scholarly journals Computing the Set of Epsilon-Efficient Solutions in Multiobjective Space Mission Design

2011 ◽  
Vol 8 (3) ◽  
pp. 53-70 ◽  
Author(s):  
Oliver Schutze ◽  
Massimiliano Vasile ◽  
Carlos A. Coello Coello
Keyword(s):  
Space Mission ◽  
Efficient Solutions ◽  
Mission Design ◽  
Space Mission Design

scholarly journals Hyperbolic normal forms and invariant manifolds: Astronomical applications

2012 ◽  
pp. 1-12 ◽  
Author(s):  
C. Efthymiopoulos
Keyword(s):  
Normal Form ◽  
Invariant Manifolds ◽  
Continuation Method ◽  
Space Mission ◽  
Mission Design ◽  
Unstable Periodic Orbits ◽  
Space Mission Design ◽  
Dynamical Astronomy ◽  
Initial Domain ◽  
Asymptotic Orbits

In recent years, the study of the dynamics induced by the invariant manifolds of unstable periodic orbits in nonlinear Hamiltonian dynamical systems has led to a number of applications in celestial mechanics and dynamical astronomy. Two applications of main current interest are i) space manifold dynamics, i.e. the use of the manifolds in space mission design, and, in a quite different context, ii) the study of spiral structure in galaxies. At present, most approaches to the computation of orbits associated with manifold dynamics (i.e. periodic or asymptotic orbits) rely either on the use of the so-called Poincar? - Lindstedt method, or on purely numerical methods. In the present article we briefly review an analytic method of computation of invariant manifolds, first introduced by Moser (1958), and developed in the canonical framework by Giorgilli (2001). We use a simple example to demonstrate how hyperbolic normal form computations can be performed, and we refer to the analytic continuation method of Ozorio de Almeida and co-workers, by which we can considerably extend the initial domain of convergence of Moser?s normal form.

Risk-based technology portfolio optimization for early space mission design

2006 ◽  
Vol 42 (1) ◽  
pp. 22-36 ◽  
Author(s):  
A. Elfes ◽  
W.P. Lincoln ◽  
G. Rodriguez ◽  
C.R. Weisbin ◽  
J.A. Wertz
Keyword(s):  
Portfolio Optimization ◽  
Space Mission ◽  
Mission Design ◽  
Space Mission Design

scholarly journals THE WINCUBE SATTELITE PROJECT MANITOBA HIGH SCHOOL STUDENTS CONSTRUCTING AND LAUNCHING PICO-SATELLITE AND HIGH ALTITUDE BALLOON PAYLOADS

2011 ◽  
Author(s):  
Jeff Cieszecki ◽  
Stevan Wagener
Keyword(s):  
High School ◽  
High School Students ◽  
High Altitude ◽  
Engineering Students ◽  
Space Mission ◽  
Mission Design ◽  
School Students ◽  
Cooperative Effort ◽  
Mentorship Program ◽  
Space Mission Design

The WinCube Satellite Project is a cooperative effort among Manitoba high schools, the Manitoba Satellite Interest group (MSIG), the Faculty of Engineering at the University of Manitoba, Maples Collegiate Space Exploration Academy, the Manitoba Aerospace Human Resources Coordinating Committee and numerous aerospace industry partners. Through a mentorship program, Manitoba high school students will design, construct, and launch a pico-satellite with technical support provided by aerospace faculty and engineering students. Basic system design and construction experience for the high school students is provided by the construction and launch of high altitude balloon payloads. Students learn first hand about space mission design, telecommunications, programming, electrical and mechanical engineering.

scholarly journals Conceptual interplanetary space mission design using multi-objective evolutionary optimization and design grammars

2011 ◽  
Vol 225 (11) ◽  
pp. 1253-1261
Author(s):  
A Weber ◽  
S Fasoulas ◽  
K Wolf
Keyword(s):  
Interplanetary Space ◽  
Space Mission ◽  
Mission Design ◽  
Mission Analysis ◽  
Design Concepts ◽  
Space Mission Design ◽  
Asteroid Mission ◽  
Modular Modelling ◽  
Better Than ◽  
Mission Objective

Conceptual design optimization (CDO) is a technique proposed for the structured evaluation of different design concepts. Design grammars provide a flexible modular modelling architecture. The model is generated by a compiler based on predefined components and rules. The rules describe the composition of the model; thus, different models can be optimized by the CDO in one run. This allows considering a mission design including the mission analysis and the system design. The combination of a CDO approach with a model based on design grammars is shown for the concept study of a near-Earth asteroid mission. The mission objective is to investigate two asteroids of different kinds. The CDO reveals that a mission concept using two identical spacecrafts flying to one target each is better than a mission concept with one spacecraft flying to two asteroids consecutively.

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