CN108639318A - A kind of helicopter reaction torque balance system and helicopter - Google Patents
A kind of helicopter reaction torque balance system and helicopter Download PDFInfo
- Publication number
- CN108639318A CN108639318A CN201810677009.4A CN201810677009A CN108639318A CN 108639318 A CN108639318 A CN 108639318A CN 201810677009 A CN201810677009 A CN 201810677009A CN 108639318 A CN108639318 A CN 108639318A
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- Prior art keywords
- helicopter
- reaction torque
- balance system
- fan
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to a kind of helicopter reaction torque balance systems, belong to helicopter Pneumatic component design field comprising：Shell, the shell have a vessel and are equipped with the air inlet and exhaust outlet for being connected to the vessel on the housing, and the center line of the air inlet and the center line of exhaust outlet are in predetermined angle；Cross flow fan, the cross flow fan are set in the vessel, for guiding the air-flow flowed into from the air inlet to be flowed out from the exhaust outlet, to provide the lateral force for balancing helicopter reaction torque；Central shaft, the central shaft are set in the vessel and are fixed on the shell, are used to support the cross flow fan and make the cross flow fan around the central axis.The present invention can improve the safety of helicopter landing and low-latitude flying, the power consumption for reducing the system, noise and level of vibration and decline, can provide a certain size vertical component, so that helicopter center of gravity permissible range expands.
Description
Technical field
The invention belongs to helicopter Pneumatic component design field more particularly to a kind of helicopters based on cross flow fan
Reaction torque balance system and helicopter.
Background technology
The pulling force that helicopter flight is generated mainly by rotor.When rotor, which is driven by engine by rotary shaft, to be rotated, rotation
The wing to air with torque (or opplied moment), air it is inevitable the same time with the opposite reaction torque in equal in magnitude, direction (or
Claim the moment of reaction) rotor is acted on, to which this reaction torque is transmitted on helicopter body by rotor again.If do not adopted
Measure is taken to be balanced, then this reaction torque will be such that helicopter is rotated against rotor rotational direction.It is anti-twisted in order to eliminate this
Square acts to keep the course of helicopter, needs to arrange that certain structure, such as tail-rotor are anti-twisted to balance rotor on helicopter
Square is simultaneously carried out to the directional control of helicopter.
There is also many deficiencies while realizing function for traditional balance antitorque of rotor device --- tail-rotor, such as
In flight course or when ground is parked, tail-rotor may be collided with objects such as branch, electric wires, lead to the generation of accident；Tail-rotor is
Important noise source and vibration source on one helicopter can reduce component life, increase maintenance cost, aggravate flyer's fatigue.
Invention content
The object of the present invention is to provide one kind based on cross flow fan, pneumatic efficiency is higher, is arranged in single-rotor helicopter tail
Reaction torque balance system on beam balances antitorque of rotor and controls directional control and the maneuvering flight of helicopter.
The technical scheme is that：A kind of helicopter reaction torque balance system comprising：
Shell, the shell have a vessel and are equipped with air inlet and the exhaust for being connected to the vessel on the housing
Mouthful, the center line of the air inlet and the center line of exhaust outlet are in predetermined angle；
Cross flow fan, the cross flow fan are set in the vessel, for guiding the air-flow flowed into from the air inlet
It is flowed out from the exhaust outlet, to provide the lateral force for balancing helicopter reaction torque；
Central shaft, the central shaft are set in the vessel and are fixed on the shell, are used to support the crossing current
Fan simultaneously makes the cross flow fan around the central axis.
In an embodiment of the present invention, it is equipped with lip in the air inlet outer ledge of the shell, it is vertical for providing
Pulling force, wherein the lip is arc line type.
In an embodiment of the present invention, further include the flow deflector for being installed on exhaust ports, the flow deflector and housing hinge
For adjusting the air flow direction being discharged from exhaust outlet.
In the above-described embodiments, the flow deflector hinge is located at the front end for the flow deflector that air-flow flows through.
In an embodiment of the present invention, the cross flow fan includes at least two fan units, and the fan unit includes one
Group fan blade and the fan end plate for being set to the electric fan both sides, wherein gap is equipped between adjacent two fan unit.
In an embodiment of the present invention, the predetermined angle is 80 °~100 °.
In an embodiment of the present invention, further include protective cover, the protective cover is in netted, for preventing described in foreign matter entrance
Air inlet.
The present invention also provides a kind of helicopter, the helicopter includes any of the above-described helicopter reaction torque balance system,
The helicopter reaction torque balance system, which is installed on, goes straight up to drive end unit, for providing the lateral force for realizing helicopter Heading control,
The center shaft axis of the wherein described helicopter reaction torque balance system is parallel to helicopter screw propeller Plane of rotation so that the shell
The plane that air inlet and gas outlet center line are constituted in body is vertical with helicopter screw propeller Plane of rotation.
The helicopter reaction torque balance system based on cross flow fan and helicopter of the present invention is by carrying out again tail boom
Pneumatic design, by tail boom side jet provide thrust can balancing helicopter rotor reaction torque and control the course of helicopter
Manipulation and maneuvering flight.The relatively conventional tail-rotor of course control system of this helicopter is simple in structure, and safety is good, while one
Determine the vibration and the noise that reduce helicopter in degree.
Description of the drawings
The drawings herein are incorporated into the specification and forms part of this specification, and shows the implementation for meeting the present invention
Example, and be used to explain the principle of the present invention together with specification.
Fig. 1 is the helicopter reaction torque balance system structural schematic diagram of one embodiment of the invention；
Fig. 2 is the helicopter reaction torque balance system interior views of one embodiment of the invention；
Fig. 3 is the flow deflector schematic diagram of one embodiment of the invention；
Fig. 4 is the cross flow fan structural schematic diagram of one embodiment of the invention.
Specific implementation mode
To keep the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.
As depicted in figs. 1 and 2, helicopter reaction torque balance system of the invention includes mainly shell 1,3 and of cross flow fan
Central shaft 2, shell 1 be configured to have a hollow reservoir 13, and on shell 1 be equipped be connected to vessel 13 air inlet 11 and
Exhaust outlet 12, air inlet 11 (center line L1) are in predetermined angle with exhaust outlet 12 (center line L2)；Cross flow fan 3 is set to shell
In 1 vessel 13, for guiding the air-flow flowed into from air inlet 11 and air-flow being made to be flowed out from exhaust outlet 13, to provide for putting down
The lateral force for the helicopter reaction torque that weighs；Central shaft 2 is arranged in the vessel 13 in shell 1, and both ends are fixed on shell 1, uses
In support cross flow fan 3 so that cross flow fan 3 can be rotated around central shaft 2.
Helicopter reaction torque balance system, which is set to, goes straight up to drive end unit (or tail boom), passes through 11 suction airflow of air inlet, gas
Stream is turned to by cross flow fan 3 and is discharged from exhaust outlet 13, the lateral force of balancing helicopter reaction torque can be provided, to realize
The course deflection control of helicopter.
As shown in Fig. 2, the air-breathing above tail boom of cross flow fan 3 in helicopter reaction torque balance system, by cross
After flow fan 3 turns to, then the side jet offer thrust from lower right, it is accordingly used in the angle that air-flow turns to conjunction should be arranged
The predetermined angle of gas outlet and air inlet is set as 80 °~100 ° by reason in the present invention, higher lateral anti-to generate effect
Torsional forces, angle shown in legend are 90 degree.
In the present invention, it is provided with lip 14 on the shell 1 on being installed on tail boom and carries out Aerodynamic optimization design so that
Air-flow can generate certain additional lateral force when passing through, lip 14 is located at 1 gas suction side of shell (outside of air inlet 11).
In the preferred embodiment of the invention, the lip 14 is arc line shaped, and rounding off is in 1 outside of shell and air inlet in shell 1
11 edge.
In the present invention, a series of deflectable flow deflectors 4 of (i.e. gas sprays side) arrangement at the gas outlet 12 of shell 1,
For realizing the vector controlled of thrust.In embodiments of the present invention, above-mentioned deflection side hingedly can be realized with shell 1 in flow deflector 4
Case.
As shown in figure 3, the section middle part of the flow deflector 4 in the embodiment of the present invention is rectangular, both ends are rounded, air flow direction
It flows from left to right, and the hinge of flow deflector 4 is then located at the front end that air-flow flows through flow deflector 4, the i.e. left-hand portion of flow deflector 4.
It should be noted that cross flow fan 3 is driven using motor in the present invention, the tune of thrust can be realized by speed change
Section.
As shown in figure 4, cross flow fan 3 may include at least two fan units in the present invention, include one per fan unit
It organizes fan blade 31 and is arranged and be used to grip the fan end plate 32 of fan blade 31, fan unit in 31 both sides of fan blade
Fan unit is attached with central shaft 2 after parallel setting.Gap is equipped between wherein adjacent two fan unit.
Further include protective cover 5 in preferred embodiment of the present invention, protective cover 5 is reticular structure, for prevent foreign matter enter into
The aperture size of gas port, reticular structure can be adjusted according to fitness of environment.
In addition, the present invention also provides a kind of helicopter, helicopter includes above-mentioned helicopter reaction torque balance system, directly
Liter machine reaction torque balance system, which is installed on, goes straight up to drive end unit, for providing the lateral force for realizing helicopter Heading control.Helicopter
The set-up mode of reaction torque balance system is：2 axis of central shaft is parallel to the setting of helicopter screw propeller Plane of rotation so that described
The plane that air inlet and gas outlet center line are constituted in shell is vertical with helicopter screw propeller Plane of rotation.
Several aspects once should be noted that for the helicopter reaction torque balance system of the present invention：
(1) the shape basic size of helicopter reaction torque balance system should according to the tonnage of helicopter, reaction torque size and
Tail boom arrowhead etc. determines the shape basic size of tail boom air-jet device, while determining reaction torque balance system on tail boom
Longitudinally mounted position；
(2) diameter of the cross flow fan 3 embedded in helicopter reaction torque balance system and internal gas flow channel are basic
Size determines the diameter of embedded fan according to internal structure arrowhead and thrust requirements；Air-flow inner passage will ensure
There are enough air-flows to pass through area；Air inlet transition wants round and smooth, and cambered surface is used to design, and reduces the total crushing of air-flow in the channel
It loses；Inner passage also needs to the installation reserved space for cross flow fan 3.
(3) shape and size of the internal part of helicopter reaction torque balance system, internal part include：Cross flow fan 3
The parameters such as chord length, aerofoil profile, the established angle of used fan blade 31 so that the pneumatic effect of acceleration deflecting of cross flow fan 3 is preferable,
Pitot loss is smaller simultaneously, and 31 structure of fan blade is with reference to shown in Fig. 3；According to deformation and crossing current of the tail boom in flight
Structural requirement when fan 3 is arranged selects cross flow fan 3 appropriate along each drum length in tail boom direction, as described in Figure 4 i.e.
To have selected two fan units to constitute the helicopter reaction torque balance system of cross flow fan 3；Connect between each cylinder shape cross flow fan 3
Relay part is designed as detachable and has some gaps, can directly be replaced to single roller；Helicopter reaction torque balances
The suction side of system is equipped with lip 14, and lip 14 is camber line, and the appearance and size of lip 14 will meet claimed below：It being capable of maximum limit
Degree expand tail boom above suction range so that air-flow can smoothly enter into tail boom air-jet device and without larger total crushing
It loses, certain vertical force is capable of providing when air-flow flows through lip 14；The jet side setting of helicopter reaction torque balance system is led
Flow 4, flow deflector 4 are installed on exhaust outlet 12 and are hinged with shell 1, and flow deflector 4 can be rotated around hinged shaft for adjusting exhaust outlet
The air flow direction of 12 discharges, shape will reduce stagnation pressure to the greatest extent can smoothly meet the under the premise of of realizing spout air-flow deflecting requirement
Loss.
(4) surface of helicopter reaction torque balance system carries out correction of the flank shape, while suitably adjusting dependent part according to analysis result
Part size and position；It is connected using tangent rounding off between each adjacent curved surface, determines each curved surface connection interim size；End face it
Between using rounded corner connect, according to wrapping portion size and rounding off requirement, determine the radius size of rounded corner.
The helicopter reaction torque balance system and helicopter of the present invention has the following advantages that：
A) helicopter reaction torque balance system is required to meet the structure size limitation of tail boom；
B) air-breathing can utilize the energy of rotor down-wash flow under a variety of state of flights above tail boom；
C) Aerodynamic optimization design is carried out in the lip 14 of tail boom gas suction side so that can be generated when air-flow passes through certain
Additional vertical force；
D) side is sprayed in tail boom gas, arranges a series of deflectable flow deflectors 4, realizes the vector controlled of thrust.
E) the aerofoil profile parameter of fan blade 31 passes through Aerodynamic optimization design in cross flow fan 3 so that air-flow is flowing through crossing current
Pitot loss is smaller when fan and acceleration effect is good；
F) cross flow fan 3 is truncated into the fan unit of several roller series arrangements, two adjacent fan lists along tail boom direction
There are certain intervals between member, can allow the deformation of tail boom to a certain extent；Simultaneously, so that 32 spacing of fan end plate becomes
Small (i.e. length of the fan blade 31 along 2 axis direction of central shaft) so that 31 length of fan blade is relatively small, fan blade 31
Structural strength be enhanced, it is sufficient to bear rotation when centrifugal force；
G) cross flow fan 3 is driven using motor, and the variation of thrust is realized by the adjusting of cross flow fan rotating speed.
The accident that the helicopter reaction torque balance system and helicopter of the present invention can collide to avoid tail-rotor and foreign object, is improved
The safety of helicopter landing and low-latitude flying；Rotor downwash stream energy can be utilized under a variety of state of flights, reduce power
Consumption；Noise and the more conventional tail-rotor of level of vibration are declined；Vector gas puff Z-pinch module and rotational speed regulation module are used, more
Convenient for manipulating；Vector gas puff Z-pinch module is relied on, certain component can be provided in the vertical direction so that helicopter center of gravity is held
Perhaps range expands；Also more conventional tail-rotor is declined weight.
The above, only optimal specific implementation mode of the invention, but scope of protection of the present invention is not limited thereto,
Any one skilled in the art in the technical scope disclosed by the present invention, the change or replacement that can be readily occurred in,
It should be covered by the protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of the claim
Subject to enclosing.
Claims (8)
1. a kind of helicopter reaction torque balance system, which is characterized in that the helicopter reaction torque balance system includes：
Shell (1), the shell (1), which has a vessel (13) and is equipped on the shell (1), is connected to the vessel (13)
Air inlet (11) and exhaust outlet (12), the center line of the air inlet (11) and the center line of exhaust outlet (12) be in preset angle
Degree；
Cross flow fan (3), the cross flow fan (3) are set in the vessel (13), for guiding from the air inlet (11)
The air-flow of inflow is flowed out from the exhaust outlet (12), to provide the lateral force for balancing helicopter reaction torque；
Central shaft (2), the central shaft (2) are set in the vessel (13) and are fixed on the shell (1), be used to support
The cross flow fan (3) simultaneously makes the cross flow fan (3) be rotated around the central shaft (2).
2. helicopter reaction torque balance system according to claim 1, which is characterized in that the air inlet in the shell (1)
Mouth (11) outer ledge is equipped with lip (14), for providing vertical pulling force, wherein the lip (14) is arc line type.
3. helicopter reaction torque balance system according to claim 1, which is characterized in that further include being installed on exhaust outlet
(12) flow deflector (4) at, the flow deflector (4) are hinged for adjusting the air-flow stream being discharged from exhaust outlet (12) with shell (1)
To.
4. helicopter reaction torque balance system according to claim 3, which is characterized in that flow deflector (4) the hinge position
In the front end for the flow deflector (4) that air-flow flows through.
5. helicopter reaction torque balance system according to claim 1, which is characterized in that the cross flow fan (3) is at least
Including two fan units, the fan unit is including one group of fan blade (31) and is set to the electric fan (31) both sides
Fan end plate (32), wherein gap is equipped between adjacent two fan unit.
6. helicopter reaction torque balance system according to claim 1, which is characterized in that the predetermined angle be 80 °~
100°。
7. helicopter reaction torque balance system according to claim 1, which is characterized in that further include protective cover (5), it is described
Protective cover (5) is in netted, for preventing foreign matter from entering the air inlet (11).
8. a kind of helicopter, which is characterized in that the helicopter includes that the helicopter as described in claim 1 to 7 is any is anti-twisted
Square balance system, the helicopter reaction torque balance system, which is installed on, goes straight up to drive end unit, and the control of helicopter course is realized for providing
The lateral force of system, wherein central shaft (2) axis of the helicopter reaction torque balance system is parallel to helicopter screw propeller rotation
Plane so that the plane that air inlet (11) and gas outlet (12) center line are constituted in the shell is rotated with helicopter screw propeller
Plane is vertical.
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 true CN108639318A (en) | 2018-10-12 |
| CN108639318B 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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| CN (1) | CN108639318B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113928554A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Helicopter tail reaction torque device and pneumatic design method |
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| US20120111994A1 (en) * | 2010-01-15 | 2012-05-10 | Propulsive Wing, LLC | Cross-flow fan propulsion system |
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| 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 |
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2018
- 2018-06-27 CN CN201810677009.4A patent/CN108639318B/en active Active
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|---|---|---|---|---|
| CN101037140A (en) * | 2007-04-18 | 2007-09-19 | 万涛 | Centrifugal balance reaction-torque heat-dispensing system for helicopter |
| US20120111994A1 (en) * | 2010-01-15 | 2012-05-10 | Propulsive Wing, LLC | Cross-flow fan propulsion system |
| EP2808253A1 (en) * | 2013-05-30 | 2014-12-03 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Helicopter with cross flow fan |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113928554A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Helicopter tail reaction torque device and pneumatic design method |
| 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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| Publication number | Publication date |
|---|---|
| CN108639318B (en) | 2023-10-20 |
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