TY - GEN

T1 - On the optimization and application of electric propulsion to Mars and sample and return mission

AU - Kawaguchi, Jun'ichiro

AU - Takiura, Kouki

AU - Matsuo, Hiroki

PY - 1994

Y1 - 1994

N2 - Generally speaking, optimization of trajectory inevitably requires so called Two Point Boundary Value Problem (TPBVP). This is true even for optimizing trajectory using low thrust electric propulsion system, which may have been a tough obstacle that prevents propulsion researchers from searching for applications. However, it may well be validated that placing discrete impulsive maneuver points are approximating finite thrusting arcs if gravitational field is almost uniform. That condition is realized in interplanetary field. What this short paper presents is how TPBVP is avoided by introducing multi-impulse method, where linear analysis can be applied to. The process noted here is capable of incorporating a wide variety of practical constraints on the propulsion elements. Numerical illustrations listed here are comprised of 1) Sample and Return Trajectory to Near Earth Asteroid as well as 2) Trans-Mars Trajectory with Spin Stabilized Spacecraft. The latter example is given for the purpose of demonstrating this scheme's versatility in combining attitude constraint. For researchers' convenience, FORTRAN source code examples are attached to.

AB - Generally speaking, optimization of trajectory inevitably requires so called Two Point Boundary Value Problem (TPBVP). This is true even for optimizing trajectory using low thrust electric propulsion system, which may have been a tough obstacle that prevents propulsion researchers from searching for applications. However, it may well be validated that placing discrete impulsive maneuver points are approximating finite thrusting arcs if gravitational field is almost uniform. That condition is realized in interplanetary field. What this short paper presents is how TPBVP is avoided by introducing multi-impulse method, where linear analysis can be applied to. The process noted here is capable of incorporating a wide variety of practical constraints on the propulsion elements. Numerical illustrations listed here are comprised of 1) Sample and Return Trajectory to Near Earth Asteroid as well as 2) Trans-Mars Trajectory with Spin Stabilized Spacecraft. The latter example is given for the purpose of demonstrating this scheme's versatility in combining attitude constraint. For researchers' convenience, FORTRAN source code examples are attached to.

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M3 - Conference contribution

AN - SCOPUS:0027961815

SN - 0877033862

T3 - Advances in the Astronautical Sciences

SP - 539

EP - 556

BT - Advances in the Astronautical Sciences

A2 - Cochran, John E.Jr.

A2 - Edwards, Charles D.Jr.

A2 - Hoffman, Stephen J.

A2 - Holdaway, Richard

PB - Publ by Univelt Inc

T2 - Proceedings of the AAS/AIAA Spaceflight Mechanics Meeting. Part 1 (of 2)

Y2 - 14 February 1994 through 16 February 1994

ER -