Merge branch 'documentation/update_initial_Sizing' into 'develop'

Documentation/update initial sizing

See merge request !43

docs/documentation/sizing/initial_sizing/figures/sizing_chart.svg

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docs/documentation/sizing/initial_sizing/getting-started.md

@@ -15,38 +15,175 @@ It is assumed that you have the `UNICADO Package` installed including the execut
         - the initial assumptions of values for the stated parameters
 3. Open terminal and run **initialSizing**
 
-Following will happen:
-- you see output in the console window
-- a HTML report is created in the directory of `aircraft_exchange_file_directory` (no plots if they are turned off)
+Following will happen  
+
+- you see output in the console window  
+- a HTML report is created in the directory of `aircraft_exchange_file_directory` (no plots if they are turned off)  
 - results are saved in the _acXML_ file
 
 
 ## Settings and outputs {#settingsandoutputs}
 Generally, we use 2 files to set our configuration in UNICADO:
+
 - the aircraft exchange file (or _acXML_) includes
-    - data related inputs (e.g. range, pax number, cargo)
-    - data related outputs (e.g. MTOM, OME)
+    - data related inputs (e.g. range, pax number, cargo)  
+    - data related outputs (e.g. MTOM, OME)  
 - the configuration file `initial_sizing_conf.xml` (or _configXML_) includes
-    - control settings (e.g. enable/disable generating plots)
+    - control settings (e.g. enable/disable generating plots)  
     - program settings (e.g. set parameters to consider for specific technologies or change of methods)
 
-### Aircraft exchange file
+### Aircraft exchange file  
 !!! note
-    _acXML_ is an exchange file - we agreed on that only data will be saved as output which is needed by another tool!
+    _acXML_ is an exchange file - that only safes the data as output which is needed by another tool!
 
 **Inputs**: 
+
 The following is needed from the _acXML_:
-1) the accomodation requirements (pax number, pax mass, luggage mass, cargo mass), 
-2) the mission requirements (range, reserves, TOFL, cruise speed and altitude, approach speed),
+
+1) the accomodation requirements (pax number, pax mass, luggage mass, cargo mass)  
+2) the mission requirements (range, reserves, TOFL, cruise speed and altitude, approach speed)  
 3) the user settings of the energy carrier
 
-Naturally, the initial_sizing needs an assumption for the initial MTOM to start the iteration of MTOM. This initial MTOM is calculated from the pax number requirement in the _acXML_ 
+Naturally, the initial_sizing needs an assumption for the initial MTOM to start the iteration of MTOM. This initial MTOM is calculated from the pax number requirement in the _acXML_ .
 
 Additionally, the user settings need to be defined. In the node `/aircraft_exchange\_file/requirements_and_specifications/design_specification` (for more information on the variables, please read the description in the _acXML_).
 
-**Outputs**: 
+**Outputs**:
+
+The following is written into the _acXML_:  
+1) the Maximum Takeoff Mass (MTOM)  
+2) the Operating Mass Empty (OME)  
+3) the Design Sizing Point which consists of the wing loading and the Thrust to weight ratio needed to fulfill the TLARs
+
+### Configuration file
+The _configXML_ is structured into two blocks: the ^^control^^ and ^^program^^ settings.
+
+The ^^control settings^^ are standardized in UNICADO and will not be described in detail here. But to get started, you have to change at least
+
+- the `aircraft_exchange_file_name` and `aircraft_exchange_file_directory` to your respective settings  
+- the `console_output` at least to `mode_1`  
+- the `plot_output` to false (or define `inkscape_path` and `gnuplot_path`).
+
+!!! note
+    If the tool is executed via the workflow, those settings are set by the workflow settings.
+
+The ^^program settings^^ are special settings and input parameters only needed for the individual module. For your convenience there is always a default value given. For initial sizing they are structured like this(descriptions are in the `initialSizing_conf.xml`):
+
+At first the aircraft configuration for which the initial sizing shall be done needs to be set. The second setting is the approach how the initial sizing shall be done. There is an analytical method and there will be a database method.
+
+```        
+<tube_and_wing description="settings for tube and wing (TAW)">
+    <approach_selection description="selection of approach level">
+		<value>analytical</value>
+	</approach_selection>
+```
+        
+For the analytical approach of the initial sizing module further parameter assumptions and requirements needs to be set in the program settings.
+
+```        
+<General>
+    <OswaldFactor description="Oswald efficency factor in clean configuration" Unit="-">
+		<value>0.85</value>
+	    <default>0.85</default>
+	</OswaldFactor>
+    <AspectRatio description="aspect ratio" Unit="count">
+	    <value>9.5</value>
+	    <default>9.5</default>
+    </AspectRatio>
+    <n_pilots description="Number of Pilots" Unit="count">
+	    <value>2</value>
+	    <default>2</default>
+	</n_pilots>
+	<n_engines description="Number of engines" Unit="count">
+	    <value>2</value>
+	    <default>2</default>
+    </n_engines>
+    <Cf description="equivalent friction coefficient" Unit="count">
+	    <value>0.002</value>
+	    <default>0.002</default>
+    <SFC_kerosene description="Specific Fuel Consumption factor for Kerosene">
+	    <value>0.0001389</value>
+	    <default>0.0001389</default>
+```
+
+For the TLARs takeoff, climb, cruise and landing set in the _acXML_ further parameter assumptions are necessary for initial sizing in order to determine a sizing chart. These parameters are set in the initial sizing program settings and as are followed
+
+```        
+<TOFL description="takeoff distance requirement">
+    <CLmax_TO description="Maximum lift coefficient at takeoff" Unit="-">
+	    <value>2.55</value>
+        <default>2.28</default>
+    </CLmax_TO>
+</TOFL>
+<LDN description="landing distance requirement">
+    <CLmax_L description="Maximum lift coefficient at landing" Unit="-">
+    	<value>2.9</value>
+	    <default>2.85</default>
+    </CLmax_L>
+    <mlmo description="ratio between maximum landing mass and takeoff mass" Unit="-">
+	    <value>0.82</value>
+	    <default>0.82</default>
+    </mlmo>
+</LDN>
+<Climb description="climb performance requirement">
+    <deltaCD_HL description="Delta CD0 with TO-Flaps" Unit="-">
+        <value>0.07</value>
+        <default>0.07</default>
+    </deltaCD_HL>
+</Climb>
+<Cruise description="maximum cruise speed requirement">
+    <mcr_mto description="ratio between cruise mass and takeoff mass - default for mid- and short-range: 0.956, default for long range: 0.924">
+        <value>0.956</value>
+	    <default>0.956</default>
+    </mcr_mto>
+    <optimalCL description="design CL for initial cruise">
+        <value>0.57</value>
+		<default>0.57</default>
+    </optimalCL>
+</Cruise>
+<LiftToDragRatios description="initial cruise and loiter lift to drag ratios ">
+    <LD_initial_cruise description="cruise requirements">
+        <value>15</value>
+        <default>15</default>
+    </LD_initial_cruise>
+    <LD_initial_loiter description="loiter requirements">
+        <value>16</value>
+        <default>16</default>
+<LiftToDragRatios>
+```
+
+In order to provide further input for the mass estimation methodology in the analytical approach of the initial sizing module fuel mass fractions for mission phases needs to be set.
+
+```        
+<Fractions description="fuel mass fractions">
+    <mf_warmup description="Warmup (according to Raymer: 0.97(A340)-0.99(A320))" Unit="-">
+        <value>0.99</value>
+        <default>0.99</default>
+    </mf_warmup>
+    <mf_taxi description="Taxi (according to Raymer: 0.97(A340)-0.99(A320))" Unit="-">
+        <value>0.99</value>
+        <default>0.99</default>
+    </mf_taxi>
+    <mf_to description="Takeoff (according to Raymer: 0.97(A340)-0.99(A320))" Unit="-">
+        <value>0.995</value>
+        <default>0.995</default>
+    </mf_to>
+    <mf_climb description="Climb (according to Raymer: 0.97(A340)-0.99(A320))" Unit="-">
+        <value>0.98</value>
+        <default>0.98</default>
+    </mf_climb>
+    <mf_descent description="Descent (according to Raymer: 0.99(A340)-0.995(A320))" Unit="-">
+        <value>0.99</value>
+        <default>0.99</default>
+    </mf_descent>
+    <mf_missedandclimb description="missed approach and climb to alternate airport (according to Raymer: 0.992(A340)-0.997(A320))" Unit="-">
+        <value>0.988</value>
+        <default>0.988</default>
+    </mf_missedandclimb>
+    <mf_land description="Landing and Taxi out (according to Raymer: 0.992(A340)-0.997(A320))" Unit="-">
+        <value>0.995</value>
+        <default>0.995</default>
+    </mf_land>
+```
 
-The following is written into the _acXML_:
-1) the Maximum Takeoff Mass (MTOM), 
+As soon as the reference aircraft database exists the program settings for the database approach of initial sizing will be described here.
\ No newline at end of file
-2) the Operating Mass Empty (OME),
-3) the Design Sizing Point which consists of the wing loading and the Thrust to weight ratio needed to fulfil the TLARs 

docs/documentation/sizing/initial_sizing/index.md

 # Introduction {#mainpage}
-The tool _initialSizing_ is the first aircraft design tools in the UNICADO workflow. 
+The tool _initialSizing_ is the first aircraft design tool in the UNICADO workflow.
 The overall goal is the initial takeoff mass estimation based on the Top Level Aircraft Requirements "TLARs" range and payload.
-Moreover an initial sizing chart is derived from further TLARs like the desired cruise speed, approach speed or takeoff field lenght.  
+Moreover an initial sizing chart is derived from further TLARs like the desired cruise speed, approach speed or takeoff field lenght.
 
-The design window is then automatically investigated for an optimum design point resulting in the wing loading and thrust to weight ratio for the aircraft. 
-Together with the initial takeoff mass and empty mass estimation the tool delivers the first important parameters for further UNICADO design modules. 
+The design window is then automatically investigated for an optimum design point resulting in the wing loading and thrust to weight ratio for the aircraft.
+Together with the initial takeoff mass and empty mass estimation, the tool delivers the first important parameters for further UNICADO design modules.
 
-This tool is exiting because it starts the clean sheet aircraft design and you will get a first idea how large and heavy your aircraft will be for the desired mission. 
+This tool is existing because it starts the clean sheet aircraft design and you will get a first idea how large and heavy your aircraft will be for the desired mission.
 
-To remind you of the concept of an initial sizing chart and desing window, here is the diagram where each border is derived from a different TLAR - hence every combination of wing loading 
+To remind you of the concept of an initial sizing chart and design window, here is the diagram where each border is derived from a different TLAR - hence every combination of wing loading
 and thrust to weight ratio within the borders are possible design points for the aircraft.
 ![](figures/sizing_chart.svg)
 
-The @subpage getting-started gives you a first insight in how to execute the tool and how it generally works.
+The [Getting Started](getting-started.md) gives you a first insight in how to execute the tool and how it generally works.
 
 So let's get started!
 

docs/documentation/sizing/initial_sizing/initialSizing.md

 # Implemented Aircraft Sizing Methods and Models
 
-## Initial Takeoff Mass Estimation MTOM 
+## Initial Takeoff Mass Estimation (MTOM) 
 The MTOM is initially iterated from Top Level Aircraft Requirements (TLARs), user assumptions and certification requirements.
 
+
 **Methods**
 
-The *Payload* is like its name the mass that pays for a trip. It is calculated from the number of passengers (PAX) and additional cargo requirement.
-It is a fixed value for the whole iteration. 
+Like its name suggests, the *Payload* is the mass that pays for a trip. It is calculated from the number of passengers (PAX) and additional cargo requirement.
+It is a fixed value for the whole iteration.
 For the determination the following parameters from the acXML are necessary:
 
-* Number of PAX [-]
-* Mass per person  [kg]
-* Luggage per PAX [kg]
-* Additional cargo mass [kg]
+1) acXML:
+
+  - Number of PAX  [-]
+  - Mass per person   [kg]
+  - Luggage per PAX  [kg]
+  - Additional cargo mass  [kg]
+  
 
 
-The *Crew mass* is not part of the payload but once determined it is also a fixed value for the iteration of the MTOM. 
+The *Crew mass* is not part of the payload but once determined it is also a fixed value for the iteration of the MTOM.
 The crew mass is dependent on the different seating classes (FC, BC, EC) and number of PAX in each class the aircraft shall have.
-Furthermore, the certification requirements define the number of pilots.  
+Furthermore, the certification requirements define the number of pilots.
 For the determination the following parameters are necessary:
 
-acXML:
-* Number of PAX in each class [-]
-* Mass per person [kg] and luggage per crew are the same than for the passengers
-initialSizing_conf:
-* Number of pilots [-]
-in source code
-* Ratio for flight attendants per PAX amount in each class [-]: i.e. 1 Flight Attendant per 14 PAX in FC, 1 per 40 in EC
+1) acXML:
+
+  - Number of PAX in each class  [-]
+  - Mass per person  [kg] and luggage per crew are the same than for the passengers
+
+2) initialSizing_conf:
+
+  - Number of pilots  [-]
+
+3) in source code:
 
+  -  Ratio for flight attendants per PAX amount in each class  [-]: e.g. 1 Flight Attendant per 14 PAX in FC, 1 per 40 in EC
+  
 
-The *fuel* which is needed for individual mission segments is not calculated in absolute values but as mass fractions from the total remeining fuel. The fuel fractions of the cruise segment, the reserve needed to the flight to an alternate distance and the reserve for a holding time are calculated with the Breguet equation. 
+
+The *fuel* which is needed for individual mission segments is not calculated in absolute values but as mass fractions from the total remaining fuel. The fuel fractions of the cruise segment, the reserve needed to the flight to an alternate distance and the reserve for a holding time are calculated with the Breguet equation.
 For the determination the following parameters are necessary:
 
-acXML:
-* Design range [m]
-* Crusie flight speed [m/s]: automatically calculated from the design machNumber
-* Contingency [-]: percentage for the reserve of the trip fuel (the fuel necessary for the design range without reserves)
-* Cruise flight altitutde [m]: to calculate the air density
-initialSizing_conf:
-* SFC of the engine with regard to fuel type [-]: 
-* Glide Ratio (L/D) in cruise [-]: Initial assumption given by user
-* Glide Ratio (L/D) in Loiter [-]: Initial assumption given by user
+1) acXML:
+
+  - Design range  [m]
+  - Crusie flight speed $[\frac{m}{s}]$: automatically calculated from the design mach number
+  - Contingency  [-]: percentage for the reserve of the trip fuel (the fuel necessary for the design range without reserves)
+  - Cruise flight altitutde  [m]: to calculate the air density
+
+2) initialSizing_conf:
+
+  - SFC of the engine with regard to fuel type  [-]
+  - Glide Ratio $\frac{L}{D}_{cr}$ in cruise  [-]: Initial assumption given by user
+  - Glide Ratio $\frac{L}{D}_{loi}$ in Loiter  [-]: Initial assumption given by user
+
 
 
-The fuel fractions (i.e. engine warm up, taxi, takeoff, climb....) are set as an static input by the user in the initialSizing_conf file.
-Together with the fuel fractions from the segments calculated with the breguet equation, the overall fuel fraction of the aircraft is calculated.  
-In this way of calculating the necessary fuel, the method and also the same static fuel fractions are applicable for various aircraft sizes.  
+The fuel fractions (i.e. engine warm up, taxi, takeoff, climb....) are set as an static input by the user in the config file.
+Together with the fuel fractions from the segments calculated with the Breguet equation, the overall fuel fraction of the aircraft is calculated.
+In this way of calculating the necessary fuel, the method and also the same static fuel fractions are applicable for various aircraft sizes.
 
+The *MTOM* is calculated in an iteration because the absolute amount of fuel and the *Operating Mass Empty* (OME) or ($m_e$) changes with the aircraft MTOM ($m_0$).
+The initial value for MTOM to start the MTOM iteration is estimated with a simple formula depending on the payload and a static factor only.
 
-The *MTOM* is calculated in an iteration because the absolute amount of fuel and the *Operating Mass Empty* (OME) changes with the aircraft MTOM. 
-The initial value for MTOM in order to start the MTOM iteration is estimated with a simple formula depending on the payload and a static factor only.
-For the *OME* a mass ratio me/m0 is used in order to take into account the total aircraft size. Larger aircraft usually have a smaller empty mass / takeoff mass ratio.
-In each iteration a new me/m0 ratio is calculated. Together with the fuel mass fraction, the payload and the crew mass the MTOM is determined. This iteration goes on until the convergence criteria is reached.  
+For the *OME* a mass ratio $\frac{m_e}{m_0}$ is used in order to take into account the total aircraft size. Larger aircraft usually have a smaller $\frac{OME}{MTOM}$ ratio.
+In each iteration a new $\frac{m_e}{m_0}$ ratio is calculated. Together with the fuel mass fraction, the payload and the crew mass the MTOM is determined. This iteration goes on until the convergence criteria is reached.
 
 
-## Initial Constraint Analysis - Sizing Chart  
-A constraint analysis is conducted in order to set the initial *Design Point* for the aircraft. The Desing Point is defined as a wing loading and thrust to weight ratio. 
-The constraint analysis is a method to make sure Top Level Aircraft Requirements (TLARs) and certification requirements will be fulfilled by the designed aircraft. 
+
+## Initial Constraint Analysis - Sizing Chart
+A constraint analysis is conducted in order to set the initial *Design Point* for the aircraft. The Desing Point is defined as a wing loading $\frac{m_0}{S}$ and thrust to weight ratio $\frac{F}{m_0 \cdot g}$.
+The constraint analysis is a method to make sure Top Level Aircraft Requirements and certification requirements will be fulfilled by the designed aircraft.
 For this a sizing chart is determined and printed by the module.
 
 **Methods**
@@ -64,59 +79,76 @@ For this a sizing chart is determined and printed by the module.
 The *Takeoff* constraint makes sure to respect the takeoff field lengt TLAR.
 For the determination the following parameters are necessary:
 
-acXML:
-* Takeoff field lenght (TOFL) [m]
-initialSizing_conf:
-* Number of engines [-]: is used to set a engine proportional factor
-* CL_max_takeoff  [-]
+1) acXML:
+
+  - Takeoff field lenght (TOFL)  [m]
+
+2) initialSizing_conf:
 
+  - Number of engines  [-]: is used to set an engine proportional factor
+  - $CL_{takeoff}$  [-]
+  
+  
 
 The *Climb* constraint makes sure to respect the climb ability in the 2nd segment with one engine inoperative (OEI) by the certification standards.
 For the determination the following parameters are necessary:
 
-acXML:
-* Minimum climb angle [rad]: according to the certification standards and the total number of engines
+1) acXML:
 
-* L/D_climb [-]: with the highlift system in the state of the 2nd climb segment
-in source code:
-* Mass ratio m_climb/MTOM [-] 
+  - Minimum climb angle  [rad]: according to the certification standards and the total number of engines
+  - $\frac{L}{D}_{climb}$  [-]: with the highlift system in the state of the 2nd climb segment
 
+2) in source code:
 
-The *Cruise Flight* constraint makes sure to respect the desing cruise speed and altitude TLAR.
+  - Mass ratio $\frac{m_{climb}}{m_0}$  [-]
+  
+
+
+The *Cruise Flight* constraint makes sure to respect the design cruise speed and altitude TLAR.
 For the determination the following parameters are necessary:
 
-initialSizing_conf:
-* Cfeq [-]: Equivalent friction coefficient to estimate parasetic drag coefficient
-* Oswald efficency factor e [-]
-* Wing Aspect Ratio [-]
-in source code:
-* Thrust ratio F_total/F_cruise [-]
-* S_wet/S_rev ratio [-]: Ratio of wetted surface to wing reference area to estimate parasetic drag coefficient
-* Mass ratio m_cruise/MTOM [-] 
+1) initialSizing_conf:
+
+  - $C_{feq}$  [-]: Equivalent friction coefficient to estimate parasetic drag coefficient
+  - Oswald efficency factor $e$  [-]
+  - Wing Aspect Ratio  [-]
+    
+2) in source code:
+
+  - Thrust ratio $\frac{F_{total}}{F_{cruise}}$  [-]
+  - $\frac{S_{wet}}{S_{ref}}$ ratio  [-]: Ratio of wetted surface to wing reference area to estimate parasetic drag coefficient
+  - Mass ratio $\frac{m_{cruise}}{m_0}$  [-]
+  
 
 
 The *Landing* constraint makes sure to respect the maximum approach speed TLAR.
 For the determination the following parameters are necessary:
 
-initialSizing_conf:
-* CL_max_Landing [-]
-* Mass ratio m_land/MTOM [-]: 
-acXML:
-* v_appr [m/s]: Approch speed TLAR
+1) acXML:
+
+  - $v_{appr}$  [$\frac{m}{s}$]: Approach speed TLAR
+    
+2) initialSizing_conf:
+
+  - $CL_{Landing}$  [-]
+  - Mass ratio $\frac{m_{land}}{m_0}$  [-]
+  
+
 
 These constraints open up the design or sizing window of the aircraft where it can fulfill the TLARs and certification standards.
 
-## Initial Constraint Analysis - Desing Point  
+
+## Initial Constraint Analysis - Design Point
 The constraints from the section before open up the design or sizing window, where the aircraft can fulfill the TLARs and certification standards.
-Selecting the optimal design point within the window is again dependent on various requirements and the constellation of the design window itself. 
-This would be quite complex to implement in the module. In order to keep the module and the methods simple, only the borders of the desing window are investigated - since in many cases they deliver an optimal design point. 
-In general, a design point with a wing loading as high as possible and a thrust to weight ratio as low as possible is a good choice.  
+Selecting the optimal design point within the window is again dependent on various requirements and the constellation of the design window itself.
+This would be quite complex to implement in the module. In order to keep the module and the methods simple, only the borders of the desing window are investigated - since in many cases they deliver an optimal design point.
+In general, a design point with a wing loading as high as possible and a thrust to weight ratio as low as possible is a good choice.
 
 **Methods**
 
 * This investigation is done by calculating the intersections of the borders.
 * It is checked how many intersection points of constraints the borders of the desing window has.
-* It is checked if the CL_optimal is within the design window. CL_optimal is a user input in the initialSizing_conf.xml and describes the desing Lift coefficient at initial cruise speed and altitude. 
-* If CL_optimal is in the design window the intersection of CL_optimal and the desing window border is used as design point.
-* If CL_optimal is not in the design window and there is only one intersection from borders in the window this intetersection is used as design point.
-* If CL_optimal is not in the design window and there are two intersection from borders in the window, an interpolated point between these two is used as design point.
+* It is checked if the $CL_{optimal}$ is within the design window. $CL_{optimal}$ is a user input in the initialSizing_conf.xml and describes the design lift coefficient at initial cruise speed and altitude.
+* If $CL_{optimal}$ is in the design window the intersection of $CL_{optimal}$ and the design window border is used as design point.
+* If $CL_{optimal}$ is not in the design window and there is only one intersection from borders in the window this intersection is used as design point.
+* If $CL_{optimal}$ is not in the design window and there are two intersection from borders in the window, an interpolated point between these two is used as design point.
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