Results 171 to 180 of about 3,658 (232)

Criteria for Ignition in Monopropellant Engines

Journal of Spacecraft and Rockets, 1985
Nomenclature = interfacial area for heat transfer, 1 = gas specific heat, 60 J/mole K = solid specific heat, 1 .0 J/g K = heat transfer coefficient, 210 J/m-s K = effective thermal conductivity of catalyst bed, 0.30 Ts J/m-s K = gas pressure, atm = gas constant = rate of surface reaction per unit surface area = amount of catalyst surface area per unit ...
J. B. BENZIGER, J. E. STRONG
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Combustion of Blended Monopropellants

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2012
An experimental investigation was conducted to characterize the monopropellant droplet combustion of pure and blended isopropyl nitrate (IPN), suspended on quartz fibers in a quiescent atmosphere. The blends were prepared by mixing IPN with less viscous n-heptane in percentages of 10 to 90% by weight of IPN, and highly viscous dibutyl sebacate (DBS ...
Anirudha Ambekar, Arindrajit Chowdhury
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Lunar Oxygen as Monopropellant

AIP Conference Proceedings, 2008
This paper explores the feasibility of beamed energy propulsion to provide transportation to and from the lunar surface to low lunar orbit using lunar oxygen as propellant. Oxygen, as an Electro‐Thermal Propulsion (ETP) monopropellant, has specific impulse comparing favorably with chemical bipropellants, though not as high as cryogenic LO2+LH2.
Donald G. Johansen, Andrew V. Pakhomov
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Modeling and control for a monopropellant-powered actuator

2014 IEEE/ASME International Conference on Advanced Intelligent Mechatronics, 2014
This paper presents a physics based model for the process of decomposition of hydrogen peroxide on a manganese dioxide catalyst bed. This model is based upon reaction kinetics, and the thermodynamics of the process. An experimental setup is designed, and utilized to validate the model.
Mandar Zope, Arindrajit Chowdhury, Abhishek Gupta   +2 more
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The structure of ammonium oxalohydroxamate – a monopropellant

Acta Crystallographica Section C Crystal Structure Communications, 1988
Abstract. NHn+.C2H3NzO4, Mr= 137.1, triclinic, Pi, a=3-952(1), b=6.772(1), c=9.993(1)A, a= 98.06 (1), fl= 89.96 (1), ~= 106.96 (1) °. V=253.06 A 3, z = 2, 2(Cu Ka) = 1.5418 A, g =15.29 cm -~, D m = 1.805, D x = 1.798 g cm -3, F(000)= 144, T= 293 K, R = 0.048 for 795 observed reflections. The unit cell contains two independent centrosymmetric molecules,
Begum, Sameena A, Jain, VK, Ramakumar, S, Khetrapal, CL   +3 more
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Ignition Mechanisms in Monopropellants

Propellants, Explosives, Pyrotechnics, 1991
AbstractThe sensitivity of liquid monopropellants is examined when subjected to compression ignition, including the case of purposeful sensitization with air bubbles; and frictional heating. The monopropellant is a hydroxylammonium nitrate (HAN)‐based propellant.
Neale A. Messina, Larry S. Ingram, Marek Tarczynski, John D. Knapton   +3 more
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Case Based Reasoning for Monopropellant Propulsion

2007 IEEE International Fuzzy Systems Conference, 2007
Multi-agent prognostic health and usage monitoring (Multi-PHUM) is proposed in the paper for use in fault diagnosis and prognosis. Georgia Tech has developed a Matlab simulation model of monopropellant propulsion for studying fault diagnosis. Here we apply Multi-PHUM to the fault diagnosis of the monopropellant propulsion system.
Hamid R. Berenji, Yan Wang, George J. Vachtsevanos   +2 more
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Monopropellant Decomposition in a Reactive Atmosphere†

Combustion Science and Technology, 1978
Abstract The quasi-steady decomposition of a monopropellant is considered when the monopropellant reacts with the ambient atmosphere in a one-step irreversible process. The solution is characterized by the variation of the vaporization rate M with two Damkohler numbers, D 1 and D 2, the first a measure of the monopropellant reaction rate and the second
J. D. BUCKMASTER, A. K. KAPILA, G. S. S. LUDFORD   +2 more
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Evaluating the Miniaturisation of a Monopropellant Thruster

42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2006
In this paper the miniaturisation of a hydrogen peroxide monopropellant thruster is considered. The performance of the thruster is characterised with reference to the characteristic exhaust velocity, c* and the decomposition temperature achieved. The use of two different catalyst beds is investigated: a monolithic catalyst bed and a compressed powder ...
Sarah Barley, Phil Palmer, Ian Coxhill
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On the burning of single drops of monopropellants

1955
U.S. Navy (U.S.N.) author.
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