CN112874779A - Pure electric drive's light-duty helicopter - Google Patents
Pure electric drive's light-duty helicopter Download PDFInfo
- Publication number
- CN112874779A CN112874779A CN202011192565.6A CN202011192565A CN112874779A CN 112874779 A CN112874779 A CN 112874779A CN 202011192565 A CN202011192565 A CN 202011192565A CN 112874779 A CN112874779 A CN 112874779A
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- main rotor
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- 239000000446 fuel Substances 0.000 claims abstract description 7
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 6
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 6
- 239000001257 hydrogen Substances 0.000 claims abstract description 6
- 238000006073 displacement reaction Methods 0.000 claims description 24
- 238000005096 rolling process Methods 0.000 claims description 6
- 230000005611 electricity Effects 0.000 claims 2
- 230000033001 locomotion Effects 0.000 abstract description 4
- 230000007613 environmental effect Effects 0.000 abstract description 3
- 230000007547 defect Effects 0.000 description 3
- 239000012636 effector Substances 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/06—Helicopters with single rotor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8209—Electrically driven tail rotors
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention belongs to the technical field of helicopter design, and particularly relates to a pure electric drive helicopter. The helicopter comprises a power module (100), a main rotor assembly (200), a tail rotor assembly (300) and an operation and control system (400), wherein the power module (100) and the main rotor assembly (200) are positioned in an upper platform area of a helicopter body, the tail rotor assembly (300) is positioned at the top of a vertical tail of the helicopter, the operation and control system (400) is positioned in a front body area of the helicopter, the power module (100) is respectively electrically connected with the main rotor assembly (200), the tail rotor assembly (300) and the operation and control system (400) through cables, and the operation and control system (400) is respectively electrically connected with the main rotor assembly (200) and the tail rotor assembly (300) through electrical signal cables; the power module (100) comprises a hydrogen fuel cell power supply for supplying power to the whole machine. The invention can provide power for the rotary motion of the main rotor and the tail rotor through the hydrogen fuel cell power supply device, improve the economy, the safety and the comfort of the helicopter, and meet the requirement of environmental protection.
Description
Technical Field
The invention belongs to the technical field of helicopter design, and particularly relates to a pure electric drive helicopter.
Background
The helicopter is widely applied in various fields all over the world due to the characteristics of low altitude, low speed and capability of vertically taking off and landing in a small area, and a single-rotor tail rotor aircraft represented by the helicopter is influenced to a certain degree by inherent defects of the single-rotor tail rotor aircraft, such as high noise, high vibration level, high use cost and high maintenance cost, for example, for users and the environment.
The invention avoids the inherent defects of the current helicopter design technology, adopts a pure electric drive device to replace a fuel engine and a transmission device in the traditional design, can reduce the vibration level, adopts a variable-speed tail rotor to reduce the noise influence range, can reduce the use and maintenance cost of the helicopter, and can also reduce the noise influence range by CO2With NOXZero emission reaches the aim of environmental protection.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides a helicopter driven by pure electric power, which is used for avoiding the inherent defects of the existing helicopter, thereby improving the safety, comfort, economy and environmental protection of the helicopter.
The technical scheme of the invention is as follows: in order to achieve the above purpose, the present invention provides a light helicopter driven by pure electric power, which includes a power module 100, a main rotor assembly 200, a tail rotor assembly 300, and a control system 400; the power module 100 and the main rotor assembly 200 are located in an upper platform area of a helicopter fuselage, the tail rotor assembly 300 is located at the top of a vertical tail of the helicopter, the control system 400 is located in a front fuselage area of the helicopter, the power module 100 is electrically connected with the main rotor assembly 200, the tail rotor assembly 300 and the control system 400 through cables, and the control system 400 is electrically connected with the main rotor assembly 200 and the tail rotor assembly 300 through electrical signal cables;
the power module 100 includes a hydrogen fuel cell power supply for supplying power to the entire machine.
In one possible embodiment, the main rotor assembly 200 includes main blades 201, main blade pitch links 202, main rotor shaft 203, main rotor motor 204, main rotor motor case 205, main rotor actuator 206;
the main rotor motor 204 is located in the center of the main rotor assembly 200 for driving the main rotor actuator 206; one end of the main rotor shaft 203 is provided with a tooth, the tooth is inserted into the center of the main rotor motor 204 and is in gear fit connection with the main rotor motor 204, and the main rotor motor 204 drives the main rotor shaft 203 to rotate; the main blade 201 is connected to the other end of the main rotor shaft 203, one end of the main blade pitch-variable tie rod 202 is rotatably connected to the main blade 201, and the other end is rotatably connected to the output end of the main rotor actuating device 206; the main rotor actuating device 206 is located between the main blades 201 and the main rotor motor 204, is sleeved on the main rotor shaft 203, and is in gear fit connection with the main rotor shaft 203; said main rotor motor 204 is housed in said main rotor motor casing 205, which is used to protect the motor; the main rotor motor 204 is electrically coupled to the power module 100.
In one possible embodiment, the tail rotor assembly 300 includes a tail blade 301, a tail blade pitch horn 302, a tail rotor shaft 303, a tail rotor motor 304, a tail rotor motor case 305, a tail rotor actuation device 306;
the tail rotor motor 304 is centrally located in the tail rotor assembly 300 for driving the tail rotor actuator 306; one end of the tail rotor shaft 303 is provided with a tooth which is inserted into the center of the tail rotor motor 304 and is in gear fit connection with the tail rotor motor 304, and the tail rotor motor 304 drives the tail rotor shaft 303 to rotate; the tail rotor blade 301 is connected to the other end of the tail rotor shaft 303, one end of the tail rotor blade pitch-variable pull rod 302 is rotatably connected with the tail rotor blade 301, and the other end of the tail rotor blade pitch-variable pull rod is rotatably connected with the tail rotor actuating device 306; the tail rotor actuating device 306 is located between the tail blades 301 and the tail rotor motor 304, is sleeved on the tail rotor shaft 303, and is in gear fit connection with the tail rotor shaft 303; tail rotor motor 304 is housed in a tail rotor motor case 305, which is used to protect the motor; the tail rotor motor 304 is electrically coupled to the power module 100.
In one possible embodiment, the main rotor actuation device 206 includes a main rotor booster 2061, a main rotor booster electrical signal interface 2062, a main rotor booster output rocker arm 2063, a main rotor booster mounting connector 2064, a main rotor booster mount 2065; the main rotor booster fixing piece 2065 is positioned at the center of the main rotor actuating device 206, sleeved on the main rotor shaft 203 and matched and connected with the gear of the main rotor actuating device, the main rotor boosters 2061 are uniformly distributed around the main rotor booster fixing piece 2065 and fixedly connected with the main rotor booster fixing piece 2065 through the main rotor booster mounting connector 2064, and the mounting positions and the number of the main rotor booster fixing pieces are the same as those of the main blades 201; main rotor booster 2061 one end is equipped with main rotor booster electric signal interface 2062 for the signal of telecommunication is imported, and the other end is equipped with main rotor booster output rocking arm 2063, main rotor booster output rocking arm 2063 with main blade pitch-changing pull rod 202 rotates and is connected.
In one possible embodiment, the main rotor assembly 200 further comprises a main blade axial mount 2066, a main blade pitch horn 2067; the main blades 201 are connected to the main rotor shaft 203 by the main blade axial mount 2066; the main blade pitch link 202 is connected to the main blade 201 via the main blade pitch rocker 2067.
In one possible embodiment, the tail rotor actuation device 306 includes a tail rotor booster 3061, a tail rotor booster mount 3062, a tail rotor booster electrical signal interface 3063, a tail rotor booster output rocker arm 3064, an actuation link 3065, a ball bearing 3066, an annular effector 3067; the annular acting member 3067 is sleeved in the outer wall of the tail rotor actuator 306, and the annular acting member 3067 is in rolling fit with the outer wall of the tail rotor actuator 306 through the rolling bearing 3066;
the tail rotor booster mounting joint 3062 is arranged at the gear connection position of the tail rotor shaft 303 and the tail rotor actuating device 306, the tail rotor booster 3061 is connected with the tail rotor shaft 303 through the tail rotor booster mounting joint 3062, one end of the tail rotor booster 3061 is provided with a tail rotor booster electric signal interface 3063 for electric signal input, the other end of the tail rotor booster is provided with a tail rotor booster output rocker arm 3064, the free end of the tail rotor booster output rocker arm 3064 is rotatably connected with the actuating connecting piece 3065, and the actuating connecting piece 3065 is fixedly connected to the outer side of the annular acting piece 3067; one end of the tail blade pitch-variable pull rod 302 is rotatably connected with the annular acting piece 3067, and the other end is rotatably connected with the tail blade 301.
In one possible embodiment, the tail rotor assembly 300 further includes a tail rotor axial mount 3067, a tail rotor pitch horn 3061; the tail paddle 301 is connected to the tail rotor shaft 303 by the tail paddle axial mount 3067; the tail paddle variable-pitch pull rod 302 passes through the tail paddle variable-pitch rocker arm 3061 with the tail paddle blade 301 is connected, the tail paddle variable-pitch pull rod moves to drive the tail paddle rocker arm to enable the tail paddle blade to rotate around the tail paddle axis, and the tail paddle variable-pitch operation is achieved.
In one possible embodiment, the control system 400 includes a main rotor control system component 401, a tail rotor control system component 402, the main rotor control system component 401 including a main blade control handle, a main blade link, a main blade displacement sensor, by operating the main blade control handle, an operating displacement is transmitted by the main blade link to the main blade displacement sensor, an electrical signal is generated by the main blade displacement sensor and sent to the main rotor motor 204; tail rotor control system component 402 includes that tail paddle handles pedal, tail paddle connecting rod, tail paddle displacement sensor, through the manipulation tail paddle is pedal, by tail paddle connecting rod will operate the displacement and transmit extremely tail paddle displacement sensor, by tail paddle displacement sensor produces the signal of telecommunication and sends tail rotor motor 304.
In one possible embodiment, the number of tail rotor boosters 3062 may be 1 or more.
In a possible embodiment, the rotational connection may be an articulation.
By relative movement of the ring shaped effector 3067 with the outer wall of the tail rotor actuator 306, an increase in the pitch angle of the tail rotor blades 301 and thus a reduction in the rotational speed of the tail rotor shaft 303 is achieved.
The increase in the pitch angle of the main blades 201 can be achieved by the main rotor booster output rocker 2063, thereby achieving a reduction in the rotational speed of the main rotor shaft 303.
The invention has the beneficial effects that: the invention can provide power for the rotary motion of the main rotor and the tail rotor through the hydrogen fuel cell power supply device, and realize the change of the rotating speed of the tail rotor through the change of the tail rotor pitch, especially in the low-altitude approach flight stage, the tail rotor pitch can be increased, the rotating speed of the tail rotor can be reduced, the noise level can be reduced, and the noise influence range can be reduced; because the original gear transmission device is cancelled, the vibration level is greatly reduced, the use and maintenance cost is reduced, and simultaneously, the noise source is reduced.
Description of the drawings:
FIG. 1 is a schematic diagram of a purely electric helicopter drive system arrangement;
FIG. 2 is a schematic structural view of a main rotor assembly 200 of the electric only propulsion helicopter;
FIG. 3 is a schematic structural view of a tail rotor assembly 300 of a purely electrically powered helicopter
Fig. 4 is a schematic view of a main rotor actuator 206 of a helicopter driven by purely electric power
Fig. 5 is a schematic view of a tail rotor actuator 306 of a purely electrically powered helicopter
Wherein:
100-a power module;
200-a main rotor assembly; 201-main blade; 202-main blade pitch link; 203-main rotor shaft; 204-main rotor motor; 205-main rotor motor case; 206-main rotor actuating device, 2061-main rotor booster, 2062-main rotor booster electric signal interface, 2063-main rotor booster output rocker arm, 2064-main rotor booster mounting joint, 2065-main rotor booster fixing piece, 2066-main blade axial mounting piece and 2067-main blade pitch-changing rocker arm;
300-a tail rotor assembly; 301-tail paddle; 302-tail rotor blade pitch-changing tie rod; 303-tail rotor shaft; 304-tail rotor motor; 305-tail rotor motor case; 306-tail rotor actuator, 3061-tail rotor booster, 3062-tail rotor booster mount joint, 3063-tail rotor booster electrical signal interface, 3064-tail rotor booster output rocker arm, 3065-actuator connector, 3066-ball bearing, 3067-annular actuator, 3068-tail rotor axial mount, 3069-tail rotor pitch horn;
400-a steering system; 401-main rotor handling system components, 402-tail rotor handling system components;
the specific implementation mode is as follows:
in order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus are not to be construed as limiting the present invention, and the terms "first", "second", "third" are used for descriptive purposes only and are not intended to indicate or imply relative importance; furthermore, unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be construed broadly, as they may be fixedly connected, detachably connected, or integrally connected, for example; there may be communication between the interiors of the two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1, a light helicopter driven by pure electric power includes a power module 100, a main rotor assembly 200, a tail rotor assembly 300, and a control system 400; the power module 100 and the main rotor assembly 200 are located in an upper platform area of a helicopter fuselage, the tail rotor assembly 300 is located at the top of a vertical tail of the helicopter, the control system 400 is located in a front fuselage area of the helicopter, the power module 100 is electrically connected with the main rotor assembly 200, the tail rotor assembly 300 and the control system 400 through cables, and the control system 400 is electrically connected with the main rotor assembly 200 and the tail rotor assembly 300 through electrical signal cables;
the power module 100 comprises a hydrogen fuel cell power supply device for supplying power to the whole machine;
as shown in fig. 2, the main rotor assembly 200 includes a main blade 201, a main blade pitch link 202, a main rotor shaft 203, a main rotor motor 204, a main rotor motor casing 205, and a main rotor actuator 206;
the main rotor motor 204 is located in the center of the main rotor assembly 200 for driving the main rotor actuator 206; one end of the main rotor shaft 203 is provided with a tooth, the tooth is inserted into the center of the main rotor motor 204 and is in gear fit connection with the main rotor motor 204, and the main rotor motor 204 drives the main rotor shaft 203 to rotate; the main blade 201 is connected to the other end of the main rotor shaft 203, one end of the main blade pitch-variable tie rod 202 is rotatably connected to the main blade 201, and the other end is rotatably connected to the output end of the main rotor actuating device 206; the main rotor actuating device 206 is located between the main blades 201 and the main rotor motor 204, is sleeved on the main rotor shaft 203, and is in gear fit connection with the main rotor shaft 203; said main rotor motor 204 is housed in said main rotor motor casing 205, which is used to protect the motor; the main rotor motor 204 is electrically coupled to the power module 100;
as shown in fig. 3, the tail rotor assembly 300 includes a tail blade 301, a tail blade pitch link 302, a tail rotor shaft 303, a tail rotor motor 304, a tail rotor motor casing 305, and a tail rotor actuator 306;
the tail rotor motor 304 is centrally located in the tail rotor assembly 300 for driving the tail rotor actuator 306; one end of the tail rotor shaft 303 is provided with a tooth which is inserted into the center of the tail rotor motor 304 and is in gear fit connection with the tail rotor motor 304, and the tail rotor motor 304 drives the tail rotor shaft 303 to rotate; the tail rotor blade 301 is connected to the other end of the tail rotor shaft 303, one end of the tail rotor blade pitch-variable pull rod 302 is rotatably connected with the tail rotor blade 301, and the other end of the tail rotor blade pitch-variable pull rod is rotatably connected with the tail rotor actuating device 306; the tail rotor actuating device 306 is located between the tail blades 301 and the tail rotor motor 304, is sleeved on the tail rotor shaft 303, and is in gear fit connection with the tail rotor shaft 303; tail rotor motor 304 is housed in a tail rotor motor case 305, which is used to protect the motor; the tail rotor motor 304 is electrically coupled to the power module 100;
as shown in fig. 4, the main rotor actuation device 206 includes a main rotor booster 2061, a main rotor booster electrical signal interface 2062, a main rotor booster output rocker arm 2063, a main rotor booster mounting connector 2064, and a main rotor booster mount 2065; the main rotor booster fixing piece 2065 is positioned at the center of the main rotor actuating device 206, sleeved on the main rotor shaft 203 and matched and connected with the gear of the main rotor actuating device, the main rotor boosters 2061 are uniformly distributed around the main rotor booster fixing piece 2065 and fixedly connected with the main rotor booster fixing piece 2065 through the main rotor booster mounting connector 2064, and the mounting positions and the number of the main rotor booster fixing pieces are the same as those of the main blades 201; one end of the main rotor booster 2061 is provided with the main rotor booster electric signal interface 2062 for electric signal input, the other end is provided with the main rotor booster output rocker arm 2063, and the main rotor booster output rocker arm 2063 is rotatably connected with the main blade pitch-variable pull rod 202;
as shown in fig. 4, the main rotor assembly 200 further includes a main blade axial mount 2066, a main blade pitch horn 2067; the main blades 201 are connected to the main rotor shaft 203 by the main blade axial mount 2066; the main blade pitch-variable tie rod 202 is connected with the main blade 201 through the main blade pitch-variable rocker 2067;
as shown in fig. 5, the tail rotor actuation device 306 includes a tail rotor booster 3061, a tail rotor booster mount 3062, a tail rotor booster electrical signal interface 3063, a tail rotor booster output rocker arm 3064, an actuation link 3065, a ball bearing 3066, an annular effector 3067; the annular acting member 3067 is sleeved in the outer wall of the tail rotor actuator 306, and the annular acting member 3067 is in rolling fit with the outer wall of the tail rotor actuator 306 through the rolling bearing 3066;
the tail rotor booster mounting joint 3062 is arranged at the gear connection position of the tail rotor shaft 303 and the tail rotor actuating device 306, the tail rotor booster 3061 is connected with the tail rotor shaft 303 through the tail rotor booster mounting joint 3062, one end of the tail rotor booster 3061 is provided with a tail rotor booster electric signal interface 3063 for electric signal input, the other end of the tail rotor booster is provided with a tail rotor booster output rocker arm 3064, the free end of the tail rotor booster output rocker arm 3064 is rotatably connected with the actuating connecting piece 3065, and the actuating connecting piece 3065 is fixedly connected to the outer side of the annular acting piece 3067; one end of the tail blade pitch-variable pull rod 302 is rotationally connected with the annular acting piece 3067, and the other end of the tail blade pitch-variable pull rod is rotationally connected with the tail blade 301;
as shown in fig. 5, the tail rotor assembly 300 further includes a tail rotor axial mount 3067, a tail rotor pitch horn 3061; the tail paddle 301 is connected to the tail rotor shaft 303 by the tail paddle axial mount 3067; the tail paddle variable-pitch pull rod 302 is connected with the tail paddle 301 through the tail paddle variable-pitch rocker arm 3061, and the tail paddle variable-pitch pull rod moves to drive the tail paddle rocker arm to enable the tail paddle to rotate around the tail paddle axis, so that tail paddle variable-pitch operation is achieved;
the control system 400 includes a main rotor control system component 401 and a tail rotor control system component 402, the main rotor control system component 401 includes a main blade control handle, a main blade link, and a main blade displacement sensor, by operating the main blade control handle, the main blade link transmits an operating displacement to the main blade displacement sensor, the main blade displacement sensor generates an electrical signal and transmits the electrical signal to the main rotor motor 204; the tail rotor manipulation system component 402 includes a tail blade manipulation pedal, a tail blade link, and a tail blade displacement sensor, by manipulating the tail blade pedal, the tail blade link transmits the operational displacement to the tail blade displacement sensor, which generates an electrical signal and sends it to the tail rotor motor 304;
an increase in the pitch angle of the tail rotor blades 301 and hence a reduction in the rotational speed of the tail rotor shaft 303 is achieved by relative movement of the annular acting element 3067 with the outer wall of the tail rotor actuation means 306;
the increase in the pitch angle of the main blades 201 can be achieved by the main rotor booster output rocker 2063, thereby achieving a reduction in the rotational speed of the main rotor shaft 303.
While the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art.
Claims (10)
1. A light helicopter driven by pure electric power is characterized by comprising a power module (100), a main rotor assembly (200), a tail rotor assembly (300) and a control system (400), wherein the power module (100) and the main rotor assembly (200) are positioned in an upper platform area of a helicopter fuselage, the tail rotor assembly (300) is positioned at the top of a vertical tail of the helicopter, the control system (400) is positioned in a front fuselage area of the helicopter, the power module (100) is respectively electrically connected with the main rotor assembly (200), the tail rotor assembly (300) and the control system (400) through cables, and the control system (400) is respectively electrically connected with the main rotor assembly (200) and the tail rotor assembly (300) through electric signal cables;
the power module (100) comprises a hydrogen fuel cell power supply for supplying power to the whole machine.
2. A light helicopter powered by purely electric power, according to claim 1, characterized by that said main rotor assembly (200) comprises main blades (201), main blade pitch links (202), main rotor shaft (203), main rotor motor (204), main rotor motor casing (205), main rotor actuator (206);
said main rotor motor (204) being centrally located in said main rotor assembly (200) for driving said main rotor actuator (206); one end of the main rotor shaft (203) is provided with a tooth, the tooth is inserted into the center of the main rotor motor (204) and is in gear fit connection with the main rotor motor (204), and the main rotor motor (204) drives the main rotor shaft (203) to rotate; the main blade (201) is connected to the other end of the main rotor shaft (203), one end of the main blade variable-pitch pull rod (202) is rotatably connected with the main blade (201), and the other end of the main blade variable-pitch pull rod is rotatably connected with the output end of the main rotor actuating device (206); the main rotor wing actuating device (206) is positioned between the main blades (201) and the main rotor wing motor (204), is sleeved on the main rotor wing shaft (203), and is in gear fit connection with the main rotor wing shaft (203); said main rotor motor (204) is housed in said main rotor motor casing (205) for protecting the motor; the main rotor motor (204) is electrically connected to the power module (100).
3. A light helicopter powered by electric only as claimed in claim 1 characterized in that said tail rotor assembly (300) comprises tail blades (301), tail blade pitch links (302), tail rotor shaft (303), tail rotor motor (304), tail rotor motor case (305), tail rotor actuator (306);
the tail rotor motor (304) is located in a central location of the tail rotor assembly (300) for driving the tail rotor actuation device (306); one end of the tail rotor shaft (303) is provided with a tooth, the tooth is inserted into the center of the tail rotor motor (304) and is in gear fit connection with the tail rotor motor (304), and the tail rotor motor (304) drives the tail rotor shaft (303) to rotate; the tail rotor blade (301) is fixedly connected to the other end of the tail rotor shaft (303), one end of the tail rotor blade variable-pitch pull rod (302) is rotatably connected with the tail rotor blade (301), and the other end of the tail rotor blade variable-pitch pull rod is rotatably connected with the tail rotor blade actuating device (306); the tail rotor wing actuating device (306) is positioned between the tail blades (301) and the tail rotor wing motor (304), is sleeved on the tail rotor wing shaft (303), and is in gear fit connection with the tail rotor wing shaft (303); the tail rotor motor (304) is accommodated in the tail rotor motor casing (305) and used for protecting the motor; the tail rotor motor (304) is electrically coupled to the power module (100).
4. A light helicopter powered by electric only as claimed in claim 2 characterized in that said main rotor actuation means (206) comprises a main rotor booster (2061), a main rotor booster electrical signal interface (2062), a main rotor booster output rocker arm (2063), a main rotor booster mounting connector (2064), a main rotor booster mount (2065);
the main rotor booster fixing piece (2065) is positioned at the center of the main rotor actuating device (206), sleeved on the main rotor shaft (203) and matched and connected with a gear of the main rotor actuating device, the main rotor boosters (2061) are uniformly distributed around the main rotor booster fixing piece (2065) and connected with the main rotor booster fixing piece (2065) through the main rotor booster mounting joint (2064), and the mounting positions and the number of the main rotor booster fixing pieces correspond to the positions and the number of the main blades (201); main rotor booster (2061) one end is equipped with main rotor booster signal of electricity interface (2062) for the input signal of electricity, the other end is equipped with main rotor booster output rocker arm (2063), main rotor booster output rocker arm (2063) with main paddle displacement pull rod (202) rotate and are connected.
5. A light helicopter powered by purely electric power, as claimed in claim 2, characterized in that said main rotor assembly (200) further comprises a main blade axial mount (2066), a main blade pitch horn (2067); the main blade (201) is connected to the main rotor shaft (203) by the main blade axial mount (2066); the main blade pitch-variable pull rod (202) is connected with the main blade (201) through the main blade pitch-variable rocker (2067).
6. A purely electrically powered lightweight helicopter according to claim 3 characterized in that said tail rotor actuation means 306 comprises tail rotor booster 3061, tail rotor booster mount 3062, tail rotor booster electrical signal interface 3063, tail rotor booster output rocker arm 3064, actuation link 3065, ball bearing 3066, annular actuator 3067; the annular acting member 3067 is sleeved in the outer wall of the tail rotor actuator 306, and the annular acting member 3067 is in rolling fit with the outer wall of the tail rotor actuator 306 through the rolling bearing 3066;
the tail rotor booster mounting joint 3062 is arranged at the gear connection position of the tail rotor shaft 303 and the tail rotor actuating device 306, the tail rotor booster 3061 is connected with the tail rotor shaft 303 through the tail rotor booster mounting joint 3062, one end of the tail rotor booster 3061 is provided with a tail rotor booster electric signal interface 3063 for electric signal input, the other end of the tail rotor booster is provided with a tail rotor booster output rocker arm 3064, the free end of the tail rotor booster output rocker arm 3064 is rotatably connected with the actuating connecting piece 3065, and the actuating connecting piece 3065 is fixedly connected to the outer side of the annular acting piece 3067; one end of the tail blade pitch-variable pull rod 302 is rotatably connected with the annular acting piece 3067, and the other end is rotatably connected with the tail blade 301.
7. A purely electrically powered lightweight helicopter according to claim 3 characterized in that said tail rotor assembly (300) further comprises a tail blade axial mount (3067), a tail blade pitch horn (3061); the tail rotor blade (301) is connected to the tail rotor shaft (303) by the tail rotor blade axial mount (3067); the tail blade pitch-variable pull rod (302) is connected with the tail blade (301) through the tail blade pitch-variable rocker arm (3061).
8. A light helicopter powered by purely electric power as claimed in claim 1, characterized in that said maneuvering system (400) comprises a main rotor maneuvering system assembly (401), a tail rotor maneuvering system assembly (402), said main rotor maneuvering system assembly (401) comprising a main blade maneuvering handle, a link, a displacement sensor, through which maneuvering handle the operating displacement is transmitted by the link to the displacement sensor, and an electric signal is generated by the displacement sensor and sent to the main rotor motor; the tail rotor control system assembly (402) comprises a tail rotor blade control pedal, a connecting rod and a displacement sensor, wherein the operating displacement is transmitted to the displacement sensor through the connecting rod by operating the pedal, and an electric signal is generated by the displacement sensor and is sent to a tail rotor motor.
9. A light helicopter powered purely by electric power, according to claim 5, characterized by the fact that the number of said tail rotor boosters (3062) can be 1 or more.
10. A light helicopter powered by purely electric power as claimed in claim 1, characterized in that said rotary connection is optionally articulated.
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| CN202011192565.6A CN112874779A (en) | 2020-10-30 | 2020-10-30 | Pure electric drive's light-duty helicopter |
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| CN202011192565.6A CN112874779A (en) | 2020-10-30 | 2020-10-30 | Pure electric drive's light-duty helicopter |
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