CN114148510A

CN114148510A - Drum-type rotor helicopter lift unit

Info

Publication number: CN114148510A
Application number: CN202111504123.5A
Authority: CN
Inventors: 陈新建
Original assignee: Individual
Current assignee: Individual
Priority date: 2021-12-10
Filing date: 2021-12-10
Publication date: 2022-03-08

Abstract

The invention discloses a roller type rotor wing helicopter lift unit, which comprises a plurality of rotor wings which are arranged in an equiangular and circumferential manner to form a roller-shaped structure, wherein mounting shafts are arranged at two ends of each rotor wing, and the two ends of each rotor wing are connected between an end plate A and an end plate B through the mounting shafts; one side of installation axle is equipped with attack angle controller, end plate A is two the same plectane structures with end plate B, end plate A has the installation axle with end plate B's intermediate position through connection. The invention has simple structure and good practicability, generates lift force and thrust force by the rotor wing, can offset the counter-torque force generated by the rotor wing by the change of the gravity center of the airplane, does not need to consume energy, reduces the transmission mechanism, reduces the overall weight of the airplane, adopts a control mode of the attack angle controller to be simple and reliable, and meets the use requirements of people.

Description

Drum-type rotor helicopter lift unit

Technical Field

The invention relates to the technical field of aircraft lift units, in particular to a drum-type rotor helicopter lift unit.

Background

The existing helicopter lift unit adopts a rotor wing with an axis vertical to the ground to provide lift, the helicopter can rotate reversely under the counter-torque force of the rotor wing, and the counter-torque force of the rotor wing needs to be offset by additionally consuming the power of an engine; the power of the helicopter is mostly used for the rotation of the rotor wing to generate lift force, and the rotor wing needs to be inclined to divide a part of power when moving forward, backward and the like, and the flight speed is slow because most of the power also needs to provide the lift force and the horizontal component force is only a small part.

Because the helicopter has low transmission efficiency due to the complex transmission part of the rotor wing, and because the airspeeds of the blades at all points in the chord direction are different and the pitches are different, but the attack angles of the blades are the same, the efficiency of the rotor wing for generating lift force and thrust is low, and a part of power is needed to overcome the reaction force of the rotor wing, so that the helicopter is finally low in efficiency, high in oil consumption, low in speed and small in voyage. And because the rotor wing size is big, dangerous is high, is not suitable for taking off and land in narrow and small space. It is difficult to become an aircraft lift unit as popular as a home automobile.

Disclosure of Invention

In view of this, the present invention proposes a roller-rotor helicopter lift unit.

The technical scheme provided by the invention is as follows:

the utility model provides a drum-type rotor helicopter lift unit, includes that angular circumference such as a plurality of rotors arranges and forms cylinder column structure, the both ends of rotor are equipped with the installation axle, connect the both ends of rotor between end plate A and end plate B through the installation axle, and each rotor can be called "rotor rotation" around the installation axle free rotation.

The end plate A and the end plate B are two same circular plate structures, the middle positions of the end plate A and the end plate B are connected with a transmission shaft in a penetrating mode, the transmission shaft rotates to drive the end plates A on two sides and the end plates B to rotate, and the end plates A and the end plates B drive rotors to revolve around the axes of the transmission shaft.

Each one side of installation axle is equipped with attack angle controller, steerable rotor and air current angle of attack.

Furthermore, the opening of the end plate A and the end plate B with equal angles is provided with a plurality of mounting holes, the mounting shafts on two sides of the rotor wing are correspondingly inserted into the mounting holes, and the rotor wing rotates around the mounting shafts.

Furthermore, the attack angle controller comprises a vibrating body, springs are arranged on two sides of the vibrating body, an electromagnetic coil is arranged on the outer side of the vibrating body, the vibrating body performs sinusoidal vibration or other forms of movement under the action of magnetic force of the electromagnetic coil, and the position of the vibrating body deviating from the gravity center of the rotor wing can change the attack angle of the rotor wing relative to airflow to generate lift force.

Furthermore, the electromagnetic coil is connected to a vibrator control circuit, the vibrator control circuit generates a sinusoidal driving current or a current with other forms of time varying, and the electromagnetic coil is driven to generate an alternating magnetic field to control the position of the vibrator.

Compared with the prior art, the invention has the advantages that:

the invention has simple structure and good practicability, generates lift force and thrust force by the rotor wing, can offset the counter-torque force generated by the rotor wing by the change of the gravity center of the airplane, does not need to consume energy, reduces the transmission mechanism, reduces the overall weight of the airplane, adopts a control mode of the attack angle controller to be simple and reliable, and meets the use requirements of people.

Drawings

FIG. 1 is a schematic view of the overall structure of the present invention;

figure 2 is a schematic cross-sectional view of a rotor of the present invention;

FIG. 3 is a schematic view of an angle of attack controller according to the present invention;

FIG. 4 is a schematic view of the connection structure of the attack angle controller of the present invention;

FIG. 5 is a schematic view of the lift direction control principle of the rotor of the present invention;

FIG. 6 is a schematic view of the rotor shaft center trajectory and rotor aerodynamic center trajectory of the present invention;

in the figure: 1-a rotor wing; 2-end plate A; 3-end plate B; 4, mounting a shaft; 5-a rotating shaft; 6-an angle of attack controller; 7-mounting holes; 8-a spring; 9-vibrating body.

Detailed Description

The present invention is described in further detail below with reference to figures 1-6.

The utility model provides a drum-type rotor helicopter lift unit, includes that a plurality of rotors 1 equiangular circumference arrange and form the cylinder structure, the both ends of rotor 1 are equipped with installation axle 4, connect the both ends of rotor 1 between end plate A2 and end plate B3 through installation axle 4, and each rotor 1 can be called "rotor 1 rotation" around installation axle 4 free rotation.

End plate A2 is two the same plectane structures with end plate B3, end plate A2 has the transmission shaft with end plate B3's intermediate position through connection, and the transmission shaft is rotatory, drives both sides end plate A2 and end plate B3 rotatory, and end plate A2 and end plate B3 drive rotor 1 and revolve "rotor 1 revolution" around the rotatory name of transmission shaft axle center.

When the lift unit is rotated at a high speed, the rotor wing 1 rotates around the rotor wing 1 installation shaft 4 under the action of airflow, and the attack angle of the rotor wing 1 relative to the airflow is close to zero. By controlling the attack angle between each rotor wing 1 and the airflow direction at any moment, the direction and the size of resultant force formed by the lift force of each rotor wing 1 can be controlled, and the motion direction of the aircraft can be controlled.

Each one side of installation axle 4 is equipped with attack angle controller 6, steerable rotor 1 and air current angle of attack.

The aircraft is provided with a plurality of lift units for providing lift, and the transmission shafts of the lift units are perpendicular to the flight direction and parallel to the ground. The number of the lift units is even, and the gyroscopic effect of the lift units is counteracted.

The aircraft controls the three-dimensional motion of the aircraft by controlling the magnitude and the direction of the lift force of each lift force unit.

The opening of the equal angle of end plate A2 and end plate B3 has a plurality of mounting hole 7, the installation axle 4 of rotor 1 both sides corresponds inserts in mounting hole 7, and rotor 1 is around installation axle 4 rotation.

The attack angle controller 6 comprises a vibrator 9, springs 8 are arranged on two sides of the vibrator 9, an electromagnetic coil is arranged on the outer side of the vibrator 9, the vibrator 9 performs sinusoidal vibration or other forms of movement under the action of the magnetic force of the electromagnetic coil, and the attack angle of the rotor 1 relative to airflow can be changed when the vibrator 9 deviates from the gravity center position of the rotor 1, so that a lift force is generated.

The electromagnetic coil is connected with a control circuit of the vibrating body 9, the control circuit of the vibrating body 9 generates a sinusoidal driving current or a current with other forms of time varying, the electromagnetic coil is driven to generate an alternating magnetic field, and the position of the vibrating body 9 is controlled. The invention is used as the part of helicopter generating lift force, which is a structure that a roller rotor wing 1 is horizontally arranged transversely, the whole rotating shaft 5 is vertical to the longitudinal axis of the helicopter and parallel to the ground, the counter force of the rotor wing 1 can be counteracted by the gravity of the helicopter, the two ends of the wing beam of a plurality of rotor wings 1 are uniformly arranged on circular end plates at two sides to jointly form the roller rotor wing 1, the wing beam of the rotor wing 1 passes through the mounting holes 7 on the end plates at two sides, the diameter of the mounting hole 7 is larger than that of the mounting shaft 4 and can rotate freely, the gravity center of each rotor wing 1 is arranged at the center line of the mounting shaft 4, the pneumatic center is arranged behind the center line, and the roller rotor wing 1 has enough pneumatic arms to ensure that the attack angle of the rotor wing 1 is always kept close to 0 degree when rotating, one end of each rotor wing 1 is provided with a spring 8 vibrator to form a spring 8 double vibrator with the rotor wing 1, and generates sinusoidal oscillation under the action of an electromagnetic or mechanical exciter, the periodic deflection of the attack angle is realized, and the lift force and the thrust force are generated.

The appearance of the invention is similar to a cross-flow fan, the end plates at two sides are correspondingly provided with coaxial mounting holes 7, two ends of the rotor wing 1 are inserted into the mounting holes 7 of the end plates at two sides, the center of gravity of the rotor wing 1 is arranged at the axle center of the mounting holes 7, and the pneumatic center is arranged between the axle center and the rear edge of the rotor wing 1, so that the rotor wing 1 is ensured to always keep an attack angle under the action of aerodynamic force when doing circular motion around the axle center of a cylinder body. 4 tip of installation axle sets up the 8 oscillators of spring, forms 8 double oscillators of spring with rotor 1, and the 8 oscillators of spring make rotor 1 angle of attack do sinusoidal change under the exciter triggers, and rotor 1 is under aerodynamic and the 8 oscillator efforts of spring, when doing the circular motion, remains the angle of attack all the time, makes several rotors 1 rotate any angle and can both produce lift and the thrust that advances.

As shown in fig. 5, the upper part is the relationship between the rotation angle of the end plate and time, the lower part is the relationship between the attack angle of the rotor 1 and the P curve, when the end plate rotates, the attack angle controller 6 does not work, the rotor 1 is feathered and does not generate lift force, when the attack angle controller 6 starts working, the vibrator 9 deviates from the balance position, the center of gravity of the rotor 1 shifts, the centrifugal force and the aerodynamic force act, the rotor 1 generates the attack angle, when the vibration of the vibrator 9 and the motion phase of the end plate are shown in the upper part of fig. 5, when the rotor 1 rotates in the rotation angle range of 1-180 degrees, the attack angle is positive, when the rotor 1 rotates in the rotation angle range of 180-360 degrees, the attack angle is negative, the rotor 11 generates lift force to move upwards, and when the phase of the vibrator 9 rotates to move forwards and backwards relative to the limiting position of the end plate, the rotor 11 generates lift force which can tilt forwards and backwards, and forwards.

As shown in fig. 6, when the rotor wing is vertically raised, a constant positive attack angle is generated when the rotor wing is 10-180 degrees, and a vertical upward lift force is generated, and when the rotor wing is 180 degrees and 360 degrees, the rotor wing 1 flies backwards, and a negative attack angle and an upward lift force are also generated, and the total lift force L is upward. When the attack angle sine changes and the phase of the rotor wing 1 rotating along with the end plate changes relatively, the direction of the lift force L changes, and horizontal pushing is generated.

This patent aircraft configuration a plurality of lift unit provides lift, lift unit transmission shaft perpendicular to direction of flight, is on a parallel with ground. The number of the lift units is even, and the gyroscopic effect of the lift units is counteracted.

The invention has simple structure and good practicability, the rotor wing 1 generates lift force and thrust force, the counter-torque force generated by the rotor wing 1 can be offset by the change of the gravity center of the airplane, energy consumption is not needed, a transmission mechanism is reduced, the overall weight of the airplane is reduced, and the control mode of the attack angle controller 6 is simple and reliable, thereby meeting the use requirements of people.

The present invention and its embodiments have been described above, and the description is not intended to be limiting, and the drawings are only one embodiment of the present invention, and the actual structure is not limited thereto. In summary, those skilled in the art should appreciate that they can readily use the disclosed conception and specific embodiments as a basis for designing or modifying other structures for carrying out the same purposes of the present invention without departing from the spirit and scope of the invention as defined by the appended claims.

Claims

1. A roller rotor helicopter lift unit is characterized by comprising a plurality of rotors which are arranged in a circumferential manner at equal angles to form a roller-shaped structure, wherein installation shafts are arranged at two ends of each rotor, two ends of each rotor are connected between an end plate A and an end plate B through the installation shafts, and each rotor can freely rotate around the installation shafts to be called rotor rotation;

the end plate A and the end plate B are of two identical circular plate structures, a transmission shaft penetrates through the middle position of the end plate A and the end plate B, the transmission shaft rotates to drive the end plates A and the end plates B on two sides to rotate, and the end plates A and the end plates B drive the rotor wings to rotate around the axes of the transmission shaft, so that the rotor wing revolution is called;

2. A roller rotor helicopter lift unit according to claim 1 where said end plates a and B are equiangularly perforated with a plurality of mounting holes, the mounting holes on both sides of the rotor correspondingly inserted into the mounting holes, the rotor rotating about the mounting holes.

3. A roller rotor helicopter lift unit as claimed in claim 1 wherein said angle of attack control comprises a vibrator having springs on either side of said vibrator, a solenoid on the outside of said vibrator, said vibrator being adapted to vibrate sinusoidally or otherwise move under the influence of the magnetic force of said solenoid, said vibrator being adapted to vary the angle of attack of the rotor with respect to the airflow by being offset from the center of gravity of the rotor to produce lift.

4. A roller rotor helicopter lift unit as claimed in claim 1 wherein said electromagnetic coil is connected to a vibrator control circuit that generates a sinusoidal drive current or other form of time varying current that drives the electromagnetic coil to generate an alternating magnetic field that controls the position of the vibrator.