The RLEP - An Introduction to the Goals, Approach, and Architecture

Watzin, James G.; Burt, Joseph; Tooley, Craig

doi:10.2514/6.2005-2548

Cited by 2 publications

(4 citation statements)

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“…The advantages of this transfer are well known as it is the most proven approach from several applications, and can provide a relatively simple transfer process with an adequate performance at the lowest overall cost and risk. Also, it usually takes just four to five days to complete the transfer, which gives a faster way to the moon than other approaches [7]. Next, a phasing loop transfer can get the orbiter to a translunar injection by raising the orbit gradually from the low earth parking orbit to the distance of the nearby moon.…”

Section: Propulsion System Trade Study Of Lunar Orbitersmentioning

confidence: 98%

“…This approach can provide a chance to verify the operating condition status of the orbiters and correct any anomalies before the orbiter arrives at the moon, while it requires additional fuel due to multiburns of a liquid AKE and more operational complexities than the direct injection. In general, it takes two to three weeks to complete transfer [7]. A WSB (Weak Stability Boundary) transfer takes the orbiter to the region of the Lagrangian points of the Earth-sun system to reduce the velocity requirement by arriving at the moon with a low relative velocity.…”

Section: Propulsion System Trade Study Of Lunar Orbitersmentioning

confidence: 99%

“…Finally, the spiral approach requires the longest transfer period than the others. Hence, the electrical propulsion system is a proper way for this approach to save a considerable amount of fuel consumption, but it consequently needs an oversized electric power system [7]. SMART-1 used a low-thrust hall thruster as the main engine to transfer from a geostationary transfer orbit to the lunar orbit over a period of 16 months.…”

Section: Propulsion System Trade Study Of Lunar Orbitersmentioning

confidence: 99%

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Lunar Orbiter Trade Study and Conceptual Design of Onboard Propulsion System

Lee

2011

Journal of Spacecraft and Rockets

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In recent years, the lunar explorer programs, suspended for a long time, have resumed again with the rapid development of low-cost, high-level technologies, and hence several nations have made a success of lunar exploration programs with their own developed orbiters. Late in 2007, the Science Ministry of the Republic of Korea announced that Korea planned to send its first orbiter to the moon by the year 2020. The major objective of the present study is to set up a fundamental baseline on which to design an optimal type of onboard propulsion system. To do this, the mission requirements of the Korean lunar orbiter are summarized at first. Next, the mission requirements of various orbiters are surveyed and also an overview of their key design specifications is investigated. Based on the results of this trade study, the conceptual design of the onboard propulsion system of the Korean lunar orbiter is finally discussed with its major key design requirements of the expected propellant quantity, the minimum thrust level for lunar orbit insertion, and the specific characteristics of the necessary components along a whole system schematic diagram.Nomenclature g = gravity acceleration, m=s 2 I sp = specific impulse, sec M fuel = fuel mass, kg M wet = wet mass of the orbiter, kg V = delta-V, m=s

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Section: Propulsion System Trade Study Of Lunar Orbitersmentioning

confidence: 98%

Section: Propulsion System Trade Study Of Lunar Orbitersmentioning

confidence: 99%

Section: Propulsion System Trade Study Of Lunar Orbitersmentioning

confidence: 99%

See 1 more Smart Citation

Lunar Orbiter Trade Study and Conceptual Design of Onboard Propulsion System

Lee

2011

Journal of Spacecraft and Rockets

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“…Several launch systems are mentioned that are capable of delivering to Low Lunar Orbit (LLO), thus giving a rough range of future mission sizes being considered; estimates range from 274 kg to 6598 kg delivered [2]. For example, the Lunar Reconnaissance Orbiter (LRO) which is currently being designed, is slated to be approximately 1000 kg -1450 kg [4].…”

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confidence: 99%