scholarly journals An Interplanetary Mission Design of a Solar Sailing CubeSat to Mars

2020 ◽  
Vol 1509 ◽  
pp. 012026
Author(s):  
Andrew J Tang ◽  
Xiaofeng Wu
Keyword(s):  
Mission Design ◽  
Solar Sailing ◽  
Interplanetary Mission

A Parametric Study of Interplanetary Mission Using Solar Sail

2014 ◽  
Vol 629 ◽  
pp. 291-297 ◽  
Author(s):  
Harijono Djojodihardjo ◽  
Ali Yousefian
Keyword(s):  
Parametric Study ◽  
High Speed ◽  
Solar Sail ◽  
Space Propulsion ◽  
Solar Sailing ◽  
To Come ◽  
Interplanetary Mission

Solar sailing has been an attractive concept and possibly an alternative mean of space propulsion for decades to come since solar sail spacecrafts can generate thrust without requiring any propellant. While the resulting acceleration is small, the continuous thrust would lead to high speed.  The present work serves to demonstrate the potential of solar sail by analyzing the dynamics of a spacecraft utilizing solar sail and by carrying out a parametric study for an interplanetary mission exemplified by specific trajectory to Mars.

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.

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

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.

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.

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