Topic
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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01 May 1987
TL;DR: In this paper, the results of arcjet engine lifetime testing were evaluated for thrusters employing either decomposed N2H4 or cold mixed gases, over a power range of 900 to 2000 W. Attention was given to the compatibility of materials with N 2H4, the dependence of electrode erosion on geometry and flow field, and the erosive effects associated with the power supply.
Abstract: The present evaluation of the results of arcjet engine lifetime testing attempts to deepen understanding of the electrode erosion process, with a view to its minimization. Attention is given to the compatibility of materials with N2H4, the dependence of electrode erosion on geometry and flow field, and the erosive effects associated with the arcjet power supply. Results are presented for thrusters employing either decomposed N2H4 or cold mixed gases, over a power range of 900 to 2000 W.
14 citations
Patent•
30 Jun 1994
TL;DR: A thermal arcjet propulsion plant is particularly constructed for position and orbit corrections in a space flying body or spacecraft as discussed by the authors, where an elongated rod mounted in an electrically insulating manner centrally in the housing forms the cathode which reaches with its tip into a plenum chamber just upstream of the expansion nozzle.
Abstract: A thermal arcjet propulsion plant is particularly constructed for position and orbit corrections in a space flying body or spacecraft. A housing forms an anode and an expansion nozzle. An elongated rod mounted in an electrically insulating manner centrally in the housing forms the cathode which reaches with its tip into a plenum chamber just upstream of the nozzle. Propellant components formed by dissociating ammonia are injected into the plenum chamber. A small gap is provided between the tip of the cathode and the restrictor of the nozzle. An arc is ignited in this gap and the thermal arc energy is taken up by the by propellant. A dissociation chamber for the by propellant is arranged around the housing. The arrangement is such that the chamber in which the gas dissociation takes place is arranged in series with and upstream of the plenum chamber. The cathode is also arranged in series with the restrictor and the nozzle. The cathode is connected through a flexible electrical conductor to an electric power supply. Similarly, the housing forming the anode is connected to the same power supply. The dissociation chamber includes a catalyst for a catalytic and/or thermal dissociation of the ammonia into its components of hydrogen and nitrogen.
14 citations
TL;DR: The radio amateur satellite P3-D, weighing 400 kg, will be launched into a highly elliptical 16-h orbit in 1996, its final orbit control will be performed by a 750-W ammonia arcjet system as discussed by the authors.
Abstract: The radio amateur satellite P3-D, weighing 400 kg, will be launched into a highly elliptical 16-h orbit in 1996. Its final orbit control will be performed by a 750-W ammonia arcjet system. This work describes the arcjet system and its components as well as the qualification and operation philosophy. The implications of the satellite, the planned orbit, and the orbit control strategy for the arcjet propulsion system are also explained. The thruster system has passed two lifetime qualification tests lasting 670 and 1010 cycles with one hour of arcjet operation per cycle, which are briefly discussed.
14 citations
Dissertation•
01 Jan 1994
TL;DR: Thesis (Sc. D. D., Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1994) as discussed by the authors, was the first work of the present paper.
Abstract: Thesis (Sc. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1994.
13 citations
TL;DR: In this paper, an experimental investigation on a low-power dc arcjet with helium propellant was conducted to evaluate the thermal efficiency, to assess the performance of various cathode materials, and to investigate the effects of transpirational cooling from the electrodes.
Abstract: An experimental investigation on a low-power dc arcjet with helium propellant was conducted. Objectives were to evaluate the thermal efficiency, to assess the performance of various cathode materials, and to investigate the effects of transpirational cooling from the electrodes. The anode was made of porous tungsten so that the propellant could be supplied through the anode. The cathode materials used in this experiment were porous tungsten, thoriated tungsten, lanthanum hexaboride, and porous tungsten impregnated with barium oxide (BaO/W). Two discharge modes of low and high voltages were found, which corresponded to low and high thermal efficiency, respectively. The BaO/W cathode was the best of all the tested materials, demonstrating a thermal efficiency as high as 64.9%. The transpirational cooling resulted in a great decrease of the thermal efficiency.
13 citations