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# Parameters for ROSflight software-in-the-loop simulation | ||
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# Mass and inertia parameters are defined in fixedwing.urdf.xacro. | ||
# Mass: 11.0 | ||
# Jx: 0.8244 | ||
# Jy: 1.135 | ||
# Jz: 1.759 | ||
# Jxz: 0.1204 | ||
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/fixedwing/rosflight_sil: | ||
ros__parameters: | ||
rho: 1.2682 | ||
mass: 11.0 | ||
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wing_s: 0.55 | ||
wing_b: 2.8956 | ||
wing_c: 0.18994 | ||
wing_M: 50.0 | ||
wing_epsilon: 0.16 | ||
wing_alpha0: 0.47 | ||
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D_prop : 0.508 | ||
CT_0 : 0.09357 | ||
CT_1 : -0.06044 | ||
CT_2 : -0.1079 | ||
CQ_0 : 0.005230 | ||
CQ_1 : 0.004970 | ||
CQ_2 : -0.01664 | ||
KV : 145.0 # Motor speed constant from datasheet in RPM/V | ||
KQ : 0.06586 # ((1 /KV_rpm_per_volt) * 60 / (2 * M_PI)) | ||
# Back-emf constant, KV in V-s/rad, Motor torque constant, KQ in N-m/A | ||
V_max : 44.4 # voltage for 12s battery at 3.7 volts per cell | ||
R_motor : 0.042 # ohms | ||
I_0 : 1.5 # no-load (zero torque) current (A) | ||
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servo_tau: .02 | ||
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C_L_O: 0.23 | ||
C_L_alpha: 5.61 | ||
C_L_beta: 0.0 | ||
C_L_p: 0.0 | ||
C_L_q: 7.95 | ||
C_L_r: 0.0 | ||
C_L_delta_a: 0.0 | ||
C_L_delta_e: 0.13 | ||
C_L_delta_r: 0.0 | ||
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C_D_O: 0.043 | ||
C_D_alpha: 0.03 | ||
C_D_beta: 0.0 | ||
C_D_p: 0.0 | ||
C_D_q: 0.0 | ||
C_D_r: 0.0 | ||
C_D_delta_a: 0.0 | ||
C_D_delta_e: 0.0135 | ||
C_D_delta_r: 0.0 | ||
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C_ell_O: 0.0 | ||
C_ell_alpha: 0.00 | ||
C_ell_beta: -0.13 | ||
C_ell_p: -0.51 | ||
C_ell_q: 0.0 | ||
C_ell_r: 0.25 | ||
C_ell_delta_a: 0.17 | ||
C_ell_delta_e: 0.0 | ||
C_ell_delta_r: 0.0024 | ||
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C_m_O: 0.0135 | ||
C_m_alpha: -2.74 | ||
C_m_beta: 0.0 | ||
C_m_p: 0.0 | ||
C_m_q: -38.21 | ||
C_m_r: 0.0 | ||
C_m_delta_a: 0.0 | ||
C_m_delta_e: -0.99 | ||
C_m_delta_r: 0.0 | ||
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C_n_O: 0.0 | ||
C_n_alpha: 0.0 | ||
C_n_beta: 0.073 | ||
C_n_p: 0.069 | ||
C_n_q: 0.0 | ||
C_n_r: -0.095 | ||
C_n_delta_a: -0.011 | ||
C_n_delta_e: 0.0 | ||
C_n_delta_r: -0.069 | ||
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C_Y_O: 0.0 | ||
C_Y_alpha: 0.00 | ||
C_Y_beta: -0.98 | ||
C_Y_p: 0.0 | ||
C_Y_q: 0.0 | ||
C_Y_r: 0.0 | ||
C_Y_delta_a: 0.075 | ||
C_Y_delta_e: 0.0 | ||
C_Y_delta_r: 0.19 |
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