Decomposing solid micropropulsion nozzle performance issues
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National Aeronautics and Space Administration, Glenn Research Center, Available from the NASA Center for Aerospace Information, National Technical Information Service [distributor , [Cleveland, Ohio], Hanover, MD, Springfield, VA
Spacecraft propulsion., Solid propellants., Miniaturization., Thrustors., Nozzle design., Nozzle geometry., Nozzle effici
|Series||NASA/TM -- 2003-212225., NASA technical memorandum -- 212225.|
|Contributions||NASA Glenn Research Center.|
|The Physical Object|
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NASA Glenn Research Center has envisioned a micropropulsion concept that utilizes decomposing solid propellants for a valveless, leak-free propulsion system.
Decomposing Solid Micropropulsion Nozzle Performance Issues. Brian Reed National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio Abstract Micropropulsion technology is essential to the success of miniaturized spacecraft and can provide ultra-precise propulsion for small spacecraft.
Get this from a library. Decomposing solid micropropulsion nozzle performance issues. [Brian D Reed; NASA Glenn Research Center.]. NASA Glenn Research Center has envisioned a micropropulsion concept that utilizes decomposing solid propellants for a valveless, leak-free propulsion system.
Among the technical challenges of this decomposing solid micropropulsion concept is optimization of miniature, rectangular : Brian Reed. A decomposing solid thruster concept, which creates a more benign thermal and chemical environment than solid propellant combustion, while maintaining performance similar to solid combustion, is.
In the helium series, nozzle performance peaked for the smallest nozzle tested area ratio For both gases, there was a secondary performance peak above area ratio Author: Manish Jugroot. In addition, the large surface area-to-volume ratio characteristic of MEMS and the high thermal conductivity of the solid portion of the nozzle component makes the heat exchange at the inner wall of the nozzle a key aspect, as it drives the performance to a large by: The continuum method with slip boundary conditions has shown good performance in simulating the formation of a boundary layer inside the nozzle.
However, in the nozzle exit lip region, the DSMC. Micropropulsion for Small Spacecraft Volume of Progress in astronautics and aeronautics: Editor: Michael Matthew Micci: Publisher: AIAA, ISBN:Length: pages: Export Citation: BiBTeX EndNote RefMan.
This paper discusses on-board chemical propulsion technology, including bipropellants, monopropellants, and micropropulsion. Decomposing Solid Micropropulsion Nozzle Performance Issues.
A subliming solid microthruster consists of the propellant tank, the microvalve, microfilter, micro-nozzle, and other components. Its performance figures include: specific impulse 50–75 seconds, thrust mN, power. In this paper, both DSMC and Navier–Stokes computational approaches were applied to study micronozzle flow.
The effects of inlet condition, wall boundary condition, Reynolds number, micronozzle geometry and Knudsen number on the micronozzle flow field and propulsion performance were studied in detail.
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It is found that within the Knudsen number range under Cited by: Development of flow and heat transfer models for the carbon fiber rope in nozzle joints of the space Shuttle Reusable Solid Rocket Motor Qunzhen Wang, Mark Ewing. A review of MEMS micropropulsion systems applicable to CubeSats and PocketQubes.
these devices use nitrogen as the propellant to evaluate the performance of the nozzle and water to prove the concept in terms of vaporization or even as the actual or solid phase. The gas passes through a nozzle and it is accelerated to high velocities Cited by: MEMS-based microthrusters are now introduced and fabricated to meet micropropulsion requirements especially for the attitude control of the nanosatellites.
The key to the development of these microsystems lies in the generation of extremely accurate thrust by: Even along the nozzle wall similar trend was repeated but the Mach drop in the diverging section was faster than along the axis due to flow separation along the nozzle wall.
1 Bar ï „P SL 2 Bar ï „P SL 3 Bar ï „P SL 4 Bar ï „P SL M ac h Nu m be r Position along Cited by: 9. The micro-nozzle is an important component of micropropulsion system, which is used to increase the velocity of gas flow.
The structure of micro-nozzle has a significant impact on the performance of micropropulsion system [3, 4]. However, manufacturing 3D micro-nozzle has significant challenges due to the small size and large dimension changes Cited by: 2.
A cold gas thruster (or a cold gas propulsion system) is a type of rocket engine which uses the expansion of a (typically inert) pressurized gas to generate opposed to traditional rocket engines, a cold gas thruster does not house any combustion and therefore has lower thrust and efficiency compared to conventional monopropellant and bipropellant rocket engines.
Reliability of freestanding polysilicon microheaters to be used as igniters in solid propellant microthrusters Danick Briand∗, Phuong Quyenˆ Pham, Nicolaas F. de Rooij Institute of Microtechnology, University of Neuchatel,ˆ Rue Jaquet-Droz 1, P.O. BoxCH Neuchˆatel, Switzerland. Effect of Three-Dimensional Surface Topography on Gas Flow in Rough Micronozzles In addition, the effect of 3D surface topography on performance is also investigated.
Issue Section: Fundamental Issues and Canonical Flows. Keywords: Gas-solid, Micro Solid–Gas Surface Effect on the Performance of a MEMS-Class Nozzle for Micropropulsion, Cited by: 7. These have been outlined at an inaugural International Workshop on Micropropulsion and Cubesats, MPCS, a joint effort between Plasma Sources and Application Centre/Space Propulsion Centre (Singapore) and the Micropropulsion and Nanotechnology Lab, the G.
Washington University (USA) devoted to miniaturized space propulsion systems, and Cited by: Performance Solid Rocket Motor (SRH) Submerged Nozzle/Combustion Cavity Flowfield Assessment." The NASA-MSFC Contracting Officer's Representative for this contract was Dr.
Terry F. Greenwood, ED33, Chief of the Induced Environment Branch, Aerophysics Division, of the Structures and Dynamics Laboratory.
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ii LOCKHEED-HUNTSVILLE ENGINEERING CENTERCited by: 1. inclusion on high-performance nanosatellites but also for high-demanding future space missions of larger sizes.
By using differently sized nozzles in parallel systems the dynamic range of a cold gas micropropulsion system can be quite wide (e.g. 0 – 10 mN), while the smallest nozzle. Direct simulation Monte Carlo model of Low Reynolds number nozzle flows.
Optimum Nozzle Angle of a Micro Solid-Propellant Thruster. Nanoscale and Microscale Thermophysical Engineering, Vol. 15, No. Effects of Wavy Surface Roughness on the Performance of by: If the nozzle flow is subsonic, then the exit pressure coincides with the discharge pressure, e = p 0, at the p steady state (if at an initial state they were not equal, the time it would take to equalise is of the order of the nozzle length divided by the sound speed), and the other variables would be obtained from the isentropic relations, i.e.:File Size: KB.
Analysis, Fabrication and Testing of a MEMS-based Micropropulsion System by Robert L. Bayt FDRL TR Fluid Dynamics Research Laboratory Department of Aeronautics and Astronautics Massachusetts Institue of Technology Cambridge, MA June Rocket engines produce thrust by the expulsion of an exhaust fluid that has been accelerated to high speed through a propelling fluid is usually a gas created by high pressure (to-4,pound-per-square-inch (10 to bar)) combustion of solid or liquid propellants, consisting of fuel and oxidiser components, within a combustion chamber.
About the Author. Michael M. Micci is a professor of Aerospace Engineering at Pennsylvania State University. His research areas include solid propellant, liquid propellant, and electric rocket propulsion.
He received his B.S. and M.S. degrees in aeronautical and astronautical engineering from the University of Illinois at Urbana-Champaign Cited by: Aerospace, an international, peer-reviewed Open Access journal. Dear Colleagues, Miniaturized spacecraft in the nano-satellite class, such as CubeSats or PocketQubes, are making access to space more and more easy, fast, and cheap, especially with the recent developments in miniaturization technologies.
The micro-nozzle is an important component of the micropropulsion system for accelerating the gas flow. However, the 3D ceramic micro-nozzle is difficult to machine due to its small complex structure and high hardness of by: 2.
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benefits, include chemical propellants, both liquid and solid and electric propulsion concepts, with the focus on electro-thermal concepts. A recent review of micropropulsion systems for formation flying applications can be found in Reichbach et al.
(). As File Size: 1MB.American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Design and Fabrication of MEMS-Based Micropropulsion Devices. at JPL. Juergen Muellera, Eui-Hyeok Yanga, Amanda Greena, Victor Whitea, as well as performance.
Since nozzle throat sizes only a few microns in diameter may be machined, and thrust generated by a chemical or electrothermal device is directly proportional to nozzle throat area.
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