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Change title in overview, change libaries list and adapt css

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docs/assets/css/unicado.css
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......@@ -105,6 +105,14 @@
color: var(--secondary-accent); /* Teal accent color for specific elements */
}
.overview-item {
min-height: 240px;
}
.overview-img {
width: 200px;
}
/* Footer Styling */
.custom-footer {
display: flex;
......
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docs/documentation/analysis.md
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......@@ -10,41 +10,41 @@ glightbox: false
---
## calculateEmissions
![Icon](../assets/images/documentation/calculate-emissions.svg){.overview-img align=left}
The **calculateEmissions** is an additional module of the UNICADO toolchain.
Its purpose is to calculate the emissions and energy demand within the aircraft's lifecycle and to determine the missions based climate impact.
For the user, possible changes in the module run configuration can be made in the related calculateEmissions_conf.xml file.
The parameters comprised in this XML file can have different attributes as e.g. Filenames, Directories, Output configs, and are further subdivided into control and program settings.
## Aerodynamic analysis
![Icon](../assets/images/documentation/calculate-polar.svg){.overview-img align=left}
The tool `aerodynamic_analysis` calculates, as the tool name suggests, the polars of an aircraft.
It uses the tool Lifting Line from DLR to calculate force, lift and moment coefficients for each lifting surface of the aircraft.
These coefficients are used to calculate induced, viscous and wave drag as well as the moment coefficients for the overall aircraft.
Furthermore polars are not only calculated for off-design mach numbers but also for high
lift mach numbers.
{.overview-item}
!!! note
By now, only the calculation routines / outputs based on the flown mission are up to date.
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link]()|
---
## calculatePerformance
![Icon](../assets/images/documentation/calculate-performance.svg){.overview-img align=left}
The module `calculatePerformance` is used to evaluate the mission performance of the design.
{.overview-item}
## Mission analysis
![Icon](../assets/images/documentation/mission-analysis.png){.overview-img align=left}
The module `mission_analysis` is the key module of the aircraft performance analysis.
Its purpose is to calculate the flight trajectory, based on the inputs of the preliminary aircraft design cycle, by solving the aircraft equations of motion being simplified as a point mass model.
Depending on the method, the fuel consumption is calculated either:
- in segments by using the Breguet range formula, or
- in a full-mission time-history simulation (the flight mission is divided into increments. For each increment the movement equations are solved, followed by the thrust requirements and fuel consumption)
For the user, possible changes in the module run configuration can be made in the related *missionAnalysis_conf.xml* file. The parameters comprised in this XML file can have different attributes as e.g. Desc, Unit, Default, AllowedRelOvershoot or text and are further subdivided into control and program settings.
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus:| GPLv3 |[Link]()|
|2.1.0|:simple-cplusplus: |GPLv3|[Link]()|
---
## calculatePolar
![Icon](../assets/images/documentation/calculate-polar.svg){.overview-img align=left}
The tool `calculatePolar` calculates, as the tool name suggests, the polars of an aircraft.
CalculatePolar uses the tool Lifting Line from DLR to calculate force, lift and moment coefficients for each lifting surface of the aircraft.
These coefficients are used to calculate induced, viscous and wave drag as well as the moment coefficients for the overall aircraft.
Furthermore polars are not only calculated for off-design mach numbers but also for high
lift mach numbers.
## Weight and balance analysis
![Icon](../assets/images/documentation/mass-estimation.svg){.overview-img align=left}
The `weight_and_balance_analysis` module calculates sub-masses and total masses of the aircraft including center of gravities.
{.overview-item}
|Module Version|Language|License|Documentation|
......@@ -53,46 +53,46 @@ lift mach numbers.
---
## costEstimation
![Icon](../assets/images/documentation/cost-estimation.svg){.overview-img align=left}
This modules calculates the direct operating cost (DOC) of an aircraft.
Direct costs include all expenses incurred in operating and financing the aircraft:
## Ecological assessment
![Icon](../assets/images/documentation/calculate-emissions.svg){.overview-img align=left}
The **ecological_assessment** is an additional module of the UNICADO toolchain.
Its purpose is to calculate the emissions and energy demand within the aircraft's lifecycle and to determine the missions based climate impact.
For the user, possible changes in the module run configuration can be made in the related calculateEmissions_conf.xml file.
The parameters comprised in this XML file can have different attributes as e.g. Filenames, Directories, Output configs, and are further subdivided into control and program settings.
{.overview-item}
- Fuel
- Crew
- Maintenance
- Fees
!!! note
By now, only the calculation routines / outputs based on the flown mission are up to date.
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-python: |GPLv3|[Link]()|
|2.1.0|:simple-cplusplus: |GPLv3|[Link]()|
---
## massEstimation
![Icon](../assets/images/documentation/mass-estimation.svg){.overview-img align=left}
The Mass Estimation module calculates sub-masses and total masses of the aircraft including center of gravities.
## Performance assessment
![Icon](../assets/images/documentation/calculate-performance.svg){.overview-img align=left}
The module `calculatePerformance` is used to evaluate the mission performance of the design.
{.overview-item}
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link]()|
|2.1.0|:simple-cplusplus:| GPLv3 |[Link]()|
---
## missionAnalysis
![Icon](../assets/images/documentation/mission-analysis.png){.overview-img align=left}
The module `missionAnalysis` is the key module of the aircraft performance analysis.
Its purpose is to calculate the flight trajectory, based on the inputs of the preliminary aircraft design cycle, by solving the aircraft equations of motion being simplified as a point mass model.
Depending on the method, the fuel consumption is calculated either:
- in segments by using the Breguet range formula, or
- in a full-mission time-history simulation (the flight mission is divided into increments. For each increment the movement equations are solved, followed by the thrust requirements and fuel consumption)
## Cost estimation
![Icon](../assets/images/documentation/cost-estimation.svg){.overview-img align=left}
This modules calculates the direct operating cost (DOC) of an aircraft.
Direct costs include all expenses incurred in operating and financing the aircraft:
For the user, possible changes in the module run configuration can be made in the related *missionAnalysis_conf.xml* file. The parameters comprised in this XML file can have different attributes as e.g. Desc, Unit, Default, AllowedRelOvershoot or text and are further subdivided into control and program settings.
- Fuel
- Crew
- Maintenance
- Fees
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link]()|
|2.1.0|:simple-python: |GPLv3|[Link]()|
---
\ No newline at end of file
---
docs/documentation/libraries.md
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......@@ -19,29 +19,8 @@ It has helper functions to extract and interpolate data of provided airfoil pola
---
## aircraftGeometry
![Icon](../assets/images/documentation/aircraft-geometry.svg){.overview-img align=left}
This library defines geometry classes which are generally used within an aircraft.
The geometry describes the general shape of the different components.
The available components are:
- *liftingSurface*
- *verticalSurface*
- *Fuselage*
- *Nacelle*
- *Pylon*
- *Landing Gear*
The library furthermore provides functions to extract and measure geometry properties of the different shapes at certain locations.
|Module Version|Language|License|Documentation|Dependencies|
|:---:|:---:|:---:|---|---|
|2.0.0|:simple-cplusplus: |GPLv3|[Link]()|-|
---
## aircraftGeometry2
![Icon](../assets/images/logos/unicado-icon.png){.overview-img align=left}
![Icon](../assets/images/documentation/aircraft-geometry.svg){.overview-img align=left}
This library is based on the older [aircraftGeometry](#aircraftgeometry) library and extends it to be more modular.
The modularity and flexibility is achieved by using the high performance [Computational Geometry Algorithms Library](https://www.cgal.org/) also known as **CGAL**.
{.overview-item}
......@@ -52,15 +31,14 @@ The modularity and flexibility is achieved by using the high performance [Comput
---
## aircraftNetwork
![Icon](../assets/images/documentation/aircraft-network.svg){.overview-img align=left}
This library can be used to define wiring harnesses within an existing aircraft geometry.
You can route wire through different points and analyse the resulting network.
## airfoils
![Icon](../assets/images/documentation/airfoil.svg){.overview-img align=left}
The **airfoils** libary provides a database for different airfoils.
{.overview-item}
|Module Version|Language|License|Documentation|Dependencies|
|:---:|:---:|:---:|---|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link]()|-|
|1.0.0|:simple-cplusplus: |GPLv3|[Link]()|-|
---
......@@ -112,6 +90,14 @@ The engine decks can originate from different softwaretools as long as they prov
---
## extern
UNICADO currently uses two external libaries as submodules:
- `doxygen-awesome-css` [(see here)](https://github.com/jothepro/doxygen-awesome-css.git)
- `pybind11` [(see here)](https://github.com/pybind/pybind11.git)
---
## liftingLineInterface
![Icon](../assets/images/documentation/lifting-line.svg){.overview-img align=left}
This library helps with interacting with results provided by the tools **Lifting Line** from DLR.
......@@ -137,20 +123,14 @@ The library gives a template how modules should be structured and gives helpers
---
## propulsionsystem
![Icon](../assets/images/logos/unicado-icon.png){.overview-img align=left}
This is a versatile tool which can be used to simulate and analyse the power flow within an aircraft.
The power flow is mainly determined by the propulsive systems onboard, but the tool can account for other power needed during operation as well.
The propulsion systems are not limited to conventional types.
Due to the flexible abstraction via so-called *two-terminal block*, any system which as inputs and outputs can be implemented.
## pymodulepackage
![Icon](../assets/images/documentation/pymodulepackage.svg){.overview-img align=left}
This library provides standardized UNICADO data preprocessing, run, and postprocessing functions for Python modules.
{.overview-item}
|Module Version|Language|License|Documentation|Dependencies|
|:---:|:---:|:---:|---|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link]()|-|
!!! info
Since this is a standalone tool it will most likely move to another repository in the next release.
|1.0.0|:simple-python: |GPLv3|[Link]()|-|
---
......@@ -166,17 +146,6 @@ In provides custom output streams, which automatically handle the log files and
---
## spline
![Icon](../assets/images/documentation/spline.svg){.overview-img align=left}
The name gives it away: this library provides spline functionality for interpolating data or geometry.
{.overview-item}
|Module Version|Language|License|Documentation|Dependencies|
|:---:|:---:|:---:|---|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link]()|-|
---
## standardFiles
![Icon](../assets/images/documentation/standard-files.svg){.overview-img align=left}
This library provides file interfaces and interacts with the operating system.
......@@ -205,6 +174,8 @@ You can insert text and measurements for quickly creating meaningful reports.
---
[comment]: <> (## svl)
## unitConversion
![Icon](../assets/images/documentation/unit-conversion.svg){.overview-img align=left}
The **unitConversion** groups the most commonly used unit in aerospace and let's you convert values from one unit to another.
......
docs/documentation/sizing.md
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......@@ -14,12 +14,11 @@ The following sizing tools are available:
---
## createMissionXML
![Icon](../assets/images/documentation/create-mission.png){.overview-img align=left}
The **createMissionXML** is the third module of the UNICADO tool chain.
Its purpose is to set up the overall flight mission including e.g. a flight segment table, speed and altitude schedules, number of passengers (PAX), total payload or the engine warm up time.
For the user, possible changes in the module run configuration can be made in the related createMissionXML_conf.xml file.
The parameters comprised in this file can have different attributes as e.g. Desc, Unit, Default or #text and are further subdivided into control settings and program settings.
## Initial sizing
![Icon](../assets/images/documentation/initial-sizing.svg){.overview-img align=left}
The module **initial_sizing** is used to determine a design chart regarding Top Level Aircraft Requirements and Certification Specification Requirements.
The wing-loading ($\frac{W}{S}$) and thrust to weight ratio ($\frac{T}{W}$) can be derived as the design point for further modules from the Design Chart.
Furthermore an initial estimation of the takeoff mass is done.
{.overview-item}
|Module Version|Language|License|Documentation|
......@@ -28,10 +27,12 @@ The parameters comprised in this file can have different attributes as e.g. Desc
---
## empennageSizing
![Icon](../assets/images/documentation/empennage-sizing.png){.overview-img align=left}
The **empennageSizing** module calculates characteristic parameter of the empennage of the aircraft.
It takes takes the controllability as wells as the static margin of the aircraft into account and sizes the empennage accordingly.
## Create mission XML
![Icon](../assets/images/documentation/create-mission.png){.overview-img align=left}
The **create_mission_XML** is the third module of the UNICADO tool chain.
Its purpose is to set up the overall flight mission including e.g. a flight segment table, speed and altitude schedules, number of passengers (PAX), total payload or the engine warm up time.
For the user, possible changes in the module run configuration can be made in the related createMissionXML_conf.xml file.
The parameters comprised in this file can have different attributes as e.g. Desc, Unit, Default or #text and are further subdivided into control settings and program settings.
{.overview-item}
|Module Version|Language|License|Documentation|
......@@ -40,9 +41,9 @@ It takes takes the controllability as wells as the static margin of the aircraft
---
## fuselageDesign
## Fuselage design
![Icon](../assets/images/documentation/fuselage-design.png){.overview-img align=left}
The **fuselageDesign** module calculates characteristic parameters and generates the passenger cabin and fuselage layout for the entire aircraft project.
The **fuselage_design** module calculates characteristic parameters and generates the passenger cabin and fuselage layout for the entire aircraft project.
{.overview-item}
|Module Version|Language|License|Documentation|
......@@ -51,22 +52,21 @@ The **fuselageDesign** module calculates characteristic parameters and generates
---
## hydrogenTank
![Icon](../assets/images/documentation/hydrogen-tank.svg){.overview-img align=left}
:construction: *tbd*
## Wing design
![Icon](../assets/images/documentation/wing-design.svg){.overview-img align=left}
The **wing_design** module calculates characteristic parameter of the aircraft main wing.
{.overview-item}
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-python: |GPLv3|[Link]()|
|2.1.0|:simple-cplusplus: |GPLv3|[Link]()|
---
## initialSizing
![Icon](../assets/images/documentation/initial-sizing.svg){.overview-img align=left}
The module **initialSizing** is used to determine a design chart regarding Top Level Aircraft Requirements and Certification Specification Requirements.
The wing-loading ($\frac{W}{S}$) and thrust to weight ratio ($\frac{T}{W}$) can be derived as the design point for further modules from the Design Chart.
Furthermore an initial estimation of the takeoff mass is done.
## Empennage design
![Icon](../assets/images/documentation/empennage-sizing.png){.overview-img align=left}
The **empennage_design** module calculates characteristic parameter of the empennage of the aircraft.
It takes takes the controllability as wells as the static margin of the aircraft into account and sizes the empennage accordingly.
{.overview-item}
|Module Version|Language|License|Documentation|
......@@ -75,18 +75,19 @@ Furthermore an initial estimation of the takeoff mass is done.
---
## landingGearDesign
![Icon](../assets/images/documentation/landing-gear-design.svg){.overview-img align=left}
The **landingGearDesign** module calculates characteristic parameters for the landing gear of entire aircraft project.
## Tank design
![Icon](../assets/images/documentation/hydrogen-tank.svg){.overview-img align=left}
:construction: *tbd*
{.overview-item}
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link]()|
|2.1.0|:simple-python: |GPLv3|[Link]()|
---
## propulsionDesign
## Propulsion design
![Icon](../assets/images/documentation/propulsion-design.svg){.overview-img align=left}
The **propulsionDesign** module designs, integrates and analyzes the propulsion system to the aircraft.
It uses engine performance deck containing serval parameters (like thrust, fuel-flow, ...) as a function of the flight Mach number and the altitude.
......@@ -103,10 +104,9 @@ Also the mass properties are analyzed.
---
## systemsDesign
![Icon](../assets/images/documentation/systems-design.png){.overview-img align=left}
The **systemsDesign** is part of the tool chain in the UNICADO aircraft design environment.
It dimensions ATA chapter systems in terms of mass and energy requirement divided by hydraulic- electric- and bleed air energy requirement.
## Landing gear design
![Icon](../assets/images/documentation/landing-gear-design.svg){.overview-img align=left}
The **landing_gear_design** module calculates characteristic parameters for the landing gear of entire aircraft project.
{.overview-item}
|Module Version|Language|License|Documentation|
......@@ -115,13 +115,14 @@ It dimensions ATA chapter systems in terms of mass and energy requirement divide
---
## wingDesign
![Icon](../assets/images/documentation/wing-design.svg){.overview-img align=left}
The wing design module calculates characteristic parameter of the aircraft main wing.
## Systems design
![Icon](../assets/images/documentation/systems-design.png){.overview-img align=left}
The **systems_design** is part of the tool chain in the UNICADO aircraft design environment.
It dimensions ATA chapter systems in terms of mass and energy requirement divided by hydraulic- electric- and bleed air energy requirement.
{.overview-item}
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link]()|
---
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