CN111976997B

CN111976997B - Helicopter variable-rotating-speed hybrid power system and helicopter using same

Info

Publication number: CN111976997B
Application number: CN202010743227.0A
Authority: CN
Inventors: 姜辰; 王浩文; 孙帆
Original assignee: Tsinghua University
Current assignee: Tsinghua University
Priority date: 2020-07-29
Filing date: 2020-07-29
Publication date: 2022-04-19
Anticipated expiration: 2040-07-29
Also published as: CN111976997A

Abstract

The invention discloses a helicopter variable speed hybrid power system and a helicopter using the system. The helicopter variable speed hybrid power system includes an engine, a motor, a generator, a planetary reducer and an output shaft, and the engine can drive the rotor to rotate , the engine includes: a first controller, the first controller can adjust the output of the engine; the electric motor includes: a second controller, the second controller can control the output of the electric motor for The rotation speed of the rotor is supplemented and adjusted; the generator is connected to the engine and is driven by the engine, and the generator includes: a third controller, the third controller can realize electric energy conversion and convert all the The electric energy is supplied to the electric motor; the planetary reducer is provided between the engine and the output shaft. The helicopter variable speed hybrid power system according to the present invention has a more optimized structure, simple control logic, and higher safety and stability.

Description

Helicopter variable-rotating-speed hybrid power system and helicopter using same

Technical Field

The invention relates to the technical field of aviation, in particular to a variable-rotating-speed hybrid power system of a helicopter and the helicopter using the same.

Background

At present, the variable-speed helicopter is mainly realized by adopting a gearbox with a plurality of reduction ratios or a gearbox similar to a CVT structure, and the commonly adopted modes are a mechanical reduction ratio conversion mode and a planetary reduction mode. In the mode of mechanical reduction ratio conversion, the problem of discontinuous power output can occur in the conversion process, so that the stability of the helicopter is reduced when the rotating speed is converted, and meanwhile, the helicopter is low in maintainability and poor in reliability. The planetary speed reduction mode has the problems of difficult vibration isolation design, complex structure, heavy weight, low reliability, complex control logic and the like. Therefore, there is room for improvement in the above-described technology.

Disclosure of Invention

The present invention is directed to solving at least one of the problems of the prior art. Therefore, the invention aims to provide a variable-rotation-speed hybrid power system of a helicopter, which has the advantages of more optimized structure, simple control logic and higher safety and stability.

The invention also provides a helicopter with the helicopter variable-speed hybrid power system.

The helicopter variable-speed hybrid power system comprises the following components: engine, motor, generator, planetary reducer and output shaft, the engine can drive the rotor and rotate, the engine includes: a first controller that can adjust an output of the engine; the motor includes: a second controller that can control an output of the motor for complementary adjustment of a rotational speed of the rotor; the generator is connected with the engine and driven by the engine, and the generator comprises: a third controller that can perform electric energy conversion and supply the electric energy to the motor; the planetary reduction gear is disposed between the engine and the output shaft.

The variable-rotating-speed hybrid power system of the helicopter is more optimized in structure, simple in control logic and higher in safety and stability.

According to one embodiment of the invention, the variable-speed hybrid power system of the helicopter comprises: the sun gear is connected with the output end of the engine; the gear ring is connected with the motor through the speed reducing mechanism; the planet carrier is connected with the output shaft.

According to one embodiment of the invention, the variable-speed hybrid power system of the helicopter comprises: the sun gear is connected with the motor; the gear ring is connected with the output end of the engine through the speed reducing mechanism; the planet carrier is connected with the output shaft.

According to the helicopter variable-speed hybrid power system provided by the embodiment of the invention, the rotor wing is sleeved on the output shaft.

According to the helicopter variable-speed hybrid power system provided by the embodiment of the invention, the rotor shaft is connected with the output shaft through the speed reducing mechanism.

According to the helicopter variable-speed hybrid power system provided by the embodiment of the invention, the motor is a direct-current motor.

According to an embodiment of the invention, the helicopter variable-speed hybrid power system further comprises: a battery module, the battery module and the generator may power the motor.

According to a second aspect of the invention, a helicopter variable speed hybrid system as defined in any one of the first aspects is provided. Compared with the prior art, the helicopter has the same advantages as the helicopter variable-rotating-speed hybrid power system, and the detailed description is omitted.

Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.

Drawings

The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:

FIG. 1 is a schematic main frame illustration of a helicopter variable speed hybrid system according to an embodiment of the present invention;

FIG. 2 is a frame schematic of a helicopter variable speed hybrid system according to a first embodiment of the present invention;

FIG. 3 is a schematic structural diagram of a variable speed hybrid powertrain of a helicopter in accordance with a first embodiment of the present invention;

FIG. 4 is a frame schematic of a variable speed hybrid system of a helicopter in accordance with a second embodiment of the present invention;

FIG. 5 is a schematic structural diagram of a variable speed hybrid powertrain of a helicopter in accordance with a second embodiment of the present invention;

FIG. 6 is a flow chart of engine speed regulation of a variable speed hybrid powertrain of a helicopter in accordance with an embodiment of the present invention;

FIG. 7 is a flow chart of a motor speed regulation for a helicopter variable speed hybrid system according to an embodiment of the present invention.

Reference numerals:

100-helicopter variable-speed hybrid power system, 1-engine, 11-first controller, 2-motor, 21-second controller, 3-generator, 31-third controller, 4-planetary reducer, 41-sun gear, 42-gear ring, 43-speed reducing mechanism, 44-planet carrier, 5-output shaft and 6-battery module.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.

In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the invention.

A helicopter variable speed hybrid system 100 according to an embodiment of the present invention is described below with reference to fig. 1-7. As shown in fig. 1, a helicopter variable speed hybrid system 100 according to an embodiment of the present invention includes: the engine 1, the motor 2, the generator 3, the planetary reducer 4 and the output shaft 5, further, the engine 1 can drive the rotor (not shown in the figure) to rotate, specifically, as shown in fig. 2, the engine 1 includes: a first controller 11, the first controller 11 being capable of adjusting the output of the engine 1. Further, the motor 2 includes: the second controller 21, the second controller 21 can control the output of the motor 2 to supplement and adjust the rotation speed of the rotor, which is beneficial to improving the stability of the rotation speed of the rotor and the adjustability of the rotation speed of the rotor. Further, a generator 3 is connected to the engine 1 and driven by the engine 1, and the generator 3 includes: a third controller 31, the third controller 31 being capable of converting electric energy and supplying the electric energy to the motor 2, specifically, the third controller 31 being capable of converting alternating current to direct current; further, a planetary reducer 4 is provided between the engine 1 and the output shaft 5.

The variable-speed hybrid power system 100 of the helicopter is more optimized in structure and higher in safety and stability.

According to the helicopter variable speed hybrid system 100 of one embodiment of the present invention, as shown in fig. 2 and 3, the planetary reducer 4 includes: a sun gear 41, a ring gear 42, a speed reduction mechanism 43 and a carrier 44, and further, the sun gear 41 is connected with the output end of the engine 1; further, the ring gear 42 is connected to the motor 2 through a speed reduction mechanism 43; further, the carrier 44 is connected to the output shaft 5. Further, in a specific embodiment, the ring gear 42 and the reduction mechanism 43 may not have a locking function, so that the motor 2 is in a state of being operated all the time, and when the rotor is operated at a low speed, the motor 2 is also operated at a very low speed, and the required power is also very low. In another specific embodiment, the ring gear 42 and the speed reduction mechanism 43 may be provided with a lock function, and when the ring gear 42 is locked without rotation, the motor 2 is also not operated, so that the engine 1 alone can supply power to the output shaft 5.

According to the helicopter variable speed hybrid system 100 of one embodiment of the present invention, as shown in fig. 4 and 5, the planetary reducer 4 includes: a sun gear 41, a ring gear 42, a reduction mechanism 43, and a carrier 44, and further, the sun gear 41 is connected to the motor 2; further, the ring gear 42 is connected to the output end of the engine 1 through a speed reduction mechanism 43; further, the carrier 44 is connected to the output shaft 5. Further, in a specific embodiment, the sun gear 41 and the motor 2 may not have a locking function, so that the motor 2 is in a state of being operated all the time, and when the rotor is operated at a low speed, the motor 2 is also operated at a very low speed, and the required power is also very low. In another specific embodiment, the sun gear 41 and the motor 2 may have a locking function, and when the sun gear 41 is locked and does not rotate, the motor 2 does not operate, so that the engine 1 alone can supply power to the output shaft 5.

According to the helicopter variable-speed hybrid power system 100 of one embodiment of the invention, the rotor is sleeved on the output shaft 5. The rotor rotates with the rotation of the output shaft 5. In this way, the output shaft 5 can be directly connected to the rotor as a rotor shaft (not shown). Thereby realizing a direct connection of the rotor and the output shaft 5. In the description of the invention, "above", "over" and "above" a first feature in a second feature includes the first feature being directly above and obliquely above the second feature, or simply means that the first feature is higher in level than the second feature.

According to the variable-speed hybrid power system 100 of the helicopter, a rotor shaft is connected with an output shaft 5 through a speed reducing mechanism 43, and a rotor is connected to the rotor shaft. This allows for an indirect connection of the rotor to the output shaft 5. In the description of the present invention, the first feature being "on" or "under" the second feature may include the first and second features being in direct contact, and may also include the first and second features being in contact with each other not directly but through another feature therebetween.

According to the helicopter variable-speed hybrid system 100 of one embodiment of the present invention, the motor 2 is a dc motor. Thus, the motor 2 can be directly driven to work by converting the third controller 31 into direct current.

The helicopter variable-speed hybrid system 100 according to an embodiment of the present invention, as shown in fig. 2, further includes: the battery module 6, further, the battery module 6 and the generator 3 may power the motor 2. Further, when the power of the engine 3 is insufficient, the output of the generator 3 can be turned off by the third controller 31, and the electric motor 2 and the engine 1 are powered together by the electric energy stored in the battery module 6 to meet the power demand of the helicopter flight, which is the hybrid operation mode of the helicopter. Further, when the electric energy stored in the battery module 6 is sufficient, the flight requirement of the helicopter can be met only by the electric motor 2 using the electric energy of the battery module 6, and at this time, the helicopter is in a pure electric operation mode. Further, when the engine 1 fails, the helicopter enters a self-gliding state, and the motor 2 powers the helicopter at the moment, and particularly, the overload characteristic of the motor 2 can be utilized to provide instantaneous high power, so that the grounding speed of the helicopter is further reduced.

According to the variable-speed hybrid power system 100 of the helicopter in accordance with an embodiment of the present invention, as shown in fig. 6, the first controller 11 can control the throttle (or the throttle opening) to further realize the adjustment of the rotational speed of the engine 1, so as to ensure that the engine 1 operates at the set rated rotational speed, which is the optimal rotational speed of the engine power or the fuel consumption rate.

According to the helicopter variable-speed hybrid system 100 of one embodiment of the present invention, as shown in fig. 7, the second controller 21 adjusts the output of the motor 2 according to the target speed value and the output speed value of the hybrid system 100, it should be noted that the voltage output of the motor 2 can be adjusted to meet the flight requirement of the helicopter.

In summary, the helicopter variable-speed hybrid power system 100 according to the present invention has the following advantages, firstly, the output speed can be adjusted by the supplementary adjustment of the electric motor 2 to the output speed under the condition that the rotation speed of the engine 1 is constant, so as to improve the stability during the flight process; secondly, the hybrid power output of the rotating speed control can be realized by only using one planetary reducer 4, the structure is simple, the maintainability is excellent, the reliability is high, the weight is low, thirdly, the generator 3 and the motor 2 always work in the power generation and electric states respectively, and the control mode is simpler; fourthly, there is no torque coupling relation among the motor 2, the engine 1, and the output shaft 5, and the control logic is simple.

The invention also provides a helicopter, which comprises the helicopter variable-speed hybrid power system 100, so that the helicopter has the advantages of better safety, higher stability, better power performance and the like.

In the description herein, references to the description of the term "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples" or the like mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

While embodiments of the invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. A variable-speed hybrid power system of a helicopter, comprising:

an engine capable of driving rotation of a rotor, the engine comprising: a first controller capable of adjusting an output of the engine, the first controller for controlling a throttle or throttle opening;

an electric motor, the electric motor comprising: a second controller capable of controlling the output of the motor for complementary adjustment of the rotational speed of the rotor;

a generator coupled to and driven by the engine, the generator comprising: a third controller capable of performing electric energy conversion and supplying the electric energy to the motor;

a planetary reducer and an output shaft, the planetary reducer being disposed between the engine and the output shaft;

the planetary reduction gear includes:

the sun gear is connected with the output end of the engine;

the gear ring is connected with the motor through the speed reducing mechanism;

the planet carrier is connected with the output shaft;

a battery module, the battery module and the generator being capable of powering the electric motor;

when the gear ring and the speed reducing mechanism are in a locking state, the gear ring is locked and does not rotate, and the motor does not work.

2. A helicopter variable speed hybrid system according to claim 1, wherein said rotor is sleeved on said output shaft.

3. A helicopter variable speed hybrid system as claimed in claim 2, wherein said rotor shaft is connected to said output shaft through said speed reduction mechanism.

4. A helicopter variable speed hybrid system as claimed in claim 1, wherein said electric motor is a dc motor.

5. A helicopter, characterized in that it comprises: the helicopter variable speed hybrid system of any one of claims 1-4.