CN108639318B - Helicopter reactive torque balancing system and helicopter - Google Patents
Helicopter reactive torque balancing system and helicopter Download PDFInfo
- Publication number
- CN108639318B CN108639318B CN201810677009.4A CN201810677009A CN108639318B CN 108639318 B CN108639318 B CN 108639318B CN 201810677009 A CN201810677009 A CN 201810677009A CN 108639318 B CN108639318 B CN 108639318B
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- helicopter
- reactive torque
- fan
- air
- shell
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
-
- 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
Abstract
The invention relates to a helicopter reactive torque balancing system, which belongs to the technical field of helicopter pneumatic component design, and comprises the following components: the shell is provided with a containing cavity, an air inlet and an air outlet which are communicated with the containing cavity are arranged on the shell, and the center line of the air inlet and the center line of the air outlet form a preset angle; a cross flow fan disposed in the cavity for guiding an air flow flowing in from the air inlet to flow out from the air outlet to provide a lateral force for balancing a reactive torque of the helicopter; the central shaft is arranged in the containing cavity and fixed on the shell and used for supporting the cross flow fan and enabling the cross flow fan to rotate around the central shaft. The invention can improve the safety of taking off and landing of the helicopter and low-altitude flight, reduce the power consumption of the system, reduce the noise and vibration level, and provide a vertical component force with a certain magnitude, thereby expanding the allowable range of the gravity center of the helicopter.
Description
Technical Field
The invention belongs to the technical field of helicopter pneumatic component design, and particularly relates to a helicopter reactive torque balancing system based on a cross flow fan and a helicopter.
Background
Helicopter mainly depends on the pulling force generated by the rotor wing. When the rotor is rotated by the engine through the rotating shaft, the rotor gives torque (or torque), and the air necessarily acts on the rotor at the same time with reactive torque (or reactive torque) with equal magnitude and opposite direction, so that the reactive torque is transmitted to the helicopter body through the rotor. If no countermeasures are taken to balance, this reactive torque will cause the helicopter to rotate against the direction of rotor rotation. To eliminate this reactive torque effect to maintain the heading of the helicopter, it is necessary to arrange a structure on the helicopter, such as a tail rotor, to balance the rotor reactive torque and to perform a heading maneuver of the helicopter.
The traditional counter torque device of the balance rotor, namely the tail rotor, has a plurality of defects when realizing functions, for example, the tail rotor can collide with objects such as branches, wires and the like in the flying process or when parked on the ground, so that accidents occur; the tail rotor is an important noise source and vibration source on the helicopter, so that the service life of parts can be reduced, the maintenance cost can be increased, and the fatigue of pilots can be increased.
Disclosure of Invention
The invention aims to provide a reactive torque balancing system which is based on a cross flow fan, has high aerodynamic efficiency, is arranged on a tail beam of a single-rotor helicopter, balances the reactive torque of the rotor and controls the course manipulation and maneuvering flight of the helicopter.
The technical scheme of the invention is as follows: a helicopter reactive torque balancing system, comprising:
the shell is provided with a containing cavity, an air inlet and an air outlet which are communicated with the containing cavity are arranged on the shell, and the center line of the air inlet and the center line of the air outlet form a preset angle;
a cross flow fan disposed in the cavity for guiding an air flow flowing in from the air inlet to flow out from the air outlet to provide a lateral force for balancing a reactive torque of the helicopter;
the central shaft is arranged in the containing cavity and fixed on the shell and used for supporting the cross flow fan and enabling the cross flow fan to rotate around the central shaft.
In an embodiment of the present invention, a lip is provided at an outer edge of the air inlet of the housing, for providing a vertical pulling force, wherein the lip is of an arc shape.
In an embodiment of the invention, the air conditioner further comprises a guide vane arranged at the air outlet, wherein the guide vane is hinged with the shell and used for adjusting the flow direction of the air discharged from the air outlet.
In the above embodiments, the baffle hinge point is located at the front end of the baffle through which the airflow flows.
In an embodiment of the present invention, the cross-flow fan at least includes two fan units, the fan units include a set of fan blades and fan end plates disposed at two sides of the fan blades, wherein a gap is disposed between two adjacent fan units.
In an embodiment of the present invention, the preset angle is 80 ° to 100 °.
In an embodiment of the present invention, the air inlet further comprises a protection cover, wherein the protection cover is in a net shape and is used for preventing foreign matters from entering the air inlet.
The invention also provides a helicopter, which comprises any helicopter anti-torque balancing system, wherein the helicopter anti-torque balancing system is arranged at the tail part of the helicopter and is used for providing lateral force for realizing the course control of the helicopter, and the central axis of the helicopter anti-torque balancing system is parallel to the rotating plane of the helicopter propeller, so that the plane formed by the central lines of the air inlet and the air outlet in the shell is perpendicular to the rotating plane of the helicopter propeller.
According to the helicopter reactive torque balancing system and the helicopter based on the cross flow fan, the reactive torque of the helicopter rotor wing can be balanced and the course control and maneuvering flight of the helicopter can be controlled by the thrust provided by the jet on the side face of the tail beam through the pneumatic design of the tail beam. Compared with a conventional tail rotor, the heading control system of the helicopter is simple in structure and good in safety, and meanwhile vibration and noise of the helicopter are reduced to a certain extent.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and together with the description, serve to explain the principles of the invention.
FIG. 1 is a schematic diagram of a helicopter reactive torque balance system according to an embodiment of the invention;
FIG. 2 is an internal view of a helicopter reactive torque balance system according to an embodiment of the invention;
FIG. 3 is a schematic view of a baffle according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a cross-flow fan according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention become more apparent, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention.
As shown in fig. 1 and 2, the helicopter reactive torque balance system of the present invention mainly comprises a housing 1, a cross flow fan 3 and a central shaft 2, wherein the housing 1 is provided with a hollow cavity 13, an air inlet 11 and an air outlet 12 which are communicated with the cavity 13 are arranged on the housing 1, and the air inlet 11 (a central line L1) and the air outlet 12 (a central line L2) form a preset angle; the cross flow fan 3 is disposed in the cavity 13 of the housing 1 for guiding the air flow flowing in from the air inlet 11 and flowing out from the air outlet 13 to provide a lateral force for balancing the helicopter reaction torque; the center shaft 2 is disposed in a receiving chamber 13 in the housing 1, and both ends thereof are fixed to the housing 1 for supporting the cross flow fan 3 such that the cross flow fan 3 can rotate around the center shaft 2.
The helicopter reactive torque balancing system is arranged at the tail part (or tail beam) of the helicopter, air flow is sucked through the air inlet 11, is turned by the cross flow fan 3 and is discharged from the air outlet 13, and lateral force for balancing the reactive torque of the helicopter can be provided, so that the course deflection operation of the helicopter is realized.
As shown in fig. 2, in the helicopter reactive torque balance system, the cross flow fan 3 sucks air from the upper part of the helicopter tail beam, and after the air is turned by the cross flow fan 3, the air is blown from the side face at the right lower part to provide thrust, so that the angle for turning the air flow is reasonable, namely, the preset angle of the air outlet and the air inlet is set to be 80-100 degrees in the invention, so that the lateral reactive torque with higher efficacy is generated, and the angle shown in the figure is 90 degrees.
In the invention, a lip 14 is arranged on the shell 1 mounted on the tail boom and is designed in a pneumatic optimization way, so that certain additional lateral force can be generated when the air flows through the shell, and the lip 14 is positioned on the air suction side (the outer side of the air inlet 11) of the shell 1. In the preferred embodiment of the present invention, the lip 14 is arc-shaped and smoothly transitions to the outside of the housing 1 and the edge of the air inlet 11 in the housing 1.
In the present invention, a series of deflectable deflectors 4 are arranged at the air outlet 12 of the housing 1 (i.e. the air ejection side) for achieving a vectorial control of the thrust. In the embodiment of the present invention, the deflector 4 is hinged to the housing 1 to achieve the above-mentioned deflection scheme.
As shown in fig. 3, in the embodiment of the present invention, the middle part of the cross section of the guide vane 4 is rectangular, two ends are circular, the airflow flows from left to right, and the hinge point of the guide vane 4 is located at the front end of the airflow flowing through the guide vane 4, i.e. the left side part of the guide vane 4.
In the present invention, the cross flow fan 3 is driven by a motor, and the thrust can be adjusted by changing the speed.
As shown in fig. 4, the cross flow fan 3 of the present invention may include at least two fan units, each of which includes a set of fan blades 31 and fan end plates 32 disposed at both sides of the fan blades 31 for clamping and fixing the fan blades 31, and the fan units are connected by a central shaft 2 after being disposed in parallel. Wherein a gap is arranged between two adjacent fan units.
In a preferred embodiment of the present invention, the air conditioner further comprises a protective cover 5, wherein the protective cover 5 is a mesh structure for preventing foreign matters from entering the air inlet, and the size of the orifice of the mesh structure can be properly adjusted according to the environment.
In addition, the invention also provides a helicopter, which comprises the helicopter anti-torque balancing system, wherein the helicopter anti-torque balancing system is arranged at the tail part of the helicopter and is used for providing lateral force for realizing the course control of the helicopter. The helicopter reactive torque balance system is arranged in the following mode: the axis of the central shaft 2 is parallel to the rotating plane of the helicopter propeller, so that the plane formed by the central lines of the air inlet and the air outlet in the shell is perpendicular to the rotating plane of the helicopter propeller.
Several aspects should be noted for the helicopter reactive torque balance system of the present invention:
(1) The external basic size of the helicopter reactive torque balancing system is determined according to the tonnage of the helicopter, the reactive torque, the limiting size of the tail beam and the like, and the longitudinal installation position of the reactive torque balancing system on the tail beam is determined;
(2) The diameter of the embedded cross flow fan 3 and the basic size of the internal airflow channel in the helicopter reactive torque balancing system are determined according to the internal structure limiting size and the thrust requirement; the inner passage of the air flow ensures enough air flow passing area; the transition of the air inlet is smooth, and the cambered surface design is adopted, so that the total pressure loss of the air flow in the channel is reduced; the internal channels also need to be space reserved for the installation of the crossflow fans 3.
(3) The external shape and size of the internal components of the helicopter reactive torque balance system, the internal components comprising: the parameters of chord length, wing shape, installation angle and the like of the fan blade 31 adopted by the cross flow fan 3 ensure that the acceleration and direction changing aerodynamic effect of the cross flow fan 3 is better, meanwhile, the total pressure loss is smaller, and the structure of the fan blade 31 is shown by referring to fig. 3; according to the deformation condition of the tail boom during flying and the structural requirement of the cross flow fan 3 during arrangement, selecting proper lengths of each roller of the cross flow fan 3 along the tail boom direction, and as shown in fig. 4, forming a helicopter reactive torque balance system of the cross flow fan 3 by two fan units; the connecting parts between the roller-shaped cross flow fans 3 are designed to be detachable and have some gaps, so that a single roller can be directly replaced; the suction side of the helicopter reactive torque balance system is provided with a lip 14, the lip 14 is an arc line, and the outline dimension of the lip 14 needs to meet the following requirements: the suction range above the tail boom can be expanded to the greatest extent, so that air flow can smoothly enter the tail boom air injection device without larger total pressure loss, and a certain vertical force can be provided when the air flow flows through the lip 14; the jet side of helicopter reactive torque balance system sets up the guide vane 4, and guide vane 4 installs in gas vent 12 and articulated with casing 1, and guide vane 4 can rotate and be used for adjusting gas flow direction that gas vent 12 was discharged around the hinge, and its appearance is to reduce total pressure loss as far as possible under the prerequisite that can satisfy the requirement of realizing spout air current diversion smoothly.
(4) Modifying the surface of the helicopter reactive torque balance system, and properly adjusting the sizes and positions of related components according to analysis results; the adjacent curved surfaces are connected in a tangential smooth transition manner, and the connection transition size of each curved surface is determined; the end surfaces are connected by a rounding, and the radius size of the rounding is determined according to the size of the wrapping part and the smooth transition requirement.
The helicopter reactive torque balancing system and the helicopter have the following advantages:
a) The helicopter reactive torque balance system requirements meet the structural size limit of the tail boom;
b) The air suction from the upper part of the tail boom can utilize the energy of the rotor wing downwash in various flight states;
c) The lip 14 on the gas suction side of the tail boom is designed in a pneumatic optimization manner so that a certain additional vertical force can be generated when the gas flows through the lip;
d) A series of deflectable guide vanes 4 are arranged on the gas ejection side of the tail boom, so that the vector control of thrust is realized.
e) The wing profile parameters of the fan blades 31 in the cross flow fan 3 are subjected to pneumatic optimization design, so that the total pressure loss of the air flow is small and the acceleration effect is good when the air flow flows through the cross flow fan;
f) The cross flow fan 3 is cut into fan units with a plurality of rollers arranged in series along the tail beam direction, a certain gap exists between two adjacent fan units, and the deformation of the tail beam can be allowed to a certain extent; at the same time, the distance between the fan end plates 32 is reduced (i.e. the length of the fan blades 31 along the axial direction of the central shaft 2) so that the length of the fan blades 31 is relatively small, and the structural strength of the fan blades 31 is enhanced enough to bear the centrifugal force during rotation;
g) The cross flow fan 3 is driven by a motor, and the thrust is changed by adjusting the rotation speed of the cross flow fan.
The helicopter anti-torque balancing system and the helicopter can avoid the accident that the tail rotor collides with the outside, and improve the safety of taking off and landing and low-altitude flight of the helicopter; the rotor wing downwash energy can be utilized in various flight states, so that the power consumption is reduced; noise and vibration levels are reduced compared to conventional tail rotor; the vector jet control module and the rotating speed adjusting module are adopted, so that the operation is more convenient; by means of the vector jet control module, a certain component force can be provided in the vertical direction, so that the allowable range of the gravity center of the helicopter is enlarged; the weight is also reduced compared with the conventional tail rotor.
The foregoing is merely illustrative of the preferred embodiments of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present invention should be included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (5)
1. A helicopter reactive torque balance system, said helicopter reactive torque balance system comprising:
the device comprises a shell (1), wherein the shell (1) is provided with a containing cavity (13), an air inlet (11) and an air outlet (12) which are communicated with the containing cavity (13) are arranged on the shell (1), the center line of the air inlet (11) and the center line of the air outlet (12) form a preset angle, and an arc-shaped lip (14) is arranged at the outer side edge of the air inlet (11) of the shell (1);
a cross flow fan (3), wherein the cross flow fan (3) is arranged in the accommodating cavity (13) and is used for guiding airflow flowing in from the air inlet (11) to flow out from the air outlet (12) so as to provide lateral force for balancing reactive torque of a helicopter, the cross flow fan (3) at least comprises two fan units, each fan unit comprises a group of fan blades (31) and fan end plates (32) arranged on two sides of each fan blade (31), and a gap is arranged between every two adjacent fan units;
the central shaft (2) is arranged in the accommodating cavity (13) and is fixed on the shell (1) and used for supporting the cross flow fan (3) and enabling the cross flow fan (3) to rotate around the central shaft (2);
the air deflector (4) is arranged at the air outlet (12), and the air deflector (4) is hinged with the shell (1) and used for adjusting the airflow direction discharged from the air outlet (12).
2. Helicopter reactive torque balancing system according to claim 1, characterized in that the deflector hinge point is located at the front end of the deflector (4) through which the air flow passes.
3. The helicopter reactive torque balancing system of claim 1, wherein the predetermined angle is 80 ° to 100 °.
4. Helicopter reactive torque balancing system according to claim 1, further comprising a protective cover (5), said protective cover (5) being net-shaped for preventing foreign objects from entering said air inlet (11).
5. A helicopter, characterized in that it comprises a helicopter anti-torque balancing system according to any of claims 1 to 4, which is mounted on the tail of the helicopter for providing lateral forces for achieving a helicopter heading control, wherein the central axis (2) of the helicopter anti-torque balancing system is parallel to the plane of rotation of the helicopter propeller, such that the plane formed by the centre lines of the air inlet (11) and the air outlet (12) in the housing is perpendicular to the plane of rotation of the helicopter propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810677009.4A CN108639318B (en) | 2018-06-27 | 2018-06-27 | Helicopter reactive torque balancing system and helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810677009.4A CN108639318B (en) | 2018-06-27 | 2018-06-27 | Helicopter reactive torque balancing system and helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108639318A CN108639318A (en) | 2018-10-12 |
| CN108639318B true CN108639318B (en) | 2023-10-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810677009.4A Active CN108639318B (en) | 2018-06-27 | 2018-06-27 | Helicopter reactive torque balancing system and helicopter |
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| Country | Link |
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| CN (1) | CN108639318B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113928554B (en) * | 2021-11-19 | 2023-04-28 | 中国直升机设计研究所 | Helicopter tail anti-torque device and pneumatic design method |
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| CN101037140A (en) * | 2007-04-18 | 2007-09-19 | 万涛 | Centrifugal balance reaction-torque heat-dispensing system for helicopter |
| CN103754362A (en) * | 2014-01-13 | 2014-04-30 | 南京航空航天大学 | Rotor wing with great lifting force |
| EP2808253A1 (en) * | 2013-05-30 | 2014-12-03 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Helicopter with cross flow fan |
| CN107672802A (en) * | 2017-10-24 | 2018-02-09 | 南京航空航天大学 | Fluting culvert type plume rotor craft |
| CN107719638A (en) * | 2016-08-10 | 2018-02-23 | 贝尔直升机德事隆公司 | Apparatus and method for the thrust of the inclination cross flow fan wing of vectored flight device |
| CN107719637A (en) * | 2016-08-10 | 2018-02-23 | 贝尔直升机德事隆公司 | Aircraft empennage with cross flow fan system |
| CN208530838U (en) * | 2018-06-27 | 2019-02-22 | 中国直升机设计研究所 | A kind of helicopter reaction torque balance system and helicopter |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120111994A1 (en) * | 2010-01-15 | 2012-05-10 | Propulsive Wing, LLC | Cross-flow fan propulsion system |
| SE541609C2 (en) * | 2013-06-25 | 2019-11-12 | Foersvarets Materielverk | Propulsion system for aircraft |
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2018
- 2018-06-27 CN CN201810677009.4A patent/CN108639318B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101037140A (en) * | 2007-04-18 | 2007-09-19 | 万涛 | Centrifugal balance reaction-torque heat-dispensing system for helicopter |
| EP2808253A1 (en) * | 2013-05-30 | 2014-12-03 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Helicopter with cross flow fan |
| CN103754362A (en) * | 2014-01-13 | 2014-04-30 | 南京航空航天大学 | Rotor wing with great lifting force |
| CN107719638A (en) * | 2016-08-10 | 2018-02-23 | 贝尔直升机德事隆公司 | Apparatus and method for the thrust of the inclination cross flow fan wing of vectored flight device |
| CN107719637A (en) * | 2016-08-10 | 2018-02-23 | 贝尔直升机德事隆公司 | Aircraft empennage with cross flow fan system |
| CN107672802A (en) * | 2017-10-24 | 2018-02-09 | 南京航空航天大学 | Fluting culvert type plume rotor craft |
| CN208530838U (en) * | 2018-06-27 | 2019-02-22 | 中国直升机设计研究所 | A kind of helicopter reaction torque balance system and helicopter |
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| Publication number | Publication date |
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| CN108639318A (en) | 2018-10-12 |
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