CN110733638A

CN110733638A - rotor counter-torque propeller-jacking helicopter

Info

Publication number: CN110733638A
Application number: CN201911055337.1A
Authority: CN
Inventors: 杨小松
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-10-31
Filing date: 2019-10-31
Publication date: 2020-01-31
Anticipated expiration: 2039-10-31
Also published as: CN110733638B

Abstract

The invention belongs to the technical field of aircrafts with special rotors, and discloses an rotor wing anti-torque top propeller helicopter which 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 also comprises a top propeller positioned above the rotor wing, and the top propeller is driven by the driving system.

Description

rotor counter-torque propeller-jacking helicopter

Technical Field

The invention belongs to the technical field of aircrafts with special rotors, and particularly relates to an 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 rotor anti-torque top-propeller helicopters to solve the problems that when a rotor and a tail rotor rotate, generated airflows interfere with each other, the helicopters resonate, and the running stability is low in the prior art.

In order to achieve the purpose, the invention provides the following technical scheme that the rotor wing anti-torque top-paddle 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 top paddle positioned above the rotor wing, and the top paddle 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.

, a hollow rotating shaft is rotatably connected to the top of the machine body, the rotor wing is fixed to the outer ring of the rotating shaft, a hollow top beam is further fixed to the machine body and located in the rotating shaft, the top beam further comprises a rotating shaft rotatably connected to the top of the top beam, and the top paddle is fixed to 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.

And , the top beam is V-shaped, 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 inclined with the top beam, and the rotating shaft is rotatably connected to the inclined section.

The V-shaped top beam has the beneficial effects that the top propeller can have an inclination angle of , the impact of airflow on the top beam in high altitude is reduced, and the probability of damage to the top beam is further reduced.

And , the inclined section is inclined upwards in 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.

And , wherein 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.

And , the inclined section is inclined downwards in 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.

And , wherein 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.

, a plurality of grooves are axially formed on 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.

, it also includes guide vanes fixed on the inclined section.

The air guide device has the beneficial effects that the guide vanes are arranged to guide the air flow, steps are further carried out to reduce the impact on the top beam, and the probability of damage to the top beam is reduced.

, 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

Further details are provided below 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 helicopter with rotor wing and counter-torque propeller pushing device, substantially as shown in fig. 1 and fig. 2, comprising a body 1, a lift system, a driving system, a transmission system and an airborne flying device, wherein the connection relationship and the movement principle between the above components are prior art, and are not described herein, the body 1 is oval, the lift system comprises rotor wings 2 and propeller pushing devices 3, the number and size of the rotor wings 2 can be adjusted according to actual requirements, in this embodiment, the number of the rotor wings 2 is 8, in combination with fig. 3, the top of the body 1 is rotatably connected with a hollow rotating shaft 4, the rotor wings 2 are fixed on an outer ring of the rotating shaft 4, the rotating shaft 4 provides power through the driving system, and the transmission structure in the transmission system is used for transmission, the specific structure of the transmission structure of the part can be a gear set, that is a driving gear is arranged on a driving part (e.g. a motor) of the driving system, a driven gear meshed with the driving gear is arranged at the bottom of the rotating shaft 4, when the driving system is started, the driving gear is driven to rotate the.

The machine body 1 is further fixed with a hollow top beam 5, the top beam 5 is located in the rotating shaft 4 and is arranged coaxially with the rotating shaft 4, a plurality of grooves are formed in the circumferential direction of the outer wall of an inclined section 52 of the top beam 5 and extend in the axial direction of the top beam 5, the top beam 5 is V-shaped, the top beam 5 comprises a vertical section 51 coaxial with the rotating shaft 4 and an inclined section 52 obliquely arranged with the vertical section 51, a supporting rod 6 is welded between the inclined section 52 and the vertical section 51, a triangular structure is formed among the inclined section 52, the vertical section 51 and the supporting rod 6, good stability of the top beam 5 is guaranteed, a rotating shaft 7 perpendicular to the inclined shaft is rotatably connected to the top end of the inclined section 52, the rotating shaft 7 penetrates through the side wall of the inclined section 52, the end of the rotating shaft 7 extends into the inclined section 52, and the top propeller 3 is fixed to the 35.

The rotating shaft 7 is driven by a driving system, and a transmission part of the transmission system is used for transmission, the structure of the transmission part can be selected in various ways, in the embodiment, a belt transmission structure is used, ends of the rotating shaft 7, which are positioned in the inclined section 52, are fixedly provided with driven transmission wheels, driving transmission wheels (such as motors) of the driving system are provided with driving transmission wheels, transmission belts are sleeved on the driving transmission wheels and the driven transmission wheels, the transmission belts are positioned in the hollow top beam 5, transition positions of the inclined section 52 and the vertical section 51 in the top beam 5 are rotatably connected with two auxiliary shafts, the auxiliary shafts are rotatably connected with auxiliary wheels, two sides of the transmission belts are respectively attached to the auxiliary wheels, and smooth transmission of the transmission belts can be 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:

the driving system is started, a driving piece of the driving system drives a driving gear and a driving gear to rotate, rotation of a rotating shaft 4 and a driving wheel is achieved through transmission of a driven gear and a transmission gear, the rotating shaft 4 rotates to drive a rotor 2 to rotate, the rotor 2 generates huge air flows, the air flows provide downward forces to the atmosphere, and under the reaction of the atmosphere, lift forces are provided for an engine body 1 to achieve ascending of the engine body 1.

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:

embodiment 2 is different from embodiment 1 only in that, as shown in fig. 4, the inclined section 52 is arranged to be inclined downward from left to right, the included angle between the inclined section 52 and the vertical section 51 is 75 ° to 90 °, and the included angle between the inclined section 52 and the vertical section 51 is 80 ° in this embodiment, as shown in fig. 5, in this embodiment, no groove is provided on the inclined section 52, the flow guide groove 511 is provided on the vertical section 51, the starting end of the flow guide groove 511 is located at the lower part of the vertical section 51, the terminal end of the flow guide groove 511 is located at the upper part, and the terminal end of the flow guide groove 511 faces to the side where the top paddle 3 is not provided.

Because the inclined section 52 is arranged in a downward inclination along the right direction, when encountering the air flow at high altitude, the air flow has less impact on the inclined section 52, the probability of breaking the inclined section 52 can be reduced, and the guide groove 511 can guide the air flow to the side without the top paddle 3, so that the influence on the rotation of the top paddle 3 can be reduced.

Example 3:

embodiment 3 differs from embodiment 1 only in that the body is vertically disposed in an elliptical shape as shown in fig. 6. Set up the organism into ellipse circular, compare with traditional organism shape, the outside is more smooth, after rising to the high altitude, can utilize the shape of organism to carry out the water conservancy diversion to the air current, reduces the resistance that the organism received, and then more does benefit to the flight of helicopter.

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

The rotor wing anti-torque top-paddle helicopter comprises a helicopter 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 helicopter body, and the helicopter is characterized in that the lift system further comprises a top paddle located above the rotor wing, and the top paddle is driven by the driving system.
2. The rotor wing anti-torque top paddle helicopter of claim 1, wherein the top of the helicopter body is rotatably connected with a hollow rotating shaft, the rotor wing is fixed on the outer ring of the rotating shaft, a hollow top beam is further fixed on the helicopter body, the top beam is positioned in the rotating shaft, the helicopter further comprises a rotating shaft rotatably connected with the top of the top beam, and the top paddle is fixed on the rotating shaft.
3. The rotor wing anti-torque top paddle helicopter of claim 2, wherein the top beam is V-shaped with an included angle towards the rear end of the helicopter body, the top beam comprises a vertical section coaxial with the rotating shaft and an inclined section inclined with the top beam, and the rotating shaft is rotatably connected to the inclined section.
4. The type of rotor wing anti-torque top paddle helicopter of claim 3, wherein the inclined section is inclined upward in a direction near the aft end of the helicopter body.
5. The rotor anti-torque top paddle helicopter of claim 4, wherein the included angle between the inclined section and the vertical section is 100-130 °.
6. The type of rotor wing anti-torque top paddle helicopter of claim 3, wherein the inclined section is arranged to be inclined downwards in a direction approaching the tail end of the helicopter body.
7. The type of rotor wing anti-torque top paddle helicopter of claim 6, wherein the included angle between the inclined section and the vertical section is 75-90 °.
8. The rotary-wing anti-torque prop-rotor helicopter of any of claims 1-7- , wherein the outer wall of the top beam is provided with a plurality of grooves along the axial direction.
9. The rotor anti-torque tip-rotor helicopter of claim 4 or claim 5, further comprising guide vanes affixed to the angled sections.
10. The type of rotor wing anti-torque top paddle helicopter of claim 9, wherein the angle between the guide vanes and the horizontal plane is 0-5 °.