diff --git a/Home/.documenter-siteinfo.json b/Home/.documenter-siteinfo.json index 4ba4cfd3..d9d486ac 100644 --- a/Home/.documenter-siteinfo.json +++ b/Home/.documenter-siteinfo.json @@ -1 +1 @@ -{"documenter":{"julia_version":"1.8.5","generation_timestamp":"2024-04-12T12:28:45","documenter_version":"1.3.0"}} \ No newline at end of file +{"documenter":{"julia_version":"1.8.5","generation_timestamp":"2024-04-19T12:28:52","documenter_version":"1.4.0"}} \ No newline at end of file diff --git a/Home/ecosystem/mission/index.html b/Home/ecosystem/mission/index.html index ae97edf5..7b3306f9 100644 --- a/Home/ecosystem/mission/index.html +++ b/Home/ecosystem/mission/index.html @@ -2,4 +2,4 @@ function gtag(){dataLayer.push(arguments);} gtag('js', new Date()); gtag('config', 'G-K7LNGMSXLE'); -Mission · JSMD Documentation
GitHub

Mission

We are developing a comprehensive software package ecosystem for space mission design and simulation. Our ecosystem will enable users to design and simulate every aspect of a mission, from the initial conceptual design to operations, using modular, extensible, and easy-to-use packages.

Our packages will be designed to be modular, extensible, and easy to use. This means that users can choose the packages that suit their needs, combine them in different ways, and customize them as they wish. Our packages will also follow common standards and interfaces, so that they can be integrated with other tools and frameworks.

One of the frameworks that we will leverage is [SciML], a scientific machine learning ecosystem that provides high-performance, scalable, and differentiable solutions for scientific computing. SciML offers a variety of packages for solving various scientific problems, such as differential equations, optimization, uncertainty quantification, and more.

We will also introduce AI within our ecosystem to create efficient digital twins of satellites. A digital twin is a virtual representation of a physical system that can be used to monitor, analyze, and optimize its performance. By using AI, we will create digital twins that can learn from data, adapt to changes, and generate predictions and recommendations. This will enable us to improve the design, testing, and operation of satellites, as well as to detect and prevent failures, anomalies, and faults.

Our mission is to create a software package ecosystem that can help users to design and simulate space missions in a fast, accurate, and reliable way. We hope that our ecosystem will contribute to the advancement of space science and technology, and inspire innovations.

\ No newline at end of file +Mission · JSMD Documentation
GitHub

Mission

We are developing a comprehensive software package ecosystem for space mission design and simulation. Our ecosystem will enable users to design and simulate every aspect of a mission, from the initial conceptual design to operations, using modular, extensible, and easy-to-use packages.

Our packages will be designed to be modular, extensible, and easy to use. This means that users can choose the packages that suit their needs, combine them in different ways, and customize them as they wish. Our packages will also follow common standards and interfaces, so that they can be integrated with other tools and frameworks.

One of the frameworks that we will leverage is [SciML], a scientific machine learning ecosystem that provides high-performance, scalable, and differentiable solutions for scientific computing. SciML offers a variety of packages for solving various scientific problems, such as differential equations, optimization, uncertainty quantification, and more.

We will also introduce AI within our ecosystem to create efficient digital twins of satellites. A digital twin is a virtual representation of a physical system that can be used to monitor, analyze, and optimize its performance. By using AI, we will create digital twins that can learn from data, adapt to changes, and generate predictions and recommendations. This will enable us to improve the design, testing, and operation of satellites, as well as to detect and prevent failures, anomalies, and faults.

Our mission is to create a software package ecosystem that can help users to design and simulate space missions in a fast, accurate, and reliable way. We hope that our ecosystem will contribute to the advancement of space science and technology, and inspire innovations.

\ No newline at end of file diff --git a/Home/ecosystem/roadmap/index.html b/Home/ecosystem/roadmap/index.html index bd3fcf88..35b0c0f7 100644 --- a/Home/ecosystem/roadmap/index.html +++ b/Home/ecosystem/roadmap/index.html @@ -2,4 +2,4 @@ function gtag(){dataLayer.push(arguments);} gtag('js', new Date()); gtag('config', 'G-K7LNGMSXLE'); -JSMD Roadmap · JSMD Documentation
GitHub
\ No newline at end of file +JSMD Roadmap · JSMD Documentation
GitHub
\ No newline at end of file diff --git a/Home/encyclopedia/astro/frames/iers/index.html b/Home/encyclopedia/astro/frames/iers/index.html index 2be30f82..2326a8e0 100644 --- a/Home/encyclopedia/astro/frames/iers/index.html +++ b/Home/encyclopedia/astro/frames/iers/index.html @@ -53,4 +53,4 @@ \Delta\psi &= \Delta\psi_{2000A} + (0.4697 \times 10^{-6} + f)\Delta\psi_{2000A} \\ \Delta\epsilon &= (1+f)\Delta\epsilon_{2000A} \\ \end{aligned} -\end{equation*}\]

where $f = -2.774 \times 10^{-6}t$ account for Earth's $J_2$ rate effect, which was not taken into account in IAU 2000. Additional small changes to the nutation in longitude amplitudes are required to ensure compatibility with teh IAU 2006 values for $\epsilon_0$.

Note

The coefficients for $\Delta\psi_{2000A}$ and $\Delta\epsilon_{2000A}$ available from the IERS tables already account for the amplitude change in longitude, whereas the SOFA function nut00a equals the original IAU 2000A series.

Note

The SOFA implementation of the IAU 2000A nutation takes

Fundamental Arguments

The fundamental arguments of the nutation theory are a set of parameters that account for luni-solar and planetary nutation contributions. The former, also known as Delaunay arguments are the mean anomalies for the Moon and Sun, $l$ and $l'$, the mean argument of latitude of the Moon, $F$, measured on the ecliptic from the mean equinox of date, the mean elongation from the Sun $D$, and the right ascension of the ascending node of the mean lunar orbit, $\Omega$, measured along the ecliptic from the mean equinox of date. The arguments to compute the corrections for the planetary effects on the nutation and the obliquity of the ecliptic are the mean Heliocentric longitudes of the planets ($\lambda_i$), and the general precession in longitude ($p_\lambda$). The numerical expressions of these arguments are available on the IERS Conventions 2010.

Note

The original fundamental arguments are function of time $t$ measured in TDB. However, changes in the nutation amplitudes resulting from the difference TDB-TT are responsible for a difference in the CIP location that is less than 0.01 $\mu\text{as}$, which is significantly below the required microarcseconds accuracy. Therefore, in pratice, TT is often used in place of TDB.

Note

The SOFA library, which provides standard routines and algorithms for fundamental astronomy, follows a strict compliance with the MHB2000 code for the IAU 2000A nutation model. As a consequence, simplified and slightly different expressions for the Delaunay variables and the longitude of Neptune are used. However, the maximum differences caused by this divergence are about 0.013 $\mu\text{as}$ after one century.

References

  1. Lieske, J. H. et al. (1977), Expressions for the Precession Quantities Based upon the IAU (1976) System of Astronomical ConstantsFull Text Source
  2. Seidelmann, P. K. (1982), 1980 IAU Theory of Nutation: The Final report of the IAU Working Group on NutationDOI: 10.1007/BF01228952
  3. Mathews, P. M. et al. (2002), Modeling of nutation and precession: New nutation series for nonrigid Earth, and insights into the Earth's InteriorDOI: 10.1029/2001JB000390
  4. McCarthy, D. D. and Luzum, B. J. (2003), An Abridged Model of the Precession-Nutation of the Celestial PoleDOI: 10.1023/A:1021762727016
  5. Capitaine, N. et al. (2003c), Expressions for IAU 2000 precession quantitiesDOI: 10.1051/0004-6361:20031539
  6. Lambert, S. and Bizouard C. (2002), Positioning the Terrestrial Ephemeris Origin in the Terrestrial Reference Frame, DOI: 10.1051/0004-6361:20021139
  7. Luzum, B. and Petit G. (2012). The IERS Conventions (2010), IERS Technical Note No. 36
  8. Capitaine, N. and Wallace P.T. (2006), High precision methods for locating the celestial intermediate pole and originDOI: 10.1051/0004-6361:20054550
  9. Wallace P.T. and Capitaine N. (2006), Precession-nutation procedures consistent with IAU 2006 resolutions
  10. Vallado D. Fundamentals of Astrodynamics
\ No newline at end of file +\end{equation*}\]

where $f = -2.774 \times 10^{-6}t$ account for Earth's $J_2$ rate effect, which was not taken into account in IAU 2000. Additional small changes to the nutation in longitude amplitudes are required to ensure compatibility with teh IAU 2006 values for $\epsilon_0$.

Note

The coefficients for $\Delta\psi_{2000A}$ and $\Delta\epsilon_{2000A}$ available from the IERS tables already account for the amplitude change in longitude, whereas the SOFA function nut00a equals the original IAU 2000A series.

Note

The SOFA implementation of the IAU 2000A nutation takes

Fundamental Arguments

The fundamental arguments of the nutation theory are a set of parameters that account for luni-solar and planetary nutation contributions. The former, also known as Delaunay arguments are the mean anomalies for the Moon and Sun, $l$ and $l'$, the mean argument of latitude of the Moon, $F$, measured on the ecliptic from the mean equinox of date, the mean elongation from the Sun $D$, and the right ascension of the ascending node of the mean lunar orbit, $\Omega$, measured along the ecliptic from the mean equinox of date. The arguments to compute the corrections for the planetary effects on the nutation and the obliquity of the ecliptic are the mean Heliocentric longitudes of the planets ($\lambda_i$), and the general precession in longitude ($p_\lambda$). The numerical expressions of these arguments are available on the IERS Conventions 2010.

Note

The original fundamental arguments are function of time $t$ measured in TDB. However, changes in the nutation amplitudes resulting from the difference TDB-TT are responsible for a difference in the CIP location that is less than 0.01 $\mu\text{as}$, which is significantly below the required microarcseconds accuracy. Therefore, in pratice, TT is often used in place of TDB.

Note

The SOFA library, which provides standard routines and algorithms for fundamental astronomy, follows a strict compliance with the MHB2000 code for the IAU 2000A nutation model. As a consequence, simplified and slightly different expressions for the Delaunay variables and the longitude of Neptune are used. However, the maximum differences caused by this divergence are about 0.013 $\mu\text{as}$ after one century.

References

  1. Lieske, J. H. et al. (1977), Expressions for the Precession Quantities Based upon the IAU (1976) System of Astronomical ConstantsFull Text Source
  2. Seidelmann, P. K. (1982), 1980 IAU Theory of Nutation: The Final report of the IAU Working Group on NutationDOI: 10.1007/BF01228952
  3. Mathews, P. M. et al. (2002), Modeling of nutation and precession: New nutation series for nonrigid Earth, and insights into the Earth's InteriorDOI: 10.1029/2001JB000390
  4. McCarthy, D. D. and Luzum, B. J. (2003), An Abridged Model of the Precession-Nutation of the Celestial PoleDOI: 10.1023/A:1021762727016
  5. Capitaine, N. et al. (2003c), Expressions for IAU 2000 precession quantitiesDOI: 10.1051/0004-6361:20031539
  6. Lambert, S. and Bizouard C. (2002), Positioning the Terrestrial Ephemeris Origin in the Terrestrial Reference Frame, DOI: 10.1051/0004-6361:20021139
  7. Luzum, B. and Petit G. (2012). The IERS Conventions (2010), IERS Technical Note No. 36
  8. Capitaine, N. and Wallace P.T. (2006), High precision methods for locating the celestial intermediate pole and originDOI: 10.1051/0004-6361:20054550
  9. Wallace P.T. and Capitaine N. (2006), Precession-nutation procedures consistent with IAU 2006 resolutions
  10. Vallado D. Fundamentals of Astrodynamics
\ No newline at end of file diff --git a/Home/encyclopedia/astro/frames/index.html b/Home/encyclopedia/astro/frames/index.html index 0791980f..71619381 100644 --- a/Home/encyclopedia/astro/frames/index.html +++ b/Home/encyclopedia/astro/frames/index.html @@ -2,4 +2,4 @@ function gtag(){dataLayer.push(arguments);} gtag('js', new Date()); gtag('config', 'G-K7LNGMSXLE'); -Reference Frames & Transformations · JSMD Documentation
GitHub

Reference Frames & Transformations

Astronomical reference frames play a vital role in engineering applications related to space exploration, satellite navigation, and astrodynamics. These reference frames provide a standardized system for precisely defining the positions, motions, and orientations of celestial objects, enabling engineers to navigate through space, track satellites, and plan spacecraft missions with accuracy and precision.

In engineering, different reference frames are employed to meet specific requirements and facilitate various tasks. The aim of this part of the documentation is to provide a concise, clear and mathematically accurate representation of the most used reference frames.

Models

\ No newline at end of file +Reference Frames & Transformations · JSMD Documentation
GitHub

Reference Frames & Transformations

Astronomical reference frames play a vital role in engineering applications related to space exploration, satellite navigation, and astrodynamics. These reference frames provide a standardized system for precisely defining the positions, motions, and orientations of celestial objects, enabling engineers to navigate through space, track satellites, and plan spacecraft missions with accuracy and precision.

In engineering, different reference frames are employed to meet specific requirements and facilitate various tasks. The aim of this part of the documentation is to provide a concise, clear and mathematically accurate representation of the most used reference frames.

Models

\ No newline at end of file diff --git a/Home/encyclopedia/astro/gravity/harmonics/index.html b/Home/encyclopedia/astro/gravity/harmonics/index.html index eccaabc4..d63f55c5 100644 --- a/Home/encyclopedia/astro/gravity/harmonics/index.html +++ b/Home/encyclopedia/astro/gravity/harmonics/index.html @@ -41,4 +41,4 @@ \xi_{nm} &= \frac{1}{2}\, \frac{N_{nm}}{N_{n+1,m+1}} = \frac{1}{2} \,F_{n,m,n+1,m+1}\\ \chi_{nm} &= \frac{1}{2}(n-m+2)(n-m+1)\,\frac{N_{nm}}{N_{n+1,m-1}} = \frac{1}{2}(n-m+2)(n-m+1)\, F_{n,m,n+1,m-1} \\ \beta_{nm} &= (n-m+1)\,\frac{N_{nm}}{N_{n+1,m}} = (n-m+1)\,F_{n,m,n+1,m} -\end{align*}\]

where we have define $F_{n,m,p,q}$ as the normalization factor ratio.

References

\ No newline at end of file +\end{align*}\]

where we have define $F_{n,m,p,q}$ as the normalization factor ratio.

References

\ No newline at end of file diff --git a/Home/encyclopedia/astro/gravity/intro/index.html b/Home/encyclopedia/astro/gravity/intro/index.html index 64e4026a..064408a7 100644 --- a/Home/encyclopedia/astro/gravity/intro/index.html +++ b/Home/encyclopedia/astro/gravity/intro/index.html @@ -2,4 +2,4 @@ function gtag(){dataLayer.push(arguments);} gtag('js', new Date()); gtag('config', 'G-K7LNGMSXLE'); -Introduction · JSMD Documentation
GitHub

Introduction

Gravitational models play a crucial role in engineering applications related to space missions, satellite operations, and celestial mechanics. These models provide a mathematical representation of the gravitational field of celestial bodies, enabling engineers to accurately predict orbits, plan trajectories, and design spacecraft missions with precision.

Various gravitational models are employed to meet specific requirements and account for different levels of complexity. One commonly used model is the Two-Body Problem, which assumes that the gravitational interaction between two celestial bodies, such as a satellite and a planet, is the dominant force affecting their motion. This simplified model is often leveraged for preliminary orbit design.

For more accurate calculations, more sophisticated models are required, such as the n-Body Problem: it considers the gravitational interactions among multiple celestial bodies, accounting for the gravitational influences of planets, moons, and other significant objects within a celestial system.

The gravity field of most of the bodies, however, is not usually well represented by one of a spherically symmetric body, when in vicinity of the body. For this reason, more accurate gravitational field representations are required, as the Spherical Harmonics Expansion or the Constant Density Polyhedron. The former is a gravity field expansion using spherical harmonics coefficients, the latter exploit a meshed representation of the body shape and compute the gravity field analytically, exploiting surface and line integrals.

The aim of this part of the documentation is to provide a concise, clear and mathematically accurate representation of gravitational models available within the JSMD ecosystem.

\ No newline at end of file +Introduction · JSMD Documentation
GitHub

Introduction

Gravitational models play a crucial role in engineering applications related to space missions, satellite operations, and celestial mechanics. These models provide a mathematical representation of the gravitational field of celestial bodies, enabling engineers to accurately predict orbits, plan trajectories, and design spacecraft missions with precision.

Various gravitational models are employed to meet specific requirements and account for different levels of complexity. One commonly used model is the Two-Body Problem, which assumes that the gravitational interaction between two celestial bodies, such as a satellite and a planet, is the dominant force affecting their motion. This simplified model is often leveraged for preliminary orbit design.

For more accurate calculations, more sophisticated models are required, such as the n-Body Problem: it considers the gravitational interactions among multiple celestial bodies, accounting for the gravitational influences of planets, moons, and other significant objects within a celestial system.

The gravity field of most of the bodies, however, is not usually well represented by one of a spherically symmetric body, when in vicinity of the body. For this reason, more accurate gravitational field representations are required, as the Spherical Harmonics Expansion or the Constant Density Polyhedron. The former is a gravity field expansion using spherical harmonics coefficients, the latter exploit a meshed representation of the body shape and compute the gravity field analytically, exploiting surface and line integrals.

The aim of this part of the documentation is to provide a concise, clear and mathematically accurate representation of gravitational models available within the JSMD ecosystem.

\ No newline at end of file diff --git a/Home/encyclopedia/astro/gravity/point/index.html b/Home/encyclopedia/astro/gravity/point/index.html index ce482292..3901fe15 100644 --- a/Home/encyclopedia/astro/gravity/point/index.html +++ b/Home/encyclopedia/astro/gravity/point/index.html @@ -34,4 +34,4 @@ &= \frac{\partial f_i(\boldsymbol{R}, \mu)}{\partial R_j} + \sum_k^{N-P}\frac{\partial f_i(\boldsymbol{R_k}, \mu_k)}{\partial {R_{k,j}}}\, \\ &= - \frac{\mu}{R^3} \left(\delta_{ij} - \cfrac{R_iR_j}{R^2}\right) - \sum_k^{N-P} \frac{\mu_k}{R_k^3} \left(\delta_{ij} - \cfrac{R_{k,i}R_{k,j}}{R_k^2}\right) \\ &= - \sum_l^{N} \frac{\mu_l}{R_l^3} \left(\delta_{ij} - \cfrac{R_{l,i}R_{l,j}}{R_l^2}\right) -\end{align*}\]

\ No newline at end of file +\end{align*}\]

\ No newline at end of file diff --git a/Home/encyclopedia/astro/gravity/poly/index.html b/Home/encyclopedia/astro/gravity/poly/index.html index 4cdebac2..0abcf99a 100644 --- a/Home/encyclopedia/astro/gravity/poly/index.html +++ b/Home/encyclopedia/astro/gravity/poly/index.html @@ -6,4 +6,4 @@ \mathcal{U} &= \frac{1}{2}G\rho\sum_{edges} \mathbf{r}_e\cdot\mathbb{E}_e\cdot\mathbf{r}_eL_e - \frac{1}{2}G\rho\sum_{faces}\mathbf{r}_f\cdot\mathbb{F}_f\cdot\mathbf{r}_f\omega_f \\ \nabla\mathcal{U} &= -G\rho\sum_{edges} \mathbb{E}_e\cdot\mathbf{r}_eL_e + G\rho\sum_{faces}\mathbb{F}_f\cdot\mathbf{r}_f\omega_f \\ \nabla^2\mathcal{U} &= - G\rho\sum_{faces}\omega_f \\ -\end{align*}\]

\ No newline at end of file +\end{align*}\]

\ No newline at end of file diff --git a/Home/encyclopedia/astro/time/index.html b/Home/encyclopedia/astro/time/index.html index b2698fad..808baa50 100644 --- a/Home/encyclopedia/astro/time/index.html +++ b/Home/encyclopedia/astro/time/index.html @@ -17,4 +17,4 @@ TCB -- linear --> TDB TDB -- "func(TDB, UT1, site)" --> TT
Relationship between different scales of interest -

References

\ No newline at end of file +

References

\ No newline at end of file diff --git a/Home/encyclopedia/index.html b/Home/encyclopedia/index.html index b6069ba0..4800ec0d 100644 --- a/Home/encyclopedia/index.html +++ b/Home/encyclopedia/index.html @@ -2,4 +2,4 @@ function gtag(){dataLayer.push(arguments);} gtag('js', new Date()); gtag('config', 'G-K7LNGMSXLE'); -- · JSMD Documentation
GitHub
\ No newline at end of file +- · JSMD Documentation
GitHub
\ No newline at end of file diff --git a/Home/index.html b/Home/index.html index 128ebd71..f805980f 100644 --- a/Home/index.html +++ b/Home/index.html @@ -2,4 +2,4 @@ function gtag(){dataLayer.push(arguments);} gtag('js', new Date()); gtag('config', 'G-K7LNGMSXLE'); -Welcome to Julia Space Missions Design! · JSMD Documentation
GitHub

Welcome to Julia Space Missions Design!

A Julia-based ecosystem for space missions design and operations.

Our package collection is specially crafted to provide you with a powerful and easy-to-use environment for conducting simulations, and data analysis related to space mission design and operations.

Whether you're an experienced space engineer or a curious student looking to explore the depths of space, JSMD has got you covered. With its unique features and user-friendly interface, you can design and simulate space missions with confidence and ease.

Join our growing community of space enthusiasts and experience the future of space mission design today!

\ No newline at end of file +Welcome to Julia Space Missions Design! · JSMD Documentation
GitHub

Welcome to Julia Space Missions Design!

A Julia-based ecosystem for space missions design and operations.

Our package collection is specially crafted to provide you with a powerful and easy-to-use environment for conducting simulations, and data analysis related to space mission design and operations.

Whether you're an experienced space engineer or a curious student looking to explore the depths of space, JSMD has got you covered. With its unique features and user-friendly interface, you can design and simulate space missions with confidence and ease.

Join our growing community of space enthusiasts and experience the future of space mission design today!

\ No newline at end of file diff --git a/Home/references/index.html b/Home/references/index.html index 597bd83c..021772fa 100644 --- a/Home/references/index.html +++ b/Home/references/index.html @@ -2,4 +2,4 @@ function gtag(){dataLayer.push(arguments);} gtag('js', new Date()); gtag('config', 'G-K7LNGMSXLE'); -References · JSMD Documentation
GitHub

References

[1]
W. M. Kaula. Theory of satellite geodesy: applications of satellites to geodesy (Courier Corporation, 2013).
[2]
L. E. Cunningham. On the computation of the spherical harmonic terms needed during the numerical integration of the orbital motion of an artificial satellite. Celestial Mechanics, 207–216 (1970).
[3]
O. Montenbruck, E. Gill and F. Lutze. Satellite orbits: models, methods, and applications (Springer-Verlag, 2000).
[4]
F. Barthelmes. Definition of functionals of the geopotential and their calculation from spherical harmonic models, http://publications.iass-potsdam.de/pubman/item/escidoc (2013).
\ No newline at end of file +References · JSMD Documentation
GitHub

References

[1]
W. M. Kaula. Theory of satellite geodesy: applications of satellites to geodesy (Courier Corporation, 2013).
[2]
L. E. Cunningham. On the computation of the spherical harmonic terms needed during the numerical integration of the orbital motion of an artificial satellite. Celestial Mechanics, 207–216 (1970).
[3]
O. Montenbruck, E. Gill and F. Lutze. Satellite orbits: models, methods, and applications (Springer-Verlag, 2000).
[4]
F. Barthelmes. Definition of functionals of the geopotential and their calculation from spherical harmonic models, http://publications.iass-potsdam.de/pubman/item/escidoc (2013).
\ No newline at end of file