CN110920874A - Three steering wheel dead axle displacement rotor modules and helicopter - Google Patents
Three steering wheel dead axle displacement rotor modules and helicopter Download PDFInfo
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- CN110920874A CN110920874A CN201911346051.9A CN201911346051A CN110920874A CN 110920874 A CN110920874 A CN 110920874A CN 201911346051 A CN201911346051 A CN 201911346051A CN 110920874 A CN110920874 A CN 110920874A
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- 238000006073 displacement reaction Methods 0.000 title claims description 6
- 239000002356 single layer Substances 0.000 claims description 23
- 239000010410 layer Substances 0.000 claims description 8
- 230000005540 biological transmission Effects 0.000 claims description 3
- 230000009977 dual effect Effects 0.000 claims 3
- 230000001360 synchronised effect Effects 0.000 abstract 1
- 238000000034 method Methods 0.000 description 6
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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
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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Abstract
The invention discloses a three-steering-engine fixed-shaft variable-pitch rotor module which comprises a central shaft, a rotary actuator, a servo mounting seat, a propeller hub, a propeller clamp, a servo rocker arm, a connecting rod, an inclined rotating disc, a rotary inclined rotating disc, a variable-pitch connecting rod, a propeller clamp connecting rod, an extending rod of the inclined rotating disc and a limiting piece of the inclined rotating disc. This scheme adopts the dead axle scheme, has reduced whole rotor system's volume to produced stability, vibration, friction scheduling problem when having avoided long and thin rotation axis motion. Effectively simplifying the connecting rod structure and the synchronous structure of the variable-pitch control system and fully retaining various variable-pitch characteristics of the helicopter rotor system. In addition, the scheme has a simple and compact structure, and can be used as a standard module for combined design to obtain various different helicopter configurations. The invention also discloses various different types of helicopter configurations adopting the three-steering-engine fixed-axis variable-pitch rotor module.
Description
Technical Field
The invention relates to the field of helicopters, in particular to a three-steering-engine fixed-axis variable-pitch rotor module and a helicopter.
Background
Existing helicopter rotor systems typically include a rotor power system, a pitch control system. Wherein, the rotor driving system comprises a rotary actuator, a connecting shaft, a rotor mechanism and the like. The distance between the rotor wing mechanism and the rotary actuator in the existing scheme is usually far, the rotor wing mechanism and the rotary actuator need to be connected through a slender connecting shaft, and the problems of stability, vibration, friction and the like can occur in the periodic rotation process. The pitch control system comprises a complex control mechanism such as a pitch control mechanism and a synchronization mechanism. The complex operating mechanism not only makes the manufacturing cost high, but also makes the assembly of the whole system assembly inconvenient. Therefore, the rotorcraft system and the variable-pitch control mechanism in the existing helicopter rotorcraft system not only have great complexity in the design, manufacture and assembly processes, but also have great reliability and safety hazards in actual flight.
Disclosure of Invention
The invention aims to overcome the problems and provides a three-steering engine fixed-axis variable-pitch rotor module and a helicopter.
In order to achieve the purpose, the method adopted by the invention is as follows: the utility model provides a three steering wheel dead axle displacement rotor modules, includes the center pin, rotary actuator, the server mount pad, the propeller hub, the oar presss from both sides, the server rocking arm, the connecting rod, the carousel that inclines, rotatory carousel that inclines, the displacement connecting rod, the oar presss from both sides the connecting rod, the dish extension bar that inclines, the dish locating part that inclines. One end of the central shaft is fixedly connected with a stator of the rotary actuator or fixedly connected with the stator through a connecting piece, and the other end of the central shaft is fixedly connected with a mounting seat of the servo device to form a basic framework of the system and a rotating shaft around which the rotor wing rotates; the propeller hub is fixedly connected with the rotor of the rotary actuator or connected with the rotor of the rotary actuator through a gear, and the propeller clamp is hinged with the propeller hub; 3 servers are arranged and are fixedly connected with the server mounting seats respectively; one end of the servo rocker arm is fixedly connected with the output shaft of the servo, and the other end of the servo rocker arm is hinged with one end of the connecting rod; the other end of the connecting rod is hinged with the tilting disc; the tilting turntable is connected with the rotary tilting turntable through a bearing, the tilting turntable is fixedly connected with an inner ring of the bearing, and the rotary tilting turntable is fixedly connected with an outer ring of the bearing; the inner ring of the tilting disc is connected with the central shaft in a sliding way through a spherical hinge; one end of the variable pitch connecting rod is hinged with the outer ring of the rotary tilting disc, and the other end of the variable pitch connecting rod is hinged with one end of the paddle clamp connecting rod; the other end of the paddle clamp connecting rod is fixedly connected with the paddle clamp.
As a preferred aspect of the present invention, a tilt disc limiting member is disposed on the server mounting base, and a sliding groove is disposed on the tilt disc limiting member; the tilting plate is provided with a tilting plate extension rod at a position where the tilting plate is hinged with the 3 connecting rods, one end of the tilting plate extension rod extends into the sliding groove, and the sliding groove can move up and down.
Preferably, the 3 servos form an included angle of 120 degrees with each other around the central axis and are fixedly mounted on the servo mounting seat.
As a preferred aspect of the present invention, the servo may be a torsion output type servo or a push and pull output type servo.
In order to achieve the above purpose, the invention adopts another method which comprises the following steps: a single rotor helicopter is provided. The helicopter comprises 1 set of rotor system, a helicopter body and a tail rotor; the rotor system is fixedly connected with the fuselage; the tail rotor is fixedly connected with the machine body; the rotor system is configured as the three-steering engine fixed-axis pitch-variable rotor module.
In order to achieve the above object, the present invention adopts another method comprising: a coaxial single layer pitch helicopter is provided. The coaxial single-layer variable-pitch helicopter comprises 2 sets of rotor systems; the 2 sets of rotor systems are connected in a coaxial mode; wherein, 1 set of the rotor wing modules is configured as the three-steering engine fixed-shaft variable-pitch rotor wing module, and the other set of the rotor wing system is a fixed-shaft non-variable-pitch rotor wing system; the fixed-shaft non-variable-pitch rotor system comprises a central shaft, a rotary actuator and a hub and propeller clamp integrated piece, wherein the central shaft is fixedly connected with a stator of the rotary actuator or fixedly connected with the stator of the rotary actuator through a connecting piece; the rotor of the rotary actuator is fixedly connected with the integrated hub and propeller clamp or is in transmission connection through a gear.
As a preferable aspect of the present invention, the coaxial single-layer pitch-variable helicopter is connected in a coaxial manner by any one of the following 8 types: 1. two rotary actuators are arranged in the middle, and a three-steering engine fixed-shaft variable-pitch rotor module is arranged below; 2. two rotary actuators are arranged in the middle, and a three-steering engine fixed-shaft variable-pitch rotor module is arranged on the upper part; 3. the upper end and the lower end of the two rotary actuators are arranged, and the three-steering engine fixed-shaft variable-pitch rotor module is arranged below; 4. the upper end and the lower end of the two rotary actuators are arranged, and the three-steering engine fixed-shaft variable-pitch rotor module is arranged on the upper part; 5. the three-steering engine fixed-shaft variable-pitch rotor module is arranged above, a rotary actuator of the three-steering engine fixed-shaft variable-pitch rotor module is arranged above, the fixed-shaft non-variable-pitch rotor system is arranged below, and the fixed-shaft non-variable-pitch rotor system is arranged above the rotary actuator of the fixed-shaft non-variable-pitch rotor system; 6. the three-steering engine fixed-shaft variable-pitch rotor module is arranged below, a rotary actuator of the three-steering engine fixed-shaft variable-pitch rotor module is arranged below, the fixed-shaft non-variable-pitch rotor system is arranged above, and the fixed-shaft non-variable-pitch rotor system is arranged below the rotary actuator of the fixed-shaft non-variable-pitch rotor system; 7. the three-steering engine fixed-shaft variable-pitch rotor module is arranged above, a rotary actuator of the three-steering engine fixed-shaft variable-pitch rotor module is arranged below, the fixed-shaft non-variable-pitch rotor system is arranged below, and the fixed-shaft non-variable-pitch rotor system is arranged below the rotary actuator of the fixed-shaft non-variable-pitch rotor system; 8. the three-steering engine fixed-shaft variable-pitch rotor module is arranged below, the rotary actuator of the three-steering engine fixed-shaft variable-pitch rotor module is arranged above, and the fixed-shaft non-variable-pitch rotor system is arranged above and the rotary actuator of the fixed-shaft non-variable-pitch rotor system is arranged above.
In order to achieve the above purpose, the invention adopts another method which comprises the following steps: a coaxial double-deck pitch helicopter is provided. The coaxial double-layer variable-pitch helicopter is provided with 2 sets of three-steering engine fixed-axis variable-pitch rotor modules; the 2 sets of three steering engine fixed-axis variable-pitch rotor modules are connected in a coaxial mode.
As a preferable aspect of the present invention, the coaxial double-deck pitch helicopter is connected in a coaxial manner by any one of the following 4 types: 1. two rotary actuators are arranged in the middle; 2. the upper end and the lower end of the two rotary actuators are arranged; 3. the rotary actuator of the upper three-steering engine fixed-shaft variable-pitch rotor module is arranged below, and the rotary actuator of the lower three-steering engine fixed-shaft variable-pitch rotor module is arranged below; 4. the rotary actuator of the upper three-steering engine fixed-shaft variable-pitch rotor module is arranged at the upper part, and the rotary actuator of the lower three-steering engine fixed-shaft variable-pitch rotor module is arranged at the upper part.
Preferably, the rotary actuator in the three-steering-engine fixed-axis variable-pitch rotor module, the single-rotor helicopter, the coaxial single-layer variable-pitch helicopter or the coaxial double-layer variable-pitch helicopter can be any one of a direct-drive or deceleration actuator, an electric or oil-driven actuator and a double-power or single-power actuator.
In a preferred embodiment of the present invention, in the coaxial single-layer pitch helicopter and the coaxial double-layer pitch helicopter, the central axis may be two independent axes or may be an integrated axis in a set of coaxial models.
Has the advantages that:
compared with the prior art, the technical scheme of the invention adopts the operating mechanism with simpler structure, integrates the pitch-changing mechanism and the synchronizing mechanism in the pitch-changing operating system into a whole, and greatly simplifies the structure of the pitch-changing operating system. Meanwhile, the dead axle scheme is adopted, the volume of the whole rotor system is reduced, and the problems of stability, vibration, friction and the like generated when the slender rotating shaft moves are avoided. The technical scheme of the invention has simple and compact structure, and can be used as a standardized module for combined design to obtain various helicopter configurations.
Drawings
FIG. 1 is a schematic rear side view of a three-steering engine fixed-axis variable-pitch rotor module structure;
FIG. 2 is a schematic front side view of a three-steering engine fixed-axis variable-pitch rotor module structure;
FIG. 3 is a schematic structural view of a first configuration of a coaxial single-layer pitch helicopter;
FIG. 4 is a structural schematic view of a second configuration of a coaxial single-layer pitch-variable helicopter;
FIG. 5 is a schematic structural view of a third configuration of a coaxial single-layer pitch-variable helicopter;
FIG. 6 is a schematic structural view of a fourth configuration of a coaxial single-layer pitch helicopter;
FIG. 7 is a schematic structural view of a fifth configuration of a coaxial single-layer pitch-variable helicopter;
FIG. 8 is a structural schematic view of a sixth configuration of a coaxial single-layer pitch helicopter;
FIG. 9 is a schematic structural view of a seventh configuration of a coaxial single-layer pitch-variable helicopter;
FIG. 10 is a structural schematic view of an eighth configuration of a coaxial single-layer pitch helicopter; FIG. 11 is a schematic structural view of a first configuration of a coaxial double-deck pitch helicopter;
FIG. 12 is a structural schematic view of a second configuration of a coaxial double-deck pitch helicopter;
FIG. 13 is a schematic structural view of a third configuration of a coaxial double-deck pitch helicopter;
FIG. 14 is a schematic structural view of a fourth configuration of a coaxial double-deck pitch helicopter;
shown in fig. 1 to 3, 1, center shaft, 2, rotary actuator, 3, servo mount, 4, hub, 5, paddle clamp, 6, servo, 7, servo rocker, 8, connecting rod, 9, tilting disk, 10, rotary tilting disk, 11, pitch link, 12, paddle clamp link, 13, tilting disk extension rod, 14, tilting disk limit piece, 15, hub and paddle clamp integrated piece.
Detailed Description
The present invention will be further illustrated with reference to the accompanying drawings and specific examples, which are carried out on the premise of the technical solution of the present invention, and it should be understood that these examples are only for illustrating the present invention and are not intended to limit the scope of the present invention.
Example 1:
as shown in fig. 1 and fig. 2, a three-steering engine fixed-axis variable-pitch rotor module disclosed in this embodiment includes a central shaft 1, a rotary actuator 2, a server mounting base 3, a hub 4, a paddle clamp 5, a server 6, a server rocker arm 7, a connecting rod 8, a tilting disk 9, a rotary tilting disk 10, a variable-pitch connecting rod 11, a paddle clamp connecting rod 12, a tilting disk extension rod 13, a tilting disk limiting part 14, and is characterized in that: one end of the central shaft 1 is fixedly connected with a stator of the rotary actuator 2 or fixedly connected through a connecting piece, and the other end of the central shaft is fixedly connected with the servo mounting seat 3 to form a basic framework of the system and a rotating shaft around which the rotor wing rotates; the propeller hub 4 is fixedly connected with a rotor of the rotary actuator 2 or is connected with the rotor through a gear, and 2 propeller clamps 5 are respectively hinged with two ends of the propeller hub 4; 3 servers 6 are arranged and are fixedly connected with the server mounting base 3 respectively; one end of the servo rocker arm 7 is fixedly connected with an output shaft of the servo 6, and the other end of the servo rocker arm is hinged with one end of the connecting rod 8; the other end of the connecting rod 8 is hinged with the tilting disc 9; the tilting disc 9 is connected with the rotating tilting disc 10 through a bearing, the tilting disc 9 is fixedly connected with an inner ring of the bearing, and the rotating tilting disc 10 is fixedly connected with an outer ring of the bearing; the inner ring of the tilting disc 9 is connected with the central shaft 1 in a sliding way through a spherical hinge; one end of the pitch-variable connecting rod 11 is hinged with the outer ring of the rotating inclined rotary table 10, and the other end of the pitch-variable connecting rod is hinged with one end of the paddle clamp connecting rod 12; the other end of the paddle clamp connecting rod 12 is fixedly connected with the paddle clamp 5;
as shown in fig. 1, the servo mounting base 3 is provided with a tilting disk limiting piece 14, and the tilting disk limiting piece 14 is provided with a sliding groove; tilting plate 9 on with 3 connecting rods 8 articulated department be provided with tilting plate extension bar 13, tilting plate extension bar 13 one end with stretch into the spout, can follow the spout up-and-down motion.
As shown in fig. 1, the 3 servos 6 are fixedly mounted on the servo mounting base 3 with an included angle of 120 degrees formed by two servos around the central axis 1.
As shown in fig. 1, the servo 6 may be a torsion output type servo or a push and pull output type servo.
Example 2:
the embodiment discloses a single-rotor helicopter. The helicopter comprises 1 set of rotor system, a helicopter body and a tail rotor; the rotor system is fixedly connected with the fuselage; the tail rotor is fixedly connected with the machine body; the rotor system is configured as the three-steering engine fixed-axis pitch-variable rotor module.
Example 3:
this embodiment discloses a coaxial single layer pitch helicopter, one configuration of which is shown in figures 3 to 10, respectively. The coaxial single-layer variable-pitch helicopter comprises 2 sets of rotor systems; the 2 sets of rotor systems are connected in a coaxial mode; wherein, 1 set of the rotor wing modules is configured as the three-steering engine fixed-shaft variable-pitch rotor wing module, and the other set of the rotor wing system is a fixed-shaft non-variable-pitch rotor wing system; the fixed-shaft non-variable-pitch rotor system comprises a central shaft 1, a rotary actuator 2 and a hub and propeller clamp integrated piece 15, wherein the central shaft 1 is fixedly connected with a stator of the rotary actuator 2 or fixedly connected with the stator through a connecting piece; the rotor of the rotary actuator 2 is fixedly connected with the hub and paddle clamp integrated part 15 or is in transmission connection through a gear.
The coaxial single-layer pitch-variable helicopter disclosed by the embodiment is connected in a coaxial mode in any one of the following 8 modes: 1. as shown in fig. 3, two rotary actuators 2 are arranged in the middle, and a three-steering engine fixed-axis variable-pitch rotor module is arranged in the lower part; 2. as shown in fig. 4, two rotary actuators 2 are arranged in the middle, and a three-steering engine fixed-axis variable-pitch rotor module is arranged on the upper part; 3. as shown in fig. 5, two rotary actuators 2 are arranged at the upper end and the lower end, and a three-steering engine fixed-axis variable-pitch rotor module is arranged at the lower end; 4. as shown in fig. 6, two rotary actuators 2 are arranged at the upper end and the lower end, and a three-steering engine fixed-axis variable-pitch rotor module is arranged at the upper end; 5. as shown in fig. 7, a three-steering engine fixed-axis variable-pitch rotor module is arranged on the upper portion, a rotary actuator 2 of the three-steering engine fixed-axis variable-pitch rotor module is arranged on the upper portion, a fixed-axis non-variable-pitch rotor system is arranged on the lower portion, and a fixed-axis non-variable-pitch rotor system is arranged on the upper portion, the rotary actuator 2 of the fixed-axis non-variable-pitch rotor system is; 6. as shown in fig. 8, a three-steering engine fixed-axis variable-pitch rotor module is arranged below and a rotary actuator 2 of the three-steering engine fixed-axis variable-pitch rotor module is arranged below, a fixed-axis non-variable-pitch rotor system is arranged above and a fixed-axis non-variable-pitch rotor system is arranged below the rotary actuator 2; 7. as shown in fig. 9, a three-steering engine fixed-axis variable-pitch rotor module is arranged on the upper portion, a rotary actuator 2 of the three-steering engine fixed-axis variable-pitch rotor module is arranged on the lower portion, a fixed-axis non-variable-pitch rotor system is arranged on the lower portion, and the rotary actuator 2 of the fixed-axis non-variable-pitch rotor system is arranged on the lower portion; 8. as shown in fig. 10, the three-steering engine fixed-axis variable-pitch rotor module is arranged below and the rotary actuator 2 of the three-steering engine fixed-axis variable-pitch rotor module is arranged above, and the fixed-axis non-variable-pitch rotor system is arranged above and the rotary actuator 2 of the fixed-axis non-variable-pitch rotor system is arranged above.
Example 4:
the present embodiment discloses a coaxial double-deck pitch helicopter, one configuration of which is shown in fig. 11 to 14, respectively. The coaxial double-layer variable-pitch helicopter is provided with 2 sets of three-steering engine fixed-axis variable-pitch rotor modules; the 2 sets of three steering engine fixed-axis variable-pitch rotor modules are connected in a coaxial mode.
The coaxial double-layer pitch-variable helicopter disclosed by the embodiment is connected in a coaxial mode in any one of the following 4 modes: 1. as shown in fig. 11, two rotary actuators 2 are centrally disposed; 2. as shown in fig. 12, the two rotary actuators 2 are disposed at the upper and lower ends; 3. as shown in fig. 13, the rotary actuator 2 of the upper three-steering engine fixed-axis variable-pitch rotor module is arranged at the lower part, and the rotary actuator 2 of the lower three-steering engine fixed-axis variable-pitch rotor module is arranged at the lower part; 4. as shown in fig. 14, the rotary actuator 2 of the upper three-steering engine fixed-axis variable-pitch rotor module is arranged on the upper portion, and the rotary actuator 2 of the lower three-steering engine fixed-axis variable-pitch rotor module is arranged on the upper portion.
The invention discloses a three-steering-engine fixed-axis variable-pitch rotor module, a single-rotor helicopter, a coaxial single-layer variable-pitch helicopter or a coaxial double-layer variable-pitch helicopter in embodiments 1 to 4, wherein the rotary actuator 2 can be any one of a direct-drive or deceleration actuator, an electric or oil-driven actuator and a double-power or single-power actuator.
In the coaxial single-layer pitch-variable helicopter and the coaxial double-layer pitch-variable helicopter disclosed in embodiments 3 to 4 of the present invention, in a set of coaxial models, the central shaft 1 may be two independent shafts or may be an integrated shaft.
The technical means disclosed by the scheme of the invention are not limited to the technical means disclosed by the technical means, and the technical scheme also comprises the technical scheme formed by any combination of the technical characteristics. While the foregoing is directed to embodiments of the present invention, it will be appreciated by those skilled in the art that various changes may be made in the embodiments without departing from the principles of the invention, and that such changes and modifications are intended to be included within the scope of the invention.
Claims (15)
1. The utility model provides a three steering wheel dead axle displacement rotor modules, includes the center pin, rotary actuator, the server mount pad, the propeller hub, the oar presss from both sides, the server, its characterized in that: the device also comprises a servo rocker arm, a connecting rod, an inclined rotary table, a rotary inclined rotary table, a variable pitch connecting rod, a paddle clamp connecting rod, an extension rod of the inclined rotary table and a limiting part of the inclined rotary table; one end of the central shaft is fixedly connected with a stator of the rotary actuator or fixedly connected with the stator through a connecting piece, and the other end of the central shaft is fixedly connected with a mounting seat of the servo device to form a basic framework of the system and a rotating shaft around which the rotor wing rotates; the propeller hub is fixedly connected with the rotor of the rotary actuator or connected with the rotor of the rotary actuator through a gear, and the propeller clamp is hinged with the propeller hub; 3 servers are arranged and are fixedly connected with the server mounting seats respectively; one end of the servo rocker arm is fixedly connected with the output shaft of the servo, and the other end of the servo rocker arm is hinged with one end of the connecting rod; the other end of the connecting rod is hinged with the tilting disc; the tilting turntable is connected with the rotary tilting turntable through a bearing, the tilting turntable is fixedly connected with an inner ring of the bearing, and the rotary tilting turntable is fixedly connected with an outer ring of the bearing; the inner ring of the tilting disc is connected with the central shaft in a sliding way through a spherical hinge; one end of the variable pitch connecting rod is hinged with the outer ring of the rotary tilting disc, and the other end of the variable pitch connecting rod is hinged with one end of the paddle clamp connecting rod; the other end of the paddle clamp connecting rod is fixedly connected with the paddle clamp.
2. The three-steering engine fixed-axis variable-pitch rotor module according to claim 1, wherein a tilting disc limiting part is arranged on the servo mounting seat, and a sliding groove is formed in the tilting disc limiting part; the tilting plate is provided with a tilting plate extension rod at a position where the tilting plate is hinged with the 3 connecting rods, one end of the tilting plate extension rod extends into the sliding groove, and the sliding groove can move up and down.
3. The three-steering engine fixed-axis variable-pitch rotor module according to claim 1, wherein the 3 servos form 120-degree included angles in pairs around a central axis and are fixedly mounted on a servo mounting seat.
4. The three-steering engine fixed-axis variable-pitch rotor module according to claim 1, characterized in that: the servo is a torsion output type servo or a push force and pull force output type servo.
5. The three-steering engine fixed-axis variable-pitch rotor module according to claim 1, wherein the rotary actuator is any one of a direct-drive or deceleration actuator, an electric or oil-driven actuator, and a double-power or single-power actuator.
6. A single-rotor helicopter characterized by: the helicopter comprises 1 set of rotor system, a helicopter body and a tail rotor; the rotor system is fixedly connected with the fuselage; the tail rotor is fixedly connected with the machine body; the rotor system is configured as a three-steering engine fixed-axis pitch-variable rotor module according to claim 1.
7. A single-rotor helicopter as claimed in claim 6 wherein said rotary actuator is any one of a direct drive or deceleration actuator, an electric or oil drive actuator, and a dual or single power actuator.
8. A coaxial single-layer pitch-variable helicopter is characterized in that: the coaxial single-layer variable-pitch helicopter comprises 2 sets of rotor systems; the 2 sets of rotor systems are connected in a coaxial mode; wherein 1 set is configured as a three-steering engine fixed-axis variable-pitch rotor module according to claim 1, and the other set of rotor system is a fixed-axis non-variable-pitch rotor system; the fixed-shaft non-variable-pitch rotor system comprises a central shaft, a rotary actuator and a hub and propeller clamp integrated piece, wherein the central shaft is fixedly connected with a stator of the rotary actuator or fixedly connected with the stator of the rotary actuator through a connecting piece; the rotor of the rotary actuator is fixedly connected with the integrated hub and propeller clamp or is in transmission connection through a gear.
9. A coaxial single layer pitch helicopter according to claim 8 wherein said rotary actuator is any one of a direct drive or deceleration actuator, an electric or oil drive actuator, a dual power or single power actuator.
10. A coaxial single layer pitch helicopter according to claim 8 further characterized in that it is connected in a coaxial manner in any one of the following 8: 1. two rotary actuators are arranged in the middle, and a three-steering engine fixed-shaft variable-pitch rotor module is arranged below; 2. two rotary actuators are arranged in the middle, and a three-steering engine fixed-shaft variable-pitch rotor module is arranged on the upper part; 3. the upper end and the lower end of the two rotary actuators are arranged, and the three-steering engine fixed-shaft variable-pitch rotor module is arranged below; 4. the upper end and the lower end of the two rotary actuators are arranged, and the three-steering engine fixed-shaft variable-pitch rotor module is arranged on the upper part; 5. the three-steering engine fixed-shaft variable-pitch rotor module is arranged above, a rotary actuator of the three-steering engine fixed-shaft variable-pitch rotor module is arranged above, the fixed-shaft non-variable-pitch rotor system is arranged below, and the fixed-shaft non-variable-pitch rotor system is arranged above the rotary actuator of the fixed-shaft non-variable-pitch rotor system; 6. the three-steering engine fixed-shaft variable-pitch rotor module is arranged below, a rotary actuator of the three-steering engine fixed-shaft variable-pitch rotor module is arranged below, the fixed-shaft non-variable-pitch rotor system is arranged above, and the fixed-shaft non-variable-pitch rotor system is arranged below the rotary actuator of the fixed-shaft non-variable-pitch rotor system; 7. the three-steering engine fixed-shaft variable-pitch rotor module is arranged above, a rotary actuator of the three-steering engine fixed-shaft variable-pitch rotor module is arranged below, the fixed-shaft non-variable-pitch rotor system is arranged below, and the fixed-shaft non-variable-pitch rotor system is arranged below the rotary actuator of the fixed-shaft non-variable-pitch rotor system; 8. the three-steering engine fixed-shaft variable-pitch rotor module is arranged below, the rotary actuator of the three-steering engine fixed-shaft variable-pitch rotor module is arranged above, and the fixed-shaft non-variable-pitch rotor system is arranged above and the rotary actuator of the fixed-shaft non-variable-pitch rotor system is arranged above.
11. Coaxial single-layer pitch helicopter according to claim 8 or 10, characterized in that said central axis is two independent axes or one integrated axis in a set of coaxial models.
12. A coaxial double-deck displacement helicopter which is characterized in that: the coaxial double-layer pitch-variable helicopter is provided with 2 sets of three-steering engine fixed-axis pitch-variable rotor modules according to claim 1; the 2 sets of three steering engine fixed-axis variable-pitch rotor modules are connected in a coaxial mode.
13. A coaxial double-deck pitch helicopter according to claim 12, characterized in that it is connected in a coaxial manner in any one of the following 4: 1. two rotary actuators are arranged in the middle; 2. the upper end and the lower end of the two rotary actuators are arranged; 3. the rotary actuator of the upper three-steering engine fixed-shaft variable-pitch rotor module is arranged below, and the rotary actuator of the lower three-steering engine fixed-shaft variable-pitch rotor module is arranged below; 4. the rotary actuator of the upper three-steering engine fixed-shaft variable-pitch rotor module is arranged at the upper part, and the rotary actuator of the lower three-steering engine fixed-shaft variable-pitch rotor module is arranged at the upper part.
14. A coaxial double-deck pitch helicopter according to claim 12 or 13, characterized in that said central shaft is two independent shafts or one integrated shaft in a set of coaxial models.
15. A coaxial double pitch helicopter according to claim 12 wherein said rotary actuator is any one of a direct drive or deceleration actuator, an electric or oil drive actuator, a dual power or single power actuator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911346051.9A CN110920874A (en) | 2019-12-24 | 2019-12-24 | Three steering wheel dead axle displacement rotor modules and helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911346051.9A CN110920874A (en) | 2019-12-24 | 2019-12-24 | Three steering wheel dead axle displacement rotor modules and helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110920874A true CN110920874A (en) | 2020-03-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911346051.9A Pending CN110920874A (en) | 2019-12-24 | 2019-12-24 | Three steering wheel dead axle displacement rotor modules and helicopter |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113815853A (en) * | 2021-10-29 | 2021-12-21 | 湖南韬讯航空科技有限公司 | Rotor wing propulsion device and control method |
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| CN108275264A (en) * | 2018-03-05 | 2018-07-13 | 南京韬讯航空科技有限公司 | A kind of foldable coaxial dual-rotor helicopter and its control method |
| CN109552614A (en) * | 2018-12-26 | 2019-04-02 | 中汉天际(北京)航天技术有限公司 | Portable aircraft |
| CN211731804U (en) * | 2019-12-24 | 2020-10-23 | 湖南韬讯航空科技有限公司 | Three steering wheel dead axle displacement rotor modules and helicopter |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108275264A (en) * | 2018-03-05 | 2018-07-13 | 南京韬讯航空科技有限公司 | A kind of foldable coaxial dual-rotor helicopter and its control method |
| CN109552614A (en) * | 2018-12-26 | 2019-04-02 | 中汉天际(北京)航天技术有限公司 | Portable aircraft |
| CN211731804U (en) * | 2019-12-24 | 2020-10-23 | 湖南韬讯航空科技有限公司 | Three steering wheel dead axle displacement rotor modules and helicopter |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113815853A (en) * | 2021-10-29 | 2021-12-21 | 湖南韬讯航空科技有限公司 | Rotor wing propulsion device and control method |
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