Rotor speed optimization control method and device for helicopter power system
A technology of helicopter power and rotor speed, which is applied to the power plant on the aircraft, in the direction of power plant type, piston power plant, etc., can solve the problems of narrow rotor speed variable range and reduced power turbine efficiency, so as to avoid tip stall. , improve real-time performance, improve the effect of execution efficiency
Active Publication Date: 2022-03-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology
[0003] However, the efficiency of the power turbine continues to decrease when the engine is operated away from the design point speed
Therefore, the current turboshaft engine basically operates around a constant speed, and the maximum allowable variation range of the output speed is usually not more than ±15%, resulting in a narrower variable range of the rotor speed
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[0063] Aiming at the deficiencies in the prior art, the solution idea of the present invention is based on the composite airborne model of the helicopter power system, with the main rotor speed as the optimization independent variable, according to the corresponding optimization objectives, combined with the optimal blade load operating boundary constraints, to Effectively avoid tip stall of the rotor blades, and at the same time use the improved golden section method to quickly search for the optimal rotor speed in one dimension. According to the current flight conditions, the search interval of the golden section method is dynamically adjusted based on the optimal blade load range , thereby greatly reducing the search range and effectively improving the algorithm execution efficiency.
[0064] Specifically, the rotor speed optimization control method of the helicopter power system proposed by the present invention is as follows:
[0065] The helicopter power system realize...
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The invention discloses a method for optimally controlling the rotor speed of a helicopter power system. Based on the composite airborne model of the helicopter power system, the method takes the main rotor speed as the optimization independent variable, according to the corresponding optimization objective, combined with the optimal blade load operating boundary constraints, to effectively avoid the tip stall of the rotor blades, At the same time, the improved golden section method is used for one-dimensional fast search of the optimal rotor speed. According to the current flight conditions, the search interval of the golden section method is dynamically adjusted based on the optimal blade load range, thereby greatly reducing the search range and effectively improving Algorithm execution efficiency. The invention also discloses a rotor speed optimization control device of the helicopter power system. Compared with the prior art, the invention can realize the operation of the helicopter power system at the optimum rotor speed while ensuring the safe and reliable operation of the helicopter power system.
Description
technical field [0001] The invention relates to a method for optimizing the rotor speed of a helicopter power system, and belongs to the technical field of system control and simulation in aerospace propulsion theory and engineering. Background technique [0002] With the rapid development of new-generation helicopter technology, the requirements for turboshaft engine exhaust emissions and fuel consumption are getting higher and higher, and military powers such as Europe and the United States have formulated many goals and plans [Goulos L, Pachidis V, D'Lppolito R, et al. An Integrated Approach for the Multidisciplinary Design of OptimumRotorcraft Operations[J]], in order to accelerate the pace of achieving the most economical and environmentally friendly operation of helicopters. Among them, variable rotor speed technology is recognized as one of the most direct and promising solutions to reduce helicopter fuel consumption. It is foreseeable that variable rotor speed techn...
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IPC IPC(8): B64C27/12B64D27/04B64D35/00B64D35/02G06F30/27G06F111/04G06F119/08G06F119/14
CPCB64C27/12B64D27/04B64D35/02B64D35/00G06F30/27G06F2111/04G06F2119/08G06F2119/14
Inventor 汪勇钟文城郭浩然宋劼张海波
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS