Electrostatic Probe and Camera Measurements for Modeling the iMPD SIMP-LEX

Nawaz, Anuscheh; Bauder, Uwe; Herdrich, Georg; Auweter‐Kurtz, Monika

doi:10.2514/6.2007-5280

Cited by 7 publications

(9 citation statements)

References 3 publications

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“…The equipment used therefore comprises vacuum chambers with pertinent pumping systems, a highly precise mass balance, a thrust balance, a high-speed camera as well as magnetic field probes 4,5) . Additionally, studies were undertaken to optimize the thruster with respect to the mission's requirements, i.e., the mean exhaust velocity and the thrust efficiency.…”

Section: Experimental Investigationsmentioning

confidence: 99%

“…To aid in the development of the discharge model for SIMP-LEX the plasma sheet propagation was investigated by means of a high speed camera sensitive to wavelengths between 380-900 nm 3,5) . The plasma sheet was analyzed to determine the position as a function of time, form and overall discharge behavior.…”

Section: High-speed Camera Measurementsmentioning

confidence: 99%

“…The analysis method is basing on the fact that a number of finite current filaments is assumed each carrying a fraction of the total current, and the magnetic field induced is calculated normalized by the current [5][6][7] . Integrating over the space between the electrodes eventually leads to the change in inductance as a function of the plasma position, necessary for the modeling of the thruster's performance.…”

Section: Calculation Of Magnetic Field and Change In Inductancementioning

confidence: 99%

“…The focus is, hence, put to keep the model simple enough to being easily calculated, but complex enough to attain a certain accuracy. The slug model describes the acceleration of the plasma sheet within a PPT making some assumptions, e.g., that the mass ablated is accelerated in a plasma sheet without any variations in mass 5) . In addition, the inductance is linear function of the plasma position.…”

Section: Slug Modelmentioning

confidence: 99%

See 3 more Smart Citations

Review of Pulsed Plasma Thruster Development at IRS

Schönherr

Nawaz

Lau

et al. 2010

AEROSPACE TECHNOLOGY JAPAN

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The research and development process of the ablative pulsed plasma thruster SIMP-LEX is summarized. By experiment, the magnetic field in between the electrodes was measured with an induction probe, and a high-speed camera was applied to estimate the propagation of the plasma plume. Further, the optimization process towards higher thrust efficiency by means of geometric and electrical modifications is described. By analysis, the calculation of magnetic field and change in inductance is summarized and the numerical models for the performance simulation of SIMP-LEX introduced. A peak value of 0.7 T was found for the magnetic field created during an 80 J discharge whereas a propagation velocity of 28 km/s was estimated for the first plasma plume. The optimization process towards a new engineering model yielded an increase of 40% in mean exhaust velocity to 26 km/s, and a maximum thrust efficiency of 32% was evaluated respectively. Calculation of magnetic field and change in inductance based on the Biot-Savart law yield input for the slug model, which can then predict the general performance parameters with a good accordance.

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Section: Experimental Investigationsmentioning

confidence: 99%

Section: High-speed Camera Measurementsmentioning

confidence: 99%

Section: Calculation Of Magnetic Field and Change In Inductancementioning

confidence: 99%

Section: Slug Modelmentioning

confidence: 99%

See 2 more Smart Citations

Review of Pulsed Plasma Thruster Development at IRS

Schönherr

Nawaz

Lau

et al. 2010

AEROSPACE TECHNOLOGY JAPAN

Self Cite

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show abstract

“…This semiconductor spark plug receives 1000 V and triggers the capacitor discharge. This discharge leads to the ablation and acceleration of propellant and, hence, to the thrust [10][11][12] . A side view of the thruster's electrodes during discharge is presented in Fig.…”

Section: Pulsed Mpd Thruster Add Simp-lexmentioning

confidence: 99%

Activities in Electric Propulsion Development at IRS

Herdrich

Bauder

Bock

et al. 2009

Trans. JSASS Space Tech. Japan

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More than three decades of experience have been gained in the field of electric propulsion at the Institute of Space Systems (Institut für Raumfahrtsysteme = IRS). Recent developments within the field of electric propulsion are summarized and foremost results are highlighted. The various types of electric propulsion systems are not considered as to be competitive. Here, system analysis shows that optimum parameter such as the required exhaust velocity or specific impulse result taking into account both the mission profile and system related sizes such as the power conditioner efficiency, the thrust efficiency and the specific mass of the corresponding power unit. Correspondingly, ion thrusters, Hall thrusters, thermal arcjets, or magnetoplasmadynamics (MPD) thrusters are preferable depending on the mission. Among the described electric propulsion systems are recent developments in the field of applied field MPD but also from high power hybrid thrusters. In addition, new concepts such as the hybrid systems Thermal-Inductively heated Hybrid-Thruster of the University of Stuttgart (TIHTUS) and the so-called Coupled Tether/Ion Engine Propulsion (CETEP) are analysed.

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Characteristics of plasma properties in an ablative pulsed plasma thruster

Schönherr¹,

Nees²,

Arakawa³

et al. 2013

Physics of Plasmas

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Pulsed plasma thrusters are electric space propulsion devices which create a highly transient plasma bulk in a short-time arc discharge that is expelled to create thrust. The transitional character and the dependency on the discharge properties are yet to be elucidated. In this study, optical emission spectroscopy and Mach-Zehnder interferometry are applied to investigate the plasma properties in variation of time, space, and discharge energy. Electron temperature, electron density, and Knudsen numbers are derived for the plasma bulk and discussed. Temperatures were found to be in the order of 1.7 to 3.1 eV, whereas electron densities showed maximum values of more than 1017 cm−3. Both values showed strong dependency on the discharge voltage and were typically higher closer to the electrodes. Capacitance and time showed less influence. Knudsen numbers were derived to be in the order of 10−3−10−2, thus, indicating a continuum flow behavior in the main plasma bulk.

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Electrostatic Probe and Camera Measurements for Modeling the iMPD SIMP-LEX

Cited by 7 publications

References 3 publications

Review of Pulsed Plasma Thruster Development at IRS

Review of Pulsed Plasma Thruster Development at IRS

Activities in Electric Propulsion Development at IRS

Characteristics of plasma properties in an ablative pulsed plasma thruster

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