CN110733638B - Rotor wing reaction torque propeller-jacking helicopter - Google Patents
Rotor wing reaction torque propeller-jacking helicopter Download PDFInfo
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- CN110733638B CN110733638B CN201911055337.1A CN201911055337A CN110733638B CN 110733638 B CN110733638 B CN 110733638B CN 201911055337 A CN201911055337 A CN 201911055337A CN 110733638 B CN110733638 B CN 110733638B
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- rotor
- rotating shaft
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- top beam
- inclined section
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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
- B64C27/82—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
- B64C2027/8263—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 comprising in addition rudders, tails, fins, or the like
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- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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- Wind Motors (AREA)
Abstract
The invention belongs to the technical field of aircrafts with special rotors, and discloses a rotor wing anti-torque propeller jacking helicopter which comprises a body, a lift system, a driving system, a transmission system and airborne flight equipment, wherein the lift system comprises a rotor wing arranged at the top of the body, the lift system further comprises a propeller jacking above the rotor wing, and the propeller jacking is driven by the driving system. The invention solves the problems that the helicopter resonates and has low running stability caused by mutual interference of generated airflows when a rotor wing and a tail rotor rotate in the prior art.
Description
Technical Field
The invention belongs to the technical field of aircrafts with special rotors, and particularly relates to a rotor anti-torque propeller jacking helicopter.
Background
The helicopter mainly comprises an organism, three systems of lift force, power and transmission, airborne flight equipment and the like, wherein the lift force system mainly comprises a rotor wing and a tail rotor, the rotor wing is positioned at the top of the organism, and the tail rotor is positioned at the tail end of the organism. When the helicopter is used, power is provided through the power system, and the power is transmitted through the transmission system, so that the operation of the lift system is realized. When the rotor rotates, the helicopter is provided with a lifting force, the operation of the helicopter is realized, the reaction torque generated by the rotor can be overcome through the rotation of the tail rotor, and the stable flight of the helicopter is further realized.
But because the setting of tail boom and tail-rotor can cause the influence to the effective diameter of rotor for the rotor setting is less, and then leads to the rotor to give the lift of helicopter limited, makes the payload of helicopter low. Meanwhile, the air flow generated by the rotor and the air flow generated by the tail rotor can cause mutual interference, so that the body of the helicopter resonates with the body of the helicopter, and the running stability of the helicopter is influenced.
Disclosure of Invention
The invention aims to provide a rotor wing anti-torque jacking helicopter, which solves the problems that in the prior art, when a rotor wing and a tail rotor rotate, generated air flows interfere with each other, the helicopter resonates, and the running stability is low.
In order to achieve the purpose, the invention provides the following technical scheme that the rotor wing anti-torque propeller jacking helicopter comprises a body, a lift system, a driving system, a transmission system and an airborne flight device, wherein the lift system comprises a rotor wing arranged at the top of the body, the lift system further comprises a propeller positioned above the rotor wing, and the propeller is driven by the driving system.
The technical principle of the technical scheme is as follows:
the helicopter is driven by a power system and driven by a transmission system to rotate, the rotor and the top propeller rotate, airflow is generated by high-speed rotation of the rotor, downward huge force is applied to the atmosphere, and the reaction force of the atmosphere enables the helicopter to ascend. Meanwhile, airflow is generated through rotation of the top propeller, and the counter torque generated when the rotor wing rotates is overcome, so that stable rising of the helicopter is ensured.
The beneficial effects of the technical scheme are as follows:
1. the rotor wing and the jacking propeller are arranged at the top of the helicopter body, the rotor wing is used for providing the force for lifting the helicopter body, and the jacking propeller overcomes the reactive torque generated when the rotor wing rotates, so that the helicopter can be ensured to stably lift;
2. the rotor and the top propeller are arranged at the top of the helicopter body, and a tail beam and a tail propeller do not need to be arranged at the tail end of the helicopter body, so that the interference of air flow generated between the tail propeller and the rotor can be avoided, the resonance of the helicopter body can be avoided, and the running stability can be kept;
3. the design of tail beam and tail rotor among the prior art has been replaced in the setting that utilizes the top oar, can satisfy under the pneumatic requirement prerequisite that the wingtip linear velocity of rotor is no longer than the sound velocity, according to the nimble size, quantity, the rotational speed to the rotor of actual demand optimize the selection, the rotor that can try gives the lift improvement of helicopter, and then improves the payload of helicopter.
In the using process of the helicopter, due to the arrangement of the tail beam and the tail rotor, the diameter of the propeller is limited, so that the diameter of a rotor wing of the helicopter is limited, and the lift force of the helicopter is limited; and the air current that the tail-rotor produced and rotor produced can take place to interfere, and then leads to the organism of helicopter to take place resonance, influences the stability in use. Therefore, the top propeller is used for replacing the tail beam and the tail propeller, so that the counter torque generated by the rotor wing can be overcome, the ascending of the helicopter is realized, and the stability is kept. This setting had both overcome the problem that the air current took place to interfere, had avoided the restriction to the rotational speed, size, the quantity setting of rotor again for the lift and the stability of helicopter all obtain effectual improvement.
Further, the top of the machine body is rotatably connected with a hollow rotating shaft, and the rotor wing is fixed on the outer ring of the rotating shaft; the machine body is also fixedly provided with a hollow top beam which is positioned in the rotating shaft, and the machine body also comprises a rotating shaft which is rotatably connected with the top of the top beam, and the top paddle is fixed on the rotating shaft.
Has the advantages that: the driving system drives the rotating shaft to rotate, so that the rotation of the rotor wing is realized; the rotating shaft is hollow, so that a top beam can be conveniently arranged, and the rotating shaft is conveniently arranged because the top beam is hollow; the driving system is used for driving the rotating shaft to rotate, so that the rotation of the top paddle is realized.
Furthermore, the top beam is V-shaped, and the included angle of the top beam faces the rear end of the machine body; the back timber includes the vertical section coaxial with the axis of rotation and the slope section that sets up with the back timber slope, and the pivot rotates to be connected on the slope section.
Has the advantages that: the top beam is V-shaped, so that the top paddle can have a certain inclination angle, the impact of airflow on the top beam in high altitude is reduced, and the probability of damage of the top beam is further reduced.
Further, the inclined section is arranged in an upward inclined mode along the direction close to the tail end of the machine body.
Has the advantages that: this setting can make the distance between top oar and the rotor great, and then can reduce the mutual interference between the air current to the production.
Further, the included angle between the inclined section and the vertical section is 100-130 degrees.
Has the advantages that: the best use effect between the top paddle and the rotor wing can be ensured.
Further, the inclined section is arranged in a downward inclined mode along the direction close to the tail end of the machine body.
Has the advantages that: the influence of the air flow on the inclined section of the top beam can be reduced.
Further, the included angle between the inclined section and the vertical section is 75-90 degrees.
Has the advantages that: the mutual interference between the airflow generated by the top propeller and the airflow generated by the rotor wing can be avoided.
Furthermore, a plurality of grooves are axially formed in the outer wall of the top beam.
Has the advantages that: set up the recess, can carry out the water conservancy diversion to the air current, reduce the impact of air current to the back timber, and then reduce the impaired probability of back timber.
Further, the air conditioner also comprises a guide vane fixed on the inclined section.
Has the advantages that: the guide vanes are arranged to guide the air flow, so that the impact on the top beam is further reduced, and the probability of damage to the top beam is reduced.
Furthermore, the included angle between the guide vane and the horizontal plane is 0-5 degrees.
Has the advantages that: the air flow can be guided well, and meanwhile, the air flow cannot interfere with the air flow generated by the rotor wing and the top propeller.
Drawings
FIG. 1 is a schematic structural view of example 1 of the present invention;
FIG. 2 is a top view of FIG. 1;
FIG. 3 is a schematic structural view of a rotor and a top paddle in embodiment 1;
fig. 4 is a schematic structural view of a rotor and a top paddle in embodiment 2 of the present invention;
FIG. 5 is an enlarged view of portion A of FIG. 4;
fig. 6 is a schematic structural view of embodiment 3.
Detailed Description
The following is further detailed by way of specific embodiments:
reference numerals in the drawings of the specification include: the wind power generator comprises a generator body 1, a rotor wing 2, a top paddle 3, a rotating shaft 4, a top beam 5, a vertical section 51, a flow guide groove 511, an inclined section 52, a support rod 6, a rotating shaft 7 and a flow guide blade 8.
Example 1:
a rotor wing reaction torque top propeller helicopter is basically shown in attached figures 1 and 2 and comprises a helicopter body 1, a lift system, a driving system, a transmission system and an airborne flight device, wherein the connection relation and the movement principle of the components are the prior art and are not described in detail herein. Organism 1 is oval, and the lift system includes rotor 2 and top oar 3, and the quantity and the size of rotor 2 can be adjusted according to actual demand, and in this embodiment, the quantity of rotor 2 is 8. Referring to fig. 3, a hollow rotating shaft 4 is rotatably connected to the top of the body 1, and the rotor 2 is fixed to an outer ring of the rotating shaft 4. The axis of rotation 4 provides power through actuating system, utilize the transmission structure in the transmission system to carry out the transmission, the concrete structure of the transmission structure of this part can be the gear train, be provided with the driving gear on actuating member (for example motor) of actuating system promptly, the bottom of axis of rotation 4 is provided with the driven gear with driving gear meshing, when actuating system starts, it rotates to drive the driving gear, through the meshing of driving gear and driven gear, just can realize the rotation of axis of rotation 4, and then realize rotor 2's rotation.
A hollow top beam 5 is also fixed on the machine body 1, and the top beam 5 is positioned in the rotating shaft 4 and is coaxial with the rotating shaft 4; the outer wall of the inclined section 52 of the top beam 5 is provided with a plurality of grooves along the circumferential direction, and the grooves extend along the axial direction of the top beam 5. The back timber 5 is the V type, and back timber 5 includes with the coaxial vertical section 51 of axis of rotation 4 and with the slope section 52 of vertical section 51 slope setting, the welding has bracing piece 6 between slope section 52 and the vertical section 51 for constitute the triangle-shaped structure between slope section 52, vertical section 51 and the bracing piece 6, ensure that back timber 5's stability is good. The top end of the inclined section 52 is rotatably connected with a rotating shaft 7 perpendicular to the inclined shaft, the rotating shaft 7 penetrates through the side wall of the inclined section 52, one end of the rotating shaft 7 extends into the inclined section 52, and the top paddle 3 is fixed at one end of the rotating shaft 7, which is positioned outside the inclined section 52.
The rotating shaft 7 is driven by a driving system and is driven by a transmission part of the driving system, and the structure of the transmission part can be selected in various ways, and a belt driving structure is used in the embodiment. A driven transmission wheel is fixed on one end of the rotating shaft 7 in the inclined section 52, a driving transmission wheel is arranged on a driving piece (such as a motor) of the driving system, a transmission belt is sleeved on the driving transmission wheel and the driven transmission wheel, and the transmission belt is positioned in the hollow top beam 5. Two auxiliary shafts are rotatably connected to the transition position of the inclined section 52 and the vertical section 51 in the top beam 5, auxiliary wheels are rotatably connected to the auxiliary shafts, and two sides of the conveying belt are respectively attached to the auxiliary wheels, so that smooth transmission of the conveying belt can be realized. When the driving system drives the driving transmission wheel to rotate, the driven transmission wheel can be rotated by utilizing the transmission of the belt, so that the rotating shaft 7 is driven to rotate, and the rotation of the top paddle 3 is realized.
The inclined section 52 is arranged obliquely from left to right, the included angle between the inclined section 52 and the vertical section 51 is 100-130 degrees, and the included angle in the embodiment is 115 degrees. The lower extreme of slope section 52 is fixed with guide vane 8, and the contained angle between guide vane 8 and the horizontal plane is 0 ~5, and guide vane 8 inclines upward from left to right in this embodiment and sets up, and the contained angle between guide vane 8 and the horizontal plane is 3.
The specific implementation process is as follows:
and starting the driving system, wherein a driving part of the driving system drives the driving gear and the driving gear to rotate, and the rotation of the rotating shaft 4 and the driving transmission wheel is realized through the transmission of the driven gear and the transmission gear. The rotation axis 4 rotates and drives rotor 2 and rotate for rotor 2 produces a huge air current, and the air current gives the atmosphere a decurrent power, under atmospheric reaction, gives organism 1 lift, realizes the rising of organism 1. Meanwhile, the driven conveying wheel drives the rotating shaft 7 to rotate by utilizing the transmission of the conveying belt, and further the rotation of the top paddle 3 is realized. Because the setting of top oar direction and traditional tail-rotor is the same, when consequently top oar 3 rotates, can produce one and overcome the reaction torque when rotor 2 rotates, ensure organism 1's stability, avoid organism 1 to take place rotatoryly. And because top oar 3 is located the top of rotor 2, consequently the air current that rotor 2 produced can not rotate the air current that produces with top oar 3 and take place to interfere, and then can avoid organism 1 resonance when the operation, consequently keep the stability of organism 1 operation.
When the helicopter rises to a higher height, the airflow of the atmosphere flows fast and can impact the top beam 5, and the vertical section 51 and the inclined section 52 form a triangular structure through the arrangement of the supporting rod 6, so that the stability of the top beam 5 is maintained. Meanwhile, the grooves are formed in the top beam 5, so that air flow can be guided, and the influence of the air flow on the top beam 5 is reduced. And set up guide vane 8 through the slope, can carry out the water conservancy diversion to the air current, reduce the striking to back timber 5, reduce the impaired probability of back timber 5.
Example 2:
Since the inclined section 52 is arranged to be inclined downward in the rightward direction, when the air flow is encountered at high altitude, the air flow has less impact on the inclined section 52, and the probability of breakage of the inclined section 52 can be reduced. And the diversion trench 511 can divert the airflow to the side where the top paddle 3 is not arranged, so as to reduce the influence on the rotation of the top paddle 3.
Example 3:
It will be apparent to those skilled in the art that various changes and modifications can be made without departing from the spirit and scope of the invention, and these changes and modifications should not be construed as affecting the performance of the invention and its practical application.
Claims (5)
1. The utility model provides a rotor reaction moment top oar helicopter, includes organism, lift system, actuating system, transmission system and machine carries flight equipment, and the lift system is including setting up the rotor at the organism top, its characterized in that: the lift system also comprises a top paddle positioned above the rotor wing, and the top paddle is driven by the driving system; the top of the machine body is rotatably connected with a hollow rotating shaft, and the rotor wing is fixed on the outer ring of the rotating shaft; the machine body is also fixedly provided with a hollow top beam, the top beam is positioned in the rotating shaft, the machine body also comprises a rotating shaft which is rotatably connected with the top of the top beam, and the top paddle is fixed on the rotating shaft; a plurality of grooves are axially formed in the outer wall of the top beam; the top beam is V-shaped, and the included angle of the top beam faces the rear end of the machine body; the top beam comprises a vertical section coaxial with the rotating shaft and an inclined section obliquely arranged with the top beam, and the rotating shaft is rotatably connected to the inclined section; the guide vane is fixed on the inclined section; the included angle between the guide vane and the horizontal plane is 0-5 degrees.
2. A rotary wing anti-torque tip-rotor helicopter according to claim 1, characterized in that: the inclined section is arranged in an upward inclined mode along the direction close to the tail end of the machine body.
3. A rotary wing anti-torque tip-rotor helicopter according to claim 2, characterized in that: the included angle between the inclined section and the vertical section is 100-130 degrees.
4. A rotary wing anti-torque tip-rotor helicopter according to claim 1, characterized in that: the inclined section is arranged in a downward inclined mode along the direction close to the tail end of the machine body.
5. A rotary wing anti-torque tip-rotor helicopter according to claim 4, characterized in that: the included angle between the inclined section and the vertical section is 75-90 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911055337.1A CN110733638B (en) | 2019-10-31 | 2019-10-31 | Rotor wing reaction torque propeller-jacking helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911055337.1A CN110733638B (en) | 2019-10-31 | 2019-10-31 | Rotor wing reaction torque propeller-jacking helicopter |
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| Publication Number | Publication Date |
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| CN110733638A CN110733638A (en) | 2020-01-31 |
| CN110733638B true CN110733638B (en) | 2021-08-17 |
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| CN201911055337.1A Active CN110733638B (en) | 2019-10-31 | 2019-10-31 | Rotor wing reaction torque propeller-jacking helicopter |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20100015263A (en) * | 2008-08-04 | 2010-02-12 | 정재운 | A stability augmentation apparatus for the small model autogyro |
| CN103507947A (en) * | 2012-06-29 | 2014-01-15 | 新昌县冠阳技术开发有限公司 | Device for balancing torque for rotor craft |
| CN103507960A (en) * | 2012-06-27 | 2014-01-15 | 戴建宾 | Power paddle |
| CN105263800A (en) * | 2013-08-23 | 2016-01-20 | 国防科技研究院（公共组织） | Vertical take-off and landing unmanned aerial vehicle with twin-yaw control system |
| CN208306985U (en) * | 2018-05-08 | 2019-01-01 | 陕西天宇航空科技有限公司 | A kind of helicopter transmission mechanism |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10752343B2 (en) * | 2016-10-18 | 2020-08-25 | Sikorsky Aircraft Corporation | Electric propulsion system for a rotary wing aircraft |
-
2019
- 2019-10-31 CN CN201911055337.1A patent/CN110733638B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20100015263A (en) * | 2008-08-04 | 2010-02-12 | 정재운 | A stability augmentation apparatus for the small model autogyro |
| CN103507960A (en) * | 2012-06-27 | 2014-01-15 | 戴建宾 | Power paddle |
| CN103507947A (en) * | 2012-06-29 | 2014-01-15 | 新昌县冠阳技术开发有限公司 | Device for balancing torque for rotor craft |
| CN105263800A (en) * | 2013-08-23 | 2016-01-20 | 国防科技研究院（公共组织） | Vertical take-off and landing unmanned aerial vehicle with twin-yaw control system |
| CN208306985U (en) * | 2018-05-08 | 2019-01-01 | 陕西天宇航空科技有限公司 | A kind of helicopter transmission mechanism |
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| Publication number | Publication date |
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| CN110733638A (en) | 2020-01-31 |
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Address after: 402260 No. 116-133, beigumen street, Jiangjin District, Chongqing Patentee after: Yang Xiaosong Address before: 830001 room 1509, wanyancheng phase II, No. 222, Jiefang North Road, Tianshan District, Urumqi, Xinjiang Uygur Autonomous Region Patentee before: Yang Xiaosong |
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