Research Article
Optimization of Fuel Injection Control System of Two-Stroke Aeroengine of UAV
Table 4
Results of the GT-power simulation when α = 80°.
| α (°) | n (RPM) | λset | To (Nm) | Po (kw) | η | γ (RPM·h/Kg) | Pc (MPa) |
| 80 | 2500 | 15.5 | 7.003 | 1.833 | 0.141 | 2453.110 | 2.510 | 80 | 3000 | 15.5 | 9.582 | 3.010 | 0.194 | 2457.778 | 2.424 | 80 | 3500 | 15.5 | 11.009 | 4.035 | 0.229 | 2529.551 | 2.974 | 80 | 4000 | 15.5 | 13.881 | 5.815 | 0.231 | 2020.441 | 3.869 | 80 | 4500 | 15.5 | 14.826 | 6.987 | 0.167 | 1368.566 | 4.293 | 80 | 5000 | 15.5 | 12.003 | 6.285 | 0.188 | 1904.895 | 4.107 | 80 | 5500 | 15.5 | 8.315 | 4.789 | 0.138 | 2018.235 | 3.044 | 80 | 6000 | 15.5 | 6.094 | 3.829 | 0.205 | 4088.545 | 2.391 |
|
|