Ion Propulsion Development Activities at the NASA Glenn Research Center

Patterson, Michael J.; Domonkos, Matthew T.; Foster, John E.; Haag, Thomas; Mantenieks, M. A.; Pinero, Luis R.; Rawlin, Vincent K.; Sarver-Verhey, Timothy R.; Soulas, George C.; Sovey, James S.; Strzempkowski, Eugene

doi:10.2514/6.2003-4709

Cited by 10 publications

(8 citation statements)

References 2 publications

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“…The primary electron number densities can be calculated according to: (8) where i p is the primary electron current at plasma potential found by extrapolating the linear primary fit to the plasma potential value measured by the emissive probe. The primary electron current is then subtracted from the electron current characteristic resulting in the Maxwellian current.…”

Section: B Dual Primary and Maxwellian Electron Analysismentioning

confidence: 99%

“…A better understanding of DCA erosion mechanisms may be even more important for the next -generation of ion engines associated with NASA's Project Prometheus that require lifetimes ranging from 44,000 to 88,000 hours. 7,8 Laser Induced Fluorescence (LIF) measurements by Williams have suggested the existence of a potential hill downstream of the DCA as a possible cause of DCA erosion. [9][10][11] In this scenario, the potential hill is responsible for accelerating a portion of the ions away from the hill towards the DCA.…”

Section: Introductionmentioning

confidence: 99%

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Discharge Chamber Plasma Structure of a 30 cm NSTAR-type Ion Engine

Herman

Gallimore

2004

40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

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Section: B Dual Primary and Maxwellian Electron Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Discharge Chamber Plasma Structure of a 30 cm NSTAR-type Ion Engine

Herman

Gallimore

2004

40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

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“…The availability of these propulsion technologies will lead to new hybrid propulsion schemes that will enable missions previously thought to be unachievable. A broad literature exists covering the state-of-the-art and expectations for nearterm improvements in space electric power generation [10,11], electric propulsion [12,13,14], and solar sail technologies [9,15]. Our purpose is not to review these technologies in detail but only to introduce the relevant figures of merit for the trajectory studies to follow.…”

Section: Electric and Solar Sail Propulsionmentioning

confidence: 99%

Combining Electric and Sail Propulsion for Interplanetary Sample Return

Noble¹

2003

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Fast sample return from the outer Solar System would open an entirely new avenue for space science, but the vast distances make this a daunting task. The achievable transit velocity and the need for extra propellant on the return trip limit the feasibility of returning extraterrestrial samples to Earth. To keep the mission duration short enough to be of interest, sample return from objects farther out in the Solar System requires increasingly higher velocities. High specific impulse, electric propulsion reduces the propellant required for the outbound and return trips, but decelerating the spacecraft at the inner Solar System from high velocity still involves a long, inward spiral trajectory. The use of solar sails to rapidly decelerate incoming sample capsules and eliminate propellant is explored in this paper. The sail is essentially a "solar parachute" used for braking at the end of the interplanetary return flight, permitting a higher transit speed and truncating the deceleration spiral. In this application the sail is relatively small and manageable since only the sample capsule and its sail are decelerated. A comparison is made between using all-electric propulsion versus combining electric propulsive acceleration with sail deceleration for sample return from the distances of Saturn, Uranus, and Pluto. Solar-sail braking dramatically reduces the return flight time by one-third or more compared to using electric rocket deceleration. To elucidate the technology requirements, wide ranges for both the loaded sail density and electric propulsion specific mass are considered in this initial parametric study.

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“…First the electron temperature is varied to satisfy Equation (1). Next, the number density is determined, satisfying Equation (8).…”

Section: Nasa/t_2002-211916mentioning

confidence: 99%