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Arcjet rocket

About: Arcjet rocket is a research topic. Over the lifetime, 1121 publications have been published within this topic receiving 9687 citations. The topic is also known as: Arcjet.


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Proceedings ArticleDOI
14 Jan 2002

13 citations

Proceedings ArticleDOI
10 Jul 2005
TL;DR: In this article, a target-based measurement system has been developed and the thrust produced by a T6 ion engine hollow cathode has been evaluated, using argon and krypton as propellants, for discharge current values of 5 -25 A and a wide range of mass flow rates.
Abstract: *† ‡ A target -based measurement system has been developed and the thrust produced by a T6 ion engine hollow cathode has been evaluated, using argon and krypton as propellants, for discharge current values of 5 -25 A and a wide range of mass flow rates. The calculated values of specific impulse, which are higher for argon , a re generally in excess of those that could be attributed to heating a gas to the rmal equilibrium with the walls. This seem s to suggest , as a first hypothesis, an arcjet -like operation mechanism .

13 citations

Journal ArticleDOI
TL;DR: In this paper, a four-stage differentially pumped arcjet system generates a fully ionized current-free 1m-long plasma column of uniform density 1013 ≲ne≲1015 cm−3 and temperature Ti∼Te∼1-7 eV confined by an axial magnetic field up to 9 kG.
Abstract: A four‐stage differentially pumped arcjet system generates a fully ionized current‐free 1‐m‐long plasma column of uniform density 1013 ≲ne≲1015 cm−3 and temperature Ti∼Te∼1–7 eV confined by an axial magnetic field up to 9 kG. The first three stages consist of an arc chamber, a separation chamber, and an experimental chamber. The addition of a fourth stage converts the device into a double‐ended differentially pumped system; it ensures the uniformity of the plasma column in high‐density plasma operation. The properties of the four‐stage differentially pumped plasma system are reported.

13 citations

Journal ArticleDOI
TL;DR: The relative atomic hydrogen concentrations measured here are calibrated with an earlier calorimetric determination of the feedstock hydrogen dissociation to provide quantitative hydrogen-atom concentration distributions.
Abstract: Atomic hydrogen in the plume of a dc-arcjet plasma is monitored by use of two-photon excited laser-induced fluorescence (LIF) during the deposition of diamond film. The effluent of a dc-arc discharge in hydrogen and argon forms a luminous plume as it flows through a converging–diverging nozzle into a reactor. When a trace of methane (<2%) is added to the flow in the diverging part of the nozzle, diamond thin film grows on a water-cooled molybdenum substrate from the reactive mixture. LIF of atomic hydrogen in the arcjet plume is excited to the 3S and 3D levels with two photons near 205 nm, and the subsequent fluorescence is observed at Balmer-α near 656 nm. Spatially resolved LIF measurements of atomic hydrogen are made as a function of the ratio of hydrogen to argon feedstock gas, methane addition, and reactor pressure. At lower reactor pressures, time-resolved LIF measurements are used to verify our collisional quenching correction algorithm. The quenching rate coefficients for collisions with the major species in the arcjet (Ar, H, and H2) do not change with gas temperature variations in the plume (T < 2300 K). Corrections of the LIF intensity measurements for the spatial variation of collisional quenching are important to determine relative distributions of the atomic hydrogen concentration. The relative atomic hydrogen concentrations measured here are calibrated with an earlier calorimetric determination of the feedstock hydrogen dissociation to provide quantitative hydrogen-atom concentration distributions.

13 citations

Patent
02 Oct 1998
TL;DR: In this article, a solid rocket propulsion formulation with a burn rate slope of less than about 0.15 ips/psi (2.54 cms/69.102Pa) and a temperature sensitivity of more than 0.5 %/°F (0.15 %/0.56 °C) is provided.
Abstract: A solid rocket propellant formulation with a burn rate slope of less than about 0.15 ips/psi (2.54 cms/69.102Pa) over a substantial portion of a pressure range of about 1,000 psi (69.102Pa) to about 7,000 psi (69.102Pa) and a temperature sensitivity of less than about 0.15 %/°F (0.15 %/0.56 °C) is provided. A high performance solid propellant rocket motor including the solid rocket propellant formulation is also provided. The rocket motor is encased in a high strength low weight motor casing which is further equipped with a nozzle throat constructed of material that has an erosion rate not more than about 2 to about 3 mils (2.54.10-3cm) per second during motor operation. The solid rocket propellant formulation can be cast in a grain pattern such that an all-boost thrust profile is achieved.

13 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202315
202211
20215
202010
20193
201811