From: andy <andy>
Date: Tue, 21 May 2002 07:40:46 +0000 (+0000)
Subject: Solve for the elevator control input during approach.  It turns out that
X-Git-Url: https://git.mxchange.org/?a=commitdiff_plain;h=4535c84b993fb9b6adecc9a699309b329f23c4ee;p=flightgear.git

Solve for the elevator control input during approach.  It turns out that
the downforce from the tail due to elevator trim is a significant contribution
to total lift.
---

diff --git a/src/FDM/YASim/Airplane.cpp b/src/FDM/YASim/Airplane.cpp
index d92d4f962..be30389c1 100644
--- a/src/FDM/YASim/Airplane.cpp
+++ b/src/FDM/YASim/Airplane.cpp
@@ -1,3 +1,5 @@
+#include <stdio.h>
+
 #include "Atmosphere.hpp"
 #include "ControlMap.hpp"
 #include "Gear.hpp"
@@ -10,6 +12,10 @@
 #include "Airplane.hpp"
 namespace yasim {
 
+// gadgets
+inline float norm(float f) { return f<1 ? 1/f : f; }
+inline float abs(float f) { return f<0 ? -f : f; }
+
 Airplane::Airplane()
 {
     _emptyWeight = 0;
@@ -146,6 +152,13 @@ void Airplane::setCruise(float speed, float altitude)
     _tailIncidence = 0;
 }
 
+void Airplane::setElevatorControl(int control)
+{
+    _approachElevator.control = control;
+    _approachElevator.val = 0;
+    _approachControls.add(&_approachElevator);
+}
+
 void Airplane::addApproachControl(int control, float val)
 {
     Control* c = new Control();
@@ -804,6 +817,9 @@ void Airplane::solve()
 	// Run an approach iteration, and do likewise
 	runApproach();
 
+	_model.getBody()->getAngularAccel(tmp);
+	float apitch0 = tmp[1];
+
 	_model.getBody()->getAccel(tmp);
 	float alift = _approachWeight * tmp[2];
 
@@ -840,7 +856,23 @@ void Airplane::solve()
             return;
         }
 
-	// And apply:
+        // And the elevator control in the approach.  This works just
+        // like the tail incidence computation (it's solving for the
+        // same thing -- pitching moment -- by diddling a different
+        // variable).
+        const float ELEVDIDDLE = 0.0001f;
+        _approachElevator.val += ELEVDIDDLE;
+        runApproach();
+        _approachElevator.val -= ELEVDIDDLE;
+
+	_model.getBody()->getAngularAccel(tmp);
+	float apitch1 = tmp[1];
+        float elevDelta = -apitch0 * (ELEVDIDDLE/(apitch1-apitch0));
+
+        // Now apply the values we just computed.  Note that the
+        // "minor" variables are deferred until we get the lift/drag
+        // numbers in the right ballpark.
+
 	applyDragFactor(dragFactor);
 	applyLiftRatio(liftFactor);
 
@@ -851,15 +883,27 @@ void Airplane::solve()
 	    continue;
 	}
 
-	// OK, now we can adjust the minor variables
+	// OK, now we can adjust the minor variables:
 	_cruiseAoA += 0.5f*aoaDelta;
 	_tailIncidence += 0.5f*tailDelta;
+        _approachElevator.val += 0.5f*elevDelta;
 	
 	_cruiseAoA = clamp(_cruiseAoA, -0.174f, 0.174f);
 	_tailIncidence = clamp(_tailIncidence, -0.174f, 0.174f);
+        _approachElevator.val = clamp(_approachElevator.val, -1.f, 1.f);
+
+        fprintf(stderr, "p0 %6f p1 %6f e %5f d %5f\n",
+                apitch0, apitch1, _approachElevator.val, elevDelta); // DEBUG
+
+        fprintf(stderr, "l %5f d %5f aoa %5f inc %5f ele %5f\n",
+                _liftRatio, _dragFactor, _cruiseAoA, _tailIncidence,
+                _approachElevator.val);
 
-        if(dragFactor < 1.00001 && liftFactor < 1.00001 &&
-           aoaDelta < .000017   && tailDelta < .000017)
+        if(norm(dragFactor) < 1.00001 &&
+           norm(liftFactor) < 1.00001 &&
+           abs(aoaDelta) < .000017 &&
+           abs(tailDelta) < .000017 &&
+           abs(elevDelta) < 0.00001)
         {
             break;
         }
diff --git a/src/FDM/YASim/Airplane.hpp b/src/FDM/YASim/Airplane.hpp
index 9a38700a0..f44d496fc 100644
--- a/src/FDM/YASim/Airplane.hpp
+++ b/src/FDM/YASim/Airplane.hpp
@@ -46,6 +46,7 @@ public:
     void setApproach(float speed, float altitude, float aoa); 
     void setCruise(float speed, float altitude);
 
+    void setElevatorControl(int control);
     void addApproachControl(int control, float val);
     void addCruiseControl(int control, float val);
 
@@ -67,6 +68,7 @@ public:
     float getLiftRatio();
     float getCruiseAoA();
     float getTailIncidence();
+    float getApproachElevator() { return _approachElevator.val; }
     char* getFailureMsg();
 
 private:
@@ -135,6 +137,7 @@ private:
     float _liftRatio;
     float _cruiseAoA;
     float _tailIncidence;
+    Control _approachElevator;
     char* _failureMsg;
 };
 
diff --git a/src/FDM/YASim/FGFDM.cpp b/src/FDM/YASim/FGFDM.cpp
index dc34a0759..edd2cc231 100644
--- a/src/FDM/YASim/FGFDM.cpp
+++ b/src/FDM/YASim/FGFDM.cpp
@@ -36,6 +36,11 @@ static const float CIN2CM = 1.6387064e-5;
 FGFDM::FGFDM()
 {
     _nextEngine = 0;
+
+    // Map /controls/elevator to the approach elevator control.  This
+    // should probably be settable, but there are very few aircraft
+    // who trim their approaches using things other than elevator.
+    _airplane.setElevatorControl(parseAxis("/controls/elevator"));
 }
 
 FGFDM::~FGFDM()
diff --git a/src/FDM/YASim/YASim.cxx b/src/FDM/YASim/YASim.cxx
index aa3ed775c..7b33a8fd5 100644
--- a/src/FDM/YASim/YASim.cxx
+++ b/src/FDM/YASim/YASim.cxx
@@ -74,11 +74,13 @@ void YASim::report()
     float drag = 1000 * a->getDragCoefficient();
 
     SG_LOG(SG_FLIGHT,SG_INFO,"YASim solution results:");
-    SG_LOG(SG_FLIGHT,SG_INFO,"      Iterations: "<<a->getSolutionIterations());
-    SG_LOG(SG_FLIGHT,SG_INFO,"Drag Coefficient: "<< drag);
-    SG_LOG(SG_FLIGHT,SG_INFO,"      Lift Ratio: "<<a->getLiftRatio());
-    SG_LOG(SG_FLIGHT,SG_INFO,"      Cruise AoA: "<< aoa);
-    SG_LOG(SG_FLIGHT,SG_INFO,"  Tail Incidence: "<< tail);
+    SG_LOG(SG_FLIGHT,SG_INFO,"       Iterations: "<<a->getSolutionIterations());
+    SG_LOG(SG_FLIGHT,SG_INFO," Drag Coefficient: "<< drag);
+    SG_LOG(SG_FLIGHT,SG_INFO,"       Lift Ratio: "<<a->getLiftRatio());
+    SG_LOG(SG_FLIGHT,SG_INFO,"       Cruise AoA: "<< aoa);
+    SG_LOG(SG_FLIGHT,SG_INFO,"   Tail Incidence: "<< tail);
+    SG_LOG(SG_FLIGHT,SG_INFO,"Approach Elevator: "<<a->getApproachElevator());
+    
 
     float cg[3];
     char buf[256];