Parallel hybrid power aircraft dynamic coupling system and driving control method thereof

Abstract

The invention discloses a parallel hybrid power aircraft dynamic coupling system and a driving control method thereof. The system comprises a power source and a dynamic coupling system; the power source comprises an internal combustion engine, a motor and an energy storage device; the power coupling system is a parallel hybrid power coupling device formed by combining and connecting a planetary gear row, a brake and a clutch; the clutch is arranged between a sun gear and a planetary frame, the brake is arranged between the planetary frame and a power system shell, the internal combustion engine is connected with the sun gear, and the motor is connected with a gear ring and a system output shaft. By means of the system, various working modes that the motor starts the internal combustion engine, the motor or the internal combustion engine independently outputs power, the motor and the internal combustion engine output power at the same time, the internal combustion engine outputs power,the motor generates electricity, the internal combustion engine is turned off and the motor generates electricity can be achieved. The system is simpler in structure, has multiple working modes and can lower the power grade and working noise of the arranged internal combustion engine and reduce fuel consumption.

Description

technical field [0001] The invention relates to the technical field of aviation aircraft, in particular to a parallel hybrid aircraft power coupling system and a drive control method for the system. Background technique [0002] The general flight conditions of a fixed-wing aircraft can be divided into seven stages: takeoff, climb, cruise, descent, level off, landing, and roll-off deceleration. For a traditional fixed-wing aircraft with an internal combustion engine as its single power source, the internal combustion engine generally operates at maximum power during the take-off phase, and the components are stressed, noisy, high in temperature, insufficient in combustion, and high in fuel consumption; the climb phase is generally about 90% The fuel consumption is also high when the load rate is running; while the load rate of the internal combustion engine in the cruising section is mostly 40% to 60%; the internal combustion engine is in a slow state in the descent section,...

AI Technical Summary

Problems solved by technology

However, the existing related technologies are not mature enough

For example, the Chinese patent publication number is CN102933461A, and the publication date is 2013-02-13, which discloses a hybrid drive device for a helicopter, which is a serial hybrid configuration equipped with an engine, a generator and an electric motor, although the Transmission parts such as clutches and drive shafts are easy to maintain, but there are always energy conversion losses between the two motors during power generation and electric motoring, and the overall system efficiency is low; another example is the Chinese patent publication number CN104290907A, and the publication date is 2015-01-21 , disclosed a new type of hybrid vertical short take-off and landing unmanned aerial vehicle. The electric ducted fan of the aircraft provides lift and assists in balance during vertical take-off and landing. It is based on a series hybrid configuration, but it includes three motors driving ducted fans and a generator, the system is complex, and the fuselage is a U-shaped structure, which is not easy to manufacture, the cockpit is narrow, and the field of view is poor; another example is the Chinese patent disclosure The number is CN105173075A, and the publication date is 2015-12-23. It discloses a hybrid tiltable wing aircraft. The aircraft is composed of two independent systems: an electric multi-rotor module and an aeroengine multi-rotor module. The electric rotor realizes vertical take-off and landing, but its drive motor is only powered by an independent lithium battery, which will result in a large battery demand, high quality, and inconvenient charging; another example is the Chinese patent publication number CN105836141A, and the publication date is 2016-08-10. Disclosed is a hybrid helicopter driving mechanism and driving method. The mechanism is a hybrid hybrid system, including two lockers, a clutch, two motors and an engine. The structure is relatively complicated, and the output power of the engine is 2. The two motors / generators are both in the electric state. According to the characteristics of the two degrees of freedom of the planetary gear transmission, motion interference will be generated to offset part of the driving energy; another example is the Chinese patent publication number CN106184779A, and the publication date is 2016-12-07. A hybrid aircraft coupling system has been developed. The planetary gear ring gear is fixed, and the planetary carrier meshes with the transmission wheel on the transmission shaft to realize power coupling. However, the gear meshing method between the planetary carrier and the transmission shaft is complicated to process and assemble, and the cost is high. , if connected by keys or splines, the same function can be realized and the cost can be reduced, and the system’s engine, generator, clutch, motor, planetary row and other components are arranged axially in sequence, resulting in a large axial size of the system, which is not easy Installation; Another example is that the Chinese patent publication number is CN106494625A, and the publication date is 2017-03-15, which discloses a parallel-type general-purpose aircraft gas-electric hybrid power system, which is composed of an LNG internal combustion engine and an electric motor, but its LNG fuel Storage and supply circuit valve groups and pipelines are complicated, difficult to arrange, difficult to maintain, and poor safety when the aircraft fails and lands hard

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