A power allocation scheme and control method for a hybrid power system of a helicopter

Abstract

The invention discloses a power allocation scheme and a control method of a hybrid power system for a helicopter, which relates to the technical field of an aeronautical aircraft. A main rotor pow system comprises an engine, a main rotor motor, a first clutch, a second clutch, a terminal gear box, an automatic tilt and a main rotor; Tail rotor power system includes: battery, tail rotor motor, tailrotor; The whole machine control system includes: the whole machine controller, the battery management system, the engine controller, the main rotor motor controller, the tail rotor motor controller;In addition, the battery is connected with an external electric network through a plug, the fuel tank is connected with an engine through an oil pipeline, and the battery is connected with a main rotor motor through an inverter / rectifier. The helicopter power allocation scheme and advanced control methods are developed to meet the requirements of different flight environments, and the helicopterhas the advantages of simple structure, high energy utilization rate, high engine fuel efficiency, energy saving and emission reduction, strong power, safety and reliability.

Description

technical field [0001] The invention relates to the technical field of aviation aircraft, more specifically, a hybrid power system, a power configuration scheme and a control method for a helicopter. technical background [0002] Helicopters have the characteristics of vertical take-off and landing, hovering, cruising, and rapid heading changes, and are widely used in transportation, patrol , travel , ambulance and many other fields. As helicopters demand high fuel economy, redundant power, and high reliability, gasoline-electric hybrids will become the future development direction of helicopter power systems. Compared with the traditional fuel engine system, it increases the types of components and flight combination modes of the power system, and optimizes the combination according to the flight tasks of the helicopter, so that the engine as the main power source can keep running at high efficiency, low fuel consumption, and low The ideal operating range of emissions...

AI Technical Summary

Problems solved by technology

For example, Chinese Patent Publication No. CN105836141A, published on 2016-08-10, discloses a hybrid helicopter driving mechanism and driving method. The system includes a basic power source and an auxiliary power source, and uses a single-row planetary gear mechanism for power distribution. , the structure is complex, the function is single, and the influence of the state of the energy storage device on the control of the helicopter is not considered

Chinese patent publication number CN105691610A, date of publication 2016-06-22, discloses a hybrid power system for a helicopter and a helicopter with it, the system includes an engine, a power battery, an ISG motor and a tail rotor motor, wherein the ISG motor cannot When the total power demand of the helicopter is high, electric power assist is provided to prevent the engine from entering high fuel consumption conditions. At the same time, the braking energy of the main rotor is not recovered, and the energy saving effect is average.

Images