CN118270234A - Steering engine-free variable-pitch rotor system, aircraft and control method - Google Patents
Steering engine-free variable-pitch rotor system, aircraft and control method Download PDFInfo
- Publication number
- CN118270234A CN118270234A CN202211731433.5A CN202211731433A CN118270234A CN 118270234 A CN118270234 A CN 118270234A CN 202211731433 A CN202211731433 A CN 202211731433A CN 118270234 A CN118270234 A CN 118270234A
- Authority
- CN
- China
- Prior art keywords
- pitch
- variable
- changing
- driver
- magnet
- 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
- 238000000034 method Methods 0.000 title claims abstract description 13
- 238000001514 detection method Methods 0.000 claims abstract description 37
- 125000004122 cyclic group Chemical group 0.000 claims description 3
- 230000003287 optical effect Effects 0.000 claims description 3
- 230000000737 periodic effect Effects 0.000 claims description 3
- 230000005484 gravity Effects 0.000 abstract description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
Landscapes
- Steering Control In Accordance With Driving Conditions (AREA)
Abstract
The invention discloses a steering engine-free variable-pitch rotor system, an aircraft and a control method, wherein the steering engine-free variable-pitch rotor system comprises a variable-pitch system, a rotor system and a power system; the pitch-changing system comprises a pitch-changing coil assembly bracket, a driving detection bottom plate, a pitch-changing coil assembly, an angle detection component A, an angle detection component B, an opposite pitch-changing magnet A and an opposite pitch-changing magnet B; the rotor system comprises a variable pitch blade clamp A, a variable pitch blade clamp B, a rotor hub, a blade A and a blade B; the power system comprises an outer rotor of the driver, a torque output shaft of the driver, a stator of the driver, a fixed middle shaft of the driver and a base connected with the driver. The magnetic field which is quickly changed through the air coil assembly controls the magnet to control the pitch angle of the blade, replaces a swash plate component, a connecting rod and at least three steering engines of the helicopter, reduces the specific gravity of a rotor power control component of the aircraft, has a simple structure, is convenient for reducing the size, and is extremely suitable for miniature aircrafts.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a rotor wing system, an aircraft and a control method.
Background
Today, when micro-aircraft are growing, as technology advances, aircraft like multi-rotor, single-pitch helicopters want to reduce weight size. More technical problems need to be broken through. For example, multiple rotors, the smaller their aerodynamically less efficient, the poorer performance. For example, a helicopter is more fragile in structure as it is reduced, is more complex to maintain, and is more susceptible to damage.
Disclosure of Invention
The invention aims to overcome the problems and provide a steering engine-free variable-pitch rotor system, an aircraft and a control method.
In order to achieve the aim, the invention adopts the method of providing a steering engine-free variable-pitch rotor system, which comprises a variable-pitch system, a rotor system and a power system;
The pitch-changing system comprises a pitch-changing coil assembly bracket, a driving detection bottom plate, a pitch-changing coil assembly, an angle detection component A, an angle detection component B, a counter-direction pitch-changing magnet A and a counter-direction pitch-changing magnet B;
the rotor system comprises a variable pitch blade clamp A, a variable pitch blade clamp B, a rotor hub, blades A and blades B;
The power system comprises a driver outer rotor, a driver torque output shaft, a driver stator, a driver fixed center shaft and a driver connecting base;
The driving detection bottom plate is fixedly connected with the variable-pitch coil assembly bracket, the variable-pitch coil assembly is fixedly connected with the driving detection bottom plate, the opposite variable-pitch magnets A and B are magnets distributed on magnetic objects and are all placed in the middle of the variable-pitch coil assembly;
The root of the connecting rod of the opposite pitch-changing magnet A is hinged with one end of the pitch-changing blade clamp A, the pitch-changing blade clamp A passes through the middle of the bearing and is hinged with one end of the rotor hub, and the other end of the pitch-changing blade clamp A is hinged with the root of the blade A;
The root of the connecting rod of the opposite pitch-changing magnet B is hinged with one end of the pitch-changing blade clamp B, and the pitch-changing blade clamp B passes through the middle part of the bearing and is hinged with the other end of the rotor hub; the other end of the variable pitch blade clamp B is hinged with the root of the blade B;
The angle detection component A and the angle detection component B are arranged on the drive detection bottom plate to detect the rotating angle of the opposite direction variable-pitch magnet A and the opposite direction variable-pitch magnet B, and simultaneously detect the circumferential rotating angle of the rotor system.
Preferably, the distance-changing coil assembly bracket is fixedly arranged at one end of the fixed center shaft of the driver; the other end of the driver fixing center shaft is fixedly connected with the driver connecting base; the driver connecting base is fixedly connected with the bottom of the driver stator; the driver stator is hinged with the driver outer rotor through a bearing; one end of the driver torque output shaft is fixedly connected with the top of the driver outer rotor; the other end of the torque output shaft of the driver is fixedly connected with the middle position of the rotor hub to drive the rotor system to rotate.
In one preferred embodiment of the present invention, the angle detecting component a and the angle detecting component B are optical sensors or hall sensors.
The invention also discloses an aircraft, which comprises at least the steering engine-free variable-pitch rotor system.
The invention also discloses a control method of the steering engine-free variable-pitch rotor system, which comprises the following steps:
When the rotor system rotates, the opposite variable-pitch magnet A and the opposite variable-pitch magnet B synchronously rotate in the variable-pitch coil assembly, and the variable-pitch coil assembly is fixed;
the angle detection component A and the angle detection component B are used for detecting the magnetic field of the opposite variable-pitch magnet A and the opposite variable-pitch magnet B to obtain the rotating phase angle of the rotor system;
Providing periodically-changing current for coils with different poles of the variable-pitch coil assembly so as to control the opposite-pitch magnet A and the opposite-pitch magnet B to generate periodically-changing swing in the rotating process and drive the paddles to generate periodic pitch change and total pitch change;
Controlling the phase angle of the signal input to the pitch coil assembly to control the phase angle of the cyclic pitch produces a pitch or roll steering force.
The beneficial effects are that:
According to the steering engine-free variable-pitch rotor wing system aircraft and the control method, the pitch angle of the blade is controlled by controlling the magnet through the magnetic field rapidly transformed by the air coil assembly. The structure replaces a swash plate component, a connecting rod and at least three steering engines of the helicopter, so that the specific gravity of a rotor wing power control component of the aircraft is reduced, and the structure is simple, convenient to reduce the size and extremely suitable for the miniature aircraft. In the aspect of production and manufacture, the number of manufactured parts is reduced, the material cost is reduced, and the maintenance difficulty is reduced. The aerodynamic efficiency of the aircraft is increased and the maneuverability is increased.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a schematic view of another angle of the present invention;
Fig. 3 is a schematic cross-sectional structure of the present invention.
Detailed Description
The invention will be further illustrated by the following drawings and specific examples, which are carried out on the basis of the technical solutions of the invention, it being understood that these examples are only intended to illustrate the invention and are not intended to limit the scope of the invention.
Example 1:
As shown in fig. 1 to 3, the embodiment discloses a steering engine-free torque-variable rotor system which comprises a torque-variable system 1, a rotor system 2 and a power system 3.
The variable pitch system comprises: the pitch-changing coil assembly bracket 11, the drive detection base plate 12, the pitch-changing coil assembly 13, the angle detection component a14a, the angle detection component B14B, the opposite pitch-changing magnet a15a, the opposite pitch-changing magnet B15B, the angle detection component a14a, and the angle detection component B14B may be an optical sensor or a hall sensor.
The rotor system 2 includes: pitch clip A21a, pitch clip B21B, rotor hub 22, blade A23a, and blade B23B.
The power system 3 includes: the outer rotor 31, the torque output shaft 32, the stator 33, the fixed middle shaft 34 and the connecting base 35.
The drive detection bottom plate 12 is fixedly connected with the variable-pitch coil assembly bracket 11. The variable-pitch coil assembly 13 is fixedly connected with the drive detection bottom plate 12. The opposite variable-pitch magnets A15a and B15B are magnets distributed on a magnetic object, and are all arranged in the middle of the variable-pitch coil assembly 13, and the variable-pitch coil assembly 13 is a radially wound multi-stage hollow coil.
The pitch coil assembly 13 is stationary and the opposing pitch magnets a15a, B15B can rotate synchronously with the rotation of the rotor system 2 within the pitch coil assembly 13.
The root of the connecting rod of the opposite pitch changing magnet A15a is hinged with one end of the pitch changing paddle clamp A21 a. The pitch clip a21a is hinged to one end of the rotor hub 22 through the middle of the bearing. The other end of the variable pitch blade clamp A21a is hinged with the root of the blade A23 a.
The root of the connecting rod of the opposite pitch changing magnet B15B is hinged with one end of the pitch changing paddle clamp B21B. Pitch clip B21B is hinged to the other end of rotor hub 22 through a bearing at its middle portion. The other end of the pitch-changing blade clamp B21B is hinged with the root of the blade B23B. The rotation angle of the opposite pitch magnet A15a around the rotation shaft of the pitch changing clamp A21a is controlled by the air coil magnetic field control of the pitch changing coil assembly 13 in the chord direction of the opposite pitch magnet A15 a. The rotation angle of the opposite pitch changing magnet B15B around the rotation shaft of the pitch changing clamp B21B is controlled by the chord-up air coil magnetic field of the pitch changing coil assembly 13, wherein the direction of the magnetic pole of the opposite pitch changing magnet A15a is located.
The angle detection component A14a and the angle detection component B14B are arranged on the drive detection bottom plate 12 to detect the rotation angle of the opposite direction variable-pitch magnet A15a and the opposite direction variable-pitch magnet B15B and detect the circumferential rotation angle of the rotor system 2.
The pitch-changing coil block bracket 11 is fixedly mounted at one end of the drive-fixing center shaft 34. The other end of the driver fixing center shaft 34 is fixedly connected with a driver connecting base 35. The driver connection base 35 is fixedly connected with the bottom of the driver stator 33. The driver stator 33 is hinged with the driver outer rotor 31 through a bearing. One end of the driver torque output shaft 32 is fixedly connected with the top of the driver outer rotor 31. The other end of the driver torque output shaft 32 is fixedly connected to the middle position of the rotor hub 22, so as to drive the rotor system 2 to rotate. The rotor system 2 includes at least two sets of the independently variable pitch blades.
The steering engine-free variable-pitch rotor system of the embodiment comprises the following control method:
When the rotor system 2 rotates, the opposite variable-pitch magnet A15a and the opposite variable-pitch magnet B15B synchronously rotate in the variable-pitch coil assembly 13, and the variable-pitch coil assembly 13 is fixed.
The angle detection component a14a and the angle detection component B14B detect the magnetic field of the opposing pitch magnet a15a and the opposing pitch magnet B15B to obtain the phase angle of the rotation of the rotor system 2.
The periodic variable pitch and total pitch of the blades are driven by periodically varying current supplied to coils of different poles of the variable pitch coil assembly 13 to control the opposite variable pitch magnet A15a and the opposite variable pitch magnet B15B to generate periodically varying oscillation in the rotation process.
The pitch or roll steering force is generated by controlling the phase angle of the signal input to the pitch coil assembly 13 to control the phase angle of the cyclic pitch.
Example 2:
the embodiment also discloses an aircraft, which comprises the steering engine-free variable-pitch rotor system.
The technical means disclosed by the scheme of the invention is not limited to the technical means disclosed by the technical means, and also comprises the technical scheme formed by any combination of the technical features. While the foregoing is directed to embodiments of the present invention, it will be appreciated by those skilled in the art that changes and modifications may be made without departing from the principles of the invention, and such changes and modifications are intended to be included within the scope of the invention.
Claims (5)
1. A steering engine-free torque-variable rotor system, characterized in that: comprises a variable-pitch system (1), a rotor system (2) and a power system (3);
the pitch-changing system comprises a pitch-changing coil assembly bracket (11), a driving detection bottom plate (12), a pitch-changing coil assembly (13), an angle detection component A (14 a), an angle detection component B (14B), an opposite pitch-changing magnet A (15 a) and an opposite pitch-changing magnet B (15B);
the rotor system (2) comprises a variable pitch blade clamp A (21 a), a variable pitch blade clamp B (21B), a rotor hub (22), a blade A (23 a) and a blade B (23B);
The power system (3) comprises a driver outer rotor (31), a driver torque output shaft (32), a driver stator (33), a driver fixing center shaft (34) and a driver connecting base (35);
The driving detection bottom plate (12) is fixedly connected with the variable-pitch coil assembly bracket (11), the variable-pitch coil assembly (13) is fixedly connected with the driving detection bottom plate (12), the opposite variable-pitch magnet A (15 a) and the opposite variable-pitch magnet B (15B) are all arranged at the middle position of the variable-pitch coil assembly (13),
The root of the connecting rod of the opposite pitch changing magnet A (15 a) is hinged with one end of the pitch changing blade clamp A (21 a), the pitch changing blade clamp A (21 a) passes through the middle part of the bearing and is hinged with one end of the rotor hub (22), and the other end of the pitch changing blade clamp A (21 a) is hinged with the root of the blade A (23 a);
The root of the connecting rod of the opposite pitch changing magnet B (15B) is hinged with one end of the pitch changing paddle clamp B (21B), and the pitch changing paddle clamp B (21B) passes through the middle part of the bearing and is hinged with the other end of the rotor hub (22); the other end of the variable pitch blade clamp B (21B) is hinged with the root of the blade B (23B);
the angle detection component A (14 a) and the angle detection component B (14B) are arranged on the drive detection bottom plate (12) to detect the rotation angle of the opposite direction variable-pitch magnet A (15 a) and the opposite direction variable-pitch magnet B (15B) and detect the circumferential rotation angle of the rotor system (2).
2. The steering engine-free torque-variable rotor system of claim 1, wherein: the variable-pitch coil assembly bracket (11) is fixedly arranged at one end of the driver fixing center shaft (34); the other end of the driver fixing center shaft (34) is fixedly connected with a driver connecting base (35); the driver connecting base (35) is fixedly connected with the bottom of the driver stator (33); the driver stator (33) is hinged with the driver outer rotor (31) through a bearing; one end of the driver torque output shaft (32) is fixedly connected with the top of the driver outer rotor (31); the other end of the driver torque output shaft (32) is fixedly connected with the middle position of the rotor hub (22) to drive the rotor system (2) to rotate.
3. The steering engine-free torque-variable rotor system of claim 1, wherein: the angle detection component A (14 a) and the angle detection component B (14B) are optical sensors or Hall sensors.
4. An aircraft, characterized in that: the aircraft comprising a steering-engine-free torque-converting rotor system according to at least any one of claims 1 to 3.
5. A method of controlling a steering engine-free torque-converting rotor system according to any one of claims 1-3, comprising the steps of:
When the rotor system (2) rotates, the opposite distance changing magnet A (15 a) and the opposite distance changing magnet B (15B) synchronously rotate in the distance changing coil assembly (13), and the distance changing coil assembly (13) is fixed;
The angle detection component A (14 a) and the angle detection component B (14B) are used for detecting the magnetic field of the opposite variable-pitch magnet A (15 a) and the opposite variable-pitch magnet B (15B) to obtain the phase angle of the rotation of the rotor system (2);
Providing periodically-changing current for coils with different poles of the variable-pitch coil assembly (13) so as to control the opposite-pitch magnet A (15 a) and the opposite-pitch magnet B (15B) to generate periodically-changing swing in the rotating process and drive the paddles to generate periodic pitch change and total pitch change;
Controlling the phase angle of the signal input to the pitch coil assembly (13) to control the phase angle of the cyclic pitch produces a pitch or roll steering force.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211731433.5A CN118270234A (en) | 2022-12-31 | 2022-12-31 | Steering engine-free variable-pitch rotor system, aircraft and control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211731433.5A CN118270234A (en) | 2022-12-31 | 2022-12-31 | Steering engine-free variable-pitch rotor system, aircraft and control method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN118270234A true CN118270234A (en) | 2024-07-02 |
Family
ID=91634959
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211731433.5A Pending CN118270234A (en) | 2022-12-31 | 2022-12-31 | Steering engine-free variable-pitch rotor system, aircraft and control method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN118270234A (en) |
-
2022
- 2022-12-31 CN CN202211731433.5A patent/CN118270234A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9174728B2 (en) | Electrical powered tail rotor of a helicopter | |
| EP2432999A1 (en) | Vertical axis wind turbine and generator therefore | |
| WO2009109918A4 (en) | Cycloidal rotor with non-circular blade orbit | |
| JP2012527864A5 (en) | ||
| CN108163193B (en) | A kind of active main rotor vertically taking off and landing flyer | |
| US6476534B1 (en) | Permanent magnet phase-control motor | |
| US8845290B1 (en) | System and method for magnetically and aerodynamically optimized control of rotorhead | |
| CN108438209B (en) | Cycloidal propeller eccentric circle control mechanism | |
| CN208993923U (en) | Propeller, Power Component and unmanned vehicle | |
| CN219277786U (en) | Steering engine-free variable-pitch rotor system and aircraft | |
| CN109455295B (en) | Rotor control device and rotor craft | |
| CA2794077C (en) | Electrical powered tail rotor of a helicopter | |
| CN118270234A (en) | Steering engine-free variable-pitch rotor system, aircraft and control method | |
| CN113928540B (en) | Helicopter inertia displacement rotor wing | |
| CN108482646B (en) | Unmanned aerial vehicle propeller locking device and method in non-contact separation type arrangement | |
| CN216916275U (en) | Top direct-drive rotor wing device | |
| CN115061487A (en) | Aircraft and attitude control method and device thereof and related equipment | |
| CN205168884U (en) | Many rotor crafts and actuating mechanism mount pad thereof | |
| CN117365874A (en) | Gyro assembly, fan blade, impeller and wind generating set | |
| CN211001822U (en) | Butterfly-shaped aircraft | |
| CN209852594U (en) | Propeller assembly and aircraft | |
| CN107237720A (en) | Opposite rotary vertical shaft type wind-mill generator control system | |
| CN107856849B (en) | Gyro disk propeller type vertical take-off and landing aircraft | |
| WO2018040094A1 (en) | Rotary inertial impeller | |
| CN2828366Y (en) | Cylindrical rotor horizontal axis wind-mill generator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |