-// airspeed_indicator.cxx - a regular VSI.
+// airspeed_indicator.cxx - a regular pitot-static airspeed indicator.
// Written by David Megginson, started 2002.
+// Last modified by Eric van den Berg, 09 Dec 2012
//
// This file is in the Public Domain and comes with no warranty.
+#ifdef HAVE_CONFIG_H
+# include "config.h"
+#endif
+
#include <math.h>
+#include <simgear/constants.h>
#include <simgear/math/interpolater.hxx>
#include "airspeed_indicator.hxx"
#include <Main/fg_props.hxx>
#include <Main/util.hxx>
-
-
-AirspeedIndicator::AirspeedIndicator ()
+#include <Environment/environment_mgr.hxx>
+#include <Environment/environment.hxx>
+
+
+// A higher number means more responsive.
+#define RESPONSIVENESS 50.0
+
+AirspeedIndicator::AirspeedIndicator ( SGPropertyNode *node )
+ :
+ _name(node->getStringValue("name", "airspeed-indicator")),
+ _num(node->getIntValue("number", 0)),
+ _total_pressure(node->getStringValue("total-pressure", "/systems/pitot/total-pressure-inhg")),
+ _static_pressure(node->getStringValue("static-pressure", "/systems/static/pressure-inhg")),
+ _has_overspeed(node->getBoolValue("has-overspeed-indicator",false)),
+ _pressure_alt_source(node->getStringValue("pressure-alt-source", "/instrumentation/altimeter/pressure-alt-ft")),
+ _ias_limit(node->getDoubleValue("ias-limit", 248.0)),
+ _mach_limit(node->getDoubleValue("mach-limit", 0.48)),
+ _alt_threshold(node->getDoubleValue("alt-threshold", 13200))
{
+ _environmentManager = NULL;
}
AirspeedIndicator::~AirspeedIndicator ()
void
AirspeedIndicator::init ()
{
- _serviceable_node =
- fgGetNode("/instrumentation/airspeed-indicator/serviceable",
- true);
- _total_pressure_node =
- fgGetNode("/systems/pitot/total-pressure-inhg", true);
- _static_pressure_node =
- fgGetNode("/systems/static/pressure-inhg", true);
- _speed_node =
- fgGetNode("/instrumentation/airspeed-indicator/indicated-speed-kt",
- true);
+ std::string branch;
+ branch = "/instrumentation/" + _name;
+
+ SGPropertyNode *node = fgGetNode(branch.c_str(), _num, true );
+ _serviceable_node = node->getChild("serviceable", 0, true);
+ _total_pressure_node = fgGetNode(_total_pressure.c_str(), true);
+ _static_pressure_node = fgGetNode(_static_pressure.c_str(), true);
+ _density_node = fgGetNode("/environment/density-slugft3", true);
+ _speed_node = node->getChild("indicated-speed-kt", 0, true);
+ _tas_node = node->getChild("true-speed-kt", 0, true);
+ _mach_node = node->getChild("indicated-mach", 0, true);
+
+ // overspeed-indicator properties
+ if (_has_overspeed) {
+ _ias_limit_node = node->getNode("ias-limit",0, true);
+ _mach_limit_node = node->getNode("mach-limit",0, true);
+ _alt_threshold_node = node->getNode("alt-threshold",0, true);
+
+ if (!_ias_limit_node->hasValue()) {
+ _ias_limit_node->setDoubleValue(_ias_limit);
+ }
+
+ if (!_mach_limit_node->hasValue()) {
+ _mach_limit_node->setDoubleValue(_mach_limit);
+ }
+
+ if (!_alt_threshold_node->hasValue()) {
+ _alt_threshold_node->setDoubleValue(_alt_threshold);
+ }
+
+ _airspeed_limit = node->getChild("airspeed-limit-kt", 0, true);
+ _pressure_alt = fgGetNode(_pressure_alt_source.c_str(), true);
+ }
+
+ _environmentManager = (FGEnvironmentMgr*) globals->get_subsystem("environment");
}
void
-AirspeedIndicator::bind ()
+AirspeedIndicator::reinit ()
{
+ _speed_node->setDoubleValue(0.0);
}
void
-AirspeedIndicator::unbind ()
+AirspeedIndicator::update (double dt)
{
+ if (!_serviceable_node->getBoolValue()) {
+ return;
+ }
+
+ double pt = _total_pressure_node->getDoubleValue() ;
+ double p = _static_pressure_node->getDoubleValue() ;
+ double qc = ( pt - p ) * SG_INHG_TO_PA ; // Impact pressure in Pa, _not_ to be confused with dynamic pressure!!!
+
+ // Now, reverse the equation (normalize impact pressure to
+ // avoid "nan" results from sqrt)
+ qc = std::max( qc , 0.0 );
+ // Calibrated airspeed (using compressible aerodynamics) based on impact pressure qc in m/s
+ // Using calibrated airspeed as indicated airspeed, neglecting any airspeed indicator errors.
+ double v_cal = sqrt( 7 * SG_p0_Pa/SG_rho0_kg_p_m3 * ( pow( 1 + qc/SG_p0_Pa , 1/3.5 ) -1 ) );
+
+ // Publish the indicated airspeed
+ double last_speed_kt = _speed_node->getDoubleValue();
+ double current_speed_kt = v_cal * SG_MPS_TO_KT;
+ double filtered_speed = fgGetLowPass(last_speed_kt,
+ current_speed_kt,
+ dt * RESPONSIVENESS);
+ _speed_node->setDoubleValue(filtered_speed);
+ computeMach();
+
+ if (!_has_overspeed) {
+ return;
+ }
+
+ double lmt = _ias_limit_node->getDoubleValue();
+ if (_pressure_alt->getDoubleValue() > _alt_threshold_node->getDoubleValue()) {
+ double mmo = _mach_limit_node->getDoubleValue();
+ lmt = (filtered_speed/_mach_node->getDoubleValue())* mmo;
+ }
+
+ _airspeed_limit->setDoubleValue(lmt);
}
-
-#ifndef SEA_LEVEL_DENSITY_SLUGFG3
-# define SEA_LEVEL_DENSITY_SLUGFT3 0.002378
-#endif
-
-#ifndef FPSTOKTS
-# define FPSTOKTS 0.592484
-#endif
-
void
-AirspeedIndicator::update (double dt)
+AirspeedIndicator::computeMach()
{
- if (_serviceable_node->getBoolValue()) {
- double pt = _total_pressure_node->getDoubleValue();
- double p = _static_pressure_node->getDoubleValue();
- double q = pt - p; // dynamic pressure
-
- // Now, reverse the equation
- double v_fps = sqrt((2 * q) / SEA_LEVEL_DENSITY_SLUGFT3);
-
- _speed_node->setDoubleValue(v_fps * FPSTOKTS);
- }
+ if (!_environmentManager) {
+ return;
+ }
+
+ FGEnvironment env(_environmentManager->getEnvironment());
+
+ double oatK = env.get_temperature_degc() + SG_T0_K - 15.0 ; // OAT in Kelvin
+ oatK = std::max( oatK , 0.001 ); // should never happen, but just in case someone flies into space...
+ double c = sqrt(SG_gamma * SG_R_m2_p_s2_p_K * oatK); // speed-of-sound in m/s at aircraft position
+ double pt = _total_pressure_node->getDoubleValue() * SG_INHG_TO_PA; // total pressure in Pa
+ double p = _static_pressure_node->getDoubleValue() * SG_INHG_TO_PA; // static pressure in Pa
+ p = std::max( p , 0.001 ); // should never happen, but just in case someone flies into space...
+ double rho = _density_node->getDoubleValue() * SG_SLUGFT3_TO_KGPM3; // air density in kg/m3
+ rho = std::max( rho , 0.001 ); // should never happen, but just in case someone flies into space...
+
+ // true airspeed in m/s
+ pt = std::max( pt , p );
+ double V_true = sqrt( 7 * p/rho * (pow( 1 + (pt-p)/p , 1/3.5 ) -1 ) );
+ // Mach number; _see notes in systems/pitot.cxx_
+ double mach = V_true / c;
+
+ // publish Mach and TAS
+ _mach_node->setDoubleValue(mach);
+ _tas_node->setDoubleValue(V_true * SG_MPS_TO_KT );
}
// end of airspeed_indicator.cxx
projects / flightgear.git / blobdiff