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.

Solar cell degradation during the 26-kilowatt Electric Propulsion Space Experiment flight

Abstract: The Electric Propulsion Space Experiment (ESEX) was launched and operated in early 1999 to demonstrate the compatibility and readiness of a 30-kW class ammonia arcjet for satellite propulsion applications. As part of thisflight, an array of onboard contamination sensors assessed the effects of the arcjet on the spacecraft. The sensors consisted of microbalances to measure material deposition, radiometers to assess material degradation due to thermal radiation, and solar cell segments to investigate solar array degradation. During firings, the solar cell segments showed decreasing open-circuit voltages, probably due to additional electrical load imposed by currents through the plume plasma. Over eight firings of the ESEX arcjet, and 33-min, 44-s operating time, the solar cells exhibited a 3% decrease in short-circuit current, attributable to decreased solar transmission of the cover glass. The spacecraft's main solar arrays, however, exhibited no degradation in performance. Contamination affected only the solar cell sensor segments placed near the thruster exhaust nozzle. In the backplane of the thruster, where the main arrays are located, no deleterious effects occurred, indicating that although engineering measures may be required for equipment in the immediate vicinity of the thruster, the arcjet environment is generally benign.

Electric propulsion for lunar exploration and lunar base development

Abstract: Using electric propulsion to deliver materials to lunar orbit for the development and construction of a lunar base was investigated Because the mass of the base and its life-cycle resupply mass are large, high specific impulse propulsion systems may significantly reduce the transportation system mass and cost Three electric propulsion technologies (arcjet, ion, and magnetoplasmadynamic (MPD) propulsion) were compared with oxygen/hydrogen propulsion for a lunar base development scenario Detailed estimates of the orbital transfer vehicles' (OTV's) masses and their propellant masses are presented The fleet sizes for the chemical and electric propulsion systems are estimated Ion and MPD propulsion systems enable significant launch mass savings over O2/H2 propulsion Because of the longer trip time required for the low-thrust OTV's, more of them are required to perform the mission model By offloading the lunar cargo from the manned O2/H2 OTV missions onto the electric propulsion OTV's, a significant reduction of the low Earth orbit (LEO) launch mass is possible over the 19-year base development period

Preliminary Study of High Power Hydrogen Electric Propulsion for the Space Exploration

Abstract: High power electric propulsion system is strongly required for future orbital space transportation. MPD (Magneto-Plasma-Dynamic) thrusters and DC (Direct Current) arcjets with hydrogen as a propellant are promising candidates for the missions because of their high performance and adaptability to high power operation. However, to use hydrogen for long term orbital missions, its storage in orbit is crucial issue to be considered. Firstly, we proposed a hydrogen storage and feed system for electric thrusters by applying our technologies derived from the liquid hydrogen launch vehicles. Secondly, we present R&D activities of hydrogen MPD thruster and DC arcjet, especially focusing on the improvement of their performance and durability. Then, development strategy of hydrogen electric thrusters is also discussed. Finally, advantages of hydrogen electric thruster were shown compared with conventional xenon thrusters through mission analyses of lunar orbit insertion and GTO-GEO transportation.