Low-Thrust Interplanetary Mission Design Using Differential Inclusion

2002 ◽  
Author(s):  
Jennifer Hargens ◽  
Victoria Coverstone
Keyword(s):  
Differential Inclusion ◽  
Mission Design ◽  
Low Thrust ◽  
Interplanetary Mission

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

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.

scholarly journals IRMA: a Graphical Tool for Interplanetary Mission Design

2018 ◽  
Vol 210 ◽  
pp. 02049
Author(s):  
Giancarlo Genta ◽  
P. Federica Maffione
Keyword(s):  
Direct Methods ◽  
Optimization Techniques ◽  
Mission Design ◽  
Complex Task ◽  
Solar Sails ◽  
Graphical Tool ◽  
Arrival Dates ◽  
Patched Conics ◽  
The Cost ◽  
Interplanetary Mission

Designing an interplanetary mission is a complex task and requires the choice of the launch opportunity and of the exact launch and arrival dates. Depending on these choices, the trajectory must be defined and, in case of continuous thrust, also the thrust profile needs to be optimized.. Traditionally, these choices are made using some plots which allow to find a good compromise between the travel duration and the cost of the mission, which is often expressed in terms of initial mass in Earth orbit (IMLEO). IRMA (InterPlanetary Mission Analysis) code, based on the MATLAB®environment, is here described. It allows to deal with both impulsive propulsion (using the patched conics approach) and low continuous thrust (Solar or Nuclear electric or propellantless, like solar sails). A specific solver, based on indirect optimization techniques, has been developed specifically for this program, but IRMA can be used also as an interface for standard solvers, based on direct methods, like the FALCON.m code.

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

scholarly journals A Clementine II Mission to the Asteroids

1997 ◽  
Vol 165 ◽  
pp. 183-190
Author(s):  
A.S. Hope ◽  
B. Kaufman ◽  
R. Dasenbrock ◽  
D. Bakeris
Keyword(s):  
Department Of Defense ◽  
Mission Design ◽  
Interplanetary Mission

AbstractClementine II is a Department of Defense (DoD) and industry interplanetary mission designed to flyby several asteroids and release science probes that will impact these asteroids. Candidate asteroids were identified and a nominal and backup mission was chosen from these candidates. The mission design is discussed and the baseline encounters are presented. A backup mission is briefly described. A mass breakdown for the baseline mission is provided as well as the proposed mission sensors. The final encounter approach B-Plane errors are determined and analyzed. A final summary of the Clementine II mission is presented.

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