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.

Low Bus Voltage Hydrazine Arcjet System for Geostationary Satellites

Abstract: The capabilities of arcjet propulsion systems were recently extended to accommodate operation on the NASD A Data Relay Test Satellite (DRTS) providing a power bus voltage between 31 and 51.5 VDC. This paper summarizes the newly attained qualification status of the MR 509-A/B arcjet system demonstrating the flexibility of the current design. A redesign of the Power Processing Unit (PPU) became necessary as well as a delta-qualification of the thruster to validate spacecraft integration, and to provide compliance with the DRTS satellite environmental requirements. Two types of thrusters with different thrust levels were made available to meet mission requirements. The delta-qualification included a pyro-shock test, vibration tests to a higher level than previously tested, and performance mapping beyond the original range. Included in the paper is an assessment of the PPU performance characteristics as well as the discussion of the system operation and system telemetry.

Tungsten and Molybdenum Ablation Modeling for Re-entry Applications

Abstract: Refractory metals are attractive candidates for re-entry vehicle nosetips due to their high resistance to water droplet and ice particle erosion. Ablation models are presented for tungsten, tungsten/25% rhenium, and molybdenum, including gas diffusion-limited thermochemical ablation and liquid phase removal. Chemical eqtilibrium is assumed in the gas phase with kinetics for tungsten ablation considered only at the ablating surface. These models have been incorporated into computer programs that also include shape change, boundarylayer transition, surface roughness, and two-dimensional transient conduction. Good correlation for highand low-pressure arcjet tests, ballistic range firings, and sounding rocket flights has been obtained with these models.

Numerical simulation of a hydrogen arcjet

Abstract: The two-dimensional, axisymmetric, nonequilibrium ionizing and reacting flow in a hydrogen arcjet thruster is simulated numerically using the linearized block implicit method. A single ionic species (H), single temperature (i.e., equal electron and heavy particle temperatures), and variable properties are used in this formulation to solve the governing equations of mass, species, momentum, and energy. The current distribution is obtained by solving the magnetic diffusion equation at each time step of the time-marching scheme. As an illustration, a hydrogen arcjet having an exit-to-throat area ratio of 25 (nominal 30-kW geometry) is studied. It is found that the species in order of their abundance at the centerline of the exit plane of the thruster consist of atomic hydrogen (H), ions (H), and electrons (e~), and molecular hydrogen (H2), respectively. As expected, near the colder walls of the anode at the exit plane, this abundance shifts in favor of molecular hydrogen, atomic hydrogen, H, and electrons, respectively.