1) LVD: Added total thrust constraint

2) Adjusted all altitude constraints to have an allowable lower bound of -Inf

Author: Arrowstar

helper_methods/ksptot_ma/launch_vehicle_designer/classes/Optimization/constraints/@ConstraintEnum/ConstraintEnum.m

@@ -64,6 +64,8 @@
         InertialBankAngle('Inertial Bank Angle','InertialBankAngleConstraint',[]);
         InertialSideSlipAngle('Inertial Side Slip Angle','InertialSideSlipAngleConstraint',[]);
 
+        TotalThrust('Total Thrust','TotalThrustConstraint',[]);
+        
         StopwatchValue('Stopwatch Value','StopwatchValueConstraint',[]);
     end
 

helper_methods/ksptot_ma/launch_vehicle_designer/classes/Optimization/constraints/@TotalThrustConstraint/TotalThrustConstraint.m

@@ -0,0 +1,135 @@
+classdef TotalThrustConstraint < AbstractConstraint
+    %TotalThrustConstraint Summary of this class goes here
+    %   Detailed explanation goes here
+    
+    properties
+        normFact = 1;
+        event(1,:) LaunchVehicleEvent
+        
+        lb(1,1) double = 0;
+        ub(1,1) double = 0;
+    end
+    
+    methods
+        function obj = TotalThrustConstraint(event, lb, ub)
+            obj.event = event;
+            obj.lb = lb;
+            obj.ub = ub;   
+            
+             obj.id = rand();
+        end
+        
+        function [lb, ub] = getBounds(obj)
+            lb = obj.lb;
+            ub = obj.ub;
+        end
+        
+        function [c, ceq, value, lwrBnd, uprBnd, type, eventNum] = evalConstraint(obj, stateLog, celBodyData)           
+            type = obj.getConstraintType();
+            stateLogEntry = stateLog.getLastStateLogForEvent(obj.event);
+            
+            ut = stateLogEntry.time;
+            rVect = stateLogEntry.position;
+            vVect = stateLogEntry.velocity;
+            
+            bodyInfo = stateLogEntry.centralBody;
+            tankStates = stateLogEntry.getAllActiveTankStates();
+            stageStates = stateLogEntry.stageStates;
+            lvState = stateLogEntry.lvState;
+            
+            dryMass = stateLogEntry.getTotalVehicleDryMass();
+            tankStatesMasses = [tankStates.tankMass]';
+            
+            throttleModel = stateLogEntry.throttleModel;
+            steeringModel = stateLogEntry.steeringModel;
+            
+            altitude = norm(rVect) - bodyInfo.radius;
+            pressure = getPressureAtAltitude(bodyInfo, altitude); 
+            
+            throttle = throttleModel.getThrottleAtTime(ut, rVect, vVect, tankStatesMasses, dryMass, stageStates, lvState, tankStates, bodyInfo);
+            
+            [~, totalThrust, ~] = LaunchVehicleStateLogEntry.getTankMassFlowRatesDueToEngines(tankStates, tankStatesMasses, stageStates, throttle, lvState, pressure, ut, rVect, vVect, bodyInfo, steeringModel);
+            
+            value = totalThrust;
+                       
+            if(obj.lb == obj.ub)
+                c = [];
+                ceq(1) = value - obj.ub;
+            else
+                c(1) = obj.lb - value;
+                c(2) = value - obj.ub;
+                ceq = [];
+            end
+            c = c/obj.normFact;
+            ceq = ceq/obj.normFact;  
+            
+            lwrBnd = obj.lb;
+            uprBnd = obj.ub;
+            
+            eventNum = obj.event.getEventNum();
+        end
+        
+        function sF = getScaleFactor(obj)
+            sF = obj.normFact;
+        end
+        
+        function setScaleFactor(obj, sF)
+            obj.normFact = sF;
+        end
+        
+        function tf = usesStage(obj, stage)
+            tf = false;
+        end
+        
+        function tf = usesEngine(obj, engine)
+            tf = false;
+        end
+        
+        function tf = usesTank(obj, tank)
+            tf = false;
+        end
+        
+        function tf = usesEngineToTankConn(obj, engineToTank)
+            tf = false;
+        end
+        
+        function tf = usesEvent(obj, event)
+            tf = obj.event == event;
+        end
+        
+        function tf = usesStopwatch(obj, stopwatch)
+            tf = false;
+        end
+        
+        function event = getConstraintEvent(obj)
+            event = obj.event;
+        end
+        
+        function type = getConstraintType(obj)
+            type = 'Total Thrust';
+        end
+        
+        function name = getName(obj)
+            name = sprintf('%s - Event %i', obj.getConstraintType(), obj.event.getEventNum());
+        end
+        
+        function [unit, lbLim, ubLim, usesLbUb, usesCelBody, usesRefSc] = getConstraintStaticDetails(obj)
+            unit = 'kN';
+            lbLim = 0;
+            ubLim = Inf;
+            usesLbUb = true;
+            usesCelBody = false;
+            usesRefSc = false;
+        end
+        
+        function addConstraintTf = openEditConstraintUI(obj, lvdData)
+            addConstraintTf = lvd_EditGenericMAConstraintGUI(obj, lvdData);
+        end
+    end
+    
+    methods(Static)
+        function constraint = getDefaultConstraint(~)            
+            constraint = TotalThrustConstraint(LaunchVehicleEvent.empty(1,0),0,0);
+        end
+    end
+end

helper_methods/ksptot_ma/launch_vehicle_designer/misc/computeTWRatio.m

@@ -0,0 +1,11 @@
+function twRatio = computeTWRatio(throttle, ut, rVect, vVect, tankMasses, dryMass, stgStates, lvState, tankStates, bodyInfo)
+    altitude = norm(rVect) - bodyInfo.radius;
+    presskPa = getPressureAtAltitude(bodyInfo, altitude); 
+
+    [~, totalThrust]= LaunchVehicleStateLogEntry.getTankMassFlowRatesDueToEngines(tankStates, tankMasses, stgStates, throttle, lvState, presskPa, ut, rVect, vVect, bodyInfo, []);
+
+    totalMass = (dryMass + sum(tankMasses))*1000; %kg          
+    totalThrust = totalThrust * 1000; % N
+
+    twRatio = computeSLThrustToWeight(bodyInfo, totalThrust, totalMass);
+end

helper_methods/ksptot_ma/optimization/ma_getConstraintStaticDetails.m

@@ -233,7 +233,7 @@
             usesRefSc = false;
         case 'Altitude of Apoapsis'
             unit = 'km';
-            lbLim = 0;
+            lbLim = -Inf;
             ubLim = Inf;
             lbVal = 0;
             ubVal = 0;
@@ -245,7 +245,7 @@
             usesRefSc = false;
         case 'Altitude of Periapsis'
             unit = 'km';
-            lbLim = 0;
+            lbLim = -Inf;
             ubLim = Inf;
             lbVal = 0;
             ubVal = 0;
@@ -553,7 +553,7 @@
             usesRefSc = false;
         case 'Altitude'
             unit = 'km';
-            lbLim = 0;
+            lbLim = -Inf;
             ubLim = Inf;
             lbVal = 0;
             ubVal = 0;