Plume Impingement Analysis for the European Service Module Propulsion System

Yim, John T.; Sibe, Fabien; Lerardo, Nicola

doi:10.2514/6.2014-3883

Cited by 6 publications

(6 citation statements)

References 13 publications

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“…The ESM RCS engines are arranged in an orthogonal configuration, and the ESM engine location was driven primarily by accommodation of the new solar array "x-wing" configuration in its stowed condition as well as the need to minimize plume impingement from the RCS engines on the solar arrays. 11 Having the control authority and precision requirements allowed AD&S to design an RCS engine configuration that balances the vehicle controllability needs with the solar array concerns. The ATV-heritage RCS engines selected for ESM have twice the thrust of the CxP SM RCS engines, which is a benefit to the control authority available.…”

Section: Rcs Enginesmentioning

confidence: 99%

Evolution of MPCV Service Module Propulsion and GN&C Interface Requirements between Constellation and European Service Module

Hickman¹

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The Orion Multi-Purpose Crew Vehicle Service Module Propulsion Subsystem provides propulsion for the integrated Crew and Service Module. Updates in the exploration architecture between Constellation and MPCV as well as NASA's partnership with the European Space Agency have resulted in design changes to the SM Propulsion Subsystem and updates to the Propulsion interface requirements with Guidance Navigation and Control. This paper focuses on the Propulsion and GNC interface requirement updates between the Constellation Service Module and the European ServiceModule and how the requirement updates were driven or supported by architecture updates and the desired use of hardware with heritage to United States and European spacecraft for the Exploration Missions, EM-1 and EM-2.

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Section: Rcs Enginesmentioning

confidence: 99%

Evolution of MPCV Service Module Propulsion and GN&C Interface Requirements between Constellation and European Service Module

Hickman¹

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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“…Additional computational models, including direct simulation Monte Carlo (DSMC), ray-tracing and particle-tracing methods, have been developed to aid in the prediction of plume interaction with the ambient environment and with spacecraft surfaces [Alexeenko et al, 2004;Ngalande et al, 2006;Yim et al, 2014]. These models have been used to investigate plume contamination characteristics [Alexeenko et al, 2004], surface heating due to plume impingement [Yim et al, 2014], and effects of surface roughness on near-field plume development [Ngalande et al, 2006]. Although these models address the collisional aspect of the plume, the studies have been largely focused on spacecraft plume interactions over relatively small distances and neglect environmental considerations from charge-exchange reactions or electrostatic and magnetic field effects.…”

Section: 1002/2015ja021158mentioning

confidence: 99%

Spacecraft plume interactions with the magnetosphere plasma environment in geostationary Earth orbit

Stephani

Boyd

2016

JGR Space Physics

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Particle‐based kinetic simulations of steady and unsteady hydrazine chemical rocket plumes are presented in a study of plume interactions with the ambient magnetosphere in geostationary Earth orbit. The hydrazine chemical rocket plume expands into a near‐vacuum plasma environment, requiring the use of a combined direct simulation Monte Carlo/particle‐in‐cell methodology for the rarefied plasma conditions. Detailed total and differential cross sections are employed to characterize the charge exchange reactions between the neutral hydrazine plume mixture and the ambient hydrogen ions, and ion production is also modeled for photoionization processes. These ionization processes lead to an increase in local plasma density surrounding the spacecraft owing to a partial ionization of the relatively high‐density hydrazine plume. Results from the steady plume simulations indicate that the formation of the hydrazine ion plume are driven by several competing mechanisms, including (1) local depletion and (2) replenishing of ambient H+ ions by charge exchange and thermal motion of 1 keV H+ from the ambient reservoir, respectively, and (3) photoionization processes. The self‐consistent electrostatic field forces and the geostationary magnetic field have only a small influence on the dynamics of the ion plume. The unsteady plume simulations show a variation in neutral and ion plume dissipation times consistent with the variation in relative diffusion rates of the chemical species, with full H2 dissipation (below the ambient number density levels) approximately 33 s after a 2 s thruster burn.

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“…The scenarios of greatest concern for SEPM SAW plume loading would be firing of the Orion forward facing RCS thrusters that would occur during an emergency break-out maneuver for aborting a missed docking attempt. The plumes from these 220 N bi-propellant RCS thrusters were previously modeled for self- impingement studies on the Orion vehicle 3 and the analysis is extended here for impingement to the SEPM SAWs. In particular, the Reacting And Multi-Phase (RAMP2) and PLume IMPingement (PLIMP) codes are used here for this initial assessment and further details on the general analysis approach, assumptions and methods can be found elsewhere 3 .…”

Section: E Deployed Loading -Orion Rcs Plumesmentioning

confidence: 99%

“…The plumes from these 220 N bi-propellant RCS thrusters were previously modeled for self- impingement studies on the Orion vehicle 3 and the analysis is extended here for impingement to the SEPM SAWs. In particular, the Reacting And Multi-Phase (RAMP2) and PLume IMPingement (PLIMP) codes are used here for this initial assessment and further details on the general analysis approach, assumptions and methods can be found elsewhere 3 . A sample output of the plume pressure flow field from RAMP2 is shown in Figure 12 relative to a sample docked Orion and SEPM configuration.…”

Section: E Deployed Loading -Orion Rcs Plumesmentioning

confidence: 99%

Structural Design Considerations for a 50 kW-Class Solar Array for NASA’s Asteroid Redirect Mission

Kerslake

Kraft

Yim

et al. 2016

3rd AIAA Spacecraft Structures Conference

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NASA is planning an Asteroid Redirect Mission (ARM) to take place in the 2020s. To enable this multi-year mission, a 40 kW class solar electric propulsion (SEP) system powered by an advanced 50 kW class solar array will be required. Powered by the SEP module (SEPM), the ARM vehicle will travel to a large near-Earth asteroid, descend to its surface, capture a multi-metric ton (t) asteroid boulder, ascend from the surface and return to the Earth-moon system to ultimately place the ARM vehicle and its captured asteroid boulder into a stable distant orbit. During the years that follow, astronauts flying in the Orion multipurpose crew vehicle (MPCV) will dock with the ARM vehicle and conduct extravehicular activity (EVA) operations to explore and sample the asteroid boulder. This paper will review the top structural design considerations to successfully implement this 50 kW class solar array that must meet unprecedented performance levels. These considerations include beyond state-of-the-art metrics for specific mass, specific volume, deployed area, deployed solar array wing (SAW) keep in zone (KIZ), deployed strength and deployed frequency. Analytical and design results are presented that support definition of stowed KIZ and launch restraint interface definition. An offset boom is defined to meet the deployed SAW KIZ. The resulting parametric impact of the offset boom length on spacecraft moment of inertias and deployed SAW quasistatic and dynamic load cases are also presented. Load cases include ARM spacecraft thruster plume impingement, asteroid surface operations and Orion docking operations which drive the required SAW deployed strength and damping. The authors conclude that to support NASA's ARM power needs, an advanced SAW is required with mass performance better than 125 W/kg, stowed volume better than 40 kW/m 3 , a deployed area of 200 m 2 (100 m 2 for each of two SAWs), a deployed SAW offset distance of nominally 3-4 m, a deployed SAW quasistatic strength of nominally 0.1 g in any direction, a deployed loading displacement under 2 m, a deployed fundamental frequency above 0.1 Hz and deployed damping of at least 1%. These parameters must be met on top of challenging mission environments and ground testing requirements unique to the ARM project.

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Plume Impingement Analysis for the European Service Module Propulsion System

Cited by 6 publications

References 13 publications

Evolution of MPCV Service Module Propulsion and GN&C Interface Requirements between Constellation and European Service Module

Evolution of MPCV Service Module Propulsion and GN&C Interface Requirements between Constellation and European Service Module

Spacecraft plume interactions with the magnetosphere plasma environment in geostationary Earth orbit

Structural Design Considerations for a 50 kW-Class Solar Array for NASA’s Asteroid Redirect Mission

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