Interplanetary trajectory design for the Galileo mission

1983 ◽  
Author(s):  
L. DAMARIO ◽  
D. BYRNES
Keyword(s):  
Trajectory Design ◽  
Interplanetary Trajectory

scholarly journals A Unified Framework for Aerocapture Systems Analysis

2019 ◽  
Author(s):  
Athul Pradeepkumar Girija
Keyword(s):  
Systems Analysis ◽  
Mission Design ◽  
Vehicle Design ◽  
Trajectory Design ◽  
Unified Framework ◽  
Trade Offs ◽  
Subsystem Level ◽  
Interplanetary Trajectory ◽  
Level Analysis ◽  
Systems Studies

A unified framework for aerocapture systems analysis studies is presented, taking into account the interconnected nature of interplanetary trajectory design and vehicle design. One of the limitations of previous aerocapture systems studies is their focus on a single interplanetary trajectory for detailed subsystem level analysis. The proposed framework and aerocapture feasibility charts enable a mission designer to perform rapid trajectory and vehicle design trade-offs, and is illustrated with its application to a Neptune mission. The approach can be applied to other atmosphere-bearing Solar System destinations. The framework can be be implemented in an aerocapture software suite to enable rapid mission design studies.

scholarly journals Solution for Nonlinear Three-Dimensional Intercept Problem with Minimum Energy

2013 ◽  
Vol 2013 ◽  
pp. 1-8 ◽  
Author(s):  
Henzeh Leeghim ◽  
Donghoon Kim ◽  
James Turner
Keyword(s):  
Optimization Problem ◽  
Minimum Energy ◽  
Three Dimensional ◽  
Problem Formulation ◽  
Initial Position ◽  
Iteration Algorithm ◽  
Trajectory Design ◽  
Interplanetary Trajectory ◽  
Classical Orbit ◽  
Hohmann Transfer

Classical orbit intercept applications are commonly formulated and solved as Lambert-type problems, where the time-of-flight (TOF) is prescribed. For general three-dimensional intercept problems, selecting a meaningful TOF is often a difficult and an iterative process. This work overcomes this limitation of classical Lambert’s problem by reformulating the intercept problem in terms of a minimum-energy application, which then generates both the desired initial interceptor velocity and the TOF for the minimum-energy transfer. The optimization problem is formulated by using the classical Lagrangianfandgcoefficients, which map initial position and velocity vectors to future times, and a universal time variablex. A Newton-Raphson iteration algorithm is introduced for iteratively solving the problem. A generalized problem formulation is introduced for minimizing the TOF as part of the optimization problem. Several examples are presented, and the results are compared with the Hohmann transfer solution approaches. The resulting minimum-energy intercept solution algorithm is expected to be broadly useful as a starting iterative for applications spanning: targeting, rendezvous, interplanetary trajectory design, and so on.

Optimum two-impulse transfers for preliminary interplanetary trajectory design

1984 ◽  
Vol 7 (4) ◽  
pp. 458-461 ◽  
Author(s):  
Neal D. Hulkower ◽  
Cynthia O. Lau ◽  
David F. Bender
Keyword(s):  
Trajectory Design ◽  
Interplanetary Trajectory

Mars interplanetary trajectory design via Lagrangian points

2014 ◽  
Vol 353 (1) ◽  
pp. 65-71 ◽  
Author(s):  
Roshan Thomas Eapen ◽  
Ram Krishan Sharma
Keyword(s):  
Trajectory Design ◽  
Lagrangian Points ◽  
Interplanetary Trajectory
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