CN111776212A

CN111776212A - Tail rotor structure and helicopter

Info

Publication number: CN111776212A
Application number: CN202010758514.9A
Authority: CN
Inventors: 王礼号; 王坤; 薛雄飞; 李鑫; 赵曙光
Original assignee: Tianjin Shuguang Tiancheng Technology Co ltd
Current assignee: Tianjin Phoenix Intelligent Technology Co ltd
Priority date: 2020-07-31
Filing date: 2020-07-31
Publication date: 2020-10-16

Abstract

The invention relates to the technical field of helicopters, in particular to a tail rotor structure and a helicopter, wherein the tail rotor structure comprises a vertical tail wing, a plurality of ducts are arranged on the vertical tail wing, a first power assembly and a second power assembly are arranged in each duct, the first power assembly comprises a first blade and a first driving piece for driving the first blade to rotate, the second power assembly comprises a second blade and a second driving piece for driving the second blade to rotate, the first blade and the second blade are coaxially arranged, the steering directions of the first blade and the second blade are opposite, and the acting forces generated by the first blade and the second blade are the same. According to the invention, the plurality of ducts are arranged, the two groups of power assemblies are arranged in each duct, and the directions of the pulling forces generated by the blades in the two groups of power assemblies are the same, so that the power of the tail rotor structure can be greatly improved, the reaction torque of a high-power engine can be matched, and the carrying capacity of the unmanned aerial vehicle is improved.

Description

Tail rotor structure and helicopter

Technical Field

The invention relates to the technical field of helicopters, in particular to a tail rotor structure and a helicopter.

Background

When the helicopter flies, the main rotor rotates to generate lift force, the reaction torque force of the main rotor can enable the helicopter to rotate in the direction opposite to the rotation direction of the main rotor, and the pulling force generated by the tail rotor can offset the rotation to realize stable course.

Conventional tail rotors typically consist of a tail blade, a tail rotor hub, and a pitch mechanism. The tail rotor blade is connected to the tail rotor hub and is a rotary wing surface for generating aerodynamic force; the tail rotor hub is an intermediate part for connecting the tail rotor blades with a tail transmission system and a tail control system; the tail rotor pitch-changing mechanism mainly comprises a sliding cylinder, a three-fork driving lever, a pitch-changing pull rod and the like, and is used for changing the pitch angle of the tail rotor so as to change the size and the direction of the pull force of the tail rotor.

Ducted tail rotor is an advanced form of tail rotor envisaged by the french aerospace company. Since 1968, the application of the helicopter in the form of "little antelope" has been greatly developed, and various helicopters adopt the form of the tail rotor. The duct tail rotor is a cylindrical duct made in a vertical tail, a tail blade and a tail rotor hub are arranged in the duct, and additional aerodynamic force is generated by the duct. The tail blade and the tail rotor hub of the tail rotor are directly arranged in a vertical stabilizer without moving out, and the development of the ducted tail rotor design obviously has an advantageous position in various helicopters with the tonnage of less than 6 tons compared with the common tail rotor. The performance offered by ducted tailrotors is very competitive with respect to weight and price compared to conventional tailrotors.

In conclusion, the ducted tail rotor has better effect than the common tail rotor under the condition of low load capacity, but when large load capacity is needed, the defect of small tension caused by small diameter of the tail rotor is revealed and cannot be matched with the torque force of the main rotor. And the traditional tail rotor or the traditional ducted tail rotor transmits the power of the engine to the tail rotor through a transmission system, so that the reliability is not very high.

Disclosure of Invention

The invention aims to provide a tail rotor structure and a helicopter, which aim to solve the technical problems that the tension of a duct tail rotor in the prior art is small and cannot be matched with the torque force of a main rotor, and improve the reliability of the traditional tail rotor.

In order to achieve the purpose, the invention adopts the following technical scheme:

the utility model provides a tail rotor structure, includes vertical tail wing, be provided with a plurality of ducts on the vertical tail wing, every all be provided with first power component and second power component in the duct, first power component includes first paddle and drive first paddle pivoted first driving piece, second power component includes second paddle and drive second paddle pivoted second driving piece, first paddle with the coaxial setting of second paddle, first paddle with turning to of second paddle is opposite, just first paddle with the effort direction that the second paddle produced is the same.

As a preferable technical scheme of the tail rotor structure, the number of the ducts is two.

As a preferable technical scheme of the tail rotor structure, the two ducts are distributed up and down on the vertical tail wing.

In a preferred embodiment of the tail rotor structure, a movable control surface is provided at the tail of the vertical tail fin, and the movable control surface can be driven by the third driving element to deflect in the direction.

As a preferred technical solution of the tail rotor structure, the first driving member and the second driving member are both motors.

A helicopter comprising a fuselage and a tail rotor structure as claimed in any one of the preceding claims, said tail rotor structure being attached to the rear of said fuselage.

As the preferable technical scheme of the helicopter, the tail rotor structure is detachably connected with the helicopter body.

The invention has the beneficial effects that:

the tail rotor structure comprises a vertical tail wing, wherein a plurality of ducts are arranged on the vertical tail wing, a first power assembly and a second power assembly are arranged in each duct, the first power assembly comprises a first blade and a first driving piece for driving the first blade to rotate, the second power assembly comprises a second blade and a second driving piece for driving the second blade to rotate, the first blade and the second blade are coaxially arranged, the rotation directions of the first blade and the second blade are opposite, and the acting forces generated by the first blade and the second blade are the same in direction.

Firstly, by arranging a plurality of ducts, arranging two groups of power assemblies in each duct, and enabling the pull directions of blades in the two groups of power assemblies to be the same, the power of a tail rotor structure can be greatly improved, the reaction torque of a high-power engine can be matched, and the carrying capacity of the unmanned aerial vehicle is improved; secondly, two groups of power assemblies are arranged in each duct, and blades in the two groups of power assemblies are opposite in steering direction, so that torque force generated by rotation of the blades can be offset, and the maneuverability of the helicopter is better; finally, two groups of power assemblies are arranged in each duct, when one group of power assemblies breaks down, the other group of power assemblies can continue to work, the safe landing of the helicopter is guaranteed, and the reliability of the helicopter is improved.

Drawings

FIG. 1 is a schematic structural view of a tail rotor configuration of the present invention;

fig. 2 is a schematic structural view of a first power assembly and a second power assembly in a tail rotor configuration of the present invention.

In the figure:

10-vertical tail; 11-a duct; 20-a first power assembly; 21-a first driving member; 22-a first blade; 30-a second power assembly; 31-a second drive member; 32-a second blade; 40-movable rudder surface.

Detailed Description

The technical scheme of the invention is further explained by combining the attached drawings and the embodiment. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some but not all of the elements associated with the present invention are shown in the drawings.

In the description of the present invention, unless expressly stated or limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, e.g., as meaning permanently connected, removably connected, or integral to one another; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.

In the description of the present embodiment, the terms "upper", "lower", "left", "right", and the like are used based on the orientations and positional relationships shown in the drawings only for convenience of description and simplification of operation, and do not indicate or imply that the referred device or element must have a specific orientation, be configured and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used only for descriptive purposes and are not intended to have a special meaning.

As shown in fig. 1 and 2, the present invention provides a tail rotor structure, which includes a vertical tail wing 10, wherein a plurality of ducts 11 are disposed on the vertical tail wing 10, each duct 11 has a first power assembly 20 and a second power assembly 30 disposed therein, the first power assembly 20 includes a first blade 22 and a first driving member 21 for driving the first blade 22 to rotate, the second power assembly 30 includes a second blade 32 and a second driving member 31 for driving the second blade 32 to rotate, the first blade 22 and the second blade 32 are coaxially disposed, the directions of rotation of the first blade 22 and the second blade 32 are opposite, and the directions of forces generated by the first blade 22 and the second blade 32 are the same. It should be noted that, by adjusting the blade angle of the first blade 22 and the second blade 32, the direction of the acting force generated by the first blade 22 and the second blade 32 can be the same, which is the prior art and is not described herein again.

Firstly, by arranging a plurality of ducts 11, arranging two groups of power assemblies in each duct 11, and enabling the directions of tension generated by blades in the two groups of power assemblies to be the same, the power of a tail rotor structure can be greatly improved, the reaction torque of a high-power engine can be matched, and the carrying capacity of the unmanned aerial vehicle is improved; secondly, two groups of power assemblies are arranged in each duct 11, and blades in the two groups of power assemblies are opposite in steering direction, so that torque force generated by rotation of the blades can be offset, and the maneuverability of the helicopter is better; finally, two groups of power assemblies are arranged in each duct 11, when one group of power assemblies breaks down, the other group of power assemblies can continue to work, the safe landing of the helicopter is guaranteed, and the reliability of the helicopter is improved.

In this embodiment, the number of the ducts 11 is two, which not only can achieve the effect of improving the power of the tail rotor structure, but also is convenient for the ducts 11 to be arranged. Preferably, the two ducts 11 are distributed and arranged up and down on the vertical tail 10.

Furthermore, a movable control surface 40 is arranged at the tail part of the vertical tail wing 10, the movable control surface 40 can deflect under the driving of a third driving element, the resistance direction of the near-fuselage airflow can be changed by controlling the deflection direction of the movable control surface 40, and the flight performance of the helicopter is improved.

In this embodiment, the first driving member 21 and the second driving member 31 are both motors, the first blade 22 is connected to the output shaft of the first driving member 21, and the second blade 32 is connected to the output shaft of the second driving member 31. The third driving piece is a steering engine. The first driving member 21, the second driving member 31 and the third driving member may be powered by a battery pack.

The invention also provides a helicopter which comprises a helicopter body and the tail rotor structure, wherein the tail rotor structure is connected to the tail pipe of the helicopter body. By adopting the tail rotor structure, the load capacity of the helicopter can be improved, and the maneuverability and the reliability of the helicopter are improved.

Furthermore, the tail rotor wing structure can be dismantled with the tail pipe and be connected, can dismantle the tail rotor wing structure from the tail pipe, is convenient for carry out the inspection and maintenance to the tail rotor wing structure to and be convenient for the long-distance transport of helicopter.

It should be understood that the above-described embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. The tail rotor structure is characterized by comprising a vertical tail wing (10), wherein a plurality of ducts (11) are arranged on the vertical tail wing (10), each duct (11) is internally provided with a first power assembly (20) and a second power assembly (30), the first power assembly (20) comprises a first blade (22) and a first driving piece (21) for driving the first blade (22) to rotate, the second power assembly (30) comprises a second blade (32) and a second driving piece (31) for driving the second blade (32) to rotate, the first blade (22) and the second blade (32) are coaxially arranged, the turning directions of the first blade (22) and the second blade (32) are opposite, and the acting force directions generated by the first blade (22) and the second blade (32) are the same.

2. Tail rotor structure according to claim 1, characterized in that the number of ducts (11) is two.

3. Tail rotor structure according to claim 2, characterized in that two of said ducts (11) are distributed up and down on said vertical tail (10).

4. Tail rotor structure according to claim 1, characterized in that the tail of the vertical tail fin (10) is provided with a movable control surface (40), which movable control surface (40) is capable of being deflected in direction upon actuation of a third actuator.

5. A tail rotor structure according to claim 1, wherein the first drive member (21) and the second drive member (31) are both electric motors.

6. A helicopter comprising a fuselage and a tail rotor structure according to any one of claims 1 to 5, said tail rotor structure being attached to the aft portion of said fuselage.

7. A helicopter according to claim 6, characterized in that said tail rotor structure is removably connected to said airframe.