Hybrid unmanned helicopter energy control system and its helicopter

Abstract

The invention discloses a hybrid unmanned helicopter energy control system and a helicopter having the same. The control system includes an energy management system and an engine, an integrated starter motor and an airborne battery that are respectively connected to the energy management system; when the helicopter When the power required for flight is small, the energy management system controls the starter-integrated motor to be in the power-generating state, and converts the engine's excess mechanical energy into electrical energy through the starter-integrated motor, which can be used for the operation of airborne electrical equipment or / and stored in the onboard battery. Medium; when the helicopter requires high power for flight, the energy management system controls the starter-integrated motor to be in an electric state, so that the starter-integrated motor converts the electrical energy stored in the onboard battery into mechanical energy and together with the mechanical energy output by the engine, satisfies the helicopter's flight requirements. . This control system can reduce the maximum power demand on the helicopter's engine, and at the same time, it can also make up for the engine's power loss to a certain extent when flying at high altitudes.

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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