabilized ammonium nitrate S. Date, S. Shoya, A. Toda, and Y. Tanaka. O Thermal decomposition of HAN-based monopropellant mixture using advanced mass spectrometer and high speed pyrolysis Using polymeric fuel as an additive in WAX-based hybrid rocket fuel Validation for a condensed phase reaction model of hydroxylammonium nitrate aqueous based on kinetic analysis.
Flight applications include next generation commercial aircraft, regional, and business jets, military applications, supersonic/hypersonic high speed propulsion applications, commercial and government-sponsored launch systems, and orbital insertion, satellite, and interstellar propulsion.