A realistic concept of a manned Mars mission with nuclear–electric propulsion

Loeb, H.; Petukhov, V. G.; Popov, G.A.; Mogulkin, A.I.

doi:10.1016/j.actaastro.2015.07.019

Cited by 11 publications

(3 citation statements)

References 4 publications

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“…The prospect of interplanetary travel, particularly the ambitious goal of human missions to Mars, stands as one of the most exhilarating and significant challenges in modern space exploration [1][2][3]. The concept of manned Mars missions has been the subject of extensive study and speculation [4][5][6][7]. The literature reveals a notable gap in the comprehensive understanding and development of power and propulsion systems suitable for such monumental undertakings, offering valuable insights into the challenges and potential solutions.…”

Section: Introduction 1spacecraft Electric Propulsionmentioning

confidence: 99%

Spacecraft Medium Voltage Direct-Current (MVDC) Power and Propulsion System

Talebzadeh,

Beik

2024

Electronics

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This paper introduces a medium voltage direct-current (MVDC) system for large spacecraft megawatt-scale (MW) power and propulsion systems intended for interplanetary transport, including missions to the Moon and Mars. The proposed MVDC system includes: (i) A nuclear electric propulsion (NEP) that powers a permanent magnet (PM) generator whose output is rectified and connected to the MVDC bus. (ii) A solar photovoltaic (PV) source that is interfaced to the MVDC bus using a unidirectional boost DC-DC converter. (iii) A backup battery energy storage system (BESS) that connects to the MVDC bus using a bidirectional DC-DC boost converter. (iv) A dual active bridge (DAB) converter that controls the power to the spacecraft’s electric thruster. The NEP serves as the main power source for the spacecraft’s electric thruster, while the solar PV and BESS are intended to provide power for the payload and spacecraft’s low-voltage power system. The paper will (i) provide a review of the spacecraft MVDC power and prolusion system highlighting state-of-the-art main components, (ii) address the control of boost converters for the PV and BESS sources and the DAB converter for the thruster, and (iii) propose an uncertainty and disturbance estimator (UDE) concept based on current control algorithms to mitigate MVDC instability due to unpredictable factors and external disruptions. The proposed UDE can actively estimate and compensate for the system disturbance and uncertainty in real time, and thus, both the system tracking performance and robustness can be improved. Simulation studies have been conducted to substantiate the efficacy of the proposed schemes.

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Section: Introduction 1spacecraft Electric Propulsionmentioning

confidence: 99%

Spacecraft Medium Voltage Direct-Current (MVDC) Power and Propulsion System

Talebzadeh,

Beik

2024

Electronics

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“…Electric rocket engines are extensively used in space technology. These types of engines, the main principle of which is ionization and acceleration of working substance, are used to stabilize and correct the position of spacecraft in orbit (Antropov et al, 2002;Gorshkov et al, 2008;Khartov et al, 2013;Loeb, 2015;Orlov et al, 2001;Rabinsky et al, 2016a;Sitnikov, 2017). Also, at present, the electric propulsion engines are used as mid-flight engines for flights in interplanetary space.…”

Section: Introductionmentioning

confidence: 99%

Polymer Precursors for Creating Gas Discharge Chamber for Electric Rocket Engine

Nigmatzyanov¹,

Pogodin²,

Rabinskiy³

et al. 2020

PTQ

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Electric rocket engines are widely used in space technology. Furthermore, at present, electric propulsion engines are also used as mid-flight engines for flights in interplanetary space. On modern spacecraft, the following types of electric propulsion are mostly used: SPT and grid ion thruster. When using these engines as sustainers, it is important is to increase the total power for obtaining the required thrust and specific impulse. With an increase in total power, the volume of the discharge chamber increases, which leads to technological difficulties in the manufacture of discharge chambers from ceramic materials. Thus, the task of finding alternative ceramic materials is relevant and necessary in the development of high-frequency ion thrusters. The article discusses the issues of creating a composite material based on woven quartz materials and organosilicon binder as a precursor filled with silicon nitride for the manufacture of gas discharge chamber (GDC) of high-frequency ion thruster (RFIT). By thermos-gravimetric analysis, a thermosetting binder, which meets the requirements of vibration resistance and electromagnetic permeability of GDC in the megahertz range, was selected. Based on the binder filled with silicon nitride powder, reinforced by quartz woven fabrics, manufactured GDC. The resulting product was tested as part of the laboratory electric propulsion device with a diameter of 100 mm and power of 200W.

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“…It should be mentioned that the longest project in the history of astronautics -the flight of Voyager 1 and Voyager 2 spacecraft to the boundaries of the solar system (NASA, USA, since 1977) became possible to some extent due to the use of electro thermal electric propulsion engines -"hydrazine" engines. In modern space technology, ERE is being developed for use in the correction of orbit of the spacecraft, bringing the spacecraft into the geostationary orbit, and also as a mid-flight engine in interplanetary flights (Antropov et al, 2002;Gorshkov et al, 2008;Loeb, 2015;Sitnikov, 2017;Khartov et al, 2013;Rabinsky et al, 2016a). Among all types of electric propulsion, the greatest achievements have been reached in the use of ion engines (IE).…”

Section: Introductionmentioning

confidence: 99%

The Polymer-Ceramic Material for the Manufacture of Gas Discharge Chamber for the Electric Rocket Engine

Nigmatzyanov¹,

Pogodin²,

Rabinskiy³

et al. 2019

PTQ

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This study discusses the creation of heat-resistant dielectric composite material based on organosilicon polymers for the manufacture of gas discharge chamber (GDC) for the electric rocket engine (ERE). A binder has been proposed that meets the high requirements for vibration resistance and electromagnetic permeability of GDC in the megahertz range of electromagnetic waves. Based on this binder filled with silicon nitride powder, GRС was designed; this product was fully tested as part of laboratory 200 kW ERE. The research of structural transformations that occur during heating of materials was carried out by synchronous thermal analysis. The material obtained in the result of the experiment, the basis of which was SiSiB®PVMQ filled with Si3N4 60% by mass, is characterized by a number of properties that are structured and described in this study. As a result of the study, it was demonstrated that the studied material is characterized by heat resistance up to 400 ºС. On the basis of these materials, the authors produced a GDC, which was tested as part of a laboratory model. It was established that the increase in mass loss over 400 °C is due to the initiation of the process of thermal degradation of the main polymer chain.

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A realistic concept of a manned Mars mission with nuclear–electric propulsion

Cited by 11 publications

References 4 publications

Spacecraft Medium Voltage Direct-Current (MVDC) Power and Propulsion System

Spacecraft Medium Voltage Direct-Current (MVDC) Power and Propulsion System

Polymer Precursors for Creating Gas Discharge Chamber for Electric Rocket Engine

The Polymer-Ceramic Material for the Manufacture of Gas Discharge Chamber for the Electric Rocket Engine

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