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N-body, Single Gravity-Assist Trajectory Design - OTB

版本 1.3.0 (16.2 MB) 作者： David Eagle
Divide-and-conquer approach to solving a single gravity assist interplanetary trajectory subject to n-body perturbations
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更新时间 2022/8/8

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MATLAB script named nbody_flyby_otb that can be used to design interplanetary n-body trajectories that include a single gravity assist maneuver. This script uses a patched-conic (zero sphere-of-influence, ZSOI) solution of the gravity-assist flyby problem as an initial guess for the n-body algorithm. The departure equations of motion include first-order Earth oblateness and point-mass gravity of the sun and moon. The n-body heliocentric equations of motion include the point-mass gravity of the first eight planets.
The n-body trajectory optimization algorithm allows the user to select a “targeting” option at the arrival planet from this list.
  • B-plane components (B dot T and B dot R)
  • orbital elements (periapsis radius and orbital inclination)
  • entry interface (flight path angle, altitude and inclination)
  • node/apse alignment (periapsis radius, ascending node and argument of periapsis)
The n-body simulation minimizes the scalar magnitude of an impulsive interplanetary trajectory correction maneuver (TCM) required to achieve these targets. This maneuver is performed at a user-defined delta time after the gravity-assist.

引用格式

David Eagle (2023). N-body, Single Gravity-Assist Trajectory Design - OTB (https://www.mathworks.com/matlabcentral/fileexchange/89137-n-body-single-gravity-assist-trajectory-design-otb), MATLAB Central File Exchange. 检索来源 .

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版本 已发布 发行说明
1.3.0

Algorithm and documentation updates. Flight path angle bug fix.
1.2.0

Added graphic displays of the heliocentric and planet-centered classical orbital elements and speed during the gravity assist.
1.1.0

Minor updates to source code. New PDF user's guide. Implemented JPL MICE ephemeris (DE421).
1.0.0