Tradeoff Performance of Hybrid Low-Thrust Propulsion System

2007 ◽  
Vol 44 (6) ◽  
pp. 1263-1270 ◽  
Author(s):  
Giovanni Mengali ◽  
Alessandro A. Quarta
Keyword(s):  
Propulsion System ◽  
Low Thrust

Rendez vous with Saturn's rings

1984 ◽  
Vol 75 ◽  
pp. 743-759 ◽  
Author(s):  
Kerry T. Nock
Keyword(s):  
Solar Energy ◽  
Electric Propulsion ◽  
Power Source ◽  
Propulsion System ◽  
Low Thrust ◽  
Ring Plane ◽  
The Earth ◽  
Total Impulse ◽  
Saturn's Rings

ABSTRACTA mission to rendezvous with the rings of Saturn is studied with regard to science rationale and instrumentation and engineering feasibility and design. Future detailedin situexploration of the rings of Saturn will require spacecraft systems with enormous propulsive capability. NASA is currently studying the critical technologies for just such a system, called Nuclear Electric Propulsion (NEP). Electric propulsion is the only technology which can effectively provide the required total impulse for this demanding mission. Furthermore, the power source must be nuclear because the solar energy reaching Saturn is only 1% of that at the Earth. An important aspect of this mission is the ability of the low thrust propulsion system to continuously boost the spacecraft above the ring plane as it spirals in toward Saturn, thus enabling scientific measurements of ring particles from only a few kilometers.

Gravitational towing of asteroids by spacecrafts with a solar sail as a propulsion system

2020 ◽  
Author(s):  
R.M. Poluektov ◽  
M.V. Skrob
Keyword(s):  
Comparative Analysis ◽  
Solar Sail ◽  
Propulsion System ◽  
Joint Motion ◽  
Jet Engines ◽  
Low Thrust ◽  
Design Features ◽  
Long Period ◽  
The Impact

The paper considers the possibility of changing the orbit of potentially dangerous aste-roids using a gravity tractor. The concept of using spacecrafts equipped with a solar sail for gravitational towing is described. The analysis of this type spacecraft effectiveness is carried out on the example of changing the orbit of the Apophis asteroid. Software and mathematical support for modeling the joint motion of the asteroid-spacecraft system has been developed. The model was used to assess the impact of spacecraft with design features on the asteroid’s orbit over a long period of time. Several variants of the spacecraft configuration with different weight and sail design are considered. A comparative analysis of the results of using solar sail vehicles with similar vehicles using low-thrust jet engines is carried out.

scholarly journals Optimization of sprint interplanetary trajectories with nuclear bimodal thermal propulsion

2019 ◽  
pp. 74-77
Author(s):  
O. M. Kharytonov ◽  
S. R. Savchenko ◽  
N. Miranda
Keyword(s):  
Optimization Problem ◽  
Electrical Power ◽  
Propulsion System ◽  
Low Thrust ◽  
Small Times ◽  
Limited Power ◽  
Trajectory Method ◽  
Payload Mass ◽  
Interplanetary Missions ◽  
High Thrust

Interplanetary missions require fast and fuel-efficient transfers. Combining small times transfers of high-thrust and efficiency of low-thrust propulsion can provide a good compromise. Saving an amount of fuel from the initial high-thrust burn and using it to correct the trajectory could lead to an economy of fuel. We investigated the optimal way to take advantages of both high and low-thrust propulsion benefits in order to maximize the payload mass of the mission. Using a simple model of ideal engine of limited power and the transporting trajectory method, we determined the analytical expression of final payload mass. The solution of the optimization problem gave us the optimal repartition of fuel between high and low-thrust maneuvers for a given thrust of thermal propulsion and electrical power of low-thrust propulsion system. As the mass of the low-thrust propulsion system depends on the electrical power, we took it into account to determine the optimal electrical power for a sprint trajectory in a given time. As a result, we could obtain the interval of transfer time for which the combination of high and low thrust becomes optimal.

scholarly journals Trajectory Design with Hybrid Low-Thrust Propulsion System

2007 ◽  
Vol 30 (2) ◽  
pp. 419-426 ◽  
Author(s):  
Giovanni Mengali ◽  
Alessandro A. Quarta
Keyword(s):  
Propulsion System ◽  
Trajectory Design ◽  
Low Thrust

The concept of the auxiliary propulsion system of the III stage of the Soyuz launch vehicle

2021 ◽  
Author(s):  
V.D. Gorokhov ◽  
V.M. Fomin ◽  
V.V. Golubyatnik ◽  
D.A. Scheblykin
Keyword(s):  
Rocket Engine ◽  
Launch Vehicle ◽  
Low Earth Orbit ◽  
Propulsion System ◽  
Low Thrust ◽  
Liquid Propellant ◽  
Preliminary Calculation ◽  
Liquid Propellant Rocket Engine ◽  
Constituent Elements ◽  
Propellant Rocket

The paper introduces a concept of creating an auxiliary propulsion system for the III stage of the Soyuz launch vehicle. The concept is aimed at reducing the cost of launching a payload into low Earth orbit. The study describes the auxiliary propulsion system and its constituent elements and gives the results of a preliminary calculation of the main characteristics of a low-thrust engine. Within the research, we developed a sketch layout of the auxiliary propulsion system integrated into the 14D23 liquid propellant rocket engine and analyzed the mass characteristics of the constituent elements and the greatest contribution to the total mass of the propulsion system. The proposed propulsion system is distinguished by electric drives for the power supply system pumps used instead of the turbine drive. This auxiliary propulsion system, combined with a 14D23 liquid propellant rocket engine, powered by oxygen-naphthyl propellants, is proposed for use in the III stage of the Soyuz-2-1b launch vehicle.

Analysis of lifetime extension capabilities for CubeSats equipped with a low-thrust propulsion system for Moon missions

2019 ◽  
Vol 160 ◽  
pp. 558-571
Author(s):  
Jose Rodrigo Cordova Alarcon ◽  
Necmi Cihan Orger ◽  
Sangkyun Kim ◽  
Mengu Cho
Keyword(s):  
Propulsion System ◽  
Low Thrust ◽  
Lifetime Extension

A Continuous Proportional Low-Thrust Propulsion System

1989 ◽  
Vol 22 (7) ◽  
pp. 223-229 ◽  
Author(s):  
J.-H. Chen ◽  
J. Bull ◽  
D.B. DeBra
Keyword(s):  
Propulsion System ◽  
Low Thrust
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