A multi-power source hybrid hybrid fixed-wing aircraft and its control method
A technology of hybrid power and aircraft, applied in the direction of power plant, power distribution, aircraft parts, etc. on the aircraft, can solve the problems of insufficient utilization of the storage system, low energy utilization rate, etc., to ensure flight maneuverability and safety, and realize safety Effect of forced landing and weight reduction
Active Publication Date: 2022-04-08
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology
[0006] Aiming at the deficiencies of the above-mentioned prior art, the purpose of the present invention is to provide a multi-power source hybrid hybrid fixed-wing aircraft and its control method to solve the problems in the prior art that the energy utilization rate is low and the storage system is not fully utilized. capacity problem; the present invention mixes the engine, motor, photovoltaic cell group and supercapacitor, and adds a set of photovoltaic power generation system, which not only improves the endurance of the aircraft, but also improves the service life compared with ordinary lithium-ion batteries. Effectively improve the fuel economy and emissions of aircraft engines, thereby comprehensively improving aircraft performance
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[0099] In order to facilitate the understanding of those skilled in the art, the present invention will be further described below in conjunction with the embodiments and accompanying drawings, and the contents mentioned in the embodiments are not intended to limit the present invention.
[0100] refer to figure 1 As shown, a kind of multi-power source hybrid hybrid fixed-wing aircraft of the present invention includes: fuselage 8, left wing 7, right wing 12, propeller 1, power coupler control unit 19, drive motor 2, motor Shaft 20, engine 3, power coupling system 18, ISG motor 17, rectifier 15, inverter 16, motor controller 5, supercapacitor 6, control module 14, photovoltaic power generation system, fuel tank 10 and empennage 9;
[0101] The left wing 7 and the right wing 12 are respectively fixedly mounted on the left and right sides of the fuselage 8 middle part relative to the nose;
[0102] The ISG motor 17 is located at the head of the fuselage, and its output end is e...
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The invention discloses a multi-power source hybrid hybrid fixed-wing aircraft and a control method thereof, comprising: a fuselage, a left wing, a right wing, a propeller, a power coupler control unit, a driving motor, a motor shaft, an engine, Power coupling system, ISG motor, rectifier, inverter, motor controller, supercapacitor, control module, photovoltaic power generation system, fuel tank and empennage; the present invention adopts the multi-power source hybrid mode of engine, ISG motor and supercapacitor, compared Because the piston engine hybrid mode can reduce weight and further improve the endurance of fixed-wing aircraft; compared with other hybrid aircraft, the photovoltaic battery pack used in the present invention has the characteristics of cleanliness and long life, and will not cause environmental pollution.
Description
technical field [0001] The invention belongs to the technical field of hybrid aircraft, and specifically refers to a multi-power source hybrid hybrid fixed-wing aircraft and a control method thereof. Background technique [0002] With the rapid development of the world's transportation tools, people's demand for more convenient, energy-saving and efficient vehicles continues to increase. In recent years, China has promulgated the "Opinions on Deepening my country's Low Altitude Airspace Management Reform" document. With the proposal of relevant policies, the aircraft industry, as a new type of industry, has gradually come into our sight with the advancement of science and technology. [0003] However, the single drive system of the traditional piston-type aero-engine increases with the flight altitude of the aircraft, the oxygen content in the air decreases, the temperature decreases, and the atmospheric pressure decreases accordingly, which makes the operating efficiency of...
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IPC IPC(8): B64D27/02B64D31/00
CPCB64D27/02B64D31/00B64D2027/026B64D2221/00
Inventor 朱耀鎏王春燕赵万忠宋迎东张自宇于博洋孟琦康曹铭纯
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS