Conceptual design of a solar thermal upper stage (STUS) flight experiments

1995 ◽  
Author(s):  
Clark Hawk ◽  
Alan Adams
Keyword(s):  
Conceptual Design ◽  
Solar Thermal ◽  
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 and Performance Analysis of a Solar Thermal-Photovoltaic-Powered Absorption Refrigeration System

2015 ◽  
Vol 137 (3) ◽  
Author(s):  
Dipankar N. Basu ◽  
A. Ganguly
Keyword(s):  
Power System ◽  
Conceptual Design ◽  
Lithium Bromide ◽  
Electrical Energy ◽  
Solar Thermal ◽  
Absorption Refrigeration ◽  
Refrigeration System ◽  
Annual Average ◽  
Absorption Refrigeration System ◽  
And Performance

A conceptual design of the power system for a water–lithium bromide absorption system is presented in this work for a given cooling load. The proposed system utilizes both solar thermal and the photovoltaic (PV) generated electrical energy for its operation. The performance of the power system is analyzed over a complete year for a designed operation strategy. It is found that the proposed system can provide an annual-average surplus of 17.4 kWh of energy per day after meeting the in-house energy requirements. Finally, an economic analysis is performed to calculate the payback period of the system.

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.

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