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Commit c56458b3 authored by Alfin Johny's avatar Alfin Johny
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Fix header issue in subpages 

In the previously built UNICADO website, many pages had inconsistent
headers. This commit aims to address the issue by leveraging mkdoxy
documentation. Initially, only propulsion_design-related files have been
modified to test this approach. If successful, the solution can be
extended to all other subpages to resolve the header inconsistency
problem.
Issue: #22
parent 5b1448ae
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3 merge requests!55[WEBPAGE] Update style of current unicado page,!18Fix header issue in subpages.,!17Integrate mkdoxy in CI pipeline
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docs/documentation/analysis.md
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......@@ -22,7 +22,7 @@ lift mach numbers.
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](aerodynamic_analysis/content/index.md)|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](aircraft-design/aerodynamic_analysis/doc/content/index.md)|
---
......@@ -39,7 +39,7 @@ For the user, possible changes in the module run configuration can be made in th
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](mission_analysis/content/index.md)|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](aircraft-design/mission_analysis/doc/content/index.md)|
---
......@@ -50,7 +50,7 @@ The `weight_and_balance_analysis` module calculates sub-masses and total masses
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](weight_and_balance_analysis/content/index.md)|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](aircraft-design/weight_and_balance_analysis/doc/content/index.md)|
---
......@@ -67,7 +67,7 @@ The parameters comprised in this XML file can have different attributes as e.g.
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](ecological_assessment/content/index.md)|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](aircraft-design/ecological_assessment/doc/content/index.md)|
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......@@ -78,7 +78,7 @@ The module `calculatePerformance` is used to evaluate the mission performance of
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus:| GPLv3 |[Link](performance_assessment/content/index.md)|
|2.1.0|:simple-cplusplus:| GPLv3 |[Link](aircraft-design/performance_assessment/doc/content/index.md)|
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......@@ -94,6 +94,6 @@ Direct costs include all expenses incurred in operating and financing the aircra
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-python: |GPLv3|[Link](cost_estimation/content/index.md)|
|2.1.0|:simple-python: |GPLv3|[Link](aircraft-design/cost_estimation/doc/content/index.md)|
---
docs/documentation/sizing.md
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− 8
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......@@ -37,7 +37,7 @@ The parameters comprised in this file can have different attributes as e.g. Desc
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](create_mission_xml/content/index.md)|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](aircraft-design/create_mission_xml/doc/content/index.md)|
---
......@@ -48,7 +48,7 @@ The **fuselage_design** module calculates characteristic parameters and generate
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](fuselage_design/content/index.md)|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](aircraft-design/fuselage_design/doc/content/index.md)|
---
......@@ -59,7 +59,7 @@ The **wing_design** module calculates characteristic parameter of the aircraft m
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](wing_design/content/index.md)|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](aircraft-design/wing_design/doc/content/index.md)|
---
......@@ -71,7 +71,7 @@ It takes takes the controllability as wells as the static margin of the aircraft
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](empennage_design/content/index.md)|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](aircraft-design/empennage_design/doc/content/index.md)|
---
......@@ -82,7 +82,7 @@ It takes takes the controllability as wells as the static margin of the aircraft
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-python: |GPLv3|[Link](tank_design/content/index.md)|
|2.1.0|:simple-python: |GPLv3|[Link](aircraft-design/tank_design/doc/content/index.md)|
---
......@@ -100,7 +100,7 @@ Also the mass properties are analyzed.
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|3.0.0|:simple-cplusplus: |GPLv3|[Link](propulsion_design/content/index.md)|
|3.0.0|:simple-cplusplus: |GPLv3|[Link](aircraft-design/propulsion_design/doc/content/index.md)|
---
......@@ -111,7 +111,7 @@ The **landing_gear_design** module calculates characteristic parameters for the
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](landing_gear_design/content/index.md)|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](aircraft-design/landing_gear_design/doc/content/index.md)|
---
......@@ -123,6 +123,6 @@ It dimensions ATA chapter systems in terms of mass and energy requirement divide
|Module Version|Language|License|Documentation|
|:---:|:---:|:---:|---|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](systems_design/content/index.md)|
|2.1.0|:simple-cplusplus: |GPLv3|[Link](aircraft-design/systems_design/doc/content/index.md)|
---
mkdocs.yml
+ 17
− 1
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......@@ -124,7 +124,23 @@ nav: # Customizes the main navigation struc
- Documentation: # Top-level item for documentation.
- Overview: documentation/overview.md # Overview of modules.
- Aircraft Design:
- Sizing: documentation/sizing.md # Link to aircraft sizing documentation.
- Sizing:
- Overview: documentation/sizing.md # Link to aircraft sizing documentation.
- Initial Sizing: documentation/aircraft-design/initial_sizing/doc/content/index.md
- Create Mission XML: documentation/aircraft-design/create_mission_xml/doc/content/index.md
- Fuselage Design: documentation/aircraft-design/fuselage_design/doc/content/index.md
- Wing Design: documentation/aircraft-design/wing_design/doc/content/index.md
- Empennage Design: documentation/aircraft-design/empennage_design/doc/content/index.md
- Tank Design: documentation/aircraft-design/tank_design/doc/content/index.md
- Propulsion Design:
- Introduction: documentation/aircraft-design/propulsion_design/doc/content/index.md
- Getting Started: documentation/aircraft-design/propulsion_design/doc/content/getting_started.md
- Engineering Principles: documentation/aircraft-design/propulsion_design/doc/content/engineering_principles.md
- Software Architecture: documentation/aircraft-design/propulsion_design/doc/content/software_architecture.md
- Changelog: documentation/aircraft-design/propulsion_design/doc/content/changelog.md
- Additional: documentation/aircraft-design/propulsion_design/doc/content/additional.md
- Landing Gear Design: documentation/aircraft-design/landing_gear_design/doc/content/index.md
- Systems Design: documentation/aircraft-design/systems_design/doc/content/index.md
- Analysis: documentation/analysis.md # Link to analysis module page.
- Libraries: documentation/libraries.md # Link to libraries overview.
- Utilities: documentation/additional_software.md
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