/*************************************************************************** TITLE: ls_aux ---------------------------------------------------------------------------- FUNCTION: Atmospheric and auxilary relationships for LaRCSim EOM ---------------------------------------------------------------------------- MODULE STATUS: developmental ---------------------------------------------------------------------------- GENEALOGY: Created 9208026 as part of C-castle simulation project. ---------------------------------------------------------------------------- DESIGNED BY: B. Jackson CODED BY: B. Jackson MAINTAINED BY: B. Jackson ---------------------------------------------------------------------------- MODIFICATION HISTORY: DATE PURPOSE 931006 Moved calculations of auxiliary accelerations from here to ls_accel.c and corrected minus sign in front of A_Y_Pilot contribution from Q_body*P_body*D_X_pilot term. EBJ 931014 Changed calculation of Alpha from atan to atan2 so sign is correct. EBJ 931220 Added calculations for static and total temperatures & pressures, as well as dynamic and impact pressures and calibrated airspeed. EBJ 940111 Changed #included header files from old "ls_eom.h" to newer "ls_types.h", "ls_constants.h" and "ls_generic.h". EBJ 950207 Changed use of "abs" to "fabs" in calculation of signU. EBJ 950228 Fixed bug in calculation of beta_dot. EBJ CURRENT RCS HEADER INFO: $Header$ $Log$ Revision 1.3 1998/08/06 12:46:38 curt Header change. Revision 1.2 1998/01/19 18:40:24 curt Tons of little changes to clean up the code and to remove fatal errors when building with the c++ compiler. Revision 1.1 1997/05/29 00:09:54 curt Initial Flight Gear revision. * Revision 1.12 1995/02/28 17:57:16 bjax * Corrected calculation of beta_dot. EBJ * * Revision 1.11 1995/02/07 21:09:47 bjax * Corrected calculation of "signU"; was using divide by * abs(), which returns an integer; now using fabs(), which * returns a double. EBJ * * Revision 1.10 1994/05/10 20:09:42 bjax * Fixed a major problem with dx_pilot_from_cg, etc. not being calculated locally. * * Revision 1.9 1994/01/11 18:44:33 bjax * Changed header files to use ls_types, ls_constants, and ls_generic. * * Revision 1.8 1993/12/21 14:36:33 bjax * Added calcs of pressures, temps and calibrated airspeeds. * * Revision 1.7 1993/10/14 11:25:38 bjax * Changed calculation of Alpha to use 'atan2' instead of 'atan' so alphas * larger than +/- 90 degrees are calculated correctly. EBJ * * Revision 1.6 1993/10/07 18:45:56 bjax * A little cleanup; no significant changes. EBJ * * Revision 1.5 1993/10/07 18:42:22 bjax * Moved calculations of auxiliary accelerations here from ls_aux, and * corrected sign on Q_body*P_body*d_x_pilot term of A_Y_pilot calc. EBJ * * Revision 1.4 1993/07/16 18:28:58 bjax * Changed call from atmos_62 to ls_atmos. EBJ * * Revision 1.3 1993/06/02 15:02:42 bjax * Changed call to geodesy calcs from ls_geodesy to ls_geoc_to_geod. * * Revision 1.1 92/12/30 13:17:39 bjax * Initial revision * ---------------------------------------------------------------------------- REFERENCES: [ 1] Shapiro, Ascher H.: "The Dynamics and Thermodynamics of Compressible Fluid Flow", Volume I, The Ronald Press, 1953. ---------------------------------------------------------------------------- CALLED BY: ---------------------------------------------------------------------------- CALLS TO: ---------------------------------------------------------------------------- INPUTS: ---------------------------------------------------------------------------- OUTPUTS: --------------------------------------------------------------------------*/ #include "ls_types.h" #include "ls_constants.h" #include "ls_generic.h" #include "ls_aux.h" #include "atmos_62.h" #include "ls_geodesy.h" #include "ls_gravity.h" #include void ls_aux( void ) { SCALAR dx_pilot_from_cg, dy_pilot_from_cg, dz_pilot_from_cg; /* SCALAR inv_Mass; */ SCALAR v_XZ_plane_2, signU, v_tangential; /* SCALAR inv_radius_ratio; */ SCALAR cos_rwy_hdg, sin_rwy_hdg; SCALAR mach2, temp_ratio, pres_ratio; /* update geodetic position */ ls_geoc_to_geod( Lat_geocentric, Radius_to_vehicle, &Latitude, &Altitude, &Sea_level_radius ); Longitude = Lon_geocentric - Earth_position_angle; /* Calculate body axis velocities */ /* Form relative velocity vector */ V_north_rel_ground = V_north; V_east_rel_ground = V_east - OMEGA_EARTH*Sea_level_radius*cos( Lat_geocentric ); V_down_rel_ground = V_down; V_north_rel_airmass = V_north_rel_ground - V_north_airmass; V_east_rel_airmass = V_east_rel_ground - V_east_airmass; V_down_rel_airmass = V_down_rel_ground - V_down_airmass; U_body = T_local_to_body_11*V_north_rel_airmass + T_local_to_body_12*V_east_rel_airmass + T_local_to_body_13*V_down_rel_airmass + U_gust; V_body = T_local_to_body_21*V_north_rel_airmass + T_local_to_body_22*V_east_rel_airmass + T_local_to_body_23*V_down_rel_airmass + V_gust; W_body = T_local_to_body_31*V_north_rel_airmass + T_local_to_body_32*V_east_rel_airmass + T_local_to_body_33*V_down_rel_airmass + W_gust; V_rel_wind = sqrt(U_body*U_body + V_body*V_body + W_body*W_body); /* Calculate alpha and beta rates */ v_XZ_plane_2 = (U_body*U_body + W_body*W_body); if (U_body == 0) signU = 1; else signU = U_body/fabs(U_body); if( (v_XZ_plane_2 == 0) || (V_rel_wind == 0) ) { Alpha_dot = 0; Beta_dot = 0; } else { Alpha_dot = (U_body*W_dot_body - W_body*U_dot_body)/ v_XZ_plane_2; Beta_dot = (signU*v_XZ_plane_2*V_dot_body - V_body*(U_body*U_dot_body + W_body*W_dot_body)) /(V_rel_wind*V_rel_wind*sqrt(v_XZ_plane_2)); } /* Calculate flight path and other flight condition values */ if (U_body == 0) Alpha = 0; else Alpha = atan2( W_body, U_body ); Cos_alpha = cos(Alpha); Sin_alpha = sin(Alpha); if (V_rel_wind == 0) Beta = 0; else Beta = asin( V_body/ V_rel_wind ); Cos_beta = cos(Beta); Sin_beta = sin(Beta); V_true_kts = V_rel_wind * V_TO_KNOTS; V_ground_speed = sqrt(V_north_rel_ground*V_north_rel_ground + V_east_rel_ground*V_east_rel_ground ); V_rel_ground = sqrt(V_ground_speed*V_ground_speed + V_down_rel_ground*V_down_rel_ground ); v_tangential = sqrt(V_north*V_north + V_east*V_east); V_inertial = sqrt(v_tangential*v_tangential + V_down*V_down); if( (V_ground_speed == 0) && (V_down == 0) ) Gamma_vert_rad = 0; else Gamma_vert_rad = atan2( -V_down, V_ground_speed ); if( (V_north_rel_ground == 0) && (V_east_rel_ground == 0) ) Gamma_horiz_rad = 0; else Gamma_horiz_rad = atan2( V_east_rel_ground, V_north_rel_ground ); if (Gamma_horiz_rad < 0) Gamma_horiz_rad = Gamma_horiz_rad + 2*PI; /* Calculate local gravity */ ls_gravity( Radius_to_vehicle, Lat_geocentric, &Gravity ); /* call function for (smoothed) density ratio, sonic velocity, and ambient pressure */ ls_atmos(Altitude, &Sigma, &V_sound, &Static_temperature, &Static_pressure); Density = Sigma*SEA_LEVEL_DENSITY; Mach_number = V_rel_wind / V_sound; V_equiv = V_rel_wind*sqrt(Sigma); V_equiv_kts = V_equiv*V_TO_KNOTS; /* calculate temperature and pressure ratios (from [1]) */ mach2 = Mach_number*Mach_number; temp_ratio = 1.0 + 0.2*mach2; pres_ratio = pow( temp_ratio, 3.5 ); Total_temperature = temp_ratio*Static_temperature; Total_pressure = pres_ratio*Static_pressure; /* calculate impact and dynamic pressures */ Impact_pressure = Total_pressure - Static_pressure; Dynamic_pressure = 0.5*Density*V_rel_wind*V_rel_wind; /* calculate calibrated airspeed indication */ V_calibrated = sqrt( 2.0*Dynamic_pressure / SEA_LEVEL_DENSITY ); V_calibrated_kts = V_calibrated*V_TO_KNOTS; Centrifugal_relief = 1 - v_tangential/(Radius_to_vehicle*Gravity); /* Determine location in runway coordinates */ Radius_to_rwy = Sea_level_radius + Runway_altitude; cos_rwy_hdg = cos(Runway_heading*DEG_TO_RAD); sin_rwy_hdg = sin(Runway_heading*DEG_TO_RAD); D_cg_north_of_rwy = Radius_to_rwy*(Latitude - Runway_latitude); D_cg_east_of_rwy = Radius_to_rwy*cos(Runway_latitude) *(Longitude - Runway_longitude); D_cg_above_rwy = Radius_to_vehicle - Radius_to_rwy; X_cg_rwy = D_cg_north_of_rwy*cos_rwy_hdg + D_cg_east_of_rwy*sin_rwy_hdg; Y_cg_rwy =-D_cg_north_of_rwy*sin_rwy_hdg + D_cg_east_of_rwy*cos_rwy_hdg; H_cg_rwy = D_cg_above_rwy; dx_pilot_from_cg = Dx_pilot - Dx_cg; dy_pilot_from_cg = Dy_pilot - Dy_cg; dz_pilot_from_cg = Dz_pilot - Dz_cg; D_pilot_north_of_rwy = D_cg_north_of_rwy + T_local_to_body_11*dx_pilot_from_cg + T_local_to_body_21*dy_pilot_from_cg + T_local_to_body_31*dz_pilot_from_cg; D_pilot_east_of_rwy = D_cg_east_of_rwy + T_local_to_body_12*dx_pilot_from_cg + T_local_to_body_22*dy_pilot_from_cg + T_local_to_body_32*dz_pilot_from_cg; D_pilot_above_rwy = D_cg_above_rwy - T_local_to_body_13*dx_pilot_from_cg - T_local_to_body_23*dy_pilot_from_cg - T_local_to_body_33*dz_pilot_from_cg; X_pilot_rwy = D_pilot_north_of_rwy*cos_rwy_hdg + D_pilot_east_of_rwy*sin_rwy_hdg; Y_pilot_rwy = -D_pilot_north_of_rwy*sin_rwy_hdg + D_pilot_east_of_rwy*cos_rwy_hdg; H_pilot_rwy = D_pilot_above_rwy; /* Calculate Euler rates */ Sin_phi = sin(Phi); Cos_phi = cos(Phi); Sin_theta = sin(Theta); Cos_theta = cos(Theta); Sin_psi = sin(Psi); Cos_psi = cos(Psi); if( Cos_theta == 0 ) Psi_dot = 0; else Psi_dot = (Q_total*Sin_phi + R_total*Cos_phi)/Cos_theta; Theta_dot = Q_total*Cos_phi - R_total*Sin_phi; Phi_dot = P_total + Psi_dot*Sin_theta; /* end of ls_aux */ } /*************************************************************************/