Abstract
In order to improve the helicopter responsive ability during autorotation power recovery maneuvers, a new turbo-shaft engine control scheme is proposed in this paper. Using rotor flapping/lagging dynamics and an induced velocity model which is capable of capturing vortex ring characteristics, an integrated helicopter and engine model was developed to simulate autorotation process. By introducing a closed-loop with compressor guided vanes, a novel two-variable engine control law is devised using Linear Matrix Inequality Pole Placement method. This allows for a rapid adaptation of the helicopter to a large and fast needed torque variation required in autorotation power recovery. The transient performances and the robustness for the closed-loop helicopter-pilot system are validated for some examples appropriated to autorotation training procedure. Simulation results illustrate that, with this novel control law, the helicopter’s ability to respond during autorotation is strongly enhanced when compared to traditional cases.
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Abbreviations
- \(W_{\mathrm{f}}\) :
-
Fuel flow rate (kg/s)
- \(\chi \) :
-
Compressor guided vane angle (\({^{\circ }}\))
- \(N_{\mathrm{g}}\) :
-
Relative rotor speed of gas turbine (%)
- \(N_{\mathrm{p} }\) :
-
Relative rotor speed of power turbine (%)
- \(\hbox {SM}_{\mathrm{c}}\) :
-
Stall margin of compressor (%)
- \(\eta _{\mathrm{c} }\) :
-
Efficiency of compressor (–)
- \(V_{{x}}\), \(V_{{y}}\), \(V_{{z}}\) :
-
Velocities along X, Y and Z axis
- \({{\varPsi }} ,{{\varPhi }},{{\varTheta }}\) :
-
Yaw, roll and pitch angle of helicopter (\({^{\circ }})\)
- \(\theta _{0}, A_{\mathrm{1c},} B_{\mathrm{1s},} \theta _{\mathrm{T}}\) :
-
Rotor collective, lateral cyclic pitch, longitudinal cyclic pitch (\({^{\circ }})\)
- p, q, r :
-
Angular rate about X-axis, Y-axis and Z-axis with respect to b-frame (rad/s)
- G :
-
Gravity of helicopter (N)
- \(J_{\mathrm{R}}, J_{\mathrm{GB}}, J_{\mathrm{TL}}, J_{\mathrm{E}}, J_{\mathrm{acc}}\) :
-
Moment of inertia of rotor, gearbox, tail rotor, engine and other accessories(\(\hbox {kg m}^{2})\)
- \(\Omega _{\mathrm{R}}\), \(\Omega _{\mathrm{E}}\), \(\Omega _{\mathrm{GB}}\), \(\Omega _{\mathrm{TL}}\) :
-
Main rotor speed, engine output shaft speed, Gearbox output shaft speed, tail rotor speed (rad/s)
- E:
-
Engine
- H:
-
Helicopter
- t:
-
Total thermodynamic parameter
- cor:
-
Corrected thermodynamic parameter
- ds:
-
Design-point value
- g:
-
Earth fixed axes system
- b:
-
Airframe fixed axes system
- h:
-
Rotor hub fixed axes system
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Sun, F., Zhang, H. Engine Control Design Using Compressor Guided Vanes During Autorotation Power Recovery. Arab J Sci Eng 42, 2899–2914 (2017). https://doi.org/10.1007/s13369-016-2336-7
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DOI: https://doi.org/10.1007/s13369-016-2336-7