Hybrid unmanned helicopter energy control system and its helicopter

Abstract

The invention discloses a hybrid power unmanned helicopter energy control system and a helicopter with the hybrid power unmanned helicopter energy control system. The control system comprises an energy management system, an engine, a start-generation integrated motor and an onboard battery, and the engine, the start-generation integrated motor and the onboard battery are connected with the energymanagement system. When low power is needed during flying of the helicopter, the energy management system controls the start-generation integrated motor to be in a power generation state, and abundantmechanical energy of the engine is converted into electric energy through the start-generation integrated motor to be used for operation of onboard electric equipment and / or stored in the onboard battery. When high power is needed during flying of the helicopter, the energy management system controls the start-generation integrated motor to be in a motoring state, so that the electric energy stored in the onboard battery is converted into mechanical energy by the start-generation integrated motor and meets flying of the helicopter with the mechanical energy output by the engine. According tothe control system, the need for the maximum power of the engine of the helicopter can be reduced, and meanwhile when the helicopter flies on a highland, the power loss of the engine can be made up toa certain degree.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to an energy control system for a hybrid unmanned helicopter and a helicopter equipped with the same. Background technique [0002] The ceiling of an unmanned helicopter is mainly determined by the plateau performance of the engine. At present, in order to ensure that the unmanned helicopter meets the needs of plateau flight, the method of increasing the output power of the engine in high altitude areas is usually adopted, such as electronic turbocharging, exhaust gas turbocharging etc., that is, by increasing the intake pressure of the engine, the output power attenuation of the engine in a high-altitude environment is reduced. [0003] However, there are some objective problems in the traditional method: First, the engines used by small unmanned helicopters are mostly piston engines. In areas with high altitudes, due to the thin air, the power of the engines drops significantly,...

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Problems solved by technology

[0003] However, there are some objective problems in the traditional method: First, the engines used by small unmanned helicopters are mostly piston engines. In areas with high altitudes, due to the thin air, the power of the engines drops significantly, which leads to the failure of unmanned helicopters in plateau areas. Second, the use of electronic turbocharging to improve the plateau performance of the engine can increase the output power of the engine to a certain extent, thereby increasing the take-off weight of the unmanned helicopter on the plateau, due to the high power consumption of the electronic turbocharger itself , it also needs to consume part of the engine power; thirdly, the scheme of using exhaust gas turbocharging can also improve the plateau performance of the engine. Ensuring the installation of these devices will increase the empty weight of the helicopter. To a certain extent, part of the increased lift on the plateau is used to increase the weight of the exhaust turbine device; third, all modification programs need to be used for unmanned helicopters. The engine is refitted and the ECU is recalibrated, and the workload is relatively large

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