scholarly journals Low-thrust Propulsion Technologies, Mission Design, and Application

10.5772/6932 ◽  
2010 ◽  
Author(s):  
John W.
Keyword(s):  
Mission Design ◽  
Low Thrust ◽  
Design And Application

Initial design of low-thrust trajectories based on the Bezier curve-based shaping approach

2020 ◽  
Vol 234 (11) ◽  
pp. 1825-1835
Author(s):  
Zichen Fan ◽  
Mingying Huo ◽  
Naiming Qi ◽  
Ce Zhao ◽  
Ze Yu ◽  
...  
Keyword(s):  
Fourier Series ◽  
Three Dimensional ◽  
Initial Approximation ◽  
Mission Design ◽  
Bézier Curve ◽  
Design Stage ◽  
Bezier Curve ◽  
Series Method ◽  
Low Thrust ◽  
Fourier Series Method

This paper presents a method to use the Bezier curve to rapidly generate three-dimensional low-thrust trajectories, which can provide a suitable initial approximation to be used for more accurate trajectory optimal control tools. Two missions, from Earth to Mars and the asteroid Dionysus, are considered to evaluate the performance of the method. In order to verify the advantages of this method, it is compared with the finite Fourier series method. Numerical results show that the Bezier method can get better performance index in shorter computation time compared with the finite Fourier series method. The applicability of the solution obtained by Bezier method is evaluated by introducing the obtained solution into the Gauss pseudospectral method as an initial guess. The simulation results show that the Bezier method can rapidly generate a very suitable three-dimensional initial trajectory for the optimal solver. This is very important for rapid evaluation of the feasibility of a large number of low-thrust flight schemes in the preliminary mission design stage.

Mission design for deep space 1: A low-thrust technology validation mission

1999 ◽  
Vol 45 (4-9) ◽  
pp. 381-388 ◽  
Author(s):  
Marc D. Rayman ◽  
Pamela A. Chadbourne ◽  
Jeffery S. Culwell ◽  
Steven N. Williams
Keyword(s):  
Mission Design ◽  
Low Thrust ◽  
Deep Space

Response Surface Regressions for Low-Thrust Interplanetary Mission Design

2016 ◽  
Author(s):  
Eugina D. Mendez Ramos ◽  
Pranay Mishra ◽  
Stephen Edwards ◽  
Dimitri Mavris
Keyword(s):  
Response Surface ◽  
Mission Design ◽  
Low Thrust ◽  
Interplanetary Mission

Investigating the Design Space for Solar Sail Trajectories in the Earth-Moon System

2011 ◽  
Vol 4 (1) ◽  
pp. 26-44 ◽  
Author(s):  
Geoffrey G. Wawrzyniak ◽  
Kathleen C. Howell
Keyword(s):  
Design Space ◽  
Solar Sail ◽  
Mission Design ◽  
South Pole ◽  
Low Thrust ◽  
Solar Sails ◽  
Moon System ◽  
Solar Sailing ◽  
The Earth ◽  
Lunar South Pole

Solar sailing is an enabling technology for many mission applications. One potential application is the use of a sail as a communications relay for a base at the lunar south pole. A survey of the design space for a solar sail spacecraft that orbits in view of the lunar south pole at all times demonstrates that trajectory options are available for sails with characteristic acceleration values of 1.3 mm/s or higher. Although the current sail technology is presently not at this level, this survey reveals the minimum acceleration values that are required for sail technology to facilitate the lunar south pole application. This information is also useful for potential hybrid solar-sail-low-thrust designs. Other critical metrics for mission design and trajectory selection are also examined, such as body torques that are required to articulate the vehicle orientation, sail pitch angles throughout the orbit, and trajectory characteristics that would impact the design of the lunar base. This analysis and the techniques that support it supply an understanding of the design space for solar sails and their trajectories in the Earth-Moon system.

A lunar cargo mission design strategy using variable low thrust

2009 ◽  
Vol 43 (9) ◽  
pp. 1391-1406 ◽  
Author(s):  
Young-Joo Song ◽  
Sang-Young Park ◽  
Kyu-Hong Choi ◽  
Eun-Sup Sim
Keyword(s):  
Design Strategy ◽  
Mission Design ◽  
Low Thrust

Indirect low-thrust trajectory optimization with gridded ion thruster model

2021 ◽  
pp. 095441002110438
Author(s):  
Zhemin Chi ◽  
Yang Wang ◽  
Lin Cheng
Keyword(s):  
Trajectory Optimization ◽  
Electric Propulsion ◽  
Specific Impulse ◽  
Input Power ◽  
Minimum Time ◽  
Mission Design ◽  
Low Thrust ◽  
Ion Thruster ◽  
Solar Electric Propulsion ◽  
Operational Constraints

The work deals with indirect optimization of minimum-time and minimum-fuel interplanetary trajectories when gridded ion thruster models are considered. Using an accurate model of solar electric propulsion is beneficial in preliminary mission design, and allows including operational constraints. The maximum thrust and the specific impulse are expressed as a function of thruster input power, which is achieved by means of point-fitting lines that match the performance capabilities of the thrusters. Minimum-time and minimum-fuel problems are formulated to be solved by indirect optimization. In order to increase the accuracy and robustness of the shooting procedure, analytic Jacobians are derived, and a hybrid switching detection technique is used to improve the integration accuracy for minimum-fuel problems. Two examples of Earth-to-Mars transfer and Near-Earth rendezvous mission using the realistic NASA’s Evolutionary Xenon Thruster (NEXT) are given to substantiate the feasibility and effectiveness of the proposed method.

Navigation and Mission Design for Low-Thrust Insertion into Near Rectilinear Halo Orbits

2022 ◽  
Author(s):  
Ethan W. Kayser ◽  
Michael R. Thompson ◽  
Matthew Bolliger ◽  
Nathan P. Ré ◽  
Diane C. Davis ◽  
...  
Keyword(s):  
Mission Design ◽  
Low Thrust ◽  
Halo Orbits ◽  
Near Rectilinear Halo Orbits
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