Exact(2)
Propellantless continuous-thrust propulsion systems, such as electric solar wind sails, may be successfully used for new space missions, especially those requiring high-energy orbit transfers.
In this paper, we describe methods to construct complex chains of orbit transfers in the planar circular restricted Earth Moon three-body system using the invariant manifolds of unstable three-body orbits.
Similar(58)
In this guidance scheme, the ANN is adopted to determine the burn structure within each orbital revolution and the optimal low-thrust orbit transfer problem is converted to the parameter optimization problem.
To demonstrate the orbit transfer capabilities of the concurrent controller, a smooth elliptical orbit transfer trajectory for co-planar circular orbits is designed.
Orbit maneuver via tether is a promising countermeasure for space debris removal and satellite orbit transfer.
Here we explore the orbit transfer problem of a low-thrust spacecraft in the interplanetary space.
This paper discusses the thrust vector control (TVC) of the upper stage during its orbit transfer.
The direct libration point orbit transfer and injection method is adopted to solve the issue in the transfer trajectory design.
During orbit transfer, the thrust vector of this gimbaled thruster (GT) should theoretically pass through the mass center of the upper stage and align with the command direction to provide orbit transfer impetus.
In this paper, the concept of Orbit Transfer Vehicle for Deep Space Exploration Deep Space OTVV) is proposed, and its effectiveness and feasibility are discussed.
In addition, these technologies are required for spacecraft and orbit transfer vehicle propulsion and power systems, and space life support.
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