From b99bf2a0172fa3ed4f90d7373e677b705639f8ea Mon Sep 17 00:00:00 2001 From: =?UTF-8?q?Lars=20Hin=C3=BCber?= <105521415+larshinueber@users.noreply.github.com> Date: Fri, 11 Oct 2024 23:38:50 +0200 Subject: [PATCH 1/3] move mga trajectories in mission design --- README.md | 2 +- {propagation => mission_design}/mga_trajectories.ipynb | 0 {propagation => mission_design}/mga_trajectories.py | 0 3 files changed, 1 insertion(+), 1 deletion(-) rename {propagation => mission_design}/mga_trajectories.ipynb (100%) rename {propagation => mission_design}/mga_trajectories.py (100%) diff --git a/README.md b/README.md index 1c7a317..b756f98 100644 --- a/README.md +++ b/README.md @@ -27,6 +27,7 @@ Examples related to state estimation. Examples related to mission design. +- ``mga_trajectories``: simulation of Multiple Gravity Assist (MGA) transfer trajectories using high- and low-thrust transfers, as well as deep space maneuvers (DSMs). - ``cassini1_mga_optimization``: using PyGMO to optimize an interplanetary transfer trajectory simulated using the multiple gravity assist (MGA) module of Tudat. - ``hodographic_shaping_mga_optimization``: extension of the ``cassini1_mga_optimization`` example. Optimization of a low-thrust interplanetary transfer trajectory using the hodographic shaping method for the low-thrust legs. - ``earth_mars_transfer_window``: usage of the Tudatpy's `porkchop` module to determine an optimal launch window (departure and arrival date) for an Earth-Mars transfer mission. @@ -52,7 +53,6 @@ Advanced examples: - ``separation_satellites_diff_drag``: shows the effects of differential drag for CubeSats in LEO. - ``coupled_translational_rotational_dynamics``: using a multi-type propagator to simulate the coupled translational-rotational dynamics of Phobos around Mars. - ``impact_manifolds_lpo_cr3bp``: setup and propagation of orbits and their invariant manifolds in the circular restricted three body problem (CR3BP) with a polyhedral secondary body. -- ``mga_trajectories``: simulation of Multiple Gravity Assist (MGA) transfer trajectories using high- and low-thrust transfers, as well as deep space maneuvers (DSMs). ### Pygmo diff --git a/propagation/mga_trajectories.ipynb b/mission_design/mga_trajectories.ipynb similarity index 100% rename from propagation/mga_trajectories.ipynb rename to mission_design/mga_trajectories.ipynb diff --git a/propagation/mga_trajectories.py b/mission_design/mga_trajectories.py similarity index 100% rename from propagation/mga_trajectories.py rename to mission_design/mga_trajectories.py From 17c8b45de8adf775a771d9485e3ffd4f5de99d51 Mon Sep 17 00:00:00 2001 From: =?UTF-8?q?Lars=20Hin=C3=BCber?= <105521415+larshinueber@users.noreply.github.com> Date: Sat, 12 Oct 2024 00:15:25 +0200 Subject: [PATCH 2/3] demote heading section --- estimation/full_estimation_example.ipynb | 11 ++++------- 1 file changed, 4 insertions(+), 7 deletions(-) diff --git a/estimation/full_estimation_example.ipynb b/estimation/full_estimation_example.ipynb index 2f632b7..a389e5f 100644 --- a/estimation/full_estimation_example.ipynb +++ b/estimation/full_estimation_example.ipynb @@ -647,7 +647,7 @@ "id": "a77ce688-d439-4a37-94ee-ea9cd10b0d3d", "metadata": {}, "source": [ - "# True Errors, Formal Errors\n", + "## True Errors, Formal Errors\n", "\n", "Since we have now estimated the actual parameters - unlike when only getting the initial covariance matrix over the course of the orbit, as done in [Delfi-C3 Covariance Analysis example](https://docs.tudat.space/en/latest/_src_getting_started/_src_examples/notebooks/estimation/covariance_estimated_parameters.html) - we are able to qualitatively compare the goodness-of-fit of the found parameters with the known ground truth ones. \n", "\n", @@ -881,13 +881,10 @@ } ], "metadata": { - "interpreter": { - "hash": "4a4d53b53330cd83e1499268313a4bcd5eafe4bf50523883929af79f2dd687b2" - }, "kernelspec": { - "display_name": "tudat-bundle", + "display_name": "tudat-examples", "language": "python", - "name": "tudat-bundle" + "name": "python3" }, "language_info": { "codemirror_mode": { @@ -899,7 +896,7 @@ "name": "python", "nbconvert_exporter": "python", "pygments_lexer": "ipython3", - "version": "3.11.9" + "version": "3.10.14" } }, "nbformat": 4, From 0395ad428c21f610c48a9ae0108d284abd827e25 Mon Sep 17 00:00:00 2001 From: =?UTF-8?q?Lars=20Hin=C3=BCber?= <105521415+larshinueber@users.noreply.github.com> Date: Sat, 12 Oct 2024 00:41:53 +0200 Subject: [PATCH 3/3] make titles more descriptive --- propagation/linear_sensitivity_analysis.ipynb | 9 ++++----- propagation/reentry_trajectory.ipynb | 8 ++++---- propagation/solar_system_propagation.ipynb | 6 +++--- 3 files changed, 11 insertions(+), 12 deletions(-) diff --git a/propagation/linear_sensitivity_analysis.ipynb b/propagation/linear_sensitivity_analysis.ipynb index 6214150..3ef357a 100644 --- a/propagation/linear_sensitivity_analysis.ipynb +++ b/propagation/linear_sensitivity_analysis.ipynb @@ -5,7 +5,7 @@ "id": "1fe978b0-d823-4f3e-b3e6-86a3e25cedbc", "metadata": {}, "source": [ - "# Linear sensitivity analysis of perturbed orbit\n", + "# Linear sensitivity analysis using variational equations\n", "\n", "## Objectives\n", "This example is an extension of the Perturbed Satellite Orbit Application. It adopts the simulation setup from the Perturbed Satellite Orbit, considering a slightly reduced set of perturbing accelerations for the propagation of the vehicle.\n", @@ -14,7 +14,6 @@ "\n", "Via the `estimation_setup.parameter module`, the system parameters w.r.t. which the sensitivity is to be studied are defined and a `create_variational_equations_solver` function from the numerical_simulation module is used in order to setup and integrate the system's variational equations. After obtaining the state transition matrices from the integrated variational equations, the system's response to small perturbations can be tested via simple matrix multiplication.\n", "\n", - "\n", "The availability of variational equations in tudat enables many more, advanced functionalities, such as covariance analysis and precise orbit determination." ] }, @@ -563,9 +562,9 @@ ], "metadata": { "kernelspec": { - "display_name": "tudat-bundle", + "display_name": "tudat-examples", "language": "python", - "name": "tudat-bundle" + "name": "python3" }, "language_info": { "codemirror_mode": { @@ -577,7 +576,7 @@ "name": "python", "nbconvert_exporter": "python", "pygments_lexer": "ipython3", - "version": "3.11.9" + "version": "3.10.14" } }, "nbformat": 4, diff --git a/propagation/reentry_trajectory.ipynb b/propagation/reentry_trajectory.ipynb index ff66acf..87e79e1 100644 --- a/propagation/reentry_trajectory.ipynb +++ b/propagation/reentry_trajectory.ipynb @@ -5,7 +5,7 @@ "id": "fe6987ee-7907-4b32-b8b4-30927d4e7970", "metadata": {}, "source": [ - "# Re-entry trajectory\n", + "# Re-entry trajectory using custom aerodynamic guidance\n", "\n", "## Objectives\n", "\n", @@ -995,9 +995,9 @@ ], "metadata": { "kernelspec": { - "display_name": "tudat-bundle", + "display_name": "tudat-examples", "language": "python", - "name": "tudat-bundle" + "name": "python3" }, "language_info": { "codemirror_mode": { @@ -1009,7 +1009,7 @@ "name": "python", "nbconvert_exporter": "python", "pygments_lexer": "ipython3", - "version": "3.11.9" + "version": "3.10.14" } }, "nbformat": 4, diff --git a/propagation/solar_system_propagation.ipynb b/propagation/solar_system_propagation.ipynb index 4012afe..2322527 100644 --- a/propagation/solar_system_propagation.ipynb +++ b/propagation/solar_system_propagation.ipynb @@ -5,7 +5,7 @@ "id": "a22ea1d1-e56f-464d-a03e-02b2f0e27bfb", "metadata": {}, "source": [ - "# Solar System Propagation\n", + "# Solar System Propagation using Multi-Body Dynamics\n", "Copyright (c) 2010-2022, Delft University of Technology. All rights reserved. This file is part of the Tudat. Redistribution and use in source and binary forms, with or without modification, are permitted exclusively under the terms of the Modified BSD license. You should have received a copy of the license with this file. If not, please or visit: http://tudat.tudelft.nl/LICENSE.\n", "\n", "## Objectives\n", @@ -470,7 +470,7 @@ ], "metadata": { "kernelspec": { - "display_name": "Python 3 (ipykernel)", + "display_name": "tudat-examples", "language": "python", "name": "python3" }, @@ -484,7 +484,7 @@ "name": "python", "nbconvert_exporter": "python", "pygments_lexer": "ipython3", - "version": "3.11.9" + "version": "3.10.14" } }, "nbformat": 4,