DEIMOS-2: Early Life Operations Experience

Luengo, Mar; Mazzoleni, Annalisa; Bravo, Felix Alberto; Pisabarro, Patricia; Pirondini, Fabrizio; Lee, Hungu; Jeong, Yun-Hwang; Pyo, Seyoung

doi:10.2514/6.2016-2566

Cited by 1 publication

(3 citation statements)

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“…Most space missions, after the spacecraft is injected into initial orbit, perform a preliminary phase that is called In-Orbit Testing (IOT) where all systems are tested for proper operation, after the launch phase. The Electric Propulsion System (EPS) runs cascading housekeeping and health checks with the goal of assessing its health [1][2][3][4][5][6][7]. These include basic PPU electrical checks, pressure and temperature sensors health checks, initial valve activation, and cathode heater startup.…”

Section: Introductionmentioning

confidence: 99%

“…IOT is usually performed over the course of several earth revolutions. In the case of the DEIMOS-2 mission the IOT phase led to a re-calibration of the cathode mass ow rate [7].…”

Section: Introductionmentioning

confidence: 99%

“…DEIMOS-2 experienced ignition and operation issues from the rst few thruster operations. These were tracked back to erroneous cathode ow setting, resulting in a much lower cathode ow rate than required [7]. This issue was resolved by recalibration of the cathode mass ow line.…”

Section: Introductionmentioning

confidence: 99%

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On-Orbit Mission Overview of the Low Power Hall Thruster Propulsion System aboard Venμs Satellite

Katz-Franco,

Lev,

Shoor

et al. 2024

Preprint

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Venµs is a satellite launched in 2017, for super-spectral Earth imaging and Electric Propulsion System (EPS) demonstration. In this paper we overview EPS design and operation throughout all five mission phases, from open/closed-loop orbit control, through orbit descent (720→410 km), orbit maintenance under high drag environment, to orbit raising (410→560 km). The EPS consisted of two throttleable Hall thrusters, PPU, Propellant Management Assembly (PMA), and a 9 liter propellant tank carrying 16 kg of Xenon. Both thrusters operated in the 300–550 W power range, generated a combined total impulse of 158.1 kN-sec and consumed all propellant. Two methods are described to compute the remaining propellant mass – “Bookkeeping” and “PTV” methods. The advantages and disadvantages of each method are discussed in light of the Venµs mission. Thruster performance was measured on-orbit using the “Orbit Determination” method and compared to laboratory experiments conducted on the ground with identical thrusters. The measured performance on-orbit was found to be on average lower by up to 5% than the performance measured on the ground. Lastly, we present several repeating events in which the propulsion system suffered from sudden beam-outs or ignition difficulties. We present the methods used to construct a solution and implement it.

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Section: Introductionmentioning

confidence: 99%

“…IOT is usually performed over the course of several earth revolutions. In the case of the DEIMOS-2 mission the IOT phase led to a re-calibration of the cathode mass ow rate [7].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

On-Orbit Mission Overview of the Low Power Hall Thruster Propulsion System aboard Venμs Satellite

Katz-Franco,

Lev,

Shoor

et al. 2024

Preprint

View full text Add to dashboard Cite

show abstract

DEIMOS-2: Early Life Operations Experience

Cited by 1 publication

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On-Orbit Mission Overview of the Low Power Hall Thruster Propulsion System aboard Venμs Satellite

On-Orbit Mission Overview of the Low Power Hall Thruster Propulsion System aboard Venμs Satellite

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