CN109383792A - A kind of cycloid paddle balance reaction torque helicopter and its working method - Google Patents
A kind of cycloid paddle balance reaction torque helicopter and its working method Download PDFInfo
- Publication number
- CN109383792A CN109383792A CN201811397473.4A CN201811397473A CN109383792A CN 109383792 A CN109383792 A CN 109383792A CN 201811397473 A CN201811397473 A CN 201811397473A CN 109383792 A CN109383792 A CN 109383792A
- Authority
- CN
- China
- Prior art keywords
- cycloid
- helicopter
- coil holder
- propeller
- bottom coil
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000006243 chemical reaction Methods 0.000 title claims abstract description 21
- 238000000034 method Methods 0.000 title claims abstract description 12
- 238000009434 installation Methods 0.000 claims abstract description 20
- 238000006073 displacement reaction Methods 0.000 claims abstract description 9
- 238000003780 insertion Methods 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005065 mining Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- 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
-
- 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
- B64C2027/8209—Electrically driven tail rotors
-
- 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
- B64C2027/8227—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 more than one rotor
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of cycloid paddle balance reaction torque helicopter and its working method, helicopter includes fuselage, rotor, engine, undercarriage, vertical fin and tail-rotor module；Tail-rotor module includes the first cycloid propeller, the second cycloid propeller that vertical fin two sides are arranged in；First cycloid propeller, the second cycloid propeller include upper mounting plate, lower installation board, central axis, driven gear, driving gear, cycloidal generator, upper cycloid frame, bottom coil holder, eccentric rod, hinge column, several displacement connecting rods and several blades.When work, amount of bias is arranged to eccentric rod, blade is made to all have the angle of attack in different rotary position, is formed always to the rotation status of a direction (adjustable) resultant force, it is final that the thrust of a certain fixed-direction of tail-rotor module, balancing helicopter reaction torque are provided.Cycloid propeller is applied to helicopter balance reaction torque by the present invention, and simple and reliable, light-weight, high-efficient, mobility strong, noise are low, vibration is low, highly-safe, have broad application prospects.
Description
Technical field
The present invention relates to aviation fields, and in particular to a kind of cycloid paddle balance reaction torque helicopter and its working method.
Background technique
On single-rotor helicopter, tail-rotor balances reaction torque caused by main rotor and the behaviour under all flying conditions
Vertical power.However, high-speed rotating tail-rotor in terms of safety, vibration and noise all there are many disadvantage, many researchs are devoted to
Cancel the tail rotor of exposure.
In addition, the research for cycloid propeller technology continue for longer time.Blade as lifting surface, the angle of attack with
Paddle disk rotation show continuous mechanical periodicity, this pitching movement substantially increases the pneumatic efficiency of cycloid propeller.In addition, by changing
The size of variable speed, thus it is possible to vary the size of cycloid propeller pulling force；And the direction by changing eccentric rod, thus it is possible to vary cycloid propeller is drawn
The direction of power, cycloid propeller are simple for the control of pulling force size and direction and efficient.
Based on this, cycloid propeller is applied to helicopter balance reaction torque by the present invention, is simple and efficient, maneuvering performance is good, noise
Low, light weight, highly-safe is vibrated, is had broad application prospects.
Summary of the invention
Problem to be solved by this invention is asked for current single-rotor helicopter tail-rotor safety is low, noise and vibration is high etc.
Topic provides a kind of cycloid paddle balance reaction torque helicopter and its working method.
The present invention uses following technical scheme in order to solve the above problem:
A kind of cycloid paddle balance reaction torque helicopter includes fuselage, rotor, engine, undercarriage, vertical fin and tail-rotor module；
In fuselage roof, the shaft of output shaft and the rotor is connected for engine setting；
The undercarriage is arranged in fuselage bottom, rises and falls for helicopter；
The vertical fin, tail-rotor module are arranged at afterbody, wherein and the vertical fin is used to increase helicopter lateral stability,
The tail-rotor module is for balancing helicopter reaction torque and control helicopter yawing rotation；
The tail-rotor module includes the first cycloid propeller, the second cycloid propeller that vertical fin two sides are arranged in；
First cycloid propeller, the second cycloid propeller include upper mounting plate, lower installation board, central axis, driven gear, driving tooth
Wheel, cycloidal generator, upper cycloid frame, bottom coil holder, eccentric rod, hinge column, several displacement connecting rods and several blades；
The upper mounting plate, lower installation board are arranged in parallel, wherein upper mounting plate is fixed on the vertical fin, and lower installation board is fixed
In the afterbody；
Described central axis one end is connected with the center of the bottom coil holder by bearing and passes through the bottom coil holder, the other end and
The center of the upper cycloid frame is connected by bearing and passes through the upper cycloid frame, and the upper cycloid frame, bottom coil holder are set in parallel
It sets between upper mounting plate, lower installation board；
The blade includes leading edge, rear and adjustment axis, wherein the leading edge two sides are equipped with the shaft of shaft, leading edge two sides
On same straight line, the side of the rear is equipped with and the axis hole for adjusting axis and matching；Adjustment axis one end insertion
The axis hole can be rotated relatively freely by the axis hole and the blade, and the other end stretches out the axis hole；
Several blades are uniformly arranged between the upper cycloid frame, bottom coil holder, the shaft of leading edge two sides respectively with upper pendulum
Coil holder, bottom coil holder are rotatedly connected, enable the blade by the shafts of leading edge two sides upper cycloid frame, bottom coil holder it
Between be freely rotated；
The eccentric rod is arranged between upper mounting plate and upper cycloid frame, and one end and the central axis are pierced by the one of cycloid frame
End is connected, and the other end is connected by the lower end surface of the hinge column and the upper mounting plate；The hinge column and the central axis
It is arranged in parallel；
The displacement connecting rod and the blade correspond, and one end and its one end for corresponding to blade adjustment axis stretching axis hole are connected,
The other end is and described hinged column articulated；
The bottom coil holder and driven gear coaxial arrangement, and the upper end of the lower end surface of bottom coil holder and the driven gear
Face is connected；
The lower end surface of the driven gear is rotatedly connected by the upper surface of bearing and the lower installation board；
The driven gear center is equipped with through-hole, and one end that the central axis passes through bottom coil holder passes through the driven gear center
Through-hole and the lower installation board be connected；
The output shaft of the cycloidal generator and the shaft of driving gear are connected, the driving gear and driven gear engagement.
The present invention gives a kind of working method based on the cycloid paddle balance reaction torque helicopter, includes following mistake
Journey:
The first cycloid propeller, the second cycloid propeller are adjusted by the revolving speed of cycloidal generator in the first cycloid propeller of adjusting, the second cycloid propeller
Generate the size of pulling force.
The present invention gives a kind of working method based on the cycloid paddle balance reaction torque helicopter, includes following mistake
Journey:
The first cycloid propeller, the second cycloid propeller are adjusted by the amount of bias of eccentric rod in the first cycloid propeller of adjusting, the second cycloid propeller
Generate the direction of pulling force.
The invention adopts the above technical scheme compared with prior art, has following technical effect that
Cycloid propeller is applied to helicopter balance reaction torque, simple and reliable, light-weight, high-efficient, mobility strong, noise by the present invention
It vibrates low, highly-safe.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention；
Fig. 2 is the structural schematic diagram that tail-rotor in the present invention, the first cycloid propeller, the second cycloid propeller match；
Fig. 3 is the structural schematic diagram in the present invention on the first cycloid propeller at cycloid frame；
Fig. 4 is the structural schematic diagram in the present invention at the first cycloid propeller bottom coil holder；
Fig. 5 is that the first cycloid propeller generates the two-dimensional vector thrust variation schematic diagram different with its eccentric rod amount of bias.
In figure, 1- fuselage, 2- rotor, 3- tail-rotor module, 4- engine, 5- undercarriage, 6- vertical fin, 7- lower installation board, 8-
Blade, 9- bottom coil holder, 10- central axis, 11- displacement connecting rod, 12- eccentric rod, 13- upper mounting plate, 14- driven gear.
Specific embodiment
Technical solution of the present invention is described in further detail with reference to the accompanying drawing:
As shown in Figure 1, comprising fuselage, rotor, engine, being risen the invention discloses a kind of cycloid paddle balance reaction torque helicopter
Fall frame, vertical fin and tail-rotor module；
In fuselage roof, the shaft of output shaft and the rotor is connected for engine setting；
The undercarriage is arranged in fuselage bottom, rises and falls for helicopter；
The vertical fin, tail-rotor module are arranged at afterbody, wherein and the vertical fin is used to increase helicopter lateral stability,
The tail-rotor module is for balancing helicopter reaction torque and control helicopter yawing rotation.
As shown in Fig. 2, the tail-rotor module includes the first cycloid propeller, the second cycloid propeller that vertical fin two sides are arranged in.
As shown in figure 3, first cycloid propeller, the second cycloid propeller include upper mounting plate, lower installation board, central axis, from
Moving gear, driving gear, cycloidal generator, upper cycloid frame, bottom coil holder, eccentric rod, hinge column, several displacement connecting rods and several paddles
Leaf；
The upper mounting plate, lower installation board are arranged in parallel, wherein upper mounting plate is fixed on the vertical fin, and lower installation board is fixed
In the afterbody；
Described central axis one end is connected with the center of the bottom coil holder by bearing and passes through the bottom coil holder, the other end and
The center of the upper cycloid frame is connected by bearing and passes through the upper cycloid frame, and the upper cycloid frame, bottom coil holder are set in parallel
It sets between upper mounting plate, lower installation board；
The blade includes leading edge, rear and adjustment axis, wherein the leading edge two sides are equipped with the shaft of shaft, leading edge two sides
On same straight line, the side of the rear is equipped with and the axis hole for adjusting axis and matching；Adjustment axis one end insertion
The axis hole can be rotated relatively freely by the axis hole and the blade, and the other end stretches out the axis hole；
Several blades are uniformly arranged between the upper cycloid frame, bottom coil holder, the shaft of leading edge two sides respectively with upper pendulum
Coil holder, bottom coil holder are rotatedly connected, enable the blade by the shafts of leading edge two sides upper cycloid frame, bottom coil holder it
Between be freely rotated；
The eccentric rod is arranged between upper mounting plate and upper cycloid frame, and one end and the central axis are pierced by the one of cycloid frame
End is connected, and the other end is connected by the lower end surface of the hinge column and the upper mounting plate；The hinge column and the central axis
It is arranged in parallel；
The displacement connecting rod and the blade correspond, and one end and its one end for corresponding to blade adjustment axis stretching axis hole are connected,
The other end is and described hinged column articulated.
As shown in figure 4, the bottom coil holder and driven gear coaxial arrangement, and the lower end surface of bottom coil holder and described
The upper surface of driven gear is connected；
The lower end surface of the driven gear is rotatedly connected by the upper surface of bearing and the lower installation board；
The driven gear center is equipped with through-hole, and one end that the central axis passes through bottom coil holder passes through the driven gear center
Through-hole and the lower installation board be connected；
The output shaft of the cycloidal generator and the shaft of driving gear are connected, the driving gear and driven gear engagement.
When the first cycloid propeller, the work of the second cycloid propeller, cycloidal generator drives driving gear to drive driven gear and then drives
The rotation of bottom coil holder, bottom coil holder drive upper cycloid frame to rotate further through each blade, and each blade is revolving around central axis
Meanwhile vertical dip mining is done by the driving of displacement connecting rod.
The present invention, which can be realized each blade, has the optimal angle of attack in different rotary position, and the size of the angle of attack depends on
The size of the amount of bias of eccentric rod.If the amount of bias of eccentric rod be it is certain, each blade is also if the angle of attack of different location
Certain.
The first cycloid propeller, the second pendulum are adjusted by the revolving speed of cycloidal generator in the first cycloid propeller of adjusting, the second cycloid propeller
The size of line paddle generation pulling force.
The first cycloid propeller, the second pendulum are adjusted by the amount of bias of eccentric rod in the first cycloid propeller of adjusting, the second cycloid propeller
The direction of line paddle generation pulling force.
Therefore the present invention has excellent mobility and maneuverability.
Cycloid propeller two-dimensional vector thrust control schematic diagram in the present invention is as shown in Figure 5.
The cycloid propeller parallelly distribute on of the left and right two, thrust direction is identical, collective effect, with balancing helicopter reaction torque.
Those skilled in the art can understand that unless otherwise defined, all terms used herein (including skill
Art term and scientific term) there is meaning identical with the general understanding of those of ordinary skill in fields of the present invention.Also
It should be understood that those terms such as defined in the general dictionary should be understood that have in the context of the prior art
The consistent meaning of meaning will not be explained in an idealized or overly formal meaning and unless defined as here.
Above-described specific embodiment has carried out further the purpose of the present invention, technical scheme and beneficial effects
It is described in detail, it should be understood that being not limited to this hair the foregoing is merely a specific embodiment of the invention
Bright, all within the spirits and principles of the present invention, any modification, equivalent substitution, improvement and etc. done should be included in the present invention
Protection scope within.
Claims (3)
1. a kind of cycloid paddle balance reaction torque helicopter, which is characterized in that include fuselage, rotor, engine, undercarriage, vertical fin
With tail-rotor module；
In fuselage roof, the shaft of output shaft and the rotor is connected for engine setting；
The undercarriage is arranged in fuselage bottom, rises and falls for helicopter；
The vertical fin, tail-rotor module are arranged at afterbody, wherein and the vertical fin is used to increase helicopter lateral stability,
The tail-rotor module is for balancing helicopter reaction torque and control helicopter yawing rotation；
The tail-rotor module includes the first cycloid propeller, the second cycloid propeller that vertical fin two sides are arranged in；
First cycloid propeller, the second cycloid propeller include upper mounting plate, lower installation board, central axis, driven gear, driving tooth
Wheel, cycloidal generator, upper cycloid frame, bottom coil holder, eccentric rod, hinge column, several displacement connecting rods and several blades；
The upper mounting plate, lower installation board are arranged in parallel, wherein upper mounting plate is fixed on the vertical fin, and lower installation board is fixed
In the afterbody；
Described central axis one end is connected with the center of the bottom coil holder by bearing and passes through the bottom coil holder, the other end and
The center of the upper cycloid frame is connected by bearing and passes through the upper cycloid frame, and the upper cycloid frame, bottom coil holder are set in parallel
It sets between upper mounting plate, lower installation board；
The blade includes leading edge, rear and adjustment axis, wherein the leading edge two sides are equipped with the shaft of shaft, leading edge two sides
On same straight line, the side of the rear is equipped with and the axis hole for adjusting axis and matching；Adjustment axis one end insertion
The axis hole can be rotated relatively freely by the axis hole and the blade, and the other end stretches out the axis hole；
Several blades are uniformly arranged between the upper cycloid frame, bottom coil holder, the shaft of leading edge two sides respectively with upper pendulum
Coil holder, bottom coil holder are rotatedly connected, enable the blade by the shafts of leading edge two sides upper cycloid frame, bottom coil holder it
Between be freely rotated；
The eccentric rod is arranged between upper mounting plate and upper cycloid frame, and one end and the central axis are pierced by the one of cycloid frame
End is connected, and the other end is connected by the lower end surface of the hinge column and the upper mounting plate；The hinge column and the central axis
It is arranged in parallel；
The displacement connecting rod and the blade correspond, and one end and its one end for corresponding to blade adjustment axis stretching axis hole are connected,
The other end is and described hinged column articulated；
The bottom coil holder and driven gear coaxial arrangement, and the upper end of the lower end surface of bottom coil holder and the driven gear
Face is connected；
The lower end surface of the driven gear is rotatedly connected by the upper surface of bearing and the lower installation board；
The driven gear center is equipped with through-hole, and one end that the central axis passes through bottom coil holder passes through the driven gear center
Through-hole and the lower installation board be connected；
The output shaft of the cycloidal generator and the shaft of driving gear are connected, the driving gear and driven gear engagement.
2. based on the working method described in claim 1 based on the cycloid paddle balance reaction torque helicopter, which is characterized in that packet
Containing following procedure:
The first cycloid propeller, the second cycloid propeller are adjusted by the revolving speed of cycloidal generator in the first cycloid propeller of adjusting, the second cycloid propeller
Generate the size of pulling force.
3. based on the working method described in claim 1 based on the cycloid paddle balance reaction torque helicopter, which is characterized in that packet
Containing following procedure:
The first cycloid propeller, the second cycloid propeller are adjusted by the amount of bias of eccentric rod in the first cycloid propeller of adjusting, the second cycloid propeller
Generate the direction of pulling force.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811397473.4A CN109383792A (en) | 2018-11-22 | 2018-11-22 | A kind of cycloid paddle balance reaction torque helicopter and its working method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811397473.4A CN109383792A (en) | 2018-11-22 | 2018-11-22 | A kind of cycloid paddle balance reaction torque helicopter and its working method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109383792A true CN109383792A (en) | 2019-02-26 |
Family
ID=65429000
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811397473.4A Pending CN109383792A (en) | 2018-11-22 | 2018-11-22 | A kind of cycloid paddle balance reaction torque helicopter and its working method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109383792A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20220411089A1 (en) * | 2021-06-29 | 2022-12-29 | Beta Air, Llc | Electric aircraft for generating a yaw force |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108674654A (en) * | 2018-04-19 | 2018-10-19 | 南京航空航天大学 | A kind of cycloid propeller-propeller combined high-speed aircraft |
| CN209479980U (en) * | 2018-11-22 | 2019-10-11 | 南京航空航天大学 | A kind of cycloid paddle balance reaction torque helicopter |
-
2018
- 2018-11-22 CN CN201811397473.4A patent/CN109383792A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108674654A (en) * | 2018-04-19 | 2018-10-19 | 南京航空航天大学 | A kind of cycloid propeller-propeller combined high-speed aircraft |
| CN209479980U (en) * | 2018-11-22 | 2019-10-11 | 南京航空航天大学 | A kind of cycloid paddle balance reaction torque helicopter |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20220411089A1 (en) * | 2021-06-29 | 2022-12-29 | Beta Air, Llc | Electric aircraft for generating a yaw force |
| US11745886B2 (en) * | 2021-06-29 | 2023-09-05 | Beta Air, Llc | Electric aircraft for generating a yaw force |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107672802A (en) | Fluting culvert type plume rotor craft | |
| US20090226314A1 (en) | Cycloidal rotor with non-circular blade orbit | |
| US6824094B2 (en) | Power assembly for ornicopter | |
| CN110329497B (en) | Multi-rotor unmanned aerial vehicle with variable paddle surface angle and control method thereof | |
| CN104691752A (en) | Coaxial high-speed direct-driven helicopter and flight control mode thereof | |
| WO2017024623A1 (en) | Variable pitch rotorcraft and multirotor | |
| CN110171568A (en) | One kind can hover flapping wing aircraft | |
| CN109515704B (en) | Ducted plume rotorcraft based on cycloidal propeller technology | |
| CN102069905B (en) | Oblique wing helicopter | |
| CN202828092U (en) | Automatic-rotor wing helicopter with no tail rotor | |
| CN210310858U (en) | Variable-speed driving rotor wing | |
| CN107352030B (en) | Micro flapping rotor wing aircraft with double wings flapping differentially | |
| US20240158077A1 (en) | Flapping rotor device with uplink vertical rotation and downlink horizontal rotation | |
| GB666491A (en) | Improvements in or relating to aircraft | |
| CN107161330A (en) | A kind of variable abnormally-structured displacement multi-rotor unmanned aerial vehicle | |
| CN209479980U (en) | A kind of cycloid paddle balance reaction torque helicopter | |
| CN109383792A (en) | A kind of cycloid paddle balance reaction torque helicopter and its working method | |
| WO2001040052A1 (en) | Aircraft rotor and aircraft | |
| CN105799929B (en) | A kind of vector displacement propulsion device for rotor fixed-wing combined type vertically taking off and landing flyer | |
| CN111003164A (en) | Coaxial tilting three-rotor-blade helicopter | |
| CN110356546A (en) | Automatically controlled displacement single rotor No Tail Rotor electric unmanned helicopter | |
| CN112693605B (en) | Flapping wing aircraft | |
| CN207450245U (en) | Fluting culvert type plume rotor craft | |
| CN109823523A (en) | A kind of coaxial double-oar aircraft | |
| CN112278255A (en) | Unmanned aerial vehicle for attitude control by using flywheel |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190226 |