Three-Burn Centaur with Electric Propulsion Upper Stage Delivers Maximum Payload

2002 ◽  
Author(s):  
Bernard Free ◽  
James Owens ◽  
Fabio De Poli
Keyword(s):  
Electric Propulsion ◽  
Maximum Payload ◽  
Upper Stage

Conceptual design studies of an electrically propelled upper stage for deployment of a multi-plane orbital constellation of small spacecraft

2021 ◽  
pp. 76-87
Author(s):  
Aleksandr LEVANDOVICH ◽  
◽  
Dmitry MOSIN ◽  
Aleksandr TYUTYUKIN ◽  
Igor URTMINTSEV ◽  
...  
Keyword(s):  
Conceptual Design ◽  
Electric Propulsion ◽  
Aerodynamic Drag ◽  
Orbital Plane ◽  
Design Studies ◽  
Small Spacecraft ◽  
Solar Arrays ◽  
Upper Stage ◽  
The Difference ◽  
Orbital Constellation

The paper presents results of conceptual design studies to determine configuration of an electrically propelled upper (a space tug) with main engines arrays. It addresses the problem stage (EPUS) — a space transportation stage based on electric propulsion powered by solar of deploying a multi-plane orbital constellation of to in of small spacecraft (SSC) using an electrically propelled upper stage. It proposes change the SSC operational orbital planes based on the effect of precession rates between the parking and the working orbits eccentricity in the Earth gravitational field. Requirements owing have the difference to the effect been defined for the EPUS electrical propulsion system that take into account the need to operate it to offset the aerodynamic drag while waiting in the parking orbit for the SSC operational orbital plane to turn. It demonstrates the feasibility of employing four EPUS that use Stationary Plasma Thruster-type electric propulsion as their main engines and gallium arsenide solar arrays for deployment in a 600 km orbit in four planes an orbital constellation of 24 small spacecraft with a mass of ~250 kg each using one launch of a medium capacity launch vehicle of Soyuz-2.1b type.

Conceptual design studies of an electrically propelled upper stage for deployment of a multi-plane orbital constellation of small spacecraft

2021 ◽  
pp. 97-108
Author(s):  
Aleksandr V. LEVANDOVICH ◽  
Dmitry A. MOSIN ◽  
Viktor V. SINYAVSKIY ◽  
Aleksandr Ye. TYUTYUKIN ◽  
Igor A. UPTMINTSEV
Keyword(s):  
Conceptual Design ◽  
Electric Propulsion ◽  
Aerodynamic Drag ◽  
Orbital Plane ◽  
Design Studies ◽  
Small Spacecraft ◽  
Solar Arrays ◽  
Upper Stage ◽  
The Difference ◽  
Orbital Constellation

The paper presents results of conceptual design studies to determine configuration of an electrically propelled upper stage (EPUS) – a space transportation stage (a space tug) with main engines based on electric propulsion powered by solar arrays. It addresses the problem of deploying a multi-plane orbital constellation of small spacecraft (SSC) using an electrically propelled upper stage. It proposes to change the SSC operational orbital planes based on the effect of the difference in precession rates between the parking and the working orbits owing to the effect of eccentricity in the Earth gravitational field. Requirements have been defined for the EPUS electrical propulsion system that take into account the need to operate it to offset the aerodynamic drag while waiting in the parking orbit for the SSC operational orbital plane to turn. It demonstrates the feasibility of employing four EPUS that use Stationary Plasma Thruster-type electric propulsion as their main engines and gallium arsenide solar arrays for deployment in a 600 km orbit in four planes an orbital constellation of 24 small spacecraft with a mass of ~250 kg each using one launch of a medium capacity launch vehicle of Soyuz-2.1b type. Key words: Electrically propelled upper stage, electric propulsion, small spacecraft, orbital constellation.

scholarly journals Choice of mission trajectory plans and conceptual design of electrical propulsion module for launching payloads into circumterrestrial orbits

2020 ◽  
Vol 19 (4) ◽  
pp. 58-69
Author(s):  
V. V. Salmin ◽  
A. A. Kvetkin ◽  
A. S. Russkikh
Keyword(s):  
Conceptual Design ◽  
Electric Propulsion ◽  
Transportation System ◽  
Design Parameters ◽  
Low Thrust ◽  
Module Design ◽  
Time Calculation ◽  
Upper Stage ◽  
Space Transportation System ◽  
Space Transportation

The problem of increasing the efficiency of transport operations in space is currently coming to the fore. In the context of this problem, we investigated the possibility of developing a space transportation system including a chemical upper stage and an electric propulsion transport module capable of performing a specified range of space maneuvers. Electric propulsion module design was carried out for a given range of target orbits and payload mass with the provision of restrictions on the flight time. Calculation of the ballistic characteristics of the flight is performed and an optimal program of placing a low-thrust vehicle into orbit is defined. A procedure for defining the design parameters of a space transportation system and its conceptual design is proposed. The conceptual design of the space transportation system and the electric propulsion module were formed in the PTC Creo Parametric environment. On the basis of the results of the work, it can be concluded that it is possible to create a space transportation system with given parameters.

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.

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