Analysis of the Capabilities of the Space Transportation System Using an Electric Propulsion and a Gravitational Maneuver Near the Earth at the Beginning of an Interplanetary Flight

Author(s):  
M.S. Konstantinov ◽  
1982 ◽  
Vol 26 (9) ◽  
pp. 766-767
Author(s):  
A. M. Ray ◽  
A. K. Wildgen ◽  
D. J. Sexton

In order to fully exploit the Shuttle orbiter's payload delivery and retrieval capabilities and to provide on-orbit servicing of other spacecraft systems, a remotely piloted free-flyer will be an essential element of the developing space transportation system. Not only will a free-flying system be able to deliver payloads to a significantly higher orbit than can the Shuttle, it will be able to retrieve satellites from their operational orbit and return them to the orbiter or the earth for servicing. Ultimately, the free-flyer can be used in the construction of large space systems that exceed a single Shuttle launch capability. Following completion of its mission, the free-flyer can return to the earth, or it can remain in orbit for storage between Shuttle missions to eliminate relaunch expenses. The free-flyer may be controlled from either the aft flight deck or a ground based station. Remote control from a ground based station has distinct advantages because it will eliminate all requirements imposed on the Shuttle for aft flight deck and cargo bay flight support equipment and interfaces.


2020 ◽  
Vol 19 (4) ◽  
pp. 58-69
Author(s):  
V. V. Salmin ◽  
A. A. Kvetkin ◽  
A. S. Russkikh

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.


AIAA Journal ◽  
2002 ◽  
Vol 40 ◽  
pp. 781-790
Author(s):  
S. F. Gimelshein ◽  
D. A. Levin ◽  
R. J. Collins

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