Analysis of System Margins on Deep Space Missions Using Solar Electric Propulsion

Oh, David Y.; Landau, Damon; Randolph, Tom; Timmerman, P.; Chase, James; Sims, J. D.; Kowalkowski, Theresa

doi:10.2514/6.2008-5286

Cited by 14 publications

(3 citation statements)

References 4 publications

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“…Therefore, according to Table 1, only the mission scenario in which m 0 ≤ 1050 kg is consistent with the actual characteristics of a single propulsive unit. Table 1 also shows that, when m 0 = 1050 kg, the spacecraft dry mass is less than m 1 600 kg, a value consistent with those reported in Table 2 of Oh et al (2008) for a rendezvous mission towards comet Tempel 1 of a SEP spacecraft with a NEXT thruster and P ⊕ = 10 kW. However, laboratory tests (Herman et al, 2009;Reckart, 2009) indicate that the NEXT thruster could (potentially) provide a propellant throughput greater than 750 kg, and this enhanced capability would make other mission scenarios possible.…”

Section: Sensitivity Analysissupporting

confidence: 83%

Time-optimal trajectories to circumsolar space using solar electric propulsion

Quarta

Izzo

Vasile

2013

Advances in Space Research

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Section: Sensitivity Analysissupporting

confidence: 83%

Time-optimal trajectories to circumsolar space using solar electric propulsion

Quarta

Izzo

Vasile

2013

Advances in Space Research

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“…Where additional propellant is needed, the amount required is small compared to the overall 10% propellant margin typically required for cruise propellant on deep space SEP missions. 21 The main risk with these options is associated with the development of the flight software needed to autonomously execute and control the spacecraft during momentum management maneuvers. Unlike hardware development, software development is a common part of the manufacture of any modern spacecraft.…”

Section: Table 4: Comparison Of Different Methods For Deep-space All mentioning

confidence: 99%

Feasibility of All-Electric Three Axis Momentum Management for Deep Space Small Body Rendezvous

Oh¹,

Collins²,

Randolph³

et al. 2014

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

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An all-electric approach to deep space missions offers significant benefits to spacecraft designers. The absence of a chemical propulsion system and the associated hazardous operations from the spacecraft offers a dramatically easier spacecraft integration process and simpler launch base operations. This paper provides a survey of different methods that can be used to accomplish three axis momentum management during the interplanetary transit ("cruise") portions of deep space Solar Electric Propulsion (SEP) missions without the use of chemical propulsion. The strategies described are based on the use of xenon ion or Hall effect thrusters, which are used alone or in combination with a xenon cold gas system. The methods described use currently existing flight-qualified hardware and apply only to the cruise phase of the mission. It is shown that the use of existing flight hardware combined with the existence of previously flown momentum management flight software for Earth orbit, existing experience with all-chemical momentum management in deep space, and the option to implement "primary" and "backup" momentum management methods using common hardware, all lead to the conclusion that all-electric momentum management can be effectively implemented on deep space small body rendezvous missions with relatively low development, implementation, and operational risk. Nomenclature e = elementary charge ν z = axial ion velocity B r = radial magnetic field E z = axial electric field Fθ = azimuthal force acting on an ion F z = axial force acting on an ion I sp = specific impulse L = acceleration scale length M = ion mass R = mean discharge chamber radius T = total thrust U z = potential drop over the acceleration scale length

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“…Oh et al [13] described a procedure for incorporating a missedthrust analysis into the trajectory selection process, as used in the Dawn mission. In the method they described, the spacecraft follows a trajectory with a rolling forced coast period ahead of the spacecraft.…”

Section: Introductionmentioning

confidence: 99%